diff --git a/.gitignore b/.gitignore
index eeb511e6..77dd9551 100644
--- a/.gitignore
+++ b/.gitignore
@@ -28,7 +28,9 @@
*.app
# Temporary files
-*~
+*~.*
+*~\$*
+*.*~
# other stuff
*.xpr
@@ -36,6 +38,8 @@
/bin/
.*.swp
*.sublime-*
+*\#*#
+*.DS_Store
# Java stuff
*.javac
diff --git a/data/pds4/context-pds4/instrument/no-host.lorenz_met_station_1.1.xml b/data/pds4/context-pds4/instrument/no-host.lorenz_met_station_1.1.xml
new file mode 100644
index 00000000..41ca6a9f
--- /dev/null
+++ b/data/pds4/context-pds4/instrument/no-host.lorenz_met_station_1.1.xml
@@ -0,0 +1,67 @@
+
+
+
+
+
+ urn:nasa:pds:context:instrument:no-host.lorenz_met_station
+ 1.0
+ Portable Meterological Station (Ralph Lorenz design)
+ 1.22.0.0
+ Product_Context
+
+
+ 2020-12-08
+ 1.0
+
+ Initial creation of the context product.
+
+
+
+ 2024-10-02
+ 1.1
+
+ Where applicable, updated version, title, name
+
+
+
+
+
+
+ urn:nasa:pds:context:investigation:field_campaign.dd_eldorado_nv_2015
+ instrument_to_investigation
+
+
+ 10.5194/gi-1-209-2012
+ Lorenz, R.D. (2012), Observing desert dust devils with a pressure logger, Geosci. Instrum. Method. Data Syst. 1, 209-220.
+ Original presentation of this meterological station.
+
+
+ 10.1002/2014JEE004712
+ Jackson, Brian and Lorenz, Ralph (2015). A multiyear dust devil vortex survey using an automated search of pressure time series, J. Geophys. Res. Planets, 120.
+ Citation of the official published version of the paper.
+
+
+ 10.1016/j.jastp.2016.10.017
+ Lorenz, R.D., L.D.V. Neakrase, J.P. Anderson, R.G. Harrison, and K.A. Nicoll (2016) Point discharge current measurements beneath dust devils, J. Atmos. and Solar-Terrest. Phys., 150, 55-60.
+ Further usage for voltage modified meteological stations.
+
+
+
+ Portable Meterological Station (Ralph Lorenz design)
+
+
+ Meteorology
+
+
+
+ A portable, compact meteorology station designed for dust devil field studies. The system used is based on the Gulf Coast Data Concepts B1100 pressure logger,
+ which combines a precision Bosch BMP085 pressure sensor (logged with resolution of 1 Pa or 0.01 mbar), with a microcontroller that logs pressure data and
+ housekeeping temperature as ASCII files on a 2GB microSD flash memory card. The whole unit operates as a large USB memory stick facilitating data transfer to
+ a computer. Self-contained, power for remote operation is attained by usage of 2 alkaline D cell batteries, allowing unattended multi-month operation at sample
+ rates of 2 Hz or more. The sensor and battery casing are installed in a plastic case, drilled to allow pressure equalization, with a painted exterior to minimize
+ visibility. In some cases, the instrumentation may be augmented to include analog voltage (in range 0-4.19 V) with 12-bit resolution at an interval of 1s.
+
+
+
diff --git a/data/pds4/context-pds4/instrument/ody.accel_1.1.xml b/data/pds4/context-pds4/instrument/ody.accel_1.1.xml
new file mode 100644
index 00000000..2d1eb01e
--- /dev/null
+++ b/data/pds4/context-pds4/instrument/ody.accel_1.1.xml
@@ -0,0 +1,80 @@
+
+
+
+
+
+ urn:nasa:pds:context:instrument:ody.accel
+ 1.1
+ Accelerometer for ODY
+ 1.22.0.0
+ Product_Context
+
+
+ urn:nasa:pds:context:instrument:accel.ody
+
+
+
+
+ 2023-09-15
+ 1.0
+
+ Update to ody.accel and set alias to the original accel.ody.
+ Updated to PDS4_PDS_1F00.xsd
+ Added ctli for updated Instrument class, type = Accelerometer
+ And per "Guide toPDS4 Context Products" v1.8,
+ changed all lidvid_reference to lid_reference
+
+
+
+ 2024-10-02
+ 1.1
+
+ Where applicable, updated version, title, name
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.ody
+ instrument_to_instrument_host
+
+
+ urn:nasa:pds:context:investigation:mission.2001_mars_odyssey
+ instrument_to_investigation
+
+
+
+
+ Tolson, R.H., A.M. Dwyer, J.L. Hanna, G.M. Keating, B.E. George, P.E. Escalera
+ and M.R. Werner, M. R., Application of accelerometer data to Mars Odyssey
+ aerobraking and atmospheric modeling. J. Spacecraft Rockets 42, 435-443, 2005
+
+ reference.TOLSONETAL2005
+
+
+
+
+ Accelerometer
+
+
+ Accelerometer
+
+
+
+ The Mars Odyssey Accelerometer instrument used during the spacecraft's aerobraking phase, which helped adjust its orbit around Mars. The accelerometer measured the forces acting on the spacecraft as it passed through the Martian atmosphere, providing data on atmospheric density and helping to refine the orbital trajectory. This information also contributed to understanding Mars' atmospheric properties, including variations in density, temperature, and pressure at different altitudes.
+
+
+
diff --git a/data/pds4/context-pds4/instrument/ody.grs_1.1.xml b/data/pds4/context-pds4/instrument/ody.grs_1.1.xml
new file mode 100644
index 00000000..eb946f52
--- /dev/null
+++ b/data/pds4/context-pds4/instrument/ody.grs_1.1.xml
@@ -0,0 +1,75 @@
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument:ody.grs
+ 1.1
+ Gamma Ray Spectrometer (GRS) for ODY
+ 1.22.0.0
+ Product_Context
+
+ GRS
+ urn:nasa:pds:context:instrument:grs.ody
+
+
+
+ 2021-06-09
+ 1.0
+
+ Updated the information model, LID, and other corrections.
+
+
+
+ 2024-10-02
+ 1.1
+
+ Where applicable, updated version, title, name
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.ody
+ instrument_to_instrument_host
+
+
+ urn:nasa:pds:context:investigation:mission.2001_mars_odyssey
+ instrument_to_investigation
+
+
+ urn:nasa:pds:context:investigation:mission.2001_mars_odyssey
+ instrument_to_investigation
+
+
+ 10.1023/B:SPAC.0000021007.76126.15
+
+ Boynton, W., Feldman, W., Mitrofanov, I. et al. (2004) The Mars Odyssey Gamma-Ray Spectrometer
+ Instrument Suite, Space Science Reviews, 110, 37-83.
+
+
+
+
+
+ Gamma Ray Spectrometer
+
+
+ Spectrometer
+ Gamma Ray
+
+
+
+ The Gamma Ray Spectrometer (GRS) is part of he Mars Odyssey Gamma-Ray Spectrometer suite.
+ The chief scientific objectives is to quantitatively map the elemental abundances of the Martian
+ surface.
+
+
+
diff --git a/data/pds4/context-pds4/instrument/ody.hend_1.1.xml b/data/pds4/context-pds4/instrument/ody.hend_1.1.xml
new file mode 100644
index 00000000..2f15ee1c
--- /dev/null
+++ b/data/pds4/context-pds4/instrument/ody.hend_1.1.xml
@@ -0,0 +1,79 @@
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument:ody.hend
+ 1.1
+ High Energy Neutron Detector (HEND) for ODY
+ 1.22.0.0
+ Product_Context
+
+ HEND
+ urn:nasa:pds:context:instrument:grs.ody
+
+
+
+ 2021-06-09
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+ 2024-10-02
+ 1.1
+
+ Where applicable, updated version, title, name
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.ody
+ instrument_to_instrument_host
+
+
+ urn:nasa:pds:context:investigation:mission.2001_mars_odyssey
+ instrument_to_investigation
+
+
+ urn:nasa:pds:context:investigation:mission.2001_mars_odyssey
+ instrument_to_investigation
+
+
+ 10.1023/B:SPAC.0000021007.76126.15
+
+ Boynton, W., Feldman, W., Mitrofanov, I. et al. (2004) The Mars Odyssey Gamma-Ray Spectrometer
+ Instrument Suite, Space Science Reviews, 110, 37-83.
+
+
+
+
+
+ High Energy Neutron Detector
+
+
+ Spectrometer
+ High Energy Neutron
+
+
+
+ The High-Energy Neutron Detector (HEND) is part of he Mars Odyssey Gamma-Ray Spectrometer suite.
+ The chief scientific objectives of the HEND instrument is
+ to map the near surface hydrogen (and, by inference, water) and
+ CO2 abundances and their stratigraphic distributions, and
+ determine their seasonal variations, and to determine the depth of the seasonal polar caps and their
+ variation with time.
+
+
+
diff --git a/data/pds4/context-pds4/instrument/ody.mar_1.1.xml b/data/pds4/context-pds4/instrument/ody.mar_1.1.xml
new file mode 100644
index 00000000..2903a2f7
--- /dev/null
+++ b/data/pds4/context-pds4/instrument/ody.mar_1.1.xml
@@ -0,0 +1,84 @@
+
+
+
+
+
+ urn:nasa:pds:context:instrument:ody.mar
+ 1.1
+ Mars Radiation Environment Experiment (MARIE) for ODY
+ 1.22.0.0
+ Product_Context
+
+
+ MARIE
+
+
+ urn:nasa:pds:context:instrument:mar.ody
+
+
+
+
+ 2023-09-15
+ 1.0
+
+ Update to ody.mar and set alias to the original mar.ody.
+ Updated to PDS4_PDS_1F00.xsd
+ Added ctli for updated Instrument class, type = Charged Particle Detector
+ And per "Guide toPDS4 Context Products" v1.8,
+ changed all lidvid_reference to lid_reference
+
+
+
+ 2024-10-02
+ 1.1
+
+ Where applicable, updated version, title, name
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.ody
+ instrument_to_instrument_host
+
+
+ urn:nasa:pds:context:investigation:mission.2001_mars_odyssey
+ instrument_to_investigation
+
+
+ urn:nasa:pds:context:investigation:mission.2001_mars_odyssey
+ instrument_to_investigation
+
+
+
+ MARIE ICD, JPL Document MSP01-98-0016, June 23, 1999, Jet Propulsion
+ Laboratory, Pasadena, CA, 1999.
+
+ reference.MSP01-98-0016
+
+
+
+ Mars Radiation Environment Experiment
+
+
+ Charged Particle Detector
+
+
+
+ An instrument aboard NASA's Mars Odyssey spacecraft, launched in 2001. MARIE was designed to measure the radiation environment in space around Mars, specifically the energetic charged particles (protons, heavy ions) that come from the Sun and other cosmic sources. This data is crucial for assessing potential risks to future human explorers due to radiation exposure. MARIE provided valuable insights until it ceased operation in 2003, likely due to damage from a solar storm.
+
+
+
diff --git a/data/pds4/context-pds4/instrument/ody.ns_1.1.xml b/data/pds4/context-pds4/instrument/ody.ns_1.1.xml
new file mode 100644
index 00000000..aadc07b0
--- /dev/null
+++ b/data/pds4/context-pds4/instrument/ody.ns_1.1.xml
@@ -0,0 +1,82 @@
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument:ody.ns
+ 1.1
+ Neutron Spectrometer for ODY
+ 1.22.0.0
+ Product_Context
+
+
+ NS
+
+
+ urn:nasa:pds:context:instrument:grs.ody
+
+
+
+
+ 2021-06-09
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+ 2024-10-02
+ 1.1
+
+ Where applicable, updated version, title, name
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.ody
+ instrument_to_instrument_host
+
+
+ urn:nasa:pds:context:investigation:mission.2001_mars_odyssey
+ instrument_to_investigation
+
+
+ urn:nasa:pds:context:investigation:mission.2001_mars_odyssey
+ instrument_to_investigation
+
+
+ 10.1023/B:SPAC.0000021007.76126.15
+
+ Boynton, W., Feldman, W., Mitrofanov, I. et al. (2004) The Mars Odyssey Gamma-Ray Spectrometer
+ Instrument Suite, Space Science Reviews, 110, 37-83.
+
+
+
+
+
+ Neutron Spectrometer
+
+
+ Spectrometer
+ Neutron
+
+
+
+ The Neutron Spectrometer (NS) is part of he Mars Odyssey Gamma-Ray Spectrometer suite.
+ The chief scientific objectives of the HEND instrument is
+ to map the near surface hydrogen (and, by inference, water) and
+ CO2 abundances and their stratigraphic distributions, and
+ determine their seasonal variations, and to determine the depth of the seasonal polar caps and their
+ variation with time.
+
+
+
diff --git a/data/pds4/context-pds4/instrument/ody.rss_1.0.xml b/data/pds4/context-pds4/instrument/ody.rss_1.0.xml
index df072119..9d11ad3d 100644
--- a/data/pds4/context-pds4/instrument/ody.rss_1.0.xml
+++ b/data/pds4/context-pds4/instrument/ody.rss_1.0.xml
@@ -124,1332 +124,23 @@
- RADIO SCIENCE SUBSYSTEM
+ Radio Science Subsystem
Atmospheric Structure Instrument
-
-
- Instrument Overview
- ===================
- There were no recognized radio science investigations on
- the 2001 Mars Odyssey (ODY) mission. But investigators on
- Mars Global Surveyor (MGS) requested access to ODY radio
- tracking data. To support them and future proposers to
- Mars data analysis programs (MDAPs), the Planetary Data
- System (PDS) accepted responsibility for archiving the ODY
- data with initial activities funded jointly by MGS.
-
- Radio science investigations utilize instrumentation with
- elements both on a spacecraft and at ground stations -- in
- this case, at the NASA Deep Space Network (DSN). For ODY
- much of this was equipment used for routine telecommunications.
- The performance and calibration of both the spacecraft and
- tracking stations directly affected the radio science data
- accuracy, and they played a major role in determining the
- quality of the results. The spacecraft part of the radio
- science instrument is described immediately below; that is
- followed by a description of the DSN (ground) part of the
- instrument. For more information, see [MAKOVSKY2001].
-
-
- Instrument Specifications - Spacecraft
- ======================================
- The 2001 Mars Odyssey spacecraft telecommunications
- subsystem served as part of a radio science subsystem for
- investigations of Mars. Many details of the subsystem are
- unknown; its 'build date' is taken to be 2001-04-01, which
- was near the end of the Prelaunch Phase of the ODY mission.
-
- Instrument Id : RSS
- Instrument Host Id : ODY
- Pi Pds User Id : UNK
- Instrument Name : RADIO SCIENCE SUBSYSTEM
- Instrument Type : RADIO SCIENCE
- Build Date : 2001-04-01
- Instrument Mass : UNK
- Instrument Length : UNK
- Instrument Width : UNK
- Instrument Height : UNK
- Instrument Manufacturer Name : UNK
-
-
- Instrument Overview - Spacecraft
- ================================
- The spacecraft radio system was constructed around a
- redundant pair of X-band Small Deep Space Transponders (SDSTs).
- Other components included one low-gain receive antenna (LGA);
- one medium-gain transmit antenna (MGA); one steerable
- high-gain antenna (HGA) for both transmitting (Tx) and receiving
- (Rx); two redundant solid state power amplifiers (SSPAs); a
- diplexer; several switches; and cabling. The SDSTs were
- connected to redundant Command and Data Handling (C&DH) units
- in such a way that any pairing could be chosen. A functional
- block diagram is shown below.
-
- . . . . . . . .
- DIPLEXER . .
- --- . / .
- ---------------------| |------------/ .
- | --- . \ HGA .
- | _ BPF1 | . \ .
- ----------|_| | . .
- | | / \ | . / .
- | |_____| S1 |________________________/ .
- | \ / . \ MGA .
- | \_/ | . \ .
- | |_| | . .
- | | BPF2 | . .
- |\| |\| | . HGA ASSEMBLY.
- | \ | \ | . . . . . . . .
- | / SSPA_1 | / SSPA_2 | /
- |/| |/| | /
- | | | HGA GIMBAL
- | | | ASSEMBLY
- --------------- |
- | 3 dB HYBRID | |
- | COUPLER | |
- --------------- |
- | | |
- | | |
- ------ ------ |
- |SDST_1| |SDST_2| |
- ------ ------ |
- | \ / | |
- | X | |
- | / \ | -
- ------ ------ _ / \ _ NF1
- ---|C&DH_A| |C&DH_B|-------|_| S2 |_|--
- | ------ ------ NF2 \ / |
- | - |
- | | | /
- | ----------/
- | | \ LGA
- ---------------------------------------- \
-
- S1 was a waveguide transfer switch with positions:
-1. SSPA_1 to HGA and SSPA_2 to MGA
-2. SSPA_1 to MGA and SSPA_2 to HGA
- (Insertion loss, <0.05 dB)
- S2 was a coaxial transfer switch with positions:
-1. SDST_1 to LGA and SDST_2 to HGA
-2. SDST_1 to HGA and SDST_2 to LGA
- (insertion loss, <0.3 dB)
- BPF_1 and BPF_2 were bandpass filters
- (<0.2 dB insertion loss over 8400-8450 MHz)
- NF1 and NF2 were notch filters
- (>70 dB rejection over 8400-8450 MHz)
- The X-Band Diplexer insertion loss was 0.1 DB (Tx), 0.2 dB (Rx)
-
- End-to-end circuit losses are given in the following table:
-
- ========================================================
- | Link/Direction | Elements | Value |
- +------------------+---------------+-------------------+
- | X-Band Transmit | SSPA to HGA | -0.25 +/- 0.11 dB |
- +------------------+---------------+-------------------+
- | X-Band Transmit | SSPA to MGA | -0.52 +/- 0.35 dB |
- +------------------+---------------+-------------------+
- | X-Band Receive | HGA to SDST | -8.13 +/- 0.03 dB |
- +------------------+---------------+-------------------+
- | X-Band Receive | LGA to SDST | -2.43 +/- 0.02 dB |
- ========================================================
-
- SSPA output power design was for 15 W (41.8 dBm) at end of life.
-
- The ODY telecommunications system was designed to perform the
- following functions:
-
- 1) Receive an X-band uplink carrier from a DSN station and
- demodulate the command data and ranging signal if either
- were present;
- 2) Generate an X-band downlink carrier either by coherently
- multiplying the frequency of the uplink carrier by the
- turn-around ratio of 880/749 or by utilizing an
- auxiliary crystal oscillator (AUX OSC);
- 3) Phase modulate the downlink carrier with either (or both)
- of the following:
- a composite telemetry signal, consisting of a square
- wave subcarrier (25 kHz or 375 kHz) that was BPSK
- (binary phase shift keying) modulated by telemetry data
- provided by the C&DH subsystem;
- the ranging signal that was demodulated from the uplink
- (this is referred to as two-way, or turn-around,
- ranging);
- 4) Permit control of the telecom subsystem through commands
- to select signal routing and the operational mode of the
- subsystem either from the ground or from command
- sequences previously loaded on the spacecraft;
- 5) Provide telecom status for monitoring operating
- conditions of the subsystem;
- 6) Provide ON/OFF power control for all RF transmitters;
- 7) Assume a single well-defined operating mode (a known
- baseline state) after a Power-On-Reset (POR).
-
- The X-band capability reduced plasma effects on radio
- signals by a factor of 10 compared with older S-band
- systems, but absence of a dual-frequency capability (both
- S- and X-band) meant that plasma effects could not be
- estimated and removed from radio data.
-
- The spacecraft also carried redundant ultra-high frequency (UHF)
- transceivers for communication and relay with future missions.
- Since the UHF equipment was not used for radio science, it is
- not described here.
-
-
- Science Objectives
- ==================
- There were no radio science objectives for the 2001 Mars Odyssey
- mission. The radio tracking data could be used by others to
- improve knowledge of the Mars gravity field .
-
-
- Operational Considerations - Spacecraft
- =======================================
- Descriptions given here are for nominal performance. The
- spacecraft transponder system comprised redundant units,
- each with slightly different characteristics. As
- transponder units age, their performance changes slightly.
- More importantly, the performance for radio science depended
- on operational factors such as the modulation state for the
- transmitters, which cannot be predicted in advance. The
- performance also depended on factors which were not always
- under the control of the 2001 Mars Odyssey Project.
-
- The telecom subsystem relied on C&DH to control its operating
- mode; that control could be done via real-time commands from
- the ground or via a stored sequence onboard the spacecraft.
- The only exception was the POR state, which would be entered
- directly after a Power-On-Reset.
-
- C&DH provided the data to be downlinked, it carried out the
- frame and packet formatting and the Reed-Solomon encoding,
- and it provided the clock to drive the encoding. The clock was
- either
- data clock X 2 for (7,1/2) encoding or
- data clock X 6 for (15,1/6) encoding
- C&DH also handled error control for the uplink data stream.
-
-
- Calibration Description - Spacecraft
- ====================================
- All measurements below were made during the Prelaunch Phase of
- The mission.
-
- Antenna characteristics are listed below. Masses of MGA and
- HGA are combined. Gain and axial ratio are given for boresight.
- Beamwidth is between the 3 dB points.
-
- =========================================================
- | Antenna Characteristics - 2001 Mars Odyssey |
- +-----------------+---------+--------+--------+---------+
- | | MGA | HGA | LGA |
- | Parameter +---------+--------+--------+---------|
- | | Tx Only | Tx | Rx | Rx Only |
- +-----------------+---------+--------+--------+---------+
- |Frequency (MHz) | 8406.851852 | 7155.377315 |
- +-----------------+---------+--------+--------+---------+
- |Diameter (m) | N/A | 1.3 | N/A |
- +-----------------+---------+--------+--------+---------+
- |Mass (kg) | 3.150 | 0.040 |
- +-----------------+---------+--------+--------+---------+
- |Gain (dBi) | 16.5 | 38.3 | 36.6 | 7+/-4 |
- +-----------------+---------+--------+--------+---------+
- |Axial Ratio (dB) | N/A | 1.35 | 1.24 | 3 |
- +-----------------+---------+--------+--------+---------+
- |Beamwidth (deg) | 28 | 1.9 | 2.3 | 82 |
- =========================================================
-
- Receiver Carrier Loop characteristics were as follows:
-
- =========================================================
- | Parameter | Value |
- +------------------+------------------------------------+
- |Noise Figure | 2.70 +0.60/-0.73 dB averaged over |
- | | lifetime aging, temperature,|
- | | and radiation |
- +------------------+------------------------------------|
- |Tracking | -155 to -156 dBm |
- | Threshold | |
- +------------------+------------------------------------|
- |Tracking Rate | 200 Hz/s for uplink Pt <= -120 dBm |
- +------------------+------------------------------------|
- |Capture Range | +/-1.3 kHz |
- +------------------+------------------------------------|
- |Tracking Range | +100 kHz/-200 kHz relative to best |
- | | lock frequency |
- +------------------+------------------------------------|
- |Carrier Loop | 20 Hz |
- | Threshold | |
- | Bandwidth | |
- +------------------+------------------------------------|
- |Strong Signal Open| 2.0e+07 |
- | Loop Gain | |
- +------------------+------------------------------------|
- |Predetection Noise| 12500 Hz |
- | Bandwidth | |
- +------------------+------------------------------------|
- |Loop Pole Time | 2258.6 s |
- | Constant | |
- +------------------+------------------------------------|
- |Loop Zero Time | 0.050 s |
- | Constant | |
- +------------------+------------------------------------|
- |Strong Signal Loop| 231.306 Hz two-sided at Pc/No = |
- | Noise Bandwidth | 100 dB-Hz |
- =========================================================
-
- The SDST ranging performance is listed in the table below.
- One range unit was 0.947 nanoseconds for 2001 Mars Odyssey.
-
- ==========================================================
- | Parameter | Value (average over 3 devices) |
- +---------------------+----------------------------------+
- |Range Delay | 1417.2 range units |
- +---------------------+----------------------------------+
- |Temperature Variation| +/-4.0 ru (-25C to +30C) |
- +---------------------+----------------------------------+
- |Carrier Suppression | 0.5 dB (17.5 deg range mod index)|
- | | 1.9 dB (35.0 deg range mod index)|
- +---------------------+----------------------------------+
- |3 dB Bandwidth | 1.4 MHz |
- +---------------------+----------------------------------+
- |Noise Equivalent | 2.0 MHz |
- | Bandwidth | |
- ==========================================================
-
-
-
- Platform Mounting Descriptions - Spacecraft
- ===========================================
- During the Launch, Cruise, Orbit Insertion, and Aerobraking
- phases of the mission, the HGA was stowed so that its
- boresight and the MGA boresight were along the +X axis. After
- aerobraking, the HGA was deployed and tracked the
- Earth using a pair of gimbals (azimuth and elevation) at the
- end of a boom.
- The MGA was mounted on the HGA dish so that the MGA and HGA
- boresights were equal. The SSPAs were mounted behind the HGA
- reflector to minimize circuit losses.
-
-
- Investigators
- =============
- None.
-
-
- Instrument Section / Operating Mode Descriptions - Spacecraft
- =============================================================
- Redundant components could be configured as desired. Each
- configuration had slightly different performance, but the
- quantitative differences are unknown.
-
-
- Instrument Overview - DSN
- =========================
- Three Deep Space Communications Complexes (DSCCs) (near
- Barstow, CA; Canberra, Australia; and Madrid, Spain) comprise
- the DSN tracking network. Each complex is equipped with
- several antennas [including at least one each 70-m, 34-m High
- Efficiency (HEF), and 34-m Beam WaveGuide (BWG)], associated
- electronics, and operational systems. Primary activity
- at each complex is radiation of commands to and reception of
- telemetry data from active spacecraft. Transmission and
- reception is possible in several radio-frequency bands, the
- most common being S-band (nominally a frequency of 2100-2300 MHz
- or a wavelength of 14.2-13.0 cm) and X-band (7100-8500 MHz or
- 4.2-3.5 cm). Transmitter output powers of up to 400 kW are
- available.
-
- Ground stations have the ability to transmit coded and uncoded
- waveforms which can be echoed by distant spacecraft. Analysis
- of the received coding allows navigators to determine the
- distance to the spacecraft; analysis of Doppler shift on the
- carrier signal allows estimation of the line-of-sight
- spacecraft velocity. Range and Doppler measurements are used
- to calculate the spacecraft trajectory and to infer gravity
- fields of objects near the spacecraft.
-
- Ground stations can record spacecraft signals that have
- propagated through or been scattered from target media.
- Measurements of signal parameters after wave interactions with
- surfaces, atmospheres, rings, and plasmas are used to infer
- physical and electrical properties of the target.
-
- Principal investigators vary from experiment to experiment.
- See the corresponding section of the spacecraft instrument
- description or the data set description for specifics.
-
- The Deep Space Network is managed by the Jet Propulsion
- Laboratory of the California Institute of Technology for the
- U.S. National Aeronautics and Space Administration.
- Specifications include:
-
- Instrument Id : RSS
- Instrument Host Id : DSN
- Pi Pds User Id : N/A
- Instrument Name : RADIO SCIENCE SUBSYSTEM
- Instrument Type : RADIO SCIENCE
- Build Date : N/A
- Instrument Mass : N/A
- Instrument Length : N/A
- Instrument Width : N/A
- Instrument Height : N/A
- Instrument Manufacturer Name : N/A
-
- For more information on the Deep Space Network and its use in
- radio science see reports by [ASMAR&RENZETTI1993],
- [ASMAR&HERRERA1993], and [ASMARETAL1995]. For design
- specifications on DSN subsystems see [DSN810-5]. For DSN use
- with MGS Radio Science see [TYLERETAL1992], [TYLERETAL2001],
- and [JPLD-14027].
-
-
- Subsystems - DSN
- ================
- The Deep Space Communications Complexes (DSCCs) are an integral
- part of Radio Science instrumentation, along with the spacecraft
- Radio Frequency Subsystem. Their system performance directly
- determines the degree of success of Radio Science
- investigations, and their system calibration determines the
- degree of accuracy in the results of the experiments. The
- following paragraphs describe the functions performed by the
- individual subsystems of a DSCC. This material has been adapted
- from [ASMAR&HERRERA1993] and [JPLD-14027]; for additional
- information, consult [DSN810-5].
-
- Each DSCC includes a set of antennas, a Signal Processing
- Center (SPC), and communication links to the Jet Propulsion
- Laboratory (JPL). The general configuration is illustrated
- below; antennas (Deep Space Stations, or DSS -- a term carried
- over from earlier times when antennas were individually
- instrumented) are listed in the table.
-
- -------- -------- -------- -------- --------
- | DSS 25 | | DSS 27 | | DSS 14 | | DSS 15 | | DSS 16 |
- |34-m BWG| |34-m HSB| | 70-m | |34-m HEF| | 26-m |
- -------- -------- -------- -------- --------
- | | | | |
- | v v | v
- | --------- | ---------
- --------->|GOLDSTONE|<---------- |EARTH/ORB|
- | SPC 10 |<-------------->| LINK |
- --------- ---------
- | SPC |<-------------->| 26-M |
- | COMM | ------>| COMM |
- --------- | ---------
- | | |
- v | v
- ------ --------- | ---------
- | NOCC |<--->| JPL |<------- | |
- ------ | CENTRAL | | GSFC |
- ------ | COMM | | NASCOMM |
- | MCCC |<--->| TERMINAL|<-------------->| |
- ------ --------- ---------
- ^ ^
- | |
- CANBERRA (SPC 40) <---------------- |
- |
- MADRID (SPC 60) <----------------------
-
- GOLDSTONE CANBERRA MADRID
- Antenna SPC 10 SPC 40 SPC 60
- -------- --------- -------- --------
- 26-m DSS 16 DSS 46 DSS 66
- 34-m HEF DSS 15 DSS 45 DSS 65
- 34-m BWG DSS 24 DSS 34 DSS 54
- DSS 25
- DSS 26
- 34-m HSB DSS 27
- DSS 28
- 70-m DSS 14 DSS 43 DSS 63
- Developmental DSS 13
-
-
- Subsystem interconnections at each DSCC are shown in the
- diagram below, and they are described in the sections that
- follow. The Monitor and Control Subsystem is connected to all
- other subsystems; the Test Support Subsystem can be.
-
- ----------- ------------------ --------- ---------
- |TRANSMITTER| | | | TRACKING| | COMMAND |
- | SUBSYSTEM |-| RECEIVER/EXCITER |-|SUBSYSTEM|-|SUBSYSTEM|-
- ----------- | | --------- --------- |
- | | SUBSYSTEM | | | |
- ----------- | | --------------------- |
- | MICROWAVE | | | | TELEMETRY | |
- | SUBSYSTEM |-| |-| SUBSYSTEM |-
- ----------- ------------------ --------------------- |
- | |
- ----------- ----------- --------- -------------- |
- | ANTENNA | | MONITOR | | TEST | | DIGITAL | |
- | SUBSYSTEM | |AND CONTROL| | SUPPORT | |COMMUNICATIONS|-
- ----------- | SUBSYSTEM | |SUBSYSTEM| | SUBSYSTEM |
- ----------- --------- --------------
-
-
- DSCC Monitor and Control Subsystem
- ----------------------------------
- The DSCC Monitor and Control Subsystem (DMC) is part of the
- Monitor and Control System (MON) which also includes the
- ground communications Central Communications Terminal and the
- Network Operations Control Center (NOCC) Monitor and Control
- Subsystem. The DMC is the center of activity at a DSCC. The
- DMC receives and archives most of the information from the
- NOCC needed by the various DSCC subsystems during their
- operation. Control of most of the DSCC subsystems, as well
- as the handling and displaying of any responses to control
- directives and configuration and status information received
- from each of the subsystems, is done through the DMC. The
- effect of this is to centralize the control, display, and
- archiving functions necessary to operate a DSCC.
- Communication among the various subsystems is done using a
- Local Area Network (LAN) hooked up to each subsystem via a
- network interface unit (NIU).
-
-
- DSCC Antenna Mechanical Subsystem
- ---------------------------------
- Multi-mission Radio Science activities require support from
- the 70-m, 34-m HEF, and 34-m BWG antenna subnets. The
- antennas at each DSCC function as large-aperture collectors
- which, by double reflection, cause the incoming radio
- frequency (RF) energy to enter the feed horns. The large
- collecting surface of the antenna focuses the incoming energy
- onto a subreflector, which is adjustable in both axial and
- angular position. These adjustments are made to correct for
- gravitational deformation of the antenna as it moves between
- zenith and the horizon; the deformation can be as large as
- 5 cm. The subreflector adjustments optimize the channeling
- of energy from the primary reflector to the subreflector
- and then to the feed horns. The 70-m and 34-m HEF antennas
- have 'shaped' primary and secondary reflectors, with forms
- that are modified paraboloids. This customization allows
- more uniform illumination of one reflector by another. The
- BWG reflector shape is ellipsoidal.
-
- On the 70-m antennas, the subreflector directs
- received energy from the antenna onto a dichroic plate, a
- device which reflects S-band energy to the S-band feed horn
- and passes X-band energy through to the X-band feed horn. In
- the 34-m HEF, there is one 'common aperture feed,' which
- accepts both frequencies without requiring a dichroic plate.
- In the 34-m BWG, a series of small mirrors (approximately 2.5
- meters in diameter) directs microwave energy from the
- subreflector region to a collection area at the base of
- the antenna -- typically in a pedestal room. A retractable
- dichroic reflector separates S- and X-band on some BWG
- antennas or X- and Ka-band on others. RF energy to be
- transmitted into space by the horns is focused by the
- reflectors into narrow cylindrical beams, pointed with high
- precision (either to the dichroic plate or directly to the
- subreflector) by a series of drive motors and gear trains
- that can rotate the movable components and their support
- structures.
-
- The different antennas can be pointed by several means. Two
- pointing modes commonly used during tracking passes are
- CONSCAN and 'blind pointing.' With CONSCAN enabled and a
- closed loop receiver locked to a spacecraft signal, the
- system tracks the radio source by conically scanning around
- its position in the sky. Pointing angle adjustments are
- computed from signal strength information (feedback) supplied
- by the receiver. In this mode the Antenna Pointing Assembly
- (APA) generates a circular scan pattern which is sent to the
- Antenna Control System (ACS). The ACS adds the scan pattern
- to the corrected pointing angle predicts. Software in the
- receiver-exciter controller computes the received signal
- level and sends it to the APA. The correlation of scan
- position with the received signal level variations allows the
- APA to compute offset changes which are sent to the ACS.
- Thus, within the capability of the closed-loop control
- system, the scan center is pointed precisely at the apparent
- direction of the spacecraft signal source. An additional
- function of the APA is to provide antenna position angles and
- residuals, antenna control mode/status information, and
- predict-correction parameters to the Area Routing Assembly
- (ARA) via the LAN, which then sends this information to JPL
- via the Ground Communications Facility (GCF) for antenna
- status monitoring.
-
- During periods when excessive signal level dynamics or low
- received signal levels are expected (e.g., during an
- occultation experiment), CONSCAN should not be used. Under
- these conditions, blind pointing (CONSCAN OFF) is used, and
- pointing angle adjustments are based on a predetermined
- Systematic Error Correction (SEC) model.
-
- Independent of CONSCAN state, subreflector motion in at least
- the z-axis may introduce phase variations into the received
- Radio Science data. For that reason, during certain
- experiments, the subreflector in the 70-m and 34-m HEFs may
- be frozen in the z-axis at a position (often based on
- elevation angle) selected to minimize phase change and signal
- degradation. This can be done via Operator Control Inputs
- (OCIs) from the LMC to the Subreflector Controller (SRC)
- which resides in the alidade room of the antennas. The SRC
- passes the commands to motors that drive the subreflector to
- the desired position.
-
- Pointing angles for all antenna types are computed by
- the NOCC Support System (NSS) from an ephemeris provided by
- the flight project. These predicts are received and archived
- by the CMC. Before each track, they are transferred to the
- APA, which transforms the direction cosines of the predicts
- into AZ-EL coordinates. The LMC operator then downloads the
- antenna predict points to the antenna-mounted ACS computer
- along with a selected SEC model. The pointing predicts
- consist of time-tagged AZ-EL points at selected time intervals
- along with polynomial coefficients for interpolation between
- points.
-
- The ACS automatically interpolates the predict points,
- corrects the pointing predicts for refraction and
- subreflector position, and adds the proper systematic error
- correction and any manually entered antenna offsets. The ACS
- then sends angular position commands for each axis at the
- rate of one per second. In the 70-m and 34-m HEF, rate
- commands are generated from the position commands at the
- servo controller and are subsequently used to steer the
- antenna.
-
- When not using binary predicts (the routine mode for
- spacecraft tracking), the antennas can be pointed using
- 'planetary mode' -- a simpler mode which uses right ascension
- (RA) and declination (DEC) values. These change very slowly
- with respect to the celestial frame. Values are provided to
- the station in text form for manual entry. The ACS
- quadratically interpolates among three RA and DEC points
- which are on one-day centers.
-
- A third pointing mode -- sidereal -- is available for
- tracking radio sources fixed with respect to the celestial
- frame.
-
- Regardless of the pointing mode being used, a 70-m antenna
- has a special high-accuracy pointing capability called
- 'precision' mode. A pointing control loop derives the
- main AZ-EL pointing servo drive error signals from a two-
- axis autocollimator mounted on the Intermediate Reference
- Structure. The autocollimator projects a light beam to a
- precision mirror mounted on the Master Equatorial drive
- system, a much smaller structure, independent of the main
- antenna, which is exactly positioned in HA and DEC with shaft
- encoders. The autocollimator detects elevation/cross-
- elevation errors between the two reference surfaces by
- measuring the angular displacement of the reflected light
- beam. This error is compensated for in the antenna servo by
- moving the antenna in the appropriate AZ-EL direction.
- Pointing accuracies of 0.004 degrees (15 arc seconds) are
- possible in 'precision' mode. The 'precision' mode is not
- available on 34-m antennas -- nor is it needed, since their
- beamwidths are twice as large as on the 70-m antennas.
-
-
- DSCC Antenna Microwave Subsystem
- --------------------------------
- 70-m Antennas: Each 70-m antenna has three feed cones
- installed in a structure at the center of the main reflector.
- The feeds are positioned 120 degrees apart on a circle.
- Selection of the feed is made by rotation of the
- subreflector. A dichroic mirror assembly, half on the S-band
- cone and half on the X-band cone, permits simultaneous use of
- the S- and X-band frequencies. The third cone is devoted to
- R&D and more specialized work.
-
- The Antenna Microwave Subsystem (AMS) accepts the received S-
- and X-band signals at the feed horn and transmits them
- through polarizer plates to an orthomode transducer. The
- polarizer plates are adjusted so that the signals are
- directed to a pair of redundant amplifiers for each
- frequency, thus allowing simultaneous reception of signals in
- two orthogonal polarizations. For S-band these are two Block
- IVA S-band Traveling Wave Masers (TWMs); for X-band the
- amplifiers are Block IIA TWMs.
-
- 34-m HEF Antennas: The 34-m HEF uses a single feed for both
- S- and X-band. Simultaneous S- and X-band receive as well as
- X-band transmit is possible thanks to the presence of an S/X
- 'combiner' which acts as a diplexer. For S-band, RCP or LCP
- is user selected through a switch so neither a polarizer nor
- an orthomode transducer is needed. X-band amplification
- options include two Block II TWMs or an HEMT Low Noise
- Amplifier (LNA). S-band amplification is provided by an FET
- LNA.
-
- 34-m BWG Antennas: These antennas use feeds and low-noise
- amplifiers (LNA) in the pedestal room, which can be switched
- in and out as needed. Typically the following modes are
- available:
- 1. downlink non-diplexed path (RCP or LCP) to LNA-1, with
- uplink in the opposite circular polarization;
- 2. downlink non-diplexed path (RCP or LCP) to LNA-2, with
- uplink in the opposite circular polarization
- 3. downlink diplexed path (RCP or LCP) to LNA-1, with
- uplink in the same circular polarization
- 4. downlink diplexed path (RCP or LCP) to LNA-2, with
- uplink in the same circular polarization
- For BWG antennas with dual-band capabilities (e.g., DSS 25)
- and dual LNAs, each of the above four modes can be used in a
- single-frequency or dual-frequency configuration. Thus, for
- antennas with the most complete capabilities, there are
- sixteen possible ways to receive at a single frequency
- (2 polarizations, 2 waveguide path choices, 2 LNAs, and 2
- bands).
-
-
- DSCC Receiver-Exciter Subsystem
- -------------------------------
- The Receiver-Exciter Subsystem is composed of two groups of
- equipment: the closed-loop receiver group and the open-loop
- receiver group. This subsystem is controlled by the
- Receiver-Exciter Controller (REC) which communicates
- directly with the DMC for predicts and OCI reception and
- status reporting.
-
- The exciter generates the S-band signal (or X-band for the
- 34-m HEF only) which is provided to the Transmitter Subsystem
- for the spacecraft uplink signal. It is tunable under
- command of the Digitally Controlled Oscillator (DCO) which
- receives predicts from the Metric Data Assembly (MDA).
-
- The diplexer in the signal path between the transmitter and
- the feed horn for all three antennas (used for simultaneous
- transmission and reception) may be configured such that it is
- out of the received signal path (in listen-only or bypass
- mode) in order to improve the signal-to-noise ratio in the
- receiver system.
-
- Closed Loop Receivers: The Block V receiver-exciter at the
- 70-m stations allows for two receiver channels, each capable
- of L-Band (e.g., 1668 MHz frequency or 18 cm wavelength),
- S-band, or X-band reception, and an S-band exciter for
- generation of uplink signals through the low-power or
- high-power transmitter.
-
- The closed-loop receivers provide the capability for rapid
- acquisition of a spacecraft signal and telemetry lockup. In
- order to accomplish acquisition within a short time, the
- receivers are predict driven to search for, acquire, and
- track the downlink automatically. Rapid acquisition
- precludes manual tuning though that remains as a backup
- capability. The subsystem utilizes FFT analyzers for rapid
- acquisition. The predicts are NSS generated, transmitted to
- the CMC which sends them to the Receiver-Exciter Subsystem
- where two sets can be stored. The receiver starts
- acquisition at uplink time plus one round-trip-light-time or
- at operator specified times. The receivers may also be
- operated from the LMC without a local operator attending
- them. The receivers send performance and status data,
- displays, and event messages to the LMC.
-
- Either the exciter synthesizer signal or the simulation
- (SIM) synthesizer signal is used as the reference for the
- Doppler extractor in the closed-loop receiver systems,
- depending on the spacecraft being tracked (and Project
- guidelines). The SIM synthesizer is not ramped; instead it
- uses one constant frequency, the Track Synthesizer Frequency
- (TSF), which is an average frequency for the entire pass.
-
- The closed-loop receiver AGC loop can be configured to one
- of three settings: narrow, medium, or wide. It will be
- configured such that the expected amplitude changes are
- accommodated with minimum distortion. The loop bandwidth
- (2BLo) will be configured such that the expected phase
- changes can be accommodated while maintaining the best
- possible loop SNR.
-
- Open-Loop Receivers (OLR): The OLR utilized a fixed first
- Local Oscillator (LO) frequency and a tunable second LO
- frequency to minimize phase noise and improve frequency
- stability. The OLR consisted of an RF-to-IF downconverter
- located at the feed , an IF selection switch (IFS), and a
- Radio Science Receiver (RSR). The RF-IF downconverters
- in the 70-m antennas were equipped for four IF channels:
- S-RCP, S-LCP, X-RCP, and X-LCP. The 34-m HEF stations
- were equipped with a two-channel RF-IF: S-band and X-band.
- The IFS switched the IF input among the antennas.
-
-
- DSCC Transmitter Subsystem
- --------------------------
- The Transmitter Subsystem accepts the S-band frequency
- exciter signal from the Receiver-Exciter Subsystem exciter
- and amplifies it to the required transmit output level. The
- amplified signal is routed via the diplexer through the feed
- horn to the antenna and then focused and beamed to the
- spacecraft.
-
- The Transmitter Subsystem power capabilities range from 18 kW
- to 400 kW. Power levels above 18 kW are available only at
- 70-m stations.
-
-
- DSCC Tracking Subsystem
- -----------------------
- The Tracking Subsystem primary functions are to acquire and
- maintain communications with the spacecraft and to generate
- and format radiometric data containing Doppler and range.
-
- The DSCC Tracking Subsystem (DTK) receives the carrier
- signals and ranging spectra from the Receiver-Exciter
- Subsystem. The Doppler cycle counts are counted, formatted,
- and transmitted to JPL in real time. Ranging data are also
- transmitted to JPL in real time. Also contained in these
- blocks is the AGC information from the Receiver-Exciter
- Subsystem. The Radio Metric Data Conditioning Team (RMDCT)
- at JPL produces an Archival Tracking Data File (ATDF) which
- contains Doppler and ranging data.
-
- In addition, the Tracking Subsystem receives from the CMC
- frequency predicts (used to compute frequency residuals and
- noise estimates), receiver tuning predicts (used to tune the
- closed-loop receivers), and uplink tuning predicts (used to
- tune the exciter). From the LMC, it receives configuration
- and control directives as well as configuration and status
- information on the transmitter, microwave, and frequency and
- timing subsystems.
-
- The Metric Data Assembly (MDA) controls all of the DTK
- functions supporting the uplink and downlink activities. The
- MDA receives uplink predicts and controls the uplink tuning
- by commanding the DCO. The MDA also controls the Sequential
- Ranging Assembly (SRA). It formats the Doppler and range
- measurements and provides them to the GCF for transmission to
- NOCC.
-
- The Sequential Ranging Assembly (SRA) measures the round trip
- light time (RTLT) of a radio signal traveling from a ground
- tracking station to a spacecraft and back. From the RTLT,
- phase, and Doppler data, the spacecraft range can be
- determined. A coded signal is modulated on an uplink carrier
- and transmitted to the spacecraft where it is detected and
- transponded back to the ground station. As a result, the
- signal received at the tracking station is delayed by its
- round trip through space and shifted in frequency by the
- Doppler effect due to the relative motion between the
- spacecraft and the tracking station on Earth.
-
-
- DSCC Frequency and Timing Subsystem
- -----------------------------------
- The Frequency and Timing Subsystem (FTS) provides all
- frequency and timing references required by the other DSCC
- subsystems. It contains four frequency standards of which
- one is prime and the other three are backups. Selection of
- the prime standard is done via the CMC. Of these four
- standards, two are hydrogen masers followed by clean-up loops
- (CUL) and two are cesium standards. These four standards all
- feed the Coherent Reference Generator (CRG) which provides
- the frequency references used by the rest of the complex. It
- also provides the frequency reference to the Master Clock
- Assembly (MCA) which in turn provides time to the Time
- Insertion and Distribution Assembly (TID) which provides UTC
- and SIM-time to the complex.
-
- JPL's ability to monitor the FTS at each DSCC is limited to
- the MDA calculated Doppler pseudo-residuals, the Doppler
- noise, the SSI, and to a system which uses the Global
- Positioning System (GPS). GPS receivers at each DSCC receive
- a one-pulse-per-second pulse from the station's (hydrogen
- maser referenced) FTS and a pulse from a GPS satellite at
- scheduled times. After compensating for the satellite signal
- delay, the timing offset is reported to JPL where a database
- is kept. The clock offsets stored in the JPL database are
- given in microseconds; each entry is a mean reading of
- measurements from several GPS satellites and a time tag
- associated with the mean reading. The clock offsets provided
- include those of SPC 10 relative to UTC (NIST), SPC 40
- relative to SPC 10, etc.
-
-
- Radio Science Receiver (RSR)
- ----------------------------
- A radio frequency (RF) spacecraft signal at S-band, X-band,
- or Ka-band is captured by a receiving antenna on Earth, down
- converted to an intermediate frequency (IF) near 300 MHz and
- then fed via a distribution network to one input of an IF
- Selector Switch (IFS). The IFS allows each RSR to select any
- of the available input signals for its RSR Digitizer (DIG).
- Within the RSR the digitized signal is then passed to the
- Digitial Down Converter (DDC), VME Data Processor (VDP), and
- Data Processor (DP) [JPLD-16765].
-
- \ ----------- ------ ----- ----- -----
- \ | RF TO IF | | |----| | | | | |
- |----| DOWN |----| |----| |----| DIG | | DP |
- / | CONVERTER | | |----| | | | | |
- / ----------- | IF |----| IFS | ----- -----
- ANTENNA --| DIST |----| | | |
- 300 MHz IF --| | .. | | ----- -----
- FROM OTHER --| |----| | | | | |
- ANTENNAS --| | ----- | DDC | | VDP |
- ------ | | | |
- ----- -----
- | |
- -------
-
- In the DIG the IF signal is passed through a programmable
- attenuator, adjusted to provide the proper level to the Analog
- to Digital Converter (ADC). The attenuated signal is then
- passed through a Band Pass Filter (BPF) which selects a
- frequency band in the range 265-375 MHz. The filtered output
- from the BPF is then mixed with a 256 MHz Local Oscillator
- (LO), low pass filtered (LPF), and sampled by the ADC. The
- output of the ADC is a stream of 8-bit real samples at 256
- Msamples/second (Msps). DIG timing is derived from the
- station FTS 5 MHz clock and 1 pulse per second (1PPS)
- reference; the DIG generates a 256 MHz clock signal for later
- processing. The 1PPS signal marks the data sample taken at
- the start of each second.
-
- The DDC selects one 16 MHz subchannel from the possible 128
- MHz bandwidth available from the DIG by using Finite Impulse
- Response (FIR) filters with revolving banks of filter
- coefficients. The sample stream from the DIG is separated
- into eight decimated streams, each of which is fed into two
- sets of FIR filters. One set of filters produces in-phase (I)
- 8-bit data while the other produces quadrature-phase (Q) 8-bit
- data. The center frequency of the desired 16 MHz channel is
- adjustable in 1 MHz steps and is usually chosen to be near the
- spacecraft carrier frequency. After combining the I and Q
- sample streams, the DDC feeds the samples to the VDP. The DDC
- also converts the 256 MHz data clock and 1PPS signals into a
- msec time code, which is also passed to the VDP.
-
- The VDP contains a quadruply-redundant set of custom boards
- which are controlled by a real-time control computer (RT).
- Each set of boards comprises a numerically controlled
- oscillator (NCO), a complex multiplier, a decimating FIR
- filter, and a data packer. The 16 Msps complex samples
- from the DDC are digitally mixed with the NCO signal in the
- complex multiplier. The NCO phase and frequency are updated
- every millisecond by the RT and are selected so that the
- center frequency of the desired portion of the 16 MHz channel
- is down-converted to 0 Hz. The RT uses polynomials derived
- from frequency predictions. The output of the complex
- multiplier is sent to the decimating FIR filter where its
- bandwidth and sample rate are reduced (see table below). The
- decimating FIR filter also allows adjustment of the
- sub-channel gain to take full advantage of the dynamic range
- available in the hardware. The data packer truncates samples
- to 1, 2, 4, 8, or 16 bits by dropping the least significant
- bits and packs them into 32-bit data words. Q-samples are
- packed into the first 16 bits of the word, and I-samples into
- the least significant 16 bits (see below). In 'narrow band'
- operation all four sets of sets of custom boards can be
- supported simultaneously. In 'medium band' operation no more
- than two channels can be supported simultaneously. In
- 'wide band' operation, only one sub-channel can be recorded.
-
- |============================================================|
- | RSR Sample Rates and Sample Sizes Supported |
- |================+=======+======+=================+==========|
- | Category | Rate | Size | Data Rate |Rec Length|
- | | (ksps)|(bits)|(bytes/s) (rec/s)| (bytes) |
- |================+=======+======+=========+=======+==========|
- |Narrow Band (NB)| 1 | 8 | 2000 | 1 | 2000 |
- | | 2 | 8 | 4000 | 1 | 4000 |
- | | 4 | 8 | 8000 | 1 | 8000 |
- | | 8 | 8 | 16000 | 1 | 16000 |
- | | 16 | 8 | 32000 | 2 | 16000 |
- | | 25 | 8 | 50000 | 2 | 25000 |
- | | 50 | 8 | 100000 | 4 | 25000 |
- | | 100 | 8 | 200000 | 10 | 20000 |
- | | 1 | 16 | 4000 | 1 | 4000 |
- | | 2 | 16 | 8000 | 1 | 8000 |
- | | 4 | 16 | 16000 | 1 | 16000 |
- | | 8 | 16 | 32000 | 2 | 16000 |
- | | 16 | 16 | 64000 | 4 | 16000 |
- | | 25 | 16 | 100000 | 4 | 25000 |
- | | 50 | 16 | 200000 | 10 | 20000 |
- | | 100 | 16 | 400000 | 20 | 20000 |
- |Medium Band (MB)| 250 | 1 | 62500 | 5 | 12500 |
- | | 500 | 1 | 125000 | 5 | 25000 |
- | | 1000 | 1 | 250000 | 10 | 25000 |
- | | 2000 | 1 | 500000 | 20 | 25000 |
- | | 4000 | 1 | 1000000 | 40 | 25000 |
- | | 250 | 2 | 125000 | 5 | 25000 |
- | | 500 | 2 | 250000 | 10 | 25000 |
- | | 1000 | 2 | 500000 | 20 | 25000 |
- | | 2000 | 2 | 1000000 | 40 | 25000 |
- | | 4000 | 2 | 2000000 | 100 | 20000 |
- | | 250 | 4 | 250000 | 10 | 25000 |
- | | 500 | 4 | 500000 | 20 | 25000 |
- | | 1000 | 4 | 1000000 | 40 | 25000 |
- | | 2000 | 4 | 2000000 | 100 | 20000 |
- | | 250 | 8 | 500000 | 20 | 25000 |
- | | 500 | 8 | 1000000 | 40 | 25000 |
- | | 1000 | 8 | 2000000 | 100 | 20000 |
- |Wide Band (WB) | 8000 | 1 | 2000000 | 100 | 20000 |
- | | 16000 | 1 | 4000000 | 200 | 20000 |
- | | 8000 | 2 | 4000000 | 200 | 20000 |
- |============================================================|
-
- |============================================================|
- | Sample Packing |
- |=================+==========================================|
- | Bits per Sample | Contents of 32-bit Packed Data Register |
- |=================+==========================================|
- | 16 | (Q1),(I1) |
- | 8 | (Q2,Q1),(I2,I1) |
- | 4 | (Q4,Q3,Q2,Q1),(I4,I3,I2,I1) |
- | 2 | (Q8,Q7,...Q1),(I8,I7,...I1) |
- | 1 | (Q16,Q15,...Q1),(I16,I15,...I1) |
- |============================================================|
-
- Once per second the RT sends the accumulated data records from
- each sub-channel to the Data Processor (DP) over a 100 Mbit/s
- ethernet connection. In addition to the samples, each data
- record includes header information such as time tags and NCO
- frequency and phase that are necessary for analysis. The DP
- processes the data records to provide monitor data, such as
- power spectra. If recording has been enabled, the records are
- stored by the DP.
-
- NCO Phase and Frequency
- -----------------------
- At the start of each DSN pass, the RSR is provided with a
- file containing a list of predicted frequencies. Using these
- points, the RT computes expected sky frequencies at the
- beginning, middle, and end of each one second time interval.
- Based on the local oscillator frequencies selected and any
- offsets entered, the RT computes the coefficients of a
- frequency polynomial fitted to the DDC channel frequencies
- at these three times. The RT also computes a phase
- polynomial by integrating the frequency polynomial and
- matching phases at the one second boundaries.
-
- The phase and frequency of the VDP NCO's are computed every
- millisecond (000-999) from the polynomial coefficients as
- follows:
-
- nco_phase(msec) = phase_coef_1 +
- phase_coef_2 * (msec/1000) +
- phase_coef_3 * (msec/1000)**2 +
- phase_coef_4 * (msec/1000)**3
-
- nco_freq(msec) = freq_coef_1 +
- freq_coef_2 * ((msec + 0.5)/1000) +
- freq_coef_3 * ((msec + 0.5)/1000)**2
-
- The sky frequency may be reconstructed using
-
- sky_freq = RF_to_IF_LO +
- DDC_LO -
- nco_freq +
- reside_freq
-
- where RF_to_IF_LO is the down conversion from the
- microwave frequency to IF (bytes 42-43
- in the data record header)
- DDC_LO is the down-conversion applied in the
- DIG and DDC (bytes 40-41 in the data
- record header)
- Resid_Freq is the frequency of the signal in the
- VDP output
-
-
- Detectors - DSN
- ===============
- Nominal carrier tracking loop threshold noise bandwidth at
- X-band is 10 Hz. Coherent (two-way) closed-loop
- system stability is shown in the table below:
-
- integration time Doppler uncertainty
- (secs) (one sigma, microns/sec)
- ------ ------------------------
- 10 50
- 60 20
- 1000 4
-
- For the open-loop subsystem, signal detection is done in
- software.
-
-
- Calibration - DSN
- =================
- Calibrations of hardware systems are carried out periodically
- by DSN personnel; these ensure that systems operate at required
- performance levels -- for example, that antenna patterns,
- receiver gain, propagation delays, and Doppler uncertainties
- meet specifications. No information on specific calibration
- activities is available. Nominal performance specifications
- are shown in the tables above. Additional information may be
- available in [DSN810-5].
-
- Prior to each tracking pass, station operators perform a series
- of calibrations to ensure that systems meet specifications for
- that operational period. Included in these calibrations is
- measurement of receiver system temperature in the configuration
- to be employed during the pass. Results of these calibrations
- are recorded in (hard copy) Controller's Logs for each pass.
-
- The nominal procedure for initializing open-loop receiver
- attenuator settings is described below. In cases where widely
- varying signal levels are expected, the procedure may be
- modified in advance or real-time adjustments may be made to
- attenuator settings.
-
-
- Operational Considerations - DSN
- ================================
- The DSN is a complex and dynamic 'instrument.' Its performance
- for Radio Science depends on a number of factors from equipment
- configuration to meteorological conditions. No specific
- information on 'operational considerations' can be given here.
-
-
- Operational Modes - DSN
- =======================
-
- DSCC Antenna Mechanical Subsystem
- ---------------------------------
- Pointing of DSCC antennas may be carried out in several ways.
- For details see the subsection 'DSCC Antenna Mechanical
- Subsystem' in the 'Subsystem' section. Binary pointing is
- the preferred mode for tracking spacecraft; pointing
- predicts are provided, and the antenna simply follows those.
- With CONSCAN, the antenna scans conically about the optimum
- pointing direction, using closed-loop receiver signal
- strength estimates as feedback. In planetary mode, the
- system interpolates from three (slowly changing) RA-DEC
- target coordinates; this is 'blind' pointing since there is
- no feedback from a detected signal. In sidereal mode, the
- antenna tracks a fixed point on the celestial sphere. In
- 'precision' mode, the antenna pointing is adjusted using an
- optical feedback system. It is possible on most antennas to
- freeze z-axis motion of the subreflector to minimize phase
- changes in the received signal.
-
-
- DSCC Receiver-Exciter Subsystem
- -------------------------------
- The diplexer in the signal path between the transmitter and
- the feed horns on all antennas may be configured so
- that it is out of the received signal path in order to
- improve the signal-to-noise ratio in the receiver system.
- This is known as the 'listen-only' or 'bypass' mode.
-
-
- Closed-Loop Receiver AGC Loop
- -----------------------------
- The closed-loop receiver AGC loop can be configured to one of
- three settings: narrow, medium, or wide. Ordinarily it is
- configured so that expected signal amplitude changes are
- accommodated with minimum distortion. The loop bandwidth is
- ordinarily configured so that expected phase changes can be
- accommodated while maintaining the best possible loop SNR.
-
-
- Coherent vs. Non-Coherent Operation
- -----------------------------------
- The frequency of the signal transmitted from the spacecraft
- can generally be controlled in two ways -- by locking to a
- signal received from a ground station or by locking to an
- on-board oscillator. These are known as the coherent (or
- 'two-way') and non-coherent ('one-way') modes, respectively.
- Mode selection is made at the spacecraft, based on commands
- received from the ground. When operating in the coherent
- mode, the transponder carrier frequency is derived from the
- received uplink carrier frequency with a 'turn-around ratio'
- typically of 880/749. In the non-coherent mode, the
- downlink carrier frequency is derived from the spacecraft
- on-board crystal-controlled oscillator. Either closed-loop
- or open-loop receivers (or both) can be used with either
- spacecraft frequency reference mode. Closed-loop reception
- in two-way mode is usually preferred for routine tracking.
- Occasionally the spacecraft operates coherently while two
- ground stations receive the 'downlink' signal; this is
- sometimes known as the 'three-way' mode.
-
-
- Location - DSN
- ==============
- Station locations are documented in [GEO-10REVD]. Geocentric
- coordinates are summarized here.
-
- Geocentric Geocentric Geocentric
- Station Radius (km) Latitude (N) Longitude (E)
- --------- ----------- ------------ -------------
- Goldstone
- DSS 13 (34-m R&D) 6372.125125 35.0660185 243.2055430
- DSS 14 (70-m) 6371.993286 35.2443527 243.1104638
- DSS 15 (34-m HEF) 6371.966540 35.2403133 243.1128069
- DSS 24 (34-m BWG) 6371.973553 35.1585349 243.1252079
- DSS 25 (34-m BWG) 6371.983060 35.1562594 243.1246384
- DSS 26 (34-m BWG) 6371.993032 35.1543411 243.1269849
-
- Canberra
- DSS 34 (34-m BWG) 6371.693561 -35.2169868 148.9819620
- DSS 43 (70-m) 6371.689033 -35.2209234 148.9812650
- DSS 45 (34-m HEF) 6371.675906 -35.2169652 148.9776833
-
- Madrid
- DSS 45 (34-m BWG) 6370.025429 40.2357708 355.7459008
- DSS 63 (70-m) 6370.051221 40.2413537 355.7519890
- DSS 65 (34-m HEF) (see next paragraph)
-
- The coordinates for DSS 65 until 1 February 2005 were
- 6370.021697 40.2373325 355.7485795
- In cartesian coordinates (x, y, z) this was
- (+4849336.6176, -0360488.6349, +4114748.9218)
- Between February and September 2005, the antenna was
- physically moved to
- (+4849339.6448, -0360427.6560, +4114750.7428)
-
-
- Measurement Parameters - DSN
- ============================
- Closed-loop data are recorded in Archival Tracking Data Files
- (ATDFs), as well as certain secondary products such as the
- Orbit Data File (ODF). The ATDF Tracking Logical Record
- contains 150 entries including status information and
- measurements of ranging, Doppler, and signal strength.
-
-
- ACRONYMS AND ABBREVIATIONS - DSN
- ================================
- ACS Antenna Control System
- ADC Analog-to-Digital Converter
- AGC Automatic Gain Control
- AMS Antenna Microwave System
- APA Antenna Pointing Assembly
- ARA Area Routing Assembly
- ATDF Archival Tracking Data File
- AUX Auxiliary
- AZ Azimuth
- BPF Band Pass Filter
- bps bits per second
- BWG Beam WaveGuide (antenna)
- CDU Command Detector Unit
- CMC Complex Monitor and Control
- CONSCAN Conical Scanning (antenna pointing mode)
- CRG Coherent Reference Generator
- CUL Clean-up Loop
- DANA a type of frequency synthesizer
- dB deciBel
- dBi dB relative to isotropic
- dBm dB relative to one milliwatt
- DCO Digitally Controlled Oscillator
- DDC Digital Down Converter
- DEC Declination
- deg degree
- DIG RSR Digitizer
- DMC DSCC Monitor and Control Subsystem
- DOR Differential One-way Ranging
- DP Data Processor
- DSCC Deep Space Communications Complex
- DSN Deep Space Network
- DSP DSCC Spectrum Processing Subsystem
- DSS Deep Space Station
- DTK DSCC Tracking Subsystem
- E east
- EIRP Effective Isotropic Radiated Power
- EL Elevation
- FET Field Effect Transistor
- FFT Fast Fourier Transform
- FIR Finite impulse Response
- FTS Frequency and Timing Subsystem
- GCF Ground Communications Facility
- GHz Gigahertz
- GPS Global Positioning System
- HA Hour Angle
- HEF High-Efficiency (as in 34-m HEF antennas)
- HEMT High Electron Mobility Transistor (amplifier)
- HGA High-Gain Antenna
- HSB High-Speed BWG
- IF Intermediate Frequency
- IFS IF Selector Switch
- IVC IF Selection Switch
- JPL Jet Propulsion Laboratory
- K Kelvin
- Ka-Band approximately 32 GHz
- KaBLE Ka-Band Link Experiment
- kbps kilobits per second
- kHz kilohertz
- km kilometer
- kW kilowatt
- LAN Local Area Network
- LCP Left-Circularly Polarized
- LGR Low-Gain Receive (antenna)
- LGT Low-Gain Transmit (antenna)
- LMA Lockheed Martin Astronautics
- LMC Link Monitor and Control
- LNA Low-Noise Amplifier
- LO Local Oscillator
- LPF Low Pass Filter
- m meters
- MCA Master Clock Assembly
- MCCC Mission Control and Computing Center
- MDA Metric Data Assembly
- MGS Mars Global Surveyor
- MHz Megahertz
- MOLA Mars Orbiting Laser Altimeter
- MON Monitor and Control System
- MOT Mars Observer Transponder
- MSA Mission Support Area
- N north
- NAR Noise Adding Radiometer
- NBOC Narrow-Band Occultation Converter
- NCO Numerically Controlled Oscillator
- NIST SPC 10 time relative to UTC
- NIU Network Interface Unit
- NOCC Network Operations and Control System
- NRV NOCC Radio Science/VLBI Display Subsystem
- NSS NOCC Support System
- OCI Operator Control Input
- ODF Orbit Data File
- ODR Original Data Record
- ODS Original Data Stream
- OLR Open Loop Receiver
- OSC Oscillator
- PDS Planetary Data System
- POCA Programmable Oscillator Control Assembly
- PPM Precision Power Monitor
- RA Right Ascension
- REC Receiver-Exciter Controller
- RCP Right-Circularly Polarized
- RF Radio Frequency
- RIC RIV Controller
- RIV Radio Science IF-VF Converter Assembly
- RMDCT Radio Metric Data Conditioning Team
- RMS Root Mean Square
- RSR Radio Science Receiver
- RSS Radio Science Subsystem
- RT Real-Time (control computer)
- RTLT Round-Trip Light Time
- S-band approximately 2100-2300 MHz
- sec second
- SEC System Error Correction
- SIM Simulation
- SLE Signal Level Estimator
- SNR Signal-to-Noise Ratio
- SNT System Noise Temperature
- SOE Sequence of Events
- SPA Spectrum Processing Assembly
- SPC Signal Processing Center
- sps samples per second
- SRA Sequential Ranging Assembly
- SRC Sub-Reflector Controller
- SSI Spectral Signal Indicator
- TID Time Insertion and Distribution Assembly
- TLM Telemetry
- TSF Tracking Synthesizer Frequency
- TWM Traveling Wave Maser
- TWNC Two-Way Non-Coherent
- TWTA Traveling Wave Tube Amplifier
- UNK unknown
- USO UltraStable Oscillator
- UTC Universal Coordinated Time
- VCO Voltage-Controlled Oscillator
- VDP VME Data Processor
- VF Video Frequency
- X-band approximately 7800-8500 MHz
+
+ The Radio Science Subsystem of the 2001 Mars Odyssey mission was made up of the
+ spacecraft telecommunications subsystem and the DSN (ground).
-
+ There were no recognized radio science investigations on
+ the 2001 Mars Odyssey (ODY) mission. But investigators on
+ Mars Global Surveyor (MGS) requested access to ODY radio
+ tracking data. To support them and future proposers to
+ Mars data analysis programs (MDAPs), the Planetary Data
+ System (PDS) accepted responsibility for archiving the ODY
+ data with initial activities funded jointly by MGS.
+
diff --git a/data/pds4/context-pds4/instrument/ody.rss_1.1.xml b/data/pds4/context-pds4/instrument/ody.rss_1.1.xml
new file mode 100644
index 00000000..85a1b142
--- /dev/null
+++ b/data/pds4/context-pds4/instrument/ody.rss_1.1.xml
@@ -0,0 +1,163 @@
+
+
+
+
+
+ urn:nasa:pds:context:instrument:ody.rss
+ 1.1
+ Radio Science Subsystem for ODY
+ 1.22.0.0
+ Product_Context
+
+
+ RSS
+
+ urn:nasa:pds:context:instrument:rss.ody
+
+
+
+
+ 2023-09-15
+ 1.0
+
+ Update to ody.rss and set alias to the original rss.ody.
+ Updated to PDS4_PDS_1F00.xsd
+ Added ctli for updated Instrument class, type = Atmospheric Structure Instrument
+ And per "Guide toPDS4 Context Products" v1.8,
+ changed all lidvid_reference to lid_reference
+
+
+
+ 2024-10-02
+ 1.1
+
+ Where applicable, updated version, title, name
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.ody
+ instrument_to_instrument_host
+
+
+ urn:nasa:pds:context:investigation:mission.2001_mars_odyssey
+ instrument_to_investigation
+
+
+ urn:nasa:pds:context:investigation:mission.2001_mars_odyssey
+ instrument_to_investigation
+
+
+
+ Asmar, S.W., and R.G. Herrera, Radio Science Handbook, JPL D-7938, Volume 4,
+ Jet Propulsion Laboratory, Pasadena, CA, 22 January 1993.
+
+ reference.ASMAR-HERRERA1993
+
+
+
+ Asmar, S. W., N. A. Renzetti, The Deep Space Network as an instrument for radio
+ science research, NASA Technical Reports Server, 1993STIN...9521456A, 1993.
+
+ reference.ASMAR-RENZETTI1993
+
+
+
+ Asmar, S.W., R.G. Herrera, and T. Priest, Radio Science Handbook, JPL D-7938,
+ Volume 6, Jet Propulsion Laboratory, Pasadena, CA, 1995.
+
+ reference.ASMARETAL1995
+
+
+
+ Deep Space Network / Flight Project Interface Design Book, Document 810-5, Jet
+ Propulsion Laboratory, Pasadena, CA.
+
+ reference.DSN810-5
+
+
+
+ DSN Geometry and Spacecraft Visibility, Document 810-5, Rev. D, Vol. 1,
+ DSN/Flight Project Interface Design, Jet Propulsion Laboratory, Pasadena, CA,
+ 1987.
+
+ reference.GEO-10REVD
+
+
+
+ Mars Global Surveyor Project, Telecommunications System Operations Reference
+ Handbook, Version 2.1 (MGS 542-257), JPL Document D-14027, Jet Propulsion
+ Laboratory, Pasadena, CA, 1996.
+
+ reference.JPLD-14027
+
+
+
+ Deep Space Mission System (DSMS) External Interface Specification (820-013, JPL
+ D-16765), Radio Science Receiver Standard Formatted Data Unit (SFDU), Jet
+ Propulsion Laboratory, Pasadena, CA, 2001.
+
+ reference.JPLD-16765
+
+
+
+ Makovsky, A., Mars 2001 Odyssey Telecommunications System Operations
+ Handbook, JPL Document D-19010, Jet Propulsion Laboratory, Pasadena, CA,
+ 2001.
+
+ reference.MAKOVSKY2001
+
+
+
+ Tyler, G.L., G. Balmino, D.P. Hinson, W.L. Sjogren, D.E. Smith, R. Woo, S.W.
+ Asmar, M.J. Connally, C.L. Hamilton, and R.A. Simpson, Radio Science
+ Investigations with Mars Observer, Journal of Geophysical Research, 97,
+ 7759-7779, 1992.
+
+ reference.TYLERETAL1992
+
+
+
+ Tyler, G.L., G. Balmino, D.P. Hinson, W.L. Sjogren, D.E. Smith, R.A. Simpson,
+ S.W. Asmar, P. Priest, and J.D. Twicken, Radio science observations with Mars
+ Global Surveyor: Orbit insertion through one Mars year in mapping orbit,
+ Journal of Geophysical Research, 106, 23327-23348, 2001.
+
+ reference.TYLERETAL2001
+
+
+
+ Radio Science Subsystem
+
+
+ Atmospheric Structure Instrument
+
+
+
+ The Radio Science Subsystem of the 2001 Mars Odyssey mission was made up of the
+ spacecraft telecommunications subsystem and the DSN (ground).
+
+ There were no recognized radio science investigations on
+ the 2001 Mars Odyssey (ODY) mission. But investigators on
+ Mars Global Surveyor (MGS) requested access to ODY radio
+ tracking data. To support them and future proposers to
+ Mars data analysis programs (MDAPs), the Planetary Data
+ System (PDS) accepted responsibility for archiving the ODY
+ data with initial activities funded jointly by MGS.
+
+
+
diff --git a/data/pds4/context-pds4/instrument/ody.themis_1.1.xml b/data/pds4/context-pds4/instrument/ody.themis_1.1.xml
new file mode 100644
index 00000000..358a6b01
--- /dev/null
+++ b/data/pds4/context-pds4/instrument/ody.themis_1.1.xml
@@ -0,0 +1,108 @@
+
+
+
+
+
+ urn:nasa:pds:context:instrument:ody.themis
+ 1.0
+ Thermal Emission Imaging System (THEMIS) for ODY
+ 1.22.0.0
+ Product_Context
+
+
+ THEMIS
+
+
+ urn:nasa:pds:context:instrument:themis.ody
+
+
+
+
+ 2023-09-15
+ 1.0
+ Update to ody.themis and set alias to the original themis.ody.
+ Updated to PDS4_PDS_1F00.xsd to allow for DOI and added DOI to reference.
+ And per "Guide to PDS4 Context Products" v1.8, changed all lidvid_reference to lid_reference.
+ Added and then updated (2024-06-05) ctli for Instrument class, type = Imaging Spectrometer
+
+
+
+ 2024-10-02
+ 1.1
+
+ Where applicable, updated version, title, name
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.ody
+ instrument_to_instrument_host
+
+
+
+ Christensen, P. R., Calibration Report for the Thermal Emission Imaging
+ System (THEMIS) for the Mars 2001 Odyssey Mission, September 2002.
+
+ reference.CHRISTENSEN2002
+
+
+ 10.1023/B:SPAC.0000021008.16305.94
+
+ Christensen, P. R., B. M. Jakosky, H. H. Kieffer, M. C. Malin, H. Y.
+ McSween, Jr., K. Nealson, G. L. Mehall, S. H. Silverman, S. Ferry, and M.
+ Caplinger, (2004), The Thermal Emission Imaging System (THEMIS) for the Mars 2001
+ Odyssey Mission, Space Science Reviews volume 110, pages85–120.
+
+ reference.CHRISTENSENETAL2002
+
+
+
+
+ Thermal Emission Imaging System
+
+
+ Imaging Spectrometer
+
+
+
+ The THEMIS flight instrument is a combined infrared and visible
+ multi-spectral pushbroom imager. It has a
+ 12-cm effective aperature telescope and co-aligned infrared and
+ visible area arrays. The imaging system is comprised of a
+ three-mirror anastigmat telescope in a rugged enclosure, a
+ visible/infrared beamsplitter, a silicon focal plane for visible
+ detection, and a microbolometer for infrared detection. A major
+ feature of this instrument is the use of an uncooled IR
+ microbolometer array operated at ambient temperature, eliminating
+ the need for complex passive or active cryogenic coolers. A small
+ thermal electric cooler is used to stabilize the detector
+ temperature to 0.001K. A calibration flag, the only moving part in
+ the instrument, provides thermal calibration and a DC restore
+ capability, and will also be used to protect the detectors from
+ unintentional direct illumination from the Sun when the instrument
+ is not in use. The electronics provide digital data collection and
+ processing as well as the instrument control and data interface to
+ the spacecraft. Infrared data will be collected in 9 wavelengths
+ centered from 6.6 to 15.0 microns at 100 meter per pixel resolution;
+ the 6.6 micron band is collected twice to result in a 10 band image.
+ Visible data will be collected in 5 spectral bands at a resolution
+ of 18 meters per pixel. The instrument weighs 11.2 kg, is 29 cm by
+ 37 cm by 55 cm in size, and consumes an orbital average power of
+ 14W.
+
+
+
diff --git a/data/pds4/context-pds4/instrument/pvo.oefd_2.1.xml b/data/pds4/context-pds4/instrument/pvo.oefd_2.1.xml
new file mode 100644
index 00000000..3ec464b6
--- /dev/null
+++ b/data/pds4/context-pds4/instrument/pvo.oefd_2.1.xml
@@ -0,0 +1,150 @@
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument:pvo.oefd
+ 2.1
+ Orbiter Electric Field Detector (OEFD) for Pioneer Venus Orbiter
+ 1.20.0.0
+ Product_Context
+
+
+ 2020-08-26
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+ 2024-03-04
+ 2.0
+
+ Updated to IM 1.20.0.0
+
+
+
+ 2024-08-27
+ 2.1
+
+ Updated title and name
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.pvo
+ instrument_to_instrument_host
+
+
+
+ Scarf, F.L., G.M. Crook, I.M. Green, and P.F. Virobik,
+ 'Initial results of the Pioneer 8 VLF electric field
+ experiment', J. Geophys. Res., vol. 73, p. 6665, 1968.
+
+ reference.SCARFETAL1968
+
+
+
+ Scarf, F.L., I.M. Green and G.M. Crook, 'the Pioneer 9
+ electric field experiment : Part 1', Cosmic
+ Electrodynamics, vol. 1, p. 496, 1971.
+
+ reference.SCARFETAL1971
+
+
+
+ Scarf, F.L., W.W.L. Taylor, and I.M. Green, 'Plasma waves
+ near Venus: Initial observations', Science, vol. 203,
+ p. 748, 1979.
+
+ reference.SCARFETAL1979B
+
+
+
+ Scarf, F.L., W.W.L. Taylor, and P.F. Virobik, 'The Pioneer
+ Venus Orbiter Plasma Investigation', IEEE Trans. Geoscience
+ and Remote Sensing, Jan. 1980, Vol. GE-18, No. 1, p. 36,
+ 1980.
+
+ reference.SCARFETAL1980
+
+
+
+ Taylor, W.W.L., F.L. Scarf, C.T. Russell, and L.H. Brace,
+ 'Evidence for lightning on Venus', Nature, vol. 279,
+ p. 614, 1979.
+
+ reference.TAYLORETAL1979A
+
+
+
+ Taylor, W.W.L, F.L. Scarf, C.T. Russell, and L.H. Brace,
+ 'Absorption of whistler mode waves in the ionosphere of
+ Venus', Science, vol. 205, p. 112, 1979.
+
+ reference.TAYLORETAL1979B
+
+
+
+
+ Orbiter Electric Field Detector (OEFD)
+
+
+
+ Electric Field Instrument
+
+
+ Spectrum Analyzer
+
+
+
+ not applicable
+
+ not applicable
+
+
+
+ INSTRUMENT OVERVIEW
+ ===================
+
+ This experiment consisted of a modified version of the Pioneer 8
+ and Pioneer 9 experiments to measure the electric-field components
+ in four 30%, narrow-band channels centered at 100, 730, 7350, and
+ 30,000 Hz. The aims of the investigation were to perform an analysis
+ of VLF electric fields at Venus and to elucidate the plasma interactions
+ between the solar wind and the ionospheric or exospheric plasma. The
+ role of plasma instabilities in modifying the heat flux from the solar
+ wind and in thermalizing newly-born ions from Venus was also studied.
+ A self-contained balanced V-type antenna with a differential preamplifier
+ was employed to make the measurements. At the 512 bps satellite mode,
+ one frequency scan per second was obtained.
+
+ The Pioneer Venus plasma wave instrument has a self-contained
+ balanced electric dipole (effective length = 0.75 m) and a
+ 4-channel spectrum analyzer (30-percent band width filters with
+ center frequencies at 100 Hz, 5.4 kHz, and 30 kHz). The
+ channels are continuously active and the highest Orbiter
+ telemetry rate (2048 bps) yields 4 spectral scans/s. The total
+ mass of 0.55 kg includes the electronics, the antenna, and the
+ antenna deployment mechanism.
+
+ INSTRUMENT PI : Robert Strangeway
+ BUILD DATE : 1976
+ INSTRUMENT MASS : 0.55
+ INSTRUMENT HEIGHT : 0.075
+ INSTRUMENT LENGTH : 0.190
+ INSTRUMENT WIDTH : 0.066
+ INSTRUMENT MANUFACTURER NAME : TRW
+ INSTRUMENT SERIAL NUMBER : '5971-02'
+
+
+
+
+
diff --git a/data/pds4/context-pds4/instrument/pvo.oetp_2.1.xml b/data/pds4/context-pds4/instrument/pvo.oetp_2.1.xml
new file mode 100644
index 00000000..3f79f366
--- /dev/null
+++ b/data/pds4/context-pds4/instrument/pvo.oetp_2.1.xml
@@ -0,0 +1,737 @@
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument:pvo.oetp
+ 2.1
+ Orbiter Electron Temperature Probe (OETP) for Pioneer Venus Orbiter
+ 1.20.0.0
+ Product_Context
+
+
+ 2020-08-26
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+ 2024-03-15
+ 2.0
+
+ Updated to IM 1.20.0.0
+
+
+
+ 2024-08-27
+ 2.1
+
+ Updated title and instrument name
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.pvo::1.0
+ instrument_to_instrument_host
+
+
+
+ Brace, L.H., 'Global Structure of Ionosphere Temperature', in Space
+ Research X. Amsterdam, The Netherlands: North-Holland, p.633, 1970.
+
+ reference.BRACE1970
+
+
+
+ Brace, L.H., 'Orbiter Electron Temperature Probe', L. Colin and D.M.
+ Hunten, Eds. Space Sci. Rev., Vol.20, No.4, p.454, June 1977.
+
+ reference.BRACE1977
+
+
+
+ Brace, L.H., R.F. Theis, and A. Dalgarno, 'The Cylindrical Electrostatic
+ Probes for Atmosphere Explorer -C, -D, -E', Science, Vol.8, No.4, p.341,
+ Apr.1973.
+
+ reference.BRACEETAL1973
+
+
+
+ Brace, L.H., R.F. Theis, J.P. Krehbiel, A.F. Nagy, T.M. Donahue, M.E.
+ McElroy, and A. Pedersen, 'Electron Temperatures and Densities in the Venus
+ Ionosphere', Science, Vol.203, p.763, Feb.23, 1979.
+
+ reference.BRACEETAL1979A
+
+
+
+ Brace, L.H., H.A. Taylor Jr., P.A. Cloutier, R.E. Daniell Jr., and A.F.
+ Nagy, 'On the Configuration of the Nightside Venus Ionopause', Geophys.
+ Res. Lett., Vol.6, p.345, 1979.
+
+ reference.BRACEETAL1979B
+
+
+
+ Brace, L.H., R.F. Theis, H.B. Niemann, H.G. Mayr, W.R. Hoegy, and A.F.
+ Nagy, 'Empirical Models of the Electron Temperature and Density in the
+ Nightside Venus Ionosphere', Science, Vol.205, p.102, 1979.
+
+ reference.BRACEETAL1979C
+
+
+
+ Hoegy, W.R., and L.E. Wharton, 'Current to Moving Spherical and Cylindrical
+ Electrostatic Probes', J. Appl. Phys., Vol.44, No.12, p.5365-5371, 1973.
+
+ reference.HOEGYETAL1973
+
+
+
+ Krehbiel, J.P., L.H. Brace, J.R. Cutler, W.H. Pinkus, and R.B. Kaplan,
+ 'Pioneer Venus Orbiter Electron Temperature Probe', IEEE Transactions on
+ Geoscience and Remote Sensing, GE-18, 49, 1980.
+
+ reference.KREHBIELETAL1980
+
+
+
+ Langmuir, I. and H. Mott-Smith, Jr., 'Studies of the Electric Discharges in
+ Gases at Low Pressures', Gen. Elec. Rev., p.616, Sept.1924.
+
+ reference.LANGMUIRETAL1924
+
+
+
+ Mott-Smith, H. and I. Langmuir, 'The Theory of Collectors in Gaseous
+ Discharges', Phys. Rev., Vol.28, pp.727-763, 1926.
+
+ reference.MOTTSMITHETAL1926
+
+
+
+ Shai, M.C., 'Formulation of Electrically Conductive Thermal-Control
+ Coatings ', NASA Tech. Paper 1218, Apr.1978.
+
+ reference.SHAI1978
+
+
+
+ Smith, D., 'The Application of Langmuir Probes to the Measurement of Very
+ Low Electron Temperatures', Planet. Space Sci., Vol.20, p.1721, 1972.
+
+ reference.SMITH1972
+
+
+
+ Spencer, N.W., L.H. Brace, G.R. Carignan, D.R. Taeusch, and H.B. Niemann,
+ 'Electron and Molecular Nitrogen Temperature and Density in the
+ Thermosphere', J. Geophys. Res., Vol.70, pp.2665-2698, 1965.
+
+ reference.SPENCERETAL1965
+
+
+
+ Yang, L., 'Preparation and Evaluation of CVD Rhenium Thermionic Emitters',
+ in The Third Annual Conference on Chemical Vapor Deposition, F.A. Glaski,
+ Ed., American Nuclear Society, 1972.
+
+ reference.YANG1972
+
+
+
+
+ Orbiter Electron Temperature Probe (OETP)
+
+
+ Langmuir Probe
+
+
+ not applicable
+
+ not applicable
+
+
+
+
+ Scientific Objectives
+ =====================
+ Krehbiel, J.P., L.H. Brace, R.F. Theis, J.R. Cutler, W.H.
+ Pinkus, and R.B. Kaplan, 'Pioneer Venus Orbiter Electron
+ Temperature Probe', IEEE Transactions on Geoscience and Remote
+ Sensing, January 1980. [KREHBIELETAL1980].
+
+ ABSTRACT - The Orbiter Electron Temperature Probe (OETP)
+ instrumentation and measurement technique has been designed to
+ perform in-situ measurements of electron temperature and
+ electron and ion density in the ionosphere of Venus. Adaptive
+ sweep voltage circuitry continuously tracks the changing
+ electron temperature and spacecraft potential while
+ auto-ranging electrometers adjust their gain in response to the
+ changing plasma density. Control signals used in the
+ instrument to achieve this automatic tracking provide a
+ continuous monitor of the ionospheric parameters without
+ telemetering each volt-ampere curve. Internal data storage
+ permits high data rate sampling of selected raw characteristic
+ curves for low rate transmission to Earth. These curves are
+ used to verify or correct the inflight processed data. Sample
+ in orbit measurements are presented to demonstrate instrument
+ performance.
+
+ I. INTRODUCTION
+
+ THE PIONEER VENUS Orbiter Electron Temperature Probe (OETP) is
+ one of several instruments used on the orbiter to perform
+ in-situ measurements of the ionospheric plasma of Venus. The
+ instrument employs cylindrical Langmuir probes to measure the
+ electron temperature, Te, the electron and ion densities, Ne
+ and Ni, and the spacecraft potential, Vs. To provide high
+ spatial resolution of these parameters the instrument takes
+ several hundred volt-ampere curves during each brief passage
+ through the ionosphere. Owing to the limited telemetry rate
+ available to each instrument, circuitry was included for
+ inflight processing of the volt- ampere curves. Onboard
+ storage of raw data from selected curves was provided to permit
+ ground confirmation of the inflight processing method. Prior
+ to launch, the instrument design was outlined briefly by Brace
+ in a paper edited by Colin and Hunten (1977) [BRACE1977]. The
+ purpose of this paper is to present a a more detailed account
+ of the instrument and some of the data acquired at Venus to
+ illustrate how the instrument performs and how the ground data
+ analysis is used to verify the flight measurements. Early
+ results from this experiment have been reported.
+ [BRACEETAL1979A] [BRACEETAL1979B] [BRACEETAL1979C]
+
+ II. THEORY OF THE METHOD
+
+ The OETP is the latest spaceflight version of cylindrical
+ electrostatic probe of Langmuir probe instrumentation. I.
+ Langmuir and H. Mott-Smith, Jr., first reported use of the
+ electrostatic probe in a laboratory plasma in 1924
+ [LANGMUIRETAL1924]. The cylindrical probe technique has been
+ used extensively to characterize the Earth's ionosphere
+ [BRACE1970], most recently on board the Atmosphere Explorer
+ (AE) satellites [BRACEETAL1973]. The three AE instruments with
+ their adaptive control circuitry and auto ranging electrometer
+ provided the basis for the OETP instrument.
+
+ Langmuir probe theory and application has been widely reported
+ in the literature [BRACE1977] [BRACEETAL1979A] [BRACEETAL1979B]
+ [BRACEETAL1979C] [LANGMUIRETAL1924] [BRACE1970] [BRACEETAL1973]
+ [HOEGYETAL1973]. Here it will suffice to provide a brief
+ description of the technique and to remind the reader of the
+ theoretical volt-ampere curve produced by a Langmuir probe in a
+ plasma as shown in Fig. 1 [KREHBIELETAL1980]. The curve
+ begins in the ion saturation region with the probe potential
+ sufficiently negative to prohibit plasma electrons from
+ reaching the probe. At this point, current to the probe is due
+ only to ions. In the retardation region where the probe
+ potential is less negative, the more energetic electrons
+ overcome the retarding potential, and produce an exponentially
+ increasing current. The electron temperature Te determines the
+ power of the exponential with lower Te yielding a narrower
+ retarding region. In the electron saturation region, the probe
+ is positive with respect to the plasma and therefore attracts
+ additional electrons from the plasma. Equations appropriate to
+ the three regions of the curve are given below.
+
+ In the ion saturation region at 90 degree angle of attack
+ [HOEGYETAL1973]
+
+ Ii = ANiew/pi(1 + kTi/miw2 + 2eV/miw2)1/2 (1)
+
+
+ In the electron retardation region [BRACEETAL1979A]
+
+
+ Ie = ANee(kTe/2pime)1/2 exp(eV/kTe0. (2)
+
+
+ In the electron saturation region [MOTTSMITHETAL1926]
+ [SPENCERETAL1965]
+
+
+ Ie = (ANee/pi)(2eV/me)1/2 (3) where
+
+ Ne electron density Ni ion density Te electron temperature Ti
+ ion temperature A collector surface area w collector speed with
+ respect to plasma k Boltzmann constant mi mean ion mass me
+ electron mass V collector voltage with respect to the plasma e
+ electron charge.
+
+ OETP measurements are made with respect to spacecraft ground.
+ This causes the voltage applied to the probe VA to be
+ translated by the spacecraft potential Vs, as illustrated in
+ Fig. 1 [KREHBIELETAL1980]. Special steps must be taken to
+ account for this and to assure a stable spacecraft potential.
+ This will be described later.
+
+ Instrument Overview
+ ===================
+ III. THE EXPERIMENTAL ARRANGEMENT
+
+ The OETP instrumentation system consists of two cylindrical
+ sensors and a central electronics unit. Fig. 2
+ [KREHBIELETAL1980] illustrates the relative position of the
+ sensors and the larger appendages of the spacecraft. The
+ radial sensor is mounted at the end of a 1-m boom which was
+ folded against the solar array and deployed after Venus orbit
+ insertion so as to be perpendicular to the spacecraft spin
+ axis. The axial sensor is mounted on a fixed boom which places
+ it 0.4 m away from the spacecraft forward surface. Because the
+ axis of the axial sensor is parallel to the spin axis it
+ maintains a relatively constant angle of attack to the incident
+ plasma and is therefore not subject to spin modulation.
+
+ To provide an adequate path for return current to the plasma,
+ the spacecraft provides 1.73 m2 of exposed conducting area
+ which is spacecraft ground. This area consists of a metal band
+ around the solar array, a metal mesh over the outer kapton
+ surface of the forward thermal blanket, and the outer surface
+ of the magnetometer boom. Silicone rubber was applied to all
+ solar cell edges and exposed electrical conductors making up
+ the solar array to insulate these positive potential areas from
+ the plasma and thus minimize the electron current they would
+ otherwise collect producing a concomitant change in spacecraft
+ potential.
+
+ A. The Central Electronics
+
+ The OETP central electronics unit contains independent
+ electrometer amplifiers and adaptive sweep voltage circuitry to
+ service each probe. Fig. 3 [KREHBIELETAL1980] is a simplified
+ functional block diagram of the system. Each amplifier feeds
+ its output into the common A/D converter and data handling
+ circuitry. The autoranging electrometer and adaptive sweep
+ voltage circuits are identical to that employed in the three AE
+ missions [BRACEETAL1973]. The signal multiplexing (Mux), A/D
+ conversion, data formatting, and First-In/First-Out memory
+ (FIFO) are new features to permit the inflight processing and
+ recovery of data, a capability required by the lower data rate
+ available from the orbiter. The radial probe electrometer has
+ a sensitivity range of 1 x 10 to the neg. 10 power to 1 x 10
+ to the neg. 6 power A/V, while the axial probe electrometer
+ has a sensitivity range of 1 x 10 to the neg. nine power to 1
+ x 10 to the neg. 5 power A/V. Electrometer sensitivity is
+ automatically adjusted to one of 1024 possible values.
+ Electrical power is provided by a common dc/dc converter having
+ separate floating outputs for each of the two electrometers.
+
+ Adaptive circuitry is provided to adjust the sweep voltage to
+ resolve that region of the volt-ampere curve needed to derive
+ Ni, Ne, Te, and Vs and to track changes in Te and Vs
+ encountered along the orbit. The adaptive process provides a
+ more continuous monitor of these plasma parameters than could
+ be obtained if we were to rely solely on ground-based analysis
+ of volt-ampere curves produced by the instrument, given the
+ available data rate. The VA generator converges on the proper
+ starting value VA Start, and the proper rate of change VA Slope
+ through an iterative process involving the auto-ranging
+ electrometer and the adaptive VA circuitry. When the adaptive
+ process is completed, usually within two sweeps, the curves are
+ properly framed to maximize the resolution of the measured
+ parameters. Once proper framing had been achieved, it is
+ maintained by slight adjustments in VA Start, VA Slope, and
+ electrometer gain which track the changes in electron
+ temperature, density, and spacecraft potential.
+
+ An idealized 1/2-s instrument measurement cycle of applied
+ voltage, and the resulting electrometer output for a properly
+ framed curve are shown in Fig. 4 [KREHBIELETAL1980]. Also
+ shown are the parameters used to carry out the adaptive process
+ and to achieve the inflight analysis. The cycle begins at time
+ T0 by setting VA equal to VA Start as determined from
+ parameters measured during the previous curve. After a
+ settling time the electrometer auto-ranging algorithm is
+ initiated to adjust the electrometer gain as needed to drive
+ its output to the -3.30-Vthreshold. Current to the sensor at
+ this time is entirely ion current and is used to determine Ni.
+ At time T1 the VA is increased linearly at a rate also
+ determined from the previous curve. The VA and electrometer
+ outputs are monitored by level detectors. When the
+ electrometer output reaches +1.41 V a level detector starts a
+ counter and the value of VA at T2 is measured. When the
+ electrometer output reaches +9.50 V, a second level detector
+ stops the counter and the value of VA at T3 is measured. At T3
+ the electrometer downranges by one decade and displays the rest
+ of the volt-ampere curve until the linear sweep is stopped at
+ T4. At T4 a fixed 2-V step is added to drive the sensor into
+ the electron saturation region. The electrometer then
+ downranges until its output is on scale and a reading of output
+ voltage and gain are taken and used to determine Ne.
+
+ In each 1/2-s instrument cycle we are thus able to determine,
+ from each electrometer, Ni from the gain and electrometer
+ output just prior to T1, Te from the change in VA which
+ produced a factor of e change in electrometer output, and Ne
+ from the gain and electrometer output during the Ne sample
+ time. The curve framing process continues by automatically
+ computing new values of VA Slope and VA Start. VA Slope is
+ computed from our definition of a properly framed curve which
+ requires that the full amplitude of VA be ten times the value
+ of the change in VA from T2 to T3 when the 1.41- and 9.50-V
+ thresholds are reached. VA Start is computed using (4) which
+ places the exponential electron retardation region such that
+ the 9.50-V threshold is reached at 86 percent of the sweep
+ interval.
+
+ VA Start = 8.6 VA at T2 - 7.6 VA at T3. (4)
+
+ If the VA at T1 does not provide a net ion current to the
+ collector or if the electrometer fails to reach the +9.50-V
+ output, called the T3 threshold, the VA generator will preset
+ to the 'fault' condition for the next sweep causing VA to start
+ at -7 V and sweep up to +5V. The fault sweep amplitude is
+ sufficient to locate the operating region of the volt-ampere
+ curve and to permit the convergence algorithm to repeat at the
+ beginning of the following sweep.
+
+ As a safeguard against unforeseen difficulties which might
+ cause our adaptive approach to fail, a fixed amplitude sweep
+ mode can be selected by ground command in which a sequence of
+ high and low voltage sweeps are applied to either or both
+ sensors. The high VA was -7 to +5 V and the low VA was -2 to
+ +1 V. In this mode a bias voltage of +/- 1 V can be added to
+ account for Vs uncertainties. The fixed sweep mode is not
+ normally used because the adaptive mode yields better resolved
+ stored curves.
+
+ B. The Sensors and Booms
+
+ A sensor with its guard electrode and a portion of the boom are
+ schematically shown in Fig. 5 [KREHBIELETAL1980]. The guard
+ electrode, driven at VA, is the exposed inner shield of a rigid
+ triaxial boom fabricated with titanium and teflon. The outer
+ triaxial shield is held at spacecraft ground potential. A
+ special white conductive paint, GSFC Code No. NS43C
+ [SHAI1978], was applied to the outer surface of the booms to
+ provide thermal control. Flight sensors were screwed onto the
+ boom center conductor and held in place with a high temperature
+ silicone (Dow Corning X 12561, silver filled for electrical
+ conductivity) to assure that the sensors remained in place
+ during the launch vibration.
+
+ The accuracy of the temperature measurements is affected by the
+ characteristics of the sensor surface [SMITH1972]. In
+ particular, the work function of different crystal surfaces can
+ vary by as much as several tenths of a volt and thus introduce
+ an uncertainty in the value of V in (1) - (3). To reduce this
+ error the collectors were fabricated using a chemical vapor
+ deposition (CVD) process. Studies of the CVD Rhenium show that
+ Rhenium deposited by the pyrolyctic decomposition of Rhenium
+ pentachloride (ReCl5) show a very high degree of crystal
+ orientation. Rhenium deposited in this manner exhibits a
+ (0001) preferred orientation [YANG1972] perpendicular to the
+ plane of growth. Cylindrical tubes of this type have yielded
+ uniform vacuum work functions of 5.1 eV. Molybdenum deposited
+ from MoCl6 also shows a very high degree of crystal
+ orientation. Thus both materials become candidates for sensor
+ materials.
+
+ Fig. 6 [KREHBIELETAL1980] shows part of a cross section of a
+ collector having a CVD Rhenium surface deposited on a
+ polycrystalline substrate. Flight collectors were selected on
+ the basis of examining similar cross sections cut from one end
+ of the collector and from volt-ampere curves taken in
+ laboratory plasmas. The radial collector surface is Rhemium
+ and the axial is Molybdenum.
+
+ C. Measurements Format
+
+ The orbiter is able to operate in several data formats and at
+ spacecraft data rates from 16 to 2048 b/s. The OETP is
+ designed for optimum operation when its output data rates are
+ 80, 128, or 160 b/s, one of which is normally used during a
+ periapsis pass. Various instrument data formats can be
+ selected by command to provide for more or less dense coverage
+ depending on such factors as spacecraft bit rate and whether
+ the OETP data system is dedicated to one sensor or shared by
+ both of them.
+
+ IV. Verification of Inflight Analysis
+
+ To permit ground calibration of the values of Ni, Ne, and Te
+ determined by the inflight processing, the instrument
+ periodically samples volt-ampere curves from either or both
+ electrometers. The electrometer output is measured at 50
+ equally spaced points between T1 and T4. The FIFO memory is
+ used to store the fifty measurements , made at 1132 b/s, for
+ later readout at the lower spacecraft telemetry rate. Fig. 7
+ [KREHBIELETAL1980] illustrates the ground analysis of such a
+ stored curve taken from orbit 112. The solid line represents a
+ least squares fit of a straight line (ion current) and
+ exponential (electron current) to the actual data points within
+ the electron retardation region.
+
+ V. Illustration of Operation at Venus
+
+ Fig. 8 [KREHBIELETAL1980] is a computer plot of the values of
+ Te and Ne taken from a single pass of the orbiter through the
+ nightside ionosphere. The line segments connect the inflight
+ values and reveal the small-scale spatial structure which is
+ often present. The asterisks represent the values of Te and Ne
+ derived later by computer fitting stored volt-ampere curves of
+ the type illustrated in Fig. 7 [KREHBIELETAL1980]. Values
+ derived from the stored curves are used to normalize the
+ inflight processed data. Thus through the use of on-board
+ processing of curves, high spatial resolution is achieved
+ without sacrificing the accuracy provided by ground computer
+ fitting of raw volt-ampere curves. As of this writing more
+ than 250 passes through the ionosphere of Venus have been
+ completed and the instrument continues to operate well.
+
+ ACKNOWLEDGEMENT
+
+ The authors gratefully acknowledge the aid of L.R.O. Storey in
+ the testing of candidate collectors in the low temperature
+ plasma chamber at the Centre de Recherches en Physique de
+ L'Environment Terrestre en Planetaire in Orleans, France.
+
+ REFERENCES
+
+ L.H. Brace, 'Orbiter electron temperature Probe', L. Colin
+ and D.M. Hunten, Eds. Space Sci. Rev., vol. 20, no. 4,
+ p.454, June 1977. [BRACE1977]
+
+ L.H. Brace, R.F. Theis, J.P. Krehbiel, A.F. Nagy, T.M.
+ Donahue, M.E. McElroy, and A. Pedersen, 'Electron
+ temperatures and densities in the Venus ionosphere', Science,
+ vol. 203, p. 763, Feb. 23, 1979. [BRACEETAL1979A]
+
+ L.H. Brace, H.A. Taylor Jr., P.A. Cloutier, R.E. Daniell
+ Jr., and A.F. Nagy, 'On the configuration of the nightside
+ Venus ionopause', Geophys. Res. Lett., vol. 6, p. 345, 1979.
+ [BRACEETAL1979B]
+
+ L.H. Brace, R.F. Theis, H.B. Niemann, H.G. Mccayr, W.R.
+ Hoegy, and A.F. Nagy, 'Empirical models of the electron
+ temperature and density in the nightside Venus ionosphere',
+ Science, vol. 205, p. 102, 1979. [BRACEETAL1979C]
+
+ I. Langmuir, and H. Mott-Smith, Jr., 'Studies of the electric
+ discharges in gases at low pressures', Gen. Elec. Rev., p.
+ 616, Sept. 1924. [LANGMUIRETAL1924]
+
+ L.H. Brace, 'Global structure of ionosphere temperature', in
+ Space Research X. Amsterdam, The Netherlands: North-Holland,
+ p. 633, 1970. [BRACE1970]
+
+ L.H. Brace, R.F. Theis, and A. Dalgarno, 'The cylindrical
+ electrostatic probes for atmosphere explorer -C, -D, -E',
+ Science, vol. 8, no. 4, p. 341, Apr. 1973. [BRACEETAL1973]
+
+ W.R. Hoegy and L.E. Wharton, 'Current to moving spherical and
+ cylindrical electrostatic probes', J. Appl. Phys., vol. 44,
+ no. 12, p. 5365-5371, 1973. [HOEGYETAL1973]
+
+ H. Mott-Smith and I. Langmuir, 'The theory of collectors in
+ gaseous discharges', Phys. Rev., vol. 28, pp. 727-763, 1926.
+ [MOTTSMITHETAL1926]
+
+ N.W. Spencer, L.H. Brace, G.R. Carignan, D.R. Taeusch, and
+ H.B. Niemann, 'Electron and molecular nitrogen temperature and
+ density in the thermosphere', J. Geophys. Res., vol. 70, pp.
+ 2665-2698, 1965. [SPENCERETAL1965]
+
+ M.C. Shai, 'Formulation of electrically conductive thermal-
+ control coatings ', NASA Tech. Paper 1218, Apr. 1978.
+ [SHAI1978]
+
+ D. Smith, 'The application of Langmuir probes to the
+ measurement of very low electron temperatures', Planet. Space
+ Sci., vol. 20, p. 1721, 1972. [SMITH1972]
+
+ L. Yang, 'Preparation & evaluation of CVD rhenium thermionic
+ emitters', in The Third Annual Conference on Chemical Vapor
+ Deposition, F.A. Glaski, Ed., American Nuclear Society, 1972.
+ [YANG1972]
+
+
+ Calibration
+ ===========
+ To permit ground calibration of the values of Ni, Ne, and Te
+ determined by the inflight processing, the instrument
+ periodically samples volt-ampere curves from either or both
+ electrometers. The electrometer output is measured at 50
+ equally spaced points between T1 and T4. The FIFO memory is
+ used to store the fifty measurements , made at 1132 b/s, for
+ later readout at the lower spacecraft telemetry rate. Fig. 7
+ [KREHBIELETAL1980] illustrates the ground analysis of such a
+ stored curve taken from orbit 112. The solid line represents a
+ least squares fit of a straight line (ion current) and
+ exponential (electron current) to the actual data points within
+ the electron retardation region.
+
+ The Sensors and Booms
+
+ A sensor with its guard electrode and a portion of the boom are
+ schematically shown in Fig. 5. [KREHBIELETAL1980] The guard
+ electrode, driven at VA, is the exposed inner shield of a rigid
+ triaxial boom fabricated with titanium and teflon. The outer
+ triaxial shield is held at spacecraft ground potential. A
+ special white conductive paint, GSFC Code No. NS43C
+ [SHAI1978], was applied to the outer surface of the booms to
+ provide thermal control. Flight sensors were screwed onto the
+ boom center conductor and held in place with a high temperature
+ silicone (Dow Corning X 12561, silver filled for electrical
+ conductivity) to assure that the sensors remained in place
+ during the launch vibration.
+
+ The accuracy of the temperature measurements is affected by the
+ characteristics of the sensor surface [SMITH1972]. In
+ particular, the work function of different crystal surfaces can
+ vary by as much as several tenths of a volt and thus introduce
+ an uncertainty in the value of V in (1) - (3). To reduce this
+ error the collectors were fabricated using a chemical vapor
+ deposition (CVD) process. Studies of the CVD Rhenium show that
+ Rhenium deposited by the pyrolytic decomposition of Rhenium
+ pentachloride (ReCl5) show a very high degree of crystal
+ orientation. Rhenium deposited in this manner exhibits a
+ (0001) preferred orientation [YANG1972] perpendicular to the
+ plane of growth. Cylindrical tubes of this type have yielded
+ uniform vacuum work functions of 5.1 eV. Molybdenum deposited
+ from MoCl6 also shows a very high degree of crystal
+ orientation. Thus both materials become candidates for sensor
+ materials.
+
+ Fig. 6 [KREHBIELETAL1980] shows part of a cross section of a
+ collector having a CVD Rhenium surface deposited on a
+ polycrystalline subtrate. Flight collectors were selected on
+ the basis of examining similar cross sections cut from one end
+ of the collector and from volt-ampere curves taken in
+ laboratory plasmas. The radial collector surface is Rhemium
+ and the axial is Molybdenum.
+
+
+ Instrument Electronics
+ ======================
+ A. The Central Electronics
+
+ The OETP central electronics unit contains independent
+ electrometer amplifiers and adaptive sweep voltage circuitry to
+ service each probe. Fig. 3 [KREHBIELETAL1980] is a simplified
+ functional block diagram of the system. Each amplifier feeds
+ its output into the common A/D converter and data handling
+ circuitry. The autoranging electrometer and adaptive sweep
+ voltage circuits are identical to that employed in the three AE
+ missions [BRACEETAL1973]. The signal multiplexing (Mux), A/D
+ conversion, data formatting, and First-In/First-Out memory
+ (FIFO) are new features to permit the inflight processing and
+ recovery of data, a capability required by the lower data rate
+ available from the orbiter. The radial probe electrometer has
+ a sensitivity range of 1 x 10 to the neg. 10 power to 1 x 10
+ to the neg. 6 power A/V, while the axial probe electrometer
+ has a sensitivity range of 1 x 10 to the neg. nine power to 1
+ x 10 to the neg. 5 power A/V. Electrometer sensitivity is
+ automatically adjusted to one of 1024 possible values.
+ Electrical power is provided by a common dc/dc converter having
+ separate floating outputs for each of the two electrometers.
+
+ Adaptive circuitry is provided to adjust the sweep voltage to
+ resolve that region of the volt-ampere curve needed to derive
+ Ni, Ne, Te, and Vs and to track changes in Te and Vs
+ encountered along the orbit. The adaptive process provides a
+ more continuous monitor of these plasma parameters than could
+ be obtained if we were to rely solely on ground-based analysis
+ of volt-ampere curves produced by the instrument, given the
+ available data rate. The VA generator converges on the proper
+ starting value VA Start, and the proper rate of change VA Slope
+ through an iterative process involving the auto-ranging
+ electrometer and the adaptive VA circuitry. When the adaptive
+ process is completed, usually within two sweeps, the curves are
+ properly framed to maximize the resolution of the measured
+ parameters. Once proper framing had been achieved, it is
+ maintained by slight adjustments in VA Start, VA Slope, and
+ electrometer gain which track the changes in electron
+ temperature, density, and spacecraft potential.
+
+ An idealized 1/2-s instrument measurement cycle of applied
+ voltage, and the resulting electrometer output for a properly
+ framed curve are shown in Fig. 4 [KREHBIELETAL1980]. Also
+ shown are the parameters used to carry out the adaptive process
+ and to achieve the inflight analysis. The cycle begins at time
+ T0 by setting VA equal to VA Start as determined from
+ parameters measured during the previous curve. After a
+ settling time the electrometer auto-ranging algorithm is
+ initiated to adjust the electrometer gain as needed to drive
+ its output to the -3.30-V threshold. Current to the sensor at
+ this time is entirely ion current and is used to determine Ni.
+ At time T1 the VA is increased linearly at a rate also
+ determined from the previous curve. The VA and electrometer
+ outputs are monitored by level detectors. When the
+ electrometer output reaches +1.41 V a level detector starts a
+ counter and the value of VA at T2 is measured. When the
+ electrometer output reaches +9.50 V, a second level detector
+ stops the counter and the value of VA at T3 is measured. At T3
+ the electrometer downranges by one decade and displays the rest
+ of the volt-ampere curve until the linear sweep is stopped at
+ T4. At T4 a fixed 2-V step is added to drive the sensor into
+ the electron saturation region. The electrometer then
+ downranges until its output is on scale and a reading of output
+ voltage and gain are taken and used to determine Ne.
+
+ In each 1/2-s instrument cycle we are thus able to determine,
+ from each electrometer, Ni from the gain and electrometer
+ output just prior to T1, Te from the change in VA which
+ produced a factor of e change in electrometer output, and Ne
+ from the gain and electrometer output during the Ne sample
+ time. The curve framing process continues by automatically
+ computing new values of VA Slope and VA Start. VA Slope is
+ computed from our definition of a properly framed curve which
+ requires that the full amplitude of VA be ten times the value
+ of the change in VA from T2 to T3 when the 1.41- and 9.50-V
+ thresholds are reached. VA Start is computed using (4) which
+ places the exponential electron retardation region such that
+ the 9.50-V threshold is reached at 86 percent of the sweep
+ interval.
+
+ VA Start = 8.6 VA at T2 - 7.6 VA at T3. (4)
+
+ If the VA at T1 does not provide a net ion current to the
+ collector or if the electrometer fails to reach the +9.50-V
+ output, called the T3 threshold, the VA generator will preset
+ to the 'fault' condition for the next sweep causing VA to start
+ at -7 V and sweep up to +5V. The fault sweep amplitude is
+ sufficient to locate the operating region of the volt-ampere
+ curve and to permit the convergence algorithm to repeat at the
+ beginning of the following sweep.
+
+ As a safeguard against unforeseen difficulties which might
+ cause our adaptive approach to fail, a fixed amplitude sweep
+ mode can be selected by ground command in which a sequence of
+ high and low voltage sweeps are applied to either or both
+ sensors. The high VA was -7 to +5 V and the low VA was -2 to
+ +1 V. In this mode a bias voltage of +/- 1 V can be added to
+ account for Vs uncertainties. The fixed sweep mode is not
+ normally used because the adaptive mode yields better resolved
+ stored curves.
+
+
+ Detectors
+ =========
+ The OETP instrumentation system consists of two cylindrical
+ sensors and a central electronics unit. Fig. 2
+ [KREHBIELETAL1980] illustrates the relative position of the
+ sensors and the larger appendages of the spacecraft. The
+ radial sensor is mounted at the end of a 1-m boom which was
+ folded against the solar array and deployed after Venus orbit
+ insertion so as to be perpendicular to the spacecraft spin
+ axis. The axial sensor is mounted on a fixed boom which places
+ it 0.4 m away from the spacecraft forward surface. Because the
+ axis of the axial sensor is parallel to the spin axis it
+ maintains a relatively constant angle of attack to the incident
+ plasma and is therefore not subject to spin modulation.
+
+
+
+
+
diff --git a/data/pds4/context-pds4/instrument/pvo.oims_2.1.xml b/data/pds4/context-pds4/instrument/pvo.oims_2.1.xml
new file mode 100644
index 00000000..df763778
--- /dev/null
+++ b/data/pds4/context-pds4/instrument/pvo.oims_2.1.xml
@@ -0,0 +1,110 @@
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument:pvo.oims
+ 2.1
+ Orbiter Ion Mass Spectrometer (OIMS) for Pioneer Venus Orbiter
+ 1.20.0.0
+ Product_Context
+
+
+ 2020-08-26
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+ 2024-04-02
+ 2.0
+
+ Updated to IM 1.20.0.0
+
+
+
+ 2024-08-27
+ 2.1
+
+ Updated title, instrument name, and instrument description
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.pvo
+ instrument_to_instrument_host
+
+
+
+ Brinton, H.C., L.R. Scott, M.W. Pharo, III, and J.T.C. Coulson, The
+ Bennett ion-mass spectrometer on Atmosphere Explorer-C and -E, Radio Sci.,
+ vol. 8, 323, 1973.
+
+ reference.BRINTONETAL1973
+
+
+
+ Taylor, H.A., Jr., H.C. Brinton, S.J. Bauer, R.E. Hartle, T.M. Donahue,
+ P.A. Cloutier, F.C. Michel, R.E. Daniell, Jr., B.H. Blackwell, Ionosphere
+ of Venus: First observations of the dayside ion composition near dawn and
+ dusk, Science, vol. 203, 752, 1979.
+
+ reference.TAYLORETAL1979C
+
+
+
+ Taylor, H.A., Jr., H.C. Brinton, S.J. Bauer, R.E. Hartle, P.A. Cloutier,
+ F.C. Michel, R.E. Daniell, Jr., T.M. Donahue, R.C. Maehl, Ionosphere of
+ Venus: First observations of the effects of dynamics on the dayside ion
+ composition, Science, vol. 203, 755, 1979.
+
+ reference.TAYLORETAL1979D
+
+
+
+
+ Orbiter Ion Mass Spectrometer (OIMS)
+
+
+ Mass Spectrometer
+
+
+ not applicable
+
+ not applicable
+
+
+ Using the Pioneer Venus Orbiter Ion Mass Spectrometer (OIMS), composition and concentration of thermal positive ions
+ in the ionosphere of Venus were determined and interpreted in terms of vertical and horizontal components. These provided
+ information on provided information on the solar wind interaction with Venus, upper atmosphere photochemistry, and the
+ mass and heat transport characteristics of the atmosphere. The instrument used was a Bennett radio-frequency mass spectrometer
+ based on the design of those flown on OGO and Atmospheric Explorer satellites. A mass range of 1-56 amu was covered with a
+ variety of automatic scan-search modes available.
+
+ Identical Ion Mass Spectrometers were mounted on the Pioneer Venus Orbiter and the Probe Bus. Each spectrometer, with a mass
+ of 3.0 kg, consisted of two parts, an analyzer tube and an electronics package. The electronics package held printed circuit
+ boards inside a machined magnesium housing mounted inside the spacecraft. The package contained low- and high-gain pre-amplifiers,
+ amplifiers, a log A/D converter, an RF generator, voltage regulator, command and control, and data handling. It uses 1.5 W of power,
+ and functions to supply RF and DC potentials to the ion analyzer tube; detect and amplify ion current flowing to the collectors;
+ digitize, process, and format data for telemetry; configure the sensor for subsequent measurements; and decode and implement commands.
+
+ The analyzer tube is a hollow cylinder of aluminum containing a series of knitted tungsten mesh grids and gold-plated aluminum spacers.
+ These are backed by a supressor, a low-gain collector and a high-gain collector. At the head of the tube is a guard ring and an
+ accelerating voltage. The analyzer can be set to measure any of 16 common ion masses from 1 to 56 amu (1, 2, 4, 8, 12, 14, 16, 17,
+ 18, 24, 28, 30, 32, 40, 44, and 56 amu). It also has the ability to produce simulated ion currents for calibration.
+
+ The instrument operated with repeated explore/adapt cycles, each 6.3 seconds in duration. The first 1.8 seconds of the cycle is the
+ explore portion, which consists of measuring each of the 16 pre-selected masses for approximately 0.1 second each. In the 4.5
+ second adapt portion of the cycle, up to 8 ions that are found to be present in the explore portion are measured repeatedly. The
+ ion current values from each measurement are sampled, held for A/D conversion, and transfered to telemetry storage registers.
+
+
+
diff --git a/data/pds4/context-pds4/instrument/pvo.omag_2.1.xml b/data/pds4/context-pds4/instrument/pvo.omag_2.1.xml
new file mode 100644
index 00000000..04fd2e15
--- /dev/null
+++ b/data/pds4/context-pds4/instrument/pvo.omag_2.1.xml
@@ -0,0 +1,209 @@
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument:pvo.omag
+ 2.1
+ Orbiter Fluxgate Magnetometer (OMAG) for Pioneer Venus Orbiter
+ 1.20.0.0
+ Product_Context
+
+
+ 2020-08-26
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+ 2024-04-02
+ 2.0
+
+ Updated to IM 1.20.0.0
+
+
+
+ 2024-08-28
+ 2.1
+
+ Updated title, instrument name, instrument description
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.pvo
+ instrument_to_instrument_host
+
+
+
+ Busse, F., 'Generation of planetary field by convection',
+ Phys. Earth Planet. Int., vol. 12, p. 350, 1976.
+
+ reference.BUSSE1976
+
+
+
+ Dolginov, S.S., Y.G. Yeroshenko and L. Davis, 'On the
+ nature of the magnetic field near Venus', Kosmich. Issled.,
+ vol. 7, p. 747, 1969.
+
+ reference.DOLGINOVETAL1969
+
+
+
+ [see ELPHICETAL1980A]
+
+ reference.ELPHICETAL1979
+
+
+
+ Gordon, D.I., and R.E. Brown, Recent Advances in Fluxgate Magnetometry, IEEE
+ Trans. on Magnetics, Vol. MAG-8, 76, 1972.
+
+ reference.GORDONETAL1972
+
+
+
+ Russell, C.T., 'The magnetic moment of Venus: Venera-4
+ measurements reinterpreted,' Geophys. Res. Lett., vol. 3,
+ p. 125, 1976.
+
+ reference.RUSSELL1976
+
+
+
+ Russell, C.T., The ISEE 1 and 2 fluxgate magnetometers, IEEE Trans. Geosci.
+ Electro., GE-16, P. 239, 1978.
+
+ reference.RUSSELL1978
+
+
+
+ Russell, C.T., R.C. Elphic, and J.A. Slavin, 'On the
+ strength of the Venus bow shock', Nature, 1979.
+
+ reference.RUSSELLETAL1979A
+
+
+
+ Russell, C.T., R.C. Elphic, and J.A. Slavin, 'Initial
+ Pioneer Venus magnetic field results: Dayside
+ observations', Science, vol. 203, p. 745, 1979.
+
+ reference.RUSSELLETAL1979B
+
+
+
+ Russell, C.T., and R.C. Elphic, 'Observation of magnetic
+ flux ropes in Venus ionosphere', Nature, vol. 279,
+ p. 616, 1979.
+
+ reference.RUSSELLETAL1979C
+
+
+
+ Russell, C.T., R.C. Elphic, and J.A. Slavin, 'Initial
+ Pioneer Venus magnetic field results: Nightside
+ observations', Science, vol 205, p. 114, 1979.
+
+ reference.RUSSELLETAL1979D
+
+
+
+ Russell, C.T., R.C. Snare, J.D. Means, and R.C. Elphic,
+ 'Pioneer Venus Orbiter Fluxgate Magnetometer', Ieee Trans.
+ Geo. Elec., Vol. GE 18, No. 1 p. 32, 1980.
+
+ reference.RUSSELLETAL1980
+
+
+
+ Slavin, J.A., R.C. Elphic, and C.T. Russell, 'A comparison
+ of Pioneer Venus and Venera bow shock observations:
+ Evidence for a solar cycle variation', Geophys. Res. Lett.,
+ 1979.
+
+ reference.SLAVINETAL1979A
+
+
+
+ Slavin, J.A., R.C. Elphic, C.T. Russell, J.H. Wolfe, and
+ D.S. Intriligator, 'Position and shape of the Venus bow
+ shock: Pioneer Venus orbiter magnetometer observations',
+ Geophys. Res. Lett., 1979.
+
+ reference.SLAVINETAL1979B
+
+
+
+ Smith, E.J., L. Davis, Jr., P.J. Coleman, Jr., and C.P.
+ Sonett, Science, vol. 139, p. 909, 1963.
+
+ reference.SMITHETAL1963
+
+
+
+ Snare, R.C. and J.D. Means, A Magnetometer for the Pioneer Venus Orbiter, IEEE
+ Trans. Magnetics, vol. MAG-13(5), 1107, (REPLACED BY SNARE&MEANS1977), 1977.
+
+ reference.SNAREETAL1977
+
+
+
+
+ Orbiter Fluxgate Magnetometer (OMAG)
+
+
+ Magnetometer
+
+
+ not applicable
+
+ not applicable
+
+
+ This experiment used a triaxial fluxgate magnetometer with two ring-core sensors at the end of a magnetometer boom
+ and one ring-core sensor, at 45 degrees to the spin axis, partway down the boom. The drive and electronics design had
+ been used on the Apollo 15 and 16 subsatellites. The objectives of this investigation were to: (1) determine any
+ planetary and remnant magnetic fields; (2) deduce the location and strength of the ionospheric current system; (3)
+ determine the energy and mass balance in the upper atmosphere of Venus; (4) examine the nature of the solar wind
+ interaction with Venus; and, (5) study the near-wake region of Venus and the structure of the Venusian bow shock.
+ Additional objectives for interplanetary (solar wind) studies were to determine the perturbation of the near-planet
+ region by Venus and to compare the properties of the average field at 0.7 and 1.0 AU.
+
+ The magnetometer consists of three basic units, the electronics unit mounted inside the main spacecraft bus, an inboard
+ sensor assembly mounted about one-third of the way from the end of a 4.7 meter boom, and an outboard assembly mounted on
+ the end of the boom. The electronics box is magnesium, 15 x 22 x 15 cm in size, and has a mass of 1,7 kg. It includes a
+ 12-bit analog to digital converter. the inboard sensor is 6 x 7 x 6 cm, with a mass of 110 g. It holds a single magnetometer
+ oriented at 45 degrees to the orbiter spin axis. The outboard sensor is 8 x 5 x 4.5 cm, with a mass of 170 g. It comprises
+ two magnetometers, one parallel to the spin axis and one perpendicular. Total mass including wiring is 2 kg, and the system
+ uses 2.2 W at 27 V DC.
+
+ The magnetometers are triaxial fluxgate type with large loop gain and feedback. The core of the magnetometer is a ring
+ wrapped with permeable metal. The core is surrounded by drive, sense, and feedback coils. A sinusoidal drive voltage with
+ a 7.25 kHz frequency is used, 4 V peak-to-peak and 150 mA. The sense circuit detects the second harmonic of the drive
+ frequency, which is a function of the external magnetic field along the sense axis of the magnetometer ring core. The feedback
+ circuit acts to conceal the field and the output is the measured input to the feedback circuit required to cancel the field.
+ The range of the instrument is 128 gamma, which remains constant, but the resolution can change from 1/16 gamma to 1/2 gamma.
+ The sampling rate can vary by more than two orders of magnitude. The signals flow to the data handling assembly, where it is
+ digitized to 12 bits for each of the three sensors. The 36 bits are compressed to a single 32 bit word by conversion to floating
+ point words.
+
+ The instrument was intended to, in the worst case of low-bit and low-sample rates, measure one vector per 32 s. While in Venus
+ orbit, when the spacecraft was coasting through the interplanetary region in the apoapsis mode, the sample rate was one vector
+ per 8 s. While the spacecraft was passing through Venus' ionosphere in the periapsis mode, the sample rate was four vectors per
+ second.
+
+ The last full orbit of three-axis data was 3602, which ended on 16 Oct. 1988 at 14:30 UT. After this time, only one-axis data
+ were available.
+
+
+
diff --git a/data/pds4/context-pds4/instrument/pvo.onms_2.1.xml b/data/pds4/context-pds4/instrument/pvo.onms_2.1.xml
new file mode 100644
index 00000000..2e9ecc1b
--- /dev/null
+++ b/data/pds4/context-pds4/instrument/pvo.onms_2.1.xml
@@ -0,0 +1,111 @@
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument:pvo.onms
+ 2.1
+ Orbiter Neutral Mass Spectrometer (ONMS) for Pioneer Venus Orbiter
+ 1.20.0.0
+ Product_Context
+
+
+ 2020-08-26
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+ 2024-04-02
+ 2.0
+
+ Updated to IM 1.20.0.0
+
+
+
+ 2024-08-27
+ 2.1
+
+ Updated title, instrument name, and instrument description
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.pvo
+ instrument_to_instrument_host
+
+
+
+ Hedin, A.E., H.B. Niemann, W.T. Kasprzak and A. Seiff, Global Empirical
+ Model of the Venus Thermosphere, Journal of Geophysical Research, vol. 88,
+ 73-83, 1983.
+
+ reference.HEDINETAL1983
+
+
+
+ Niemann, H.B., J.R.Booth, J.E. Cooley, R.E. Hartle, W.T. Kasprzak,
+ N.W.Spencer, S.H. Way, D.M. Hunten and G.R. Carignan, Pioneer Venus
+ Orbiter Neutral Gas Mass Spectrometer, IEEE Trans. on Geoscience and
+ Remote Sensing, vol. GE-18 (1), 60-65, 1980.
+
+ reference.NIEMANNETAL1980B
+
+
+
+
+ Orbiter Neutral Mass Spectrometer (ONMS)
+
+
+ Mass Spectrometer
+
+
+ not applicable
+
+ not applicable
+
+
+ The Neutral Mass Spectrometer (ONMS) had the primary objective of measuring the number densities of neutral atoms and
+ molecules in the upper atmosphere of Venus, from perigee near 150 km to about 500 km, to help define its chemical,
+ dynamical, and thermal state. Combined with lower atmospheric neutral mass data from the large probe and bus probe, it
+ would also help determine the profile of atmospheric mixing. The instrument was housed in a 4.5 cm diameter tube, 16 cm
+ long, with a small cylinder attached perpendicularly holding a getter pump, all held inside a shielded cylindrical
+ electronic support structure inside the orbiter bus. One end of the tube was mounted against the exterior wall of the bus,
+ connected to a cylindrical chamber mounted on the outside to hold the orifice and ion source.
+
+ The experiment used a quadrupole mass spectrometer with three ion-source operating modes and three mass-scanning modes.
+ A knife-edged orifice, located on the instrument platform of the orbiter 27 degrees from the spin axis, allows gas into a
+ chamber holding the ion source. The ion source could be operated alternately in open and closed configurations to increase
+ accuracy. In open source mode, only free-streaming particles, with large kinetic energies due to the relative velocity of
+ the orbiter (~10 km/s at periapsis), are measured. Open source mode is used to measure noble and non-reactive gases. In the
+ closed source mode all the particles measured are surface-reflected particles, basically inflowing gas stagnated in the
+ source chamber. This mode is used for measurement of chemically active gases. There was also a "flip-flop" mode,
+ alternating between the modes.
+
+ The quadrupole analyzer consisted of 7.5 cm long rods with a field radius of 0.2 cm. Gas atoms and molecules were ionized
+ and separated by the quadrupole filter according to their mass, using stepping of applied AC and DC voltages. Ions exiting
+ the analyzer were deflected into the a secondary electron multiplier for charge conversion and amplification. A pulse detector
+ counted the pulses, and an electrometer amplifier measured the current. These are proportional to the particle density.
+
+ An adaptive mass scan was used to reduce the bit rate required for a given information-return rate. The resolution was 0.0001
+ for adjacent masses, and the mass range was 1 to 46 amu. It could scan continuously through the entire mass range or to scan
+ any combination of 8 masses within that range. The kinetic energy of the ionizing electrons could be chosen to be 70 or 27 eV
+ to allow discrimination of constituents of equal mass. The maximum average vertical spacing of the sample points was approximately
+ 400 m at 500 km altitude an horizontal spacing along the orbital path was 2 km. Sampling was either equally spaced in time over
+ a spin period or restricted to 45 degrees around the ram position.
+
+ Approximately two days after orbit insertion, a metal-ceramic breakoff caps was removed by activation of a pyrotechnic device
+ to expose the ONMS. Vertical and horizontal density variations of the major neutral constituents of the upper atmosphere of
+ Venus were detected and measured to define the dynamic, chemical, and thermal states of the upper atmosphere. Important constituents
+ measured were He, O, O2, CO, CO2 and/or N2, and A. It was also possible to study H, D and/or H2, C, and NO.
+
+
+
diff --git a/data/pds4/context-pds4/instrument/pvo.orpa_2.1.xml b/data/pds4/context-pds4/instrument/pvo.orpa_2.1.xml
new file mode 100644
index 00000000..c2e285af
--- /dev/null
+++ b/data/pds4/context-pds4/instrument/pvo.orpa_2.1.xml
@@ -0,0 +1,122 @@
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument:pvo.orpa
+ 2.1
+ Orbiter Retarding Potential Analyzer (ORPA) for Pioneer Venus Orbiter
+ 1.20.0.0
+ Product_Context
+
+
+ 2020-08-26
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+ 2024-04-02
+ 2.0
+
+ Updated to IM 1.20.0.0
+
+
+
+ 2024-08-30
+ 2.1
+
+ Updated title, instrument name, and instrument description
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.pvo
+ instrument_to_instrument_host
+
+
+
+ Knudsen W.C. , Evaluation and demonstation of the use of retarding
+ potential analyzers for measuring several ionospheric quantities, J.
+ Geophys. Res., vol. 71, pp. 4669-4678, 1966.
+
+ reference.KNUDSENETAL1966
+
+
+
+ Knudsen, W.C., J. Bakke, K. Spenner, and V. Novak, Retarding Potential
+ Analyzer for the Pioneer Venus Orbiter, Space Sci. Inst., 4, 351, 1979.
+
+ reference.KNUDSENETAL1979
+
+
+
+ Knudsen, W.C., K. Spenner, J. Bakke, and V. Novak, Pioneer Venus Orbiter
+ Planar Retarding Potential Analyzer Plasma Experiment, IEEE Trans. on
+ Geosci. Remote Sens., 18, 1, 60, 1980.
+
+ reference.KNUDSENETAL1980
+
+
+
+
+ Orbiter Retarding Potential Analyzer (ORPA)
+
+
+ Langmuir Probe
+
+
+ not applicable
+
+ not applicable
+
+
+ The Retarding Potential Analyzer (ORPA) investigation used a Langmuir-probe retarding-potential analyzer designed to
+ measure electron concentration and temperature, major ion concentrations, temperatures, and masses, ion drift velocities,
+ and the energy distribution function of ambient photoelectrons in the ionosphere. It was an adaptation of the instrument
+ flown on the German Aeros satellite in 1972. Either one of two sensor heads could be used, each consisting of a multigrid
+ cup and electrometer, which could operate in electron, ion, or photoelectron modes, initiated by spacecraft roll pulses.
+ The aims of the investigation were to improve knowledge of the important ionic reactions in the Venusian ionosphere, to
+ study the plasma transport processes to determine if Venus has a polar wind, to study the processes at the solar
+ wind-ionosphere boundary, and to study similar aims concerning the ambient electron population. Although the instrument
+ was designed to detect low-energy plasma particles in the ionosphere, it could also make measurements of the interaction
+ between the ionosphere and solar wind at altitudes up to 500 km. The instrument had a mass of 2.8 kg and used 2.4 W power.
+
+ The ORPA axis is offset from the spacecraft spin axis so the ORPA axis could be close in alignment to the spacecraft velocity
+ vector near periapsis. Large entrance grids and a collector guard ring provide a uniform flux radially from the instrument axis,
+ the uniform central region of the flux is sampled by the collectors. A 30 cm diameter ground plane surrounds the entrance grid.
+ The instrument used multiple collector grids coated with colloidal graphite to selectively funnel various ionospheric particles to
+ strike a detector. The grids were 6 cm in diameter spaced over 1.6 cm, and included an entrance grid, ion suppressor grid, ion
+ retarding grid, displacement current shield, electron suppressor grid, and a collector connected to an electrometer which amplified
+ the current induced in the detector. The grids could be set with varying electric potentials, or control voltages, depending on the
+ mode of operation and the quantity being measured.
+
+ The instrument could operate in three modes: Langmuir probe mode, ion mode, or photoelectron mode. Langmuir probe mode had a linear
+ electron coarse scan of 64 steps of roughly 0.2 volts/step, covering -4.8 to 7.8 V. It also had a linear electron fine scan of 20
+ steps of 0.05 V subdividing 5 of the coarse steps. Ion mode used 80 quadratic steps over -0.5 to 39 V referenced to the plasma potential.
+ The photoelectron mode had 25 quadratic steps covering 0 to -60 V.
+
+ Scans were made at roughly 120 km (~12 sec) intervals while the orbital path was within the ionosphere, allowing for approximately
+ 50 measurements below the ionopause on the dayside. Each scan took a small fraction of the spin period, (0.04 to 0.16 seconds),
+ with on-board computing determining which scan to transmit based on being taken at the optimal point in the spacecraft's rotation
+ when the sensor axis was closest to the plasma flow velocity vector (peak select). It also had an I-V mode were every other current
+ value in the electron mode and in the ion mode were stored for transmission every third spacecraft rotation.
+
+ Concentrations (from 100 - 10,000,000 per cubic cm), temperatures (300 - 10,000 K), and masses (1-56 AMU) of the four most abundant
+ ions were measured every 12 seconds for 0.16 seconds per measurement. Ion drift velocity (from 0.05 to 5 km/s) were measured for 0.16
+ seconds or 24 seconds every 50 seconds. The low-energy electron distribution function (0-60 eV) was measured for 0.05 seconds every
+ 12 seconds, and electron temperature (300-20,000 K) was measured for 0.04 seconds every 0.04 or 12 seconds. Vector ion velocity was
+ measured by recording three scans with the instrument pointing to three different directions in three successive spin cycles. A special
+ mode of operation allowed total ion concentration to be measured over a 1 meter sampling distance at a spacecraft velocity of 10 km/sec,
+ at 20 m intervals.
+
+
+
diff --git a/data/pds4/context-pds4/instrument_host/spacecraft.ody_1.3.xml b/data/pds4/context-pds4/instrument_host/spacecraft.ody_1.3.xml
new file mode 100644
index 00000000..8dba8ce9
--- /dev/null
+++ b/data/pds4/context-pds4/instrument_host/spacecraft.ody_1.3.xml
@@ -0,0 +1,307 @@
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.ody
+ 1.2
+ 2001 MARS ODYSSEY
+ 1.20.0.0
+ Product_Context
+
+
+ 2023-09-15
+ 1.2
+
+ instrument:themis.ody -> :ody.themis, :ody.accel, :ody.mar, :ody.rss
+ with permission from nodes
+
+
+
+ 2021-07-21
+ 1.1
+
+ Replaced all lidvid_reference with lid_reference, and
+ instrument:grs.ody -> :ody.grs + :ody.hend + :ody.ns,
+ which separates 1 inst into 3 and flips the order
+
+
+
+ 2016-10-01
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.2001_mars_odyssey
+ instrument_host_to_investigation
+
+
+ urn:nasa:pds:context:instrument:ody.accel
+ instrument_host_to_instrument
+
+
+ urn:nasa:pds:context:instrument:ody.grs
+ instrument_host_to_instrument
+
+
+ urn:nasa:pds:context:instrument:ody.hend
+ instrument_host_to_instrument
+
+
+ urn:nasa:pds:context:instrument:ody.ns
+ instrument_host_to_instrument
+
+
+ urn:nasa:pds:context:instrument:ody.mar
+ instrument_host_to_instrument
+
+
+ urn:nasa:pds:context:instrument:ody.rss
+ instrument_host_to_instrument
+
+
+ urn:nasa:pds:context:instrument:ody.themis
+ instrument_host_to_instrument
+
+
+ urn:nasa:pds:context:target:planet.mars
+ instrument_host_to_target
+
+
+
+ Mars Surveyor 2001, Mission Plan, Revision B (MSP 722-201), JPL Document
+ D-16303, Jet Propulsion Laboratory, Pasadena, CA, 2000.
+
+ reference.JPLD-16303
+
+
+
+
+ 2001 MARS ODYSSEY
+ Spacecraft
+ ODY
+
+
+ Instrument Host Overview
+ ========================
+ For most Mars Odyssey experiments, data were collected by
+ instruments on the spacecraft. Those data were then relayed
+ via the telemetry system to stations of the NASA Deep Space
+ Network (DSN) on the ground. Radio Science observations (such
+ as radio tracking) required that DSN hardware also participate
+ in data acquisition. The following sections provide an
+ overview first of the spacecraft and then of the DSN ground
+ system as both supported Mars Odyssey science activities.
+
+
+ Instrument Host Overview - Spacecraft
+ =====================================
+ The Mars Odyssey spacecraft was built by Lockheed Martin
+ Astronautics (LMA). The spacecraft structure was divided into
+ two modules: the equipment module and the propulsion module.
+ The shape was not uniform, but can be approximated by
+ envisioning a box 2.2 x 1.7 x 2.6 meters. The framework was
+ composed of aluminum and titanium. Most spacecraft systems
+ were redundant in order to provide backup should a device fail.
+ For more information, see [JPLD-16303].
+
+ Command and Data Handling
+ -------------------------
+ This subsystem handled all computing functions for Mars
+ Odyssey. It ran the flight software and controlled the
+ spacecraft through interface electronics. The system was
+ based around a RAD6000 computer with 128 megabytes of
+ random access memory (RAM) and 3 megabytes non-volatile
+ memory, which allowed data to be maintained by the system
+ in the event of a power failure. The interface
+ electronics were computer cards that communicated with
+ external peripherals. The cards fit into the computer's
+ main board. There were two identical sets of the
+ computer and interface electronics for back up in case
+ one failed. One card was not redundant. It was a one
+ gigabyte mass memory card that was used to store imaging
+ data.
+
+ Telecommunications
+ ------------------
+ The telecommunication subsystem was composed of two parts.
+ The first was a radio system that operated in the X-band
+ microwave frequency range. It was used for communications
+ between Earth and the spacecraft. The other system operated
+ in the ultra high frequency (UHF) range for communications
+ between future Mars landers and Odyssey.
+
+ Communication between the spacecraft and Earth occurred
+ through the use of three antennas. The high-gain antenna was
+ a dish with 1.3 meter diameter (4.25 feet). It was used
+ during the late Cruise and Science and relay phases of the
+ mission when data rates were high. It simultaneously
+ received commands from Earth and transmitted science data to
+ Earth. The medium-gain antenna was a 7.1 cm (2.8 inch) wide
+ rectangular horn antenna that protruded through the high-gain
+ dish. The low-gain antenna was 4.4 cm (1.75 inches) and
+ provided wide- angle communications in emergencies or when
+ the high-gain antenna was not pointed directly at Earth.
+
+ Electrical Power
+ ----------------
+ A 7 square meter (75 square feet) solar panel containing an
+ array of gallium arsenide cells generated power for the
+ spacecraft. The power distribution and drive unit sent power
+ to the electrical loads of the spacecraft through a system of
+ switches.
+
+ Guidance, Navigation and Control
+ --------------------------------
+ This subsystem used three redundant pairs of sensors to
+ determine the spacecraft's attitude. A star camera was used
+ to look at star fields and a sun sensor detected the position
+ of the Sun in order to back up the star camera. The inertial
+ measurement unit collected spacecraft orientation data
+ between star camera updates. The reaction wheels along with
+ the thrusters operated to control the attitude. There were
+ four reaction wheels - three primary and one for backup.
+ Odyssey was a three-axis stabilized spacecraft.
+
+ Propulsion
+ ----------
+ The propulsion system comprised a main engine, which aided in
+ placing Odyssey in orbit around Mars, and sets of small
+ thrusters, which performed attitude control and trajectory
+ correction maneuvers. The main engine produced a thrust of
+ about 695 Newtons (156 pounds of force). Each of the four
+ attitude controlling thrusters produced a thrust of 0.9
+ Newtons (0.2 pounds of force) and the four spacecraft turning
+ thrusters produced a force of 22 Newtons (5 pounds of force).
+ The propulsion system also included one gaseous helium tank
+ used to pressurize the fuel and oxidizer tanks, miscellaneous
+ tubing, pyro valves, and filters.
+
+ Structures
+ ----------
+ The spacecraft was composed of two modules - propulsion and
+ equipment. The propulsion module contained tanks, thrusters,
+ and associated plumbing. The equipment module consisted of
+ the equipment deck, which supported the Mars Radiation
+ Environment Experiment (MARIE), and engineering components.
+ The other component of the equipment module was the science
+ deck which housed the Thermal Emission Imaging System
+ (THEMIS), Gamma Ray Spectrometer (GRS), High-Energy Neutron
+ Detector (HEND), Neutron Spectrometer (NS), and star cameras
+ on top and engineering components and the GRS central
+ electronics box on the underside.
+
+ Thermal Control
+ ---------------
+ A combination of heaters, radiators, louvers, blankets, and
+ thermal coatings maintained each spacecraft component's
+ temperature within its allowable limits.
+
+ Mechanisms
+ ----------
+ Odyssey functioned via several mechanisms, many of which were
+ associated with the high-gain antenna. The antenna was
+ locked down during launch, cruise, and aerobraking through
+ three 'retention and release devices,' or latches. The
+ antenna was released and deployed with a motor-driven hinge
+ once the science orbit around Mars was attained. A two-axis
+ gimbal assembly controlled the position of the antenna. The
+ solar array used four latches which folded together and
+ locked down the panels during launch. After deployment, a
+ two-axis gimbal assembly controlled the solar array. The
+ last mechanism was a latch for the deployment of the 6-meter
+ GRS boom.
+
+ Flight Software
+ ---------------
+ Odyssey received commands from Earth via radio and then
+ translated them into spacecraft actions. The flight software
+ had the capability to run many sequences concurrently in
+ addition to executing received commands immediately.
+
+ The data collection software was quite flexible. The science
+ and engineering data were collected and then put in a variety
+ of holding bins called Application Identifiers (APIDs). Ground
+ commands could easily modify the data routing and sampling
+ frequency.
+
+ A number of autonomous spacecraft performance functions were
+ part of the flight software. The spacecraft ran routines
+ to control attitude and orientation without commands sent
+ from Earth. The software also executed fault protection
+ routines to determine if any internal problem occurred. If
+ a problem was found, a number of automatic preset actions
+ would occur to resolve the problem and put the spacecraft
+ into a standby mode until ground controllers provided
+ further direction.
+
+ Coordinate System
+ -----------------
+ The spacecraft frame is defined with the X axis parallel to
+ the stowed HGA boresight, the Y axis normal to the stowed
+ solar arrays, and the Z axis in the direction of the main
+ engine thrust (see figure below). The origin of the frame
+ is centered on the launch vehicle separation plane.
+
+ _______________ HGA
+ \ /
+ Science .. `._________.'
+ Orbit || ._______________.
+ Velocity || | ^+Xsc | Science Deck
+ ^. || | | |
+ `. || | | |
+ `. || +Ysc | |
+ ||@| <-----o +Zsc (out of page)
+ || | |
+ || | |
+ || | Science Deck |
+ Solar || ._______________.
+ Array ..
+
+ /
+ /
+ /
+ V Nadir
+
+
+ Instrument Host Overview - DSN
+ ==============================
+ The Deep Space Network is a telecommunications facility managed
+ by the Jet Propulsion Laboratory of the California Institute of
+ Technology for the U.S. National Aeronautics and Space
+ Administration (NASA).
+
+ The primary function of the DSN is to provide two-way
+ communications between the Earth and spacecraft exploring the
+ solar system. To carry out this function it is equipped with
+ high-power transmitters, low-noise amplifiers and receivers,
+ and appropriate monitoring and control systems.
+
+ The DSN consists of three complexes situated at approximately
+ equally spaced longitudinal intervals around the globe at
+ Goldstone (near Barstow, California), Robledo (near Madrid,
+ Spain), and Tidbinbilla (near Canberra, Australia). Two of
+ the complexes are located in the Northern Hemisphere while the
+ third is in the Southern Hemisphere.
+
+ Each complex includes several antennas, defined by their
+ diameters, construction, or operational characteristics:
+ 70-m diameter, standard 34-m diameter, high-efficiency 34-m
+ diameter (HEF), and 34-m beam waveguide (BWG).
+
+
+
+
diff --git a/data/pds4/context-pds4/instrument_host/spacecraft.pvo_2.1.xml b/data/pds4/context-pds4/instrument_host/spacecraft.pvo_2.1.xml
new file mode 100644
index 00000000..10f33811
--- /dev/null
+++ b/data/pds4/context-pds4/instrument_host/spacecraft.pvo_2.1.xml
@@ -0,0 +1,337 @@
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.pvo
+ 2.1
+ Pioneer Venus Orbiter (PVO)
+ 1.20.0.0
+ Product_Context
+
+
+ 2016-10-01
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+ 2023-12-05
+ 2.0
+
+ Adding references for additional Pioneer Venus Orbiter instruments.
+
+
+
+ 2024-09-06
+ 2.1
+
+ Edited title and name.
+
+
+
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.pioneer_venus
+ instrument_host_to_investigation
+
+
+ urn:nasa:pds:context:instrument:pvo.oefd
+ instrument_host_to_instrument
+
+
+ urn:nasa:pds:context:instrument:pvo.oetp
+ instrument_host_to_instrument
+
+
+ urn:nasa:pds:context:instrument:pvo.oims
+ instrument_host_to_instrument
+
+
+ urn:nasa:pds:context:instrument:pvo.omag
+ instrument_host_to_instrument
+
+
+ urn:nasa:pds:context:instrument:pvo.onms
+ instrument_host_to_instrument
+
+
+ urn:nasa:pds:context:instrument:pvo.orad
+ instrument_host_to_instrument
+
+
+ urn:nasa:pds:context:instrument:pvo.orpa
+ instrument_host_to_instrument
+
+
+ urn:nasa:pds:context:instrument:pvo.orse
+ instrument_host_to_instrument
+
+
+ urn:nasa:pds:context:instrument:pvo.ouvs
+ instrument_host_to_instrument
+
+
+
+ urn:nasa:pds:context:instrument:pvo.oad
+ instrument_host_to_instrument
+
+
+
+ urn:nasa:pds:context:instrument:pvo.ocpp
+ instrument_host_to_instrument
+
+
+ urn:nasa:pds:context:instrument:pvo.ogbd
+ instrument_host_to_instrument
+
+
+
+ urn:nasa:pds:context:instrument:pvo.oir
+ instrument_host_to_instrument
+
+
+
+
+ urn:nasa:pds:context:instrument:pvo.opa
+ instrument_host_to_instrument
+
+
+
+ urn:nasa:pds:context:target:planet.venus
+ instrument_host_to_target
+
+
+
+ Nothwang, G.T., Pioneer Venus Spacecraft Design and Operation, IEEE
+ Transactions on Geoscience and Remote Sensing, Vol GE-18, No. 1, pp. 5-10,
+ January 1980.
+
+ reference.NOTHWANG1980
+
+
+
+
+ Pioneer Venus Orbiter (PVO)
+ Spacecraft
+ PVO
+
+
+
+ Instrument Host Overview
+ ========================
+
+ The Pioneer Venus mission objectives dictated the requirement
+ for two spacecraft designs designated the Orbiter and the
+ Multiprobe. (The Multiprobe is defined as the Bus with the one
+ Large Probe and three identical Small Probes attached in the
+ launch/cruise configuration.) The conceptual designs of these
+ spacecraft resulted from Phase B studies conducted from October
+ 1972 to July 1973, and after selection of the spacecraft
+ contractor, Hughes Aircraft Company, in February 1974, a
+ spacecraft conceptual design review was conducted in November
+ 1974.
+
+ The Orbiter and Multiprobe utilized the same designs to the
+ maximum extent possible to minimize costs. In addition,
+ designs of subsystems or portions of subsystems from previous
+ spacecraft designs (such as OSO and Intelsat) were utilized to
+ the maximum extent possible with little or no modifications.
+ This commonality in the two spacecraft designs also resulted in
+ certain amounts of commonality in ground test equipment and
+ test software as well as commonality in spacecraft flight
+ operations and associated software.
+
+ Extracted from:
+
+ NOTHWANG, George J.,'Pioneer Venus Spacecraft Design and
+ Operation', IEEE Transactions on Geoscience and Remote Sensing,
+ vol. GE-18, No. 1, January 1980
+
+
+ Platform Descriptions
+ =====================
+
+ Also from [NOTHWANG1980]:
+
+ ORBITER
+ -------
+
+ The Orbiter spacecraft consists of the following subsystems and
+ functions: Mechanical Function (including the Spacecraft Structure),
+ Thermal Function (accomplished by the Structure/Harness Subsystem),
+ Controls Subsystem, Propulsion Subystem, Data Handling Subsystem,
+ Command Subsystem, Communications Subsystem, and Power Subsystem.
+
+ Mechanical
+ ----------
+
+ The mechanical features of the spacecraft can be described by six
+ basic assemblies. The despun antenna assembly, the bearing and
+ power transfer assembly (BAPTA), the BAPTA support structure,
+ equipment shelf, substrate (solar array), orbit insertion motor
+ (OIM) and its case, and thrust tube. The shape and equipment layout
+ conform to the basic mechanical requirements of a spin-stabilized
+ vehicle. The solar cells on the cylindrical solar panel, antenna
+ orientations, and thrust vector orientations provide efficient
+ power, communications, and maneuverability while the Orbiter is
+ spinning in its cruise and orbit attitudes.
+
+ Thermal
+ -------
+
+ The thermal design is based on isolating the equipment from the
+ external solar extremes experienced during the mission. (Solar
+ intensity increases by a factor of 1.98 from Earth to Venus.)
+ Commandable heaters are provided to maintain the orbit insertion
+ motor and safe and arm device within their specified temperature
+ ranges, to prevent possible freezing of hydrazine monopropellant,
+ and to make up heat balance should there occur an inadvertent trip
+ of nonessential spacecraft loads. Fifteen thermostatically
+ controlled thermal louvers are mounted on the aft side of the
+ equipment shelf beneath units having high dissipations.
+
+ Controls
+ --------
+
+ The controls subsystem provides the sensing logic and actuators
+ to accomplish the following stabilization, control, and reference
+ functions:
+ a) spin axis attitude determination (via use of slit
+ field-of-view type sun sensors and star sensors), science
+ roll reference signals generation, and spin period
+ measurement;
+ b) control of thrusters for spin axis attitude maneuvers, spin
+ speed control, and spacecraft velocity maneuvers;
+ c) high-gain antenna azimuth despin control and elevation
+ positioning to a desired earth line-of-sight pointing;
+ additionally, antenna slew control for open-loop tracking of
+ the Earth line-of-sight;
+ d) magnetometer sensor deployment;
+ e) nutational damping, via use of a partially filled tube of
+ liquid Freon E3.
+
+ Propulsion
+ ----------
+
+ The propulsion subsystem provides the hydrazine monopropellant
+ storage, pressurization, distribution lines, isolation valves,
+ filtering, and thruster assemblies used to accomplish Orbiter
+ maneuvers throughout the mission.
+
+ Data Handling
+ ---- --------
+
+ The data handling subsystem conditions and integrates into command-
+ selectable (choice of thirteen fixed and one programmable) formats,
+ all analog and digital telemetry data (248 assigned channels)
+ originating in the subsystems and science instruments. The selected
+ format of the all-digitized data modulates a 16384-Hz subcarrier
+ at a command-selectable (choice of thirteen rates between 8 and
+ 4096 bps) bit rate. The resulting information is routed to the
+ communications subsystem for modulation of the downlink S-band
+ carrier. The data handling subsystem includes a data memory,
+ consisting of two data storage units (DSU), that is intended
+ primarily for use during any occultation. Data are stored or read
+ out at the commanded bit rate. Each DSU has a capacity of 524,288
+ bits (equivalent to 1024 telemetry minor frames).
+
+ Command
+ -------
+
+ The command subsystem decodes all commands received via the
+ communications subsystem at the fixed rate of 4 bps, and either
+ stores the command for later execution or routes the command in
+ real time to the addressed destination. Each of the 381 assigned
+ commands is either completely decoded (discrete-type command) by
+ the command subsystem and the execution command generated, or is
+ partially decoded (quantitative-type command) by the command
+ subsystem and the command is routed to the addressed destination
+ for final decoding.
+
+ Communications
+ --------------
+
+ The communications subsystem provides radiation reception and
+ transmission capabilities for the command and telemetry
+ information. The uplink command capability is maintained by
+ modulating an S-band carrier of approximately 2.115 GHz. The
+ downlink telemetry modulates an S-band carrier of approximately
+ 2.295 GHz. There are two redundant reception channels; each
+ includes a hemispherically omnidirectional antenna (aft or forward)
+ that spatially supplements the other to produce total spatial
+ coverage. Optionally by command, the forward antenna is replaceable
+ by a high-gain antenna or a high-gain back-up antenna.
+
+ The S-band downlink is assignable by command to any one of the aft
+ or forward omnidirectional antennas, or to the high-gain or high-
+ gain back-up (directional) antennas. Its frequency is a multiple of
+ the uplink frequency; or in the absence of an uplink signal, it is
+ a multiple of a crystal oscillator located in the receiver. The
+ downlink may also be transmitted via any one of, or some pairs of,
+ four 10-W power amplifiers.
+
+ There is an additional transmitter in the X-band range (the
+ frequency is 11/3 of the S-band downlink frequency) that is for
+ use in occultation measurements. The transmission is unmodulated
+ through the high-gain antenna only.
+
+ Power
+ -----
+
+ The power subsystem provides semiregulated 28V +/- 10 percent to
+ all spacecraft loads (including science instruments). The primary
+ source of power is the main solar array. When the solar panel
+ output cannot provide adequate power for all spacecraft loads (at
+ low sun angles and during eclipses), the two nickel/cadmium
+ batteries (each rated at 7.5 Ah full capacity) come on line
+ automatically through the discharge regulators. Battery energy is
+ replenished through a small boost charge array. The power interface
+ unit provides power switching for the propulsion heaters and OIM
+ heaters. It also contains fuses for these circuits and the science
+ instruments input power lines.
+
+ Power is distributed on four separate power buses. If a spacecraft
+ overcurrent condition or under-voltage on either battery occurs,
+ loads are removed to protect the spacecraft from potential
+ catastrophic failure by tripping off buses in the following
+ sequence: science, switched loads, and transmitter. This leaves
+ only those loads that are absolutely essential to spacecraft
+ survival in a continuously powered ON mode. The RF transmitters and
+ exciters are on the transmitter bus. Controls and data handling
+ units are on the switched loads bus. Scientific instruments are on
+ the science bus. Command units, OIM and propulsion heaters, power
+ conditioning units, and spacecraft receivers are on the essential
+ bus. Excitation for the pyro bus is derived from a battery tap
+ located 16 cells (of a total of 24) from the ground reference
+ level. The bus voltage is limited to 30.0 V by seven shunt limiters
+ that dissipate all excess solar panel capacity in load resistors
+ mounted on the solar panel substrate and equipment shelves.
+
+
+
+
diff --git a/data/pds4/context-pds4/investigation/field_campaign.dd_eldorado_nv_2015_1.1.xml b/data/pds4/context-pds4/investigation/field_campaign.dd_eldorado_nv_2015_1.1.xml
new file mode 100644
index 00000000..10365645
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/field_campaign.dd_eldorado_nv_2015_1.1.xml
@@ -0,0 +1,55 @@
+
+
+
+
+ urn:nasa:pds:context:investigation:field_campaign.dd_eldorado_nv_2015
+ 1.1
+ Dust Devil Field Campaign, Eldorado Playa, Nevada, 2015
+ 1.22.0.0
+ Product_Context
+
+
+ 2020-12-08
+ 1.0
+
+ Initial setup for this investigation.
+
+
+
+ 2024-10-02
+ 1.1
+
+ Where applicable, updated version, title, name
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument:no-host.lorenz_met_station
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:target:planet.earth
+ investigation_to_target
+
+
+ 10.1002/2014JEE004712
+ Jackson, Brian and Lorenz, Ralph (2015). A multiyear dust devil vortex survey using an automated search of pressure time series, J. Geophys. Res. Planets, 120.
+ Citation of the official published version of the paper.
+
+
+
+ Dust Devil Field Campaign, Eldorado Playa, Nevada, 2015
+ Field Campaign
+ 2012
+ 2013
+
+ A dust devil field campaign in Eldorado Playa, Nevada conducted over 2012-2013 by Brian Jackson and Ralph Lorenz. The work was published in JGR in 2015.
+ Terrestrial dust devils serve as planetary analogs to dust devils on Mars. The remote meterological stations used in this study provided pressure and temperature
+ data for dust devil encounters in the desert. In some cases measurements of voltage were also acquired.
+
+
+
diff --git a/data/pds4/context-pds4/investigation/individual_titan-material-database_1.1.xml b/data/pds4/context-pds4/investigation/individual_titan-material-database_1.1.xml
new file mode 100644
index 00000000..20756af6
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/individual_titan-material-database_1.1.xml
@@ -0,0 +1,63 @@
+
+
+
+
+ urn:nasa:pds:context:investigation:individual.titan-material-database
+ 1.1
+ Titan Material Database - Material Properties of Organic Liquids, Ices, and Hazes on Titan
+ 1.22.0.0
+ Product_Context
+
+
+ 2023-05-25
+ 1.0
+
+ Initial setup for this investigation.
+
+
+
+ 2024-10-02
+ 1.1
+
+ Where applicable, updated version, title, name
+
+
+
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.titan
+ investigation_to_target
+
+
+ urn:nasa:pds:context:target:laboratory_analog.saturn.titan
+ investigation_to_target
+
+
+ 10.48550/arXiv.2210.01394
+ Yu, Xinting, Yue Yu, Julia Garver, Jialin Li, Abigale Hawthorn, Ella Sciamma-O'Brien, Xi Zhang, and Erika Barth (2023). Material Properties of Organic Liquids, Ices, and Hazes on Titan,
+ Citation of the official published version of the paper.
+
+
+
+ Material Properties of Organic Liquids, Ices, and Hazes on Titan
+ Individual Investigation
+ 2022
+ 2023
+
+ Titan has a diverse range of materials in its atmosphere and on its surface: the simple organics that reside in various phases (gas, liquid, ice)
+ and the solid complex refractory organics that form Titan's haze layers. These materials all actively participate in various physical processes
+ on Titan, and many material properties are found to be important in shaping these processes. Future in-situ exploration on Titan would likely
+ encounter a range of materials, and a comprehensive database to archive the material properties of all possible material candidates will be needed.
+ Here we summarize several important material properties of the organic liquids, ices, and the refractory hazes on Titan that are available in the
+ literature and/or that we have computed. These properties include thermodynamic properties (phase change points, sublimation and vaporization
+ saturation vapor pressure, and latent heat), physical property (density), and surface properties (liquid surface tensions and solid surface
+ energies). We have developed a new database to provide a repository for these data and make them available to the science community. These data
+ can be used as inputs for various theoretical models to interpret current and future remote sensing and in-situ atmospheric and surface
+ measurements on Titan. The material properties of the simple organics may also be applicable to giant planets and icy bodies in the outer solar
+ system, interstellar medium, protoplanetary disks, and exoplanets.
+
+
+
diff --git a/data/pds4/context-pds4/investigation/mission.2001_mars_odyssey_1.1.xml b/data/pds4/context-pds4/investigation/mission.2001_mars_odyssey_1.1.xml
new file mode 100644
index 00000000..f1d0b493
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/mission.2001_mars_odyssey_1.1.xml
@@ -0,0 +1,203 @@
+
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.2001_mars_odyssey
+ 1.1
+ 2001 Mars Odyssey
+ 1.21.0.0
+ Product_Context
+
+
+ 2024-06-04
+ 1.1
+ Added instruments, NASA website external reference, terse description.
+
+
+ 2016-10-01
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.ody::1.0
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:target:planet.mars::1.0
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:instrument:ody.accel
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:ody.grs
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:ody.hend
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:ody.mar
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:ody.ns
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:ody.rss
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:ody.themis
+ investigation_to_instrument
+
+
+
+
+ Mars Surveyor 2001, Mission Plan, Revision B (MSP 722-201), JPL Document
+ D-16303, Jet Propulsion Laboratory, Pasadena, CA, 2000.
+
+ Mars Surveyor 2001, Mission Plan
+
+
+ https://science.nasa.gov/mission/odyssey/
+ Mars Odyssey NASA Website
+
+
+
+
+ 2001 Mars Odyssey
+ Mission
+ 2001-01-04
+
+
+ The Mars Odyssey spacecraft was launched from the Cape
+ Canaveral Air Station in Florida on 2001-04-07 aboard a Boeing
+ Delta II 7925 launch vehicle. At launch Odyssey weighed 729.7
+ kilograms (1606.7 pounds), including the 331.8 kilogram (731.5
+ pound) dry spacecraft with all of its subsystems, 353.4
+ kilograms (779.1 pounds) of fuel and 44.5 kilograms (98.1
+ pounds) of instruments. The spacecraft traveled more than 460
+ million kilometers over the course of a 200-day cruise period
+ to reach Mars on 2001-10-24.
+
+ Upon reaching Mars, Odyssey fired its main rocket engine for a
+ 19-minute Mars orbit insertion (MOI) burn. This maneuver
+ slowed the spacecraft and allowed the planet's gravity to
+ capture it into orbit. Initially, Odyssey whirled around the
+ red planet in a highly elliptical orbit that took 45 hours to
+ complete.
+
+ After orbit insertion, Odyssey performed a series of orbit
+ changes to drop the low point of its orbit into the upper
+ fringes of the Martian atmosphere at an altitude of about 110
+ kilometers. During every atmospheric pass, the spacecraft
+ slowed by a small amount because of air resistance. This
+ slowing caused the spacecraft to lose altitude on its next pass
+ through the atmosphere. Odyssey used this aerobraking
+ technique over a period of three months to transition from an
+ elliptical orbit into a 400 km nearly circular orbit for
+ mapping.
+
+ Mars Odyssey was intended to last for more than 2 full Mars
+ years, or 1374 days. The orbiter had its own science
+ mission and also acted as a relay for landed Mars missions in
+ 2004. The primary mapping mission began in
+ February 2002 and lasted until August 2004 for a total of
+ 917 days. An extended mission then took place through the end
+ of September 2006. The inclination of the science orbit was 93.1
+ degrees, resulting in a nearly Sun- synchronous orbit
+ [JPLD-16303]. The orbit period was just under two hours.
+
+ The spacecraft was three-axis stabilized and powered by solar
+ cells. It was built of lightweight composite materials and
+ divided into two sub-assemblies: the equipment module and the
+ propulsion module. The equipment module consisted of two decks
+ - the equipment deck, containing engineering equipment and one
+ science instrument, the Martian Radiation Environment
+ Experiment (MARIE), and the science deck, which housed the
+ remainder of the science instruments and other engineering
+ components.
+
+ Mars Odyssey carried three on-board science instruments. The
+ Thermal Emission Imaging System (THEMIS) worked both in the
+ visible and infrared spectral regions. It took multi-spectral
+ thermal-infrared images to determine the surface mineralogy at
+ a global scale and also acquired visible images with a
+ per-pixel resolution of 18 meters (59 feet). The Gamma Ray
+ Spectrometer (GRS) measured gamma rays emitted from the surface
+ of Mars to determine the elemental composition of the surface,
+ including mapping water deposits in water-ice form. It also
+ studied cosmic gamma ray bursts. GRS was actually a suite of
+ three instruments - the Gamma Ray Spectrometer, the Neuron
+ Spectrometer (NS) and the High-Energy Neutron Detector (HEND).
+ GRS and THEMIS could not operate at the same time due to
+ conflicts in the parameters necessary for operation.
+
+ The third instrument, the Martian Radiation Environment Experiment
+ (MARIE), was intended to operate continuously throughout the
+ science mission to collect data about the radiation environment of
+ the planet. Flight commanders turned off MARIE on 2001-08-18
+ because the instrument failed to reset after it did not respond
+ during a downlink session the previous week. It was turned on
+ again in early March 2002 after the mapping orbit had been
+ established. MARIE operated from that time until it was disabled
+ following an intense solar particle event on October 29, 2003.
+ Before being disabled, the instrument showed abnormally high
+ current draw and temperatures. Throughout November and early
+ December of 2003, after the solar event subsided and after
+ Odyssey recovered from entering safe mode, the Odyssey team
+ attempted unsuccessfully to reestablish communication with MARIE.
+
+ Two other instruments aboard Odyssey were, like MARIE,
+ sensitive to energetic charged particles. The first instrument
+ was the gamma detector on GRS, which used a large germanium
+ crystal to detects gamma rays coming from the Martian surface.
+ The detection of gamma rays depended on the deposition of energy
+ in the crystal by the incident photons. Charged particles also
+ deposited energy in the crystal. The second non-MARIE instrument
+ aboard Odyssey that was sensitive to charged particles was the
+ scintillation block in the high energy neutron detector (HEND,
+ an element of the GRS suite). The 'external' detector was a
+ cesium-iodide (CsI) scintillator surrounding a stilbene crystal
+ scintillator that was used for high-energy neutron detection.
+ These two detectors were available to continue the monitoring of
+ aspects of the radiation environment at Mars that was conducted
+ by MARIE during Odyssey's cruise and prime mission phases.
+
+ The local mean solar time (LMST) at the start of the Odyssey
+ mission was approximately 4:00 p.m. and was later frozen by
+ a maneuver to approximately 5:00 p.m. The local true solar time
+ (LTST) oscillated about 45 minutes around the mean. During the
+ Extended Mission, a small maneuver could be used to eliminate
+ any further drift in LMST. The solar beta angle, which is
+ closely related to the local solar time, had to be maintained
+ at values less than -55 degrees to ensure that GRS radiative cooler
+ was not exposed to the Sun. The Extended Mission orbit had several
+ notable features. In late 2005, the LTST drifted to earlier
+ values, which was favorable for THEMIS daytime infrared imaging.
+ This period also coincided with a minimum in the Earth-Mars range,
+ allowing high downlink data rates, also favorable for THEMIS.
+ A similar favorable geometry occurs in late 2007.
+
+
+
+ Odyssey
+
+
+
+
diff --git a/data/pds4/context-pds4/investigation/mission.cassini-huygens_1.4.xml b/data/pds4/context-pds4/investigation/mission.cassini-huygens_1.4.xml
new file mode 100644
index 00000000..e898c80f
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/mission.cassini-huygens_1.4.xml
@@ -0,0 +1,576 @@
+
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.cassini-huygens
+ 1.4
+ Cassini-Huygens
+ 1.21.0.0
+ Product_Context
+
+
+
+ 2024-06-04
+ 1.4
+ Added terse description and alias.
+
+
+
+ 2021-02-24
+ 1.3
+
+ Changed HP's LID from urn:nasa:pds: to urn:esa:psa:
+
+
+
+
+ 2021-02-15
+ 1.2
+
+ Updated for Cassini migration to PDS4 by PDS Radio Science Advisor.
+ Corrected case and tense of several values. Reformatted for easier reading.
+ Added radio science information.
+
+
+
+
+ 2019-01-03
+ 1.1
+
+ Per "Guide to PDS4 Context Products" v1.3,
+ - changed all lidvid_reference to lid_reference
+ - changed target LIDs to new formation rule
+
+
+
+
+ 2016-10-01
+ 1.0
+
+ Extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.co
+ investigation_to_instrument_host
+
+
+
+ urn:nasa:pds:context:facility:observatory.dsn
+ investigation_to_facility
+
+
+
+ urn:esa:psa:context:instrument_host:spacecraft.hp
+ investigation_to_instrument_host
+
+
+
+ urn:nasa:pds:context:target:asteroid.2685_masursky
+ instrument_host_to_target
+
+
+
+ urn:nasa:pds:context:target:astrophysical.gravitational_waves
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:dust.dust
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:planet.earth
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:planet.jupiter
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:planet.saturn
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:planet.venus
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:planetary_system.solar_system
+ investigation_to_target
+
+
+
+
+
+
+
+
+ urn:nasa:pds:context:target:plasma_stream.solar_wind
+ investigation_to_target
+
+
+
+
+
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.aegaeon
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.albiorix
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.anthe
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.atlas
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.bebhionn
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.bergelmir
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.bestla
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.jupiter.callisto
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.calypso
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.daphnis
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.dione
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.enceladus
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.epimetheus
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.erriapus
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.erriapus
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.jupiter.europa
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.fornjot
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.jupiter.ganymede
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.greip
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.hati
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.helene
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.hyperion
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.hyrrokkin
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.iapetus
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.ijiraq
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.jupiter.io
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.janus
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.kari
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.kiviuq
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.loge
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.methone
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.mimas
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.earth.moon
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.mundilfari
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.narvi
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.paaliaq
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.pallene
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.pan
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.pandora
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.phoebe
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.polydeuces
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.prometheus
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.rhea
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.siarnaq
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.skathi
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.skathi
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.skoll
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.surtur
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.suttungr
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.tarqeq
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.tarvos
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.telesto
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.tethys
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.thrymr
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.titan
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:satellite.saturn.ymir
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:star.wasp-3
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:target:star.alf_vir
+ investigation_to_target
+
+
+
+
+
+
+
+
+ urn:nasa:pds:context:target:star.sun
+ investigation_to_target
+
+
+
+
+ Cassini Mission Plan, Revision N (PD 699-100), JPL Document D-5564, Jet
+ Propulsion Laboratory, Pasadena, CA, 2002.
+
+ reference.JPL D-5564
+
+
+
+
+ https://science.nasa.gov/mission/cassini/
+
+ Cassini-Huygens NASA Website
+
+
+
+
+
+ Cassini-Huygens
+ Mission
+ 1997-10-15
+ 2017-09-15
+
+
+ Cruise Objectives:
+
+ While en route to Saturn, Cassini performed three sets of Gravitational
+ Wave Experiments (GWEs), each scheduled near opposition and each lasting
+ approximately 40 days. During these observations, Cassini acted as a point
+ mass which would be perturbed by propagating gravitational waves resulting
+ from sudden destruction (or creation) of large masses in the general
+ direction of the spacecraft-to-Earth line.
+
+ While en route to Saturn, Cassini was also used in two Solar Conjunction
+ Experiments (SCEs), each lasting approximately 30 days. The objectives of
+ these observations were to test general relativity and to improve our
+ understanding of the solar corona.
+
+ The general scientific objectives of the Cassini mission at Saturn were to
+ investigate the physical, chemical, and temporal characteristics of Titan
+ and of Saturn, its atmosphere, rings, icy satellites, and magnetosphere.
+ These are listed more specifically below:
+
+ Saturn (Planet) Objectives:
+
+ a) Determine temperature field, cloud properties, and composition of the
+ atmosphere of Saturn.
+
+ b) Measure the global wind field, including wave and eddy components;
+ observe synoptic cloud features and processes.
+
+ c) Infer the internal structure and rotation of the deep atmosphere.
+
+ d) Study the diurnal variations and magnetic control of the ionosphere of
+ Saturn.
+
+ e) Provide observational constraints (gas composition, isotope ratios, and
+ heat flux, etc.) on scenarios for the formation and the evolution of Saturn.
+
+ f) Investigate the sources and the morphology of Saturn lightning, Saturn
+ Electrostatic Discharges (SED), and whistlers.
+
+ Titan Objectives:
+
+ a) Determine abundance of atmospheric constituents (including any noble
+ gases), establish isotope ratios for abundant elements, constrain scenarios
+ of formation and evolution of Titan and its atmosphere.
+
+ b) Observe vertical and horizontal distributions of trace gases, search for
+ more complex organic molecules, investigate energy sources for atmospheric
+ chemistry, and model the photochemistry of the stratosphere, study
+ formation and composition of aerosols.
+
+ c) Measure winds and global temperatures; investigate cloud physics,
+ general circulation, and seasonal effects in Titan's atmosphere; search for
+ lightning discharges.
+
+ d) Determine the physical state, topography, and composition of the
+ surface; infer the internal structure of the satellite.
+
+ e) Investigate the upper atmosphere, its ionization, and its role as a
+ source of neutral and ionized material for magnetosphere of Saturn.
+
+ Ring Objectives:
+
+ a) Study configuration of the rings and dynamical processes (gravitational,
+ viscous, erosional, and electromagnetic) responsible for ring structure.
+
+ b) Map composition and size distribution of ring material.
+
+ c) Investigate interrelation of rings and satellites, including embedded
+ satellites.
+
+ d) Determine dust and meteoroid distribution in the vicinity of the rings.
+
+ e) Study interactions between the rings and Saturn's magnetosphere,
+ ionosphere, and atmosphere.
+
+ Icy Satellite Objectives:
+
+ a) Determine the general characteristics and geological histories of the
+ satellites.
+
+ b) Define the mechanisms of crustal and surface modifications, both
+ external and internal.
+
+ c) Investigate the compositions and distributions of surface materials,
+ particularly dark, organic rich materials and low melting point condensed
+ volatiles.
+
+ d) Constrain models of the satellites' bulk compositions and internal
+ structures.
+
+ e) Investigate interactions with the magnetosphere and ring systems and
+ possible gas injections into the magnetosphere.
+
+ Magnetosphere Objectives:
+
+ a) Determine the configuration of the nearly axially symmetric magnetic
+ field and its relation to the modulation of Saturn Kilometric Radiation
+ (SKR).
+
+ b) Determine current systems, composition, sources, and sinks of
+ magnetosphere charged particles.
+
+ c) Investigate wave-particle interactions and dynamics of the dayside
+ magnetosphere and the magnetotail of Saturn and their interactions with the
+ solar wind, the satellites, and the rings.
+
+ d) Study the effect of Titan's interaction with the solar wind and
+ magnetospheric plasma.
+
+ e) Investigate interactions of Titan's atmosphere and exosphere with the
+ surrounding plasma.
+
+
+
+
+ Cassini
+
+
+
+
diff --git a/data/pds4/context-pds4/investigation/mission.chandrayaan-1_1.2.xml b/data/pds4/context-pds4/investigation/mission.chandrayaan-1_1.2.xml
new file mode 100644
index 00000000..2fd62676
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/mission.chandrayaan-1_1.2.xml
@@ -0,0 +1,108 @@
+
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.chandrayaan-1
+ 1.2
+ Chandrayaan-1
+ 1.21.0.0
+ Product_Context
+
+
+ 2024-06-13
+ 1.2
+ Added terse description, acronym, alias. Added instruments. Added NASA website.
+
+
+ 2019-01-03
+ 1.1
+
+ Per "Guide toPDS4 Context Products" v1.3,
+ - changed all lidvid_reference to lid_reference
+ - changed target LIDs to new formation rule
+
+
+
+ 2016-10-01
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.ch1-orb
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:target:satellite.earth.moon
+ investigation_to_target
+
+
+ urn:nasa:pds:context:instrument:m3.ch1-orb
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mrffr.ch1-orb
+ investigation_to_instrument
+
+
+
+ Bhandari, N., Chandrayaan-1: Science Goals, Journal of Earth System Sciences,
+ 114(6), 701-709, 2005.
+
+ reference.BHANDARI2005
+
+
+
+ Goswami, J.N., and M. Annadurai, Chandrayaan-1 mission to the Moon, Acta
+ Astronautica (ISSN 0094-5765), Vol. 63, Iss. 11-12, 1215-1220, 2008,
+ doi:10.1016/j.actaastro.2008.05.013.
+
+ Chandrayann-1 Mission to the moon
+
+
+
+ https://science.nasa.gov/mission/chandrayaan-1/
+
+ Chandrayaan-1 Moon Impact Probe NASA website.
+
+
+
+
+ Chandrayaan-1
+ Mission
+ 2008-10-22
+ 2009-08-28
+
+ Chandrayaan-1, the first Indian mission to Moon, was designed to carry out
+ high resolution remote sensing studies of the Moon to further our
+ understanding of its origin and evolution. At 00:52 UT on 22 October
+ 2008, the Indian Space Research Organization (ISRO) launched Chandrayaan-1
+ on-board an upgraded Polar Satellite Launch Vehicle (PSLV-C11) from the
+ Satish Dhawan Space Center (SDSC) in Sriharikota located along the
+ southeast coast of India. The PSLV-C11 injected the orbiter spacecraft
+ into an eleven-hour elliptical transfer orbit around the Earth on 23
+ October 2008.
+
+
+
+ CH1
+ 1
+
+
+
+
+ CH1-ORB
+ 1
+
+
+
+
diff --git a/data/pds4/context-pds4/investigation/mission.clipper_1.1.xml b/data/pds4/context-pds4/investigation/mission.clipper_1.1.xml
new file mode 100644
index 00000000..6db73931
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/mission.clipper_1.1.xml
@@ -0,0 +1,142 @@
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.clipper
+ 1.1
+ Europa Clipper
+ 1.21.0.0
+ Product_Context
+
+
+ 2024-06-13
+ 1.1
+ Added terse description and alias. Fixed title. Added NASA website.
+
+
+ 2023-05-08
+ 1.0
+
+ Initial version.
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.clipper
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:instrument:clipper.ecm
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:clipper.eth
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:clipper.gnc
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:clipper.mas
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:clipper.mis
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:clipper.nac
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:clipper.pim
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:clipper.rea
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:clipper.rss
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:clipper.sud
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:clipper.uvs
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:clipper.wac
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:target:planet.jupiter
+ investigation_to_target
+
+
+ urn:nasa:pds:context:target:satellite.jupiter.callisto
+ investigation_to_target
+
+
+ urn:nasa:pds:context:target:satellite.jupiter.europa
+ investigation_to_target
+
+
+ urn:nasa:pds:context:target:satellite.jupiter.ganymede
+ investigation_to_target
+
+
+ 10.1038/34857
+
+ Carr M. H., Belton M. J., Chapman C. R., Davies M. E., Geissler P., Greenberg R., McEwen A. S., Tufts B. R., Greeley R., Sullivan R., Head J. W., Pappalardo R. T., Klaasen K. P., Johnson T. V., Kaufman J., Senske D., Moore J., Neukum G., Schubert G., Burns J. A., Thomas P., Veverka J. Evidence for a subsurface ocean on Europa. Nature 391, 363–365 (1998). doi: 10.1038/34857. PMID: 9450749.
+
+ Details evidence of a subsurface ocean on Europa based on data collected by the Voyager and Galileo missions.
+
+
+ 10.1029/1998JE000628
+
+ Pappalardo R. T., Belton M. J. S., Breneman H. H., Carr M. H., Chapman C. R., Collins G. C., Denk T., Fagents S., Geissler P. E., Giese B., Greeley R., Greenberg R., Head J. W., Helfenstein P., Hoppa G., Kadel S. D., Klaasen K. P., Klemaszewski J. E., Magee K., McEwen A. S., Moore J. M., Moore W. B., Neukum G., Phillips C. B., Prockter L. M., Schubert G., Senske D. A., Sullivan R. J., Tufts B. R., Turtle E. P., Wagner R., Williams K. K., Does Europa have a subsurface ocean? Evaluation of the geological evidence. J. Geophys. Res. 104(E10), 24015–24055 (1999). doi: 10.1029/1998JE000628.
+
+ Continued investigation into whether Europa currently possesses a global subsurface ocean of liquid water.
+
+
+ 10.1038/s41467-020-15160-9
+
+ Howell, SM, Pappalardo, RT, NASA's Europa Clipper-a mission to a potentially habitable ocean world. Nat Commun 11, 1311 (2020). doi: 10.1038/s41467-020-15160-9. PMID: 32161262; PMCID: PMC7066167.
+
+ Describes the scientific significance of exploring Europa and how the Europa Clipper Mission will investigate the moon's habitability.
+
+
+ https://europa.nasa.gov/
+ Europa Clipper, NASA mission website.
+
+
+
+ Europa Clipper
+ Mission
+ 2024-10-01
+ 2034-09-30
+
+ NASA's Europa Clipper spacecraft will perform dozens of close flybys of Jupiter’s moon Europa, gathering detailed measurements to investigate whether the moon could have conditions suitable for life. Europa Clipper is not a life detection mission – its main science goal is to determine whether there are places below Europa’s surface that could support life.
+
+
+
+ clipper
+ 1
+
+
+
+
diff --git a/data/pds4/context-pds4/investigation/mission.contour_mission_1.1.xml b/data/pds4/context-pds4/investigation/mission.contour_mission_1.1.xml
new file mode 100644
index 00000000..b6cf58f2
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/mission.contour_mission_1.1.xml
@@ -0,0 +1,91 @@
+
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.contour_mission
+ 1.1
+ CONTOUR
+ 1.21.0.0
+ Product_Context
+
+
+ 2024-06-13
+ 1.1
+ Added targets and instruments. Added NASA website. Added terse description and alias. Fixed title.
+
+
+ 2016-10-01
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.con::1.0
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:target:comet.2p_encke
+ investigation_to_target
+
+
+ urn:nasa:pds:context:target:comet.6p_d_arrest
+ investigation_to_target
+
+
+ urn:nasa:pds:context:instrument:con.cfi
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:con.cida
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:con.crispimag
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:con.crispspec
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:con.ngims
+ investigation_to_instrument
+
+
+
+ https://science.nasa.gov/mission/contour/
+
+ CONTOUR mission, NASA website.
+
+
+
+
+ CONTOUR
+ Mission
+ 2002-07-05
+ 2002-08-15
+
+The Comet Nucleus Tour, or CONTOUR, mission launched from Cape Canaveral on
+July 3, 2002. Six weeks later, on August 15, contact with the spacecraft was
+lost after a planned maneuver that was intended to propel it out of Earth
+orbit and into its comet-chasing solar orbit. Evidence suggests the
+spacecraft split into several pieces, and so far all efforts to make contact
+with CONTOUR have failed.
+
+
+
+ Comet Nucleus Tour
+ 1
+
+
+
+
diff --git a/data/pds4/context-pds4/investigation/mission.juno_2.2.xml b/data/pds4/context-pds4/investigation/mission.juno_2.2.xml
new file mode 100644
index 00000000..d87946ed
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/mission.juno_2.2.xml
@@ -0,0 +1,169 @@
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.juno
+ 2.2
+ Juno
+ 1.21.0.0
+ Product_Context
+
+
+ 2024-04-28
+ 2.2
+
+ Added instruments. Replaced deprecated instruments. Added terse descriptions. Fixed title.
+
+
+
+ 2019-01-03
+ 2.1
+
+ Per "Guide toPDS4 Context Products" v1.3,
+ - changed all lidvid_reference to lid_reference
+ - changed target LIDs to new formation rule
+
+
+
+ 2018-07-10
+ 2.0
+
+ added instrument LIDs
+
+
+
+ 2016-10-01
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.jno
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:instrument:fgm.jno
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:jno.rss
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mwr.jno
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:uvs.jno
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:waves.jno
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:jade.jno
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:jedi.jno
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:junocam.jno
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:jiram.jno
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:rmi.jno
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:target:dust.dust
+ investigation_to_target
+
+
+ urn:nasa:pds:context:target:planet.earth
+ investigation_to_target
+
+
+ urn:nasa:pds:context:target:planet.jupiter
+ investigation_to_target
+
+
+ urn:nasa:pds:context:target:planetary_system.solar_system
+ investigation_to_target
+
+
+
+
+
+
+ urn:nasa:pds:context:target:plasma_stream.solar_wind
+ investigation_to_target
+
+
+
+
+
+
+ urn:nasa:pds:context:target:satellite.jupiter.callisto
+ investigation_to_target
+
+
+ urn:nasa:pds:context:target:satellite.jupiter.europa
+ investigation_to_target
+
+
+ urn:nasa:pds:context:target:satellite.jupiter.ganymede
+ investigation_to_target
+
+
+ urn:nasa:pds:context:target:satellite.jupiter.io
+ investigation_to_target
+
+
+ urn:nasa:pds:context:target:satellite.earth.moon
+ investigation_to_target
+
+
+
+ Stephens, S. K., Juno Project Mission Plan, Rev. D, JPL D-35556, 15 August 2013.
+
+ Juno Mission Plan
+
+
+ https://science.nasa.gov/mission/juno/
+ Juno Mission, NASA website.
+
+
+
+
+ Juno
+ Mission
+ 2011-08-05
+
+
+ On August 5, 2011, NASA’s Juno spacecraft embarked on a 5-year journey to Jupiter, our solar system's largest planet. Juno arrived at Jupiter on July 4, 2016, after a five-year, 1,740-million-mile journey, and settled into a 53-day polar orbit stretching from just above Jupiter’s cloud tops to the outer reaches of the Jovian magnetosphere.
+ During the prime mission’s 35 orbits of Jupiter, Juno collected more than three terabits of science data and provided dazzling views of Jupiter and its satellites, all processed by citizen scientists with NASA’s first-ever camera dedicated to public outreach. Juno’s many discoveries have changed our view of Jupiter’s atmosphere and interior, revealing an atmospheric weather layer that extends far beyond its water clouds and a deep interior with a dilute heavy element core. Near the end of the prime mission, as the spacecraft’s orbit evolved, flybys of the moon Ganymede initiated Juno’s transition into a full Jovian system explorer.
+ Now in its extended mission, Juno will continue its investigation of the solar system’s largest planet through September 2025, or until the spacecraft’s end of life. This extension tasks Juno with becoming an explorer of the full Jovian system – Jupiter and its rings and moons – with additional rendezvous planned for two of Jupiter’s most intriguing moons: Europa and Io.
+
+
+
diff --git a/data/pds4/context-pds4/investigation/mission.mariner69_1.2.xml b/data/pds4/context-pds4/investigation/mission.mariner69_1.2.xml
new file mode 100644
index 00000000..1b310d98
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/mission.mariner69_1.2.xml
@@ -0,0 +1,123 @@
+
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.mariner69
+ 1.2
+ Mariner 69
+ 1.21.0.0
+ Product_Context
+
+
+
+ 2024-06-24
+ 1.2
+
+ Added instruments. Added terse description and aliases. Fixed titles.
+
+
+
+ 2018-06-21
+ 1.1
+
+ replaced all lidvid_reference with lid_reference
+
+
+
+ 2016-10-01
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.mr6
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.mr7
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:target:planet.mars
+ investigation_to_target
+
+
+ urn:nasa:pds:context:instrument:irs.mr6
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:nac.mr6
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:uvs.mr6
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:wac.mr6
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:irs.mr7
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:nac.mr7
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:uvs.mr7
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:wac.mr7
+ investigation_to_instrument
+
+
+
+ Mariner Mars 1969 - A preliminary Report. NASA SP-225, 1969.
+
+ Mariner 60 Preliminary Report
+
+
+
+ Preliminary reports for the Mariner 6 and 7 missions.
+ Volumes 165-166, 1969.
+
+ Preliminary Reports for Mariner 6 and 7
+
+
+
+
+ Mariner 69
+ Mission
+ 1969-02-25
+ 1969-08-05
+
+ The Mariner 69 mission involved two uncrewed NASA spacecraft, Mariner 6 and Mariner 7, which completed the first dual mission to Mars in 1969 under the Mariner program. Mariner 6 launched from Launch Complex 36B and Mariner 7 from Launch Complex 36A at Cape Canaveral Air Force Station. Both spacecraft flew over Mars' equator and south polar regions, analyzing the atmosphere and surface using remote sensors. They recorded and relayed hundreds of images back to Earth. The mission aimed to study Mars' surface and atmosphere during close flybys, laying the groundwork for future investigations, particularly the search for extraterrestrial life. Additionally, it aimed to develop and demonstrate technologies needed for future Mars missions. Mariner 6 also provided valuable experience and data to aid the Mariner 7 encounter five days later.
+
+
+
+ Mariner 6 and 7
+ 1
+
+
+ Mariner Mars 69A
+ 2
+
+
+ Mariner Mars 69B
+ 3
+
+
+
+
diff --git a/data/pds4/context-pds4/investigation/mission.mariner71_1.1.xml b/data/pds4/context-pds4/investigation/mission.mariner71_1.1.xml
new file mode 100644
index 00000000..23383fcb
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/mission.mariner71_1.1.xml
@@ -0,0 +1,87 @@
+
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.mariner71
+ 1.1
+ Mariner 71
+ 1.21.0.0
+ Product_Context
+
+
+
+ 2024-06-24
+ 1.1
+
+ Added instruments. Added terse description, alias. Fixed titles. Added NASA mission website.
+
+
+ 2016-10-01
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.mr9::1.0
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:target:planet.mars::1.0
+ investigation_to_target
+
+
+ urn:nasa:pds:context:instrument:iris.mr9
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:iss.mr9
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:rss.mr9
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:uvs.mr9
+ investigation_to_instrument
+
+
+
+ Mariner Mars 1971 Project Final Report, Science Experiment Reports, JPL
+ Technical Report 32-1550, Vol. V, Aug. 20, 1973.
+
+ Mariner Mars 1971 Project Final Report
+
+
+
+ https://science.nasa.gov/mission/mariner-9/
+
+ NASA Mission Website, Mariner 9
+
+
+
+
+ Mariner 71
+ Mission
+ 1968-06
+ 1973-06
+
+ On November 14, 1971, Mariner 9 became the first spacecraft to orbit another planet, after the failure of Mariner 8. It carried six experiments, including television, ultraviolet spectrometer, infrared spectroscopy, infrared radiometry, S-band occultation, and celestial mechanics, with some using specially developed instruments on its scan platform. Initially planned as a dual mission, Mariner 9 adapted to a single-spacecraft mission, achieving all objectives with a 65-degree inclination and a 12-hour orbit period. Mariner 9 mapped 85% of the Martian surface, transmitting over 7,000 images, including detailed views of the solar system's largest volcano, a massive canyon system, and the Martian moons Phobos and Deimos.
+
+
+
+ Mariner 9
+ 1
+
+
+
+
diff --git a/data/pds4/context-pds4/investigation/mission.mars2020_1.1.xml b/data/pds4/context-pds4/investigation/mission.mars2020_1.1.xml
new file mode 100644
index 00000000..8305ff0d
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/mission.mars2020_1.1.xml
@@ -0,0 +1,124 @@
+
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.mars2020
+ 1.1
+ Mars 2020 Perseverance Rover
+ 1.21.0.0
+ Product_Context
+
+
+
+ 2024-05-06
+ 1.1
+ Added terse description, acronym, alias. Added instruments. Added NASA website.
+
+
+ 2021-02-12
+ 1.0
+ First version
+
+
+
+
+
+ urn:nasa:pds:context:target:planet.mars
+ investigation_to_target
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.mars2020
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:instrument:mars2020.ecam
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mars2020.edlcam
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mars2020.helicam
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mars2020.lcam
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mars2020.mastcamz
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mars2020.meda
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mars2020.moxie
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mars2020.pixl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mars2020.rimfax
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mars2020.sherloc
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mars2020.supercam
+ investigation_to_instrument
+
+
+ 10.1007/s11214-020-00762-y
+
+ Farley, K.A., Williford, K.H., Stack, K.M. et al. Mars 2020 Mission Overview.
+ Space Sci Rev 216, 142 (2020)
+
+ Mars 2020 Mission Overview
+
+
+ https://science.nasa.gov/mission/mars-2020-perseverance/
+ NASA Mission Website, Mars 2020: Perseverance Rover
+
+
+
+ Mars 2020
+ Mission
+ 2020-07-30
+
+
+ The Mars 2020 Perseverance Rover searches for signs of ancient microbial life, to advance NASA's quest to explore the past habitability of Mars. The rover is collecting core samples of Martian rock and soil (broken rock and soil), for potential pickup by a future mission that would bring them to Earth for detailed study.
+
+
+
+ Perseverance
+ 1
+
+
+
+
+ M2020
+ 1
+
+
+
+
diff --git a/data/pds4/context-pds4/investigation/mission.mars_exploration_rover_1.1.xml b/data/pds4/context-pds4/investigation/mission.mars_exploration_rover_1.1.xml
new file mode 100644
index 00000000..9fdbfdf9
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/mission.mars_exploration_rover_1.1.xml
@@ -0,0 +1,346 @@
+
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.mars_exploration_rover
+ 1.1
+ Mars Exploration Rover
+ 1.22.0.0
+ Product_Context
+
+
+ 2024-03-26
+ 1.1
+
+ Added instruments. Added terse description, acronym, alias. Added NASA website. Fixed titles.
+
+
+
+ 2016-10-01
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.mer1::1.0
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.mer2::1.0
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:target:planet.mars::1.0
+ investigation_to_target
+
+
+
+ urn:nasa:pds:context:instrument:apxs.mer1
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:descam.mer1
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:hazcam.mer1
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:imu.mer1
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mb.mer1
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mini-tes.mer1
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mi.mer1
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:navcam.mer1
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:pancam.mer1
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:rat.mer1
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:rss.mer1
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:apxs.mer2
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:descam.mer2
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:hazcam.mer2
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:imu.mer2
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mb.mer2
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mini-tes.mer2
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mi.mer2
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:navcam.mer2
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:pancam.mer2
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:rat.mer2
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:rss.mer2
+ investigation_to_instrument
+
+
+ 10.1029/2008JE003188
+
+ Arvidson, R.E., Introduction to special section on results from the Mars
+ Exploration Rover Spirit and Opportunity missions, J. Geophys. Res., 113,
+ E06S01, doi:10.1029/2008JE003188, 2008.
+
+ Introduction to special section on results from the Mars
+ Exploration Rover Spirit and Opportunity missions
+
+
+ 10.1029/2007JE002976
+
+ Bell, J.F., M.S. Rice, J.R. Johnson, and T.M. Hare, Surface albedo observations
+ at Gusev Crater and Meridiani Planum, Mars, J. Geophys. Res., 113, E06S18,
+ doi:10.1029/2007JE002976, 2008.
+
+ Surface albedo observations at Gusev Crater and Meridiani Planum, Mars
+
+
+ 10.1029/2007JE002953
+
+ Cabrol, N.A., et al., Soil sedimentology at Gusev Crater from Columbia Memorial
+ Station to Winter Haven, J. Geophys. Res., 113, E06S05,
+ doi:10.1029/2007JE002953, 2008.
+
+ Soil sedimentology at Gusev Crater from Columbia Memorial
+ Station to Winter Haven
+
+
+ 10.1029/2007JE002959
+
+ Campbell, J.L., R. Gellert, M. Lee, C.L. Mallett, J.A. Maxwell, and
+ J.M.O'Meara, Quantitative in situ determination of hydration of bright
+ high-sulfate Martian soils, J. Geophys. Res., 113, E06S11,
+ doi:10.1029/2007JE002959, 2008.
+
+ Quantitative in situ determination of hydration of bright
+ high-sulfate Martian soils
+
+
+ 10.1029/2002JE002038
+
+ Crisp, J.A., M. Adler, J.R. Matijevic, S.W. Squyres, R.E. Arvidson, and D.M.
+ Kass, Mars Exploration Rover mission, J. Geophys. Res., 108(E12), 8061,
+ doi:10.1029/2002JE002038, 2003.
+
+ Mars Exploration Rover mission
+
+
+ 10.1029/2007JE003022
+
+ Fleischer, I., G. Klingelhoefer, C. Schroeder, R. V. Morris, M. Hahn, D.
+ Rodionov, R. Gellert, and P. A. de Souza, Depth selective Moessbauer
+ spectroscopy: Analysis and simulation of 6.4 keV and 14.4 keV spectra obtained
+ from rocks at Gusev Crater, Mars, and layered laboratory samples, J. Geophys.
+ Res., 113, E06S21, doi:10.1029/2007JE003022, 2008.
+
+ Depth selective Moessbauer spectroscopy
+
+
+ 10.1029/2003JE002072
+
+ Garvin, J.B., C. Weitz, O. Figueroa, and J. Crisp, Introduction to the special
+ section: Mars Exploration Rover mission and landing sites, J. Geophys. Res.,
+ 108(E12), 8060, doi:10.1029/2003JE002072, 2003.
+
+ Mars Exploration Rover mission and landing sites
+
+
+ 10.1029/2003JE002074
+
+ Golombek, M.P., et al., Selection of the Mars Exploration Rover landing sites,
+ J. Geophys. Res., 108(E12), 8072, doi:10.1029/2003JE002074, 2003.
+
+ Selection of the Mars Exploration Rover landing sites
+
+
+ 10.1029/2007JE002971
+
+ Greeley, R., et al., Columbia Hills, Mars: Aeolian features seen from the
+ ground and orbit, J. Geophys. Res., 113, E06S06, doi:10.1029/2007JE002971, 2008.
+
+ Mars: Aeolian features seen from the ground and orbit
+
+
+ 10.1029/2007JE002949
+
+ Knoll, A.H., et al., Veneers, rinds, and fracture fills: Relatively late
+ alteration of sedimentary rocks at Meridiani Planum, Mars, J. Geophys. Res.,
+ 113, E06S16, doi:10.1029/2007JE002949, 2008.
+
+ Relatively late alteration of sedimentary rocks at Meridiani Planum, Mars
+
+
+ 10.1029/2007JE003041
+
+ McCoy, T.J., et al., Structure, stratigraphy, and origin of Husband Hill,
+ Columbia Hills, Gusev Crater, Mars, J. Geophys. Res., 113, E06S03,
+ doi:10.1029/2007JE003041, 2008.
+
+ Structure, stratigraphy, and origin of Husband Hill, Columbia Hills, Gusev Crater, Mars
+
+
+ 10.1029/2007JE002970
+
+ McSween, H.Y., et al., Mineralogy of volcanic rocks in Gusev Crater, Mars:
+ Reconciling Moessbauer, Alpha Particle X-Ray Spectrometer, and Miniature
+ Thermal Emission Spectrometer spectra, J. Geophys. Res., 113, E06S04,
+ doi:10.1029/2007JE002970, 2008.
+
+ Mineralogy of volcanic rocks in Gusev Crater
+
+
+ 10.1029/2007JE002995
+
+ Rogers, A.D., and O. Aharonson, Mineralogical composition of sands in Meridiani
+ Planum determined from Mars Exploration Rover data and comparison to orbital
+ measurements, J. Geophys. Res., 113, E06S14, doi:10.1029/2007JE002995, 2008.
+
+ Mineralogical composition of sands in Meridiani Planum determined from Mars Exploration Rover data
+
+
+ 10.1029/2007JE003027
+
+ Schmidt, M.E., et al., Hydrothermal origin of halogens at Home Plate, Gusev
+ Crater, J. Geophys. Res., 113, E06S12, doi:10.1029/2007JE003027, 2008.
+
+ Hydrothermal origin of halogens at Home Plate
+
+
+ 10.1029/2007JE002990
+
+ Schroeder, C., et al., Meteorites on Mars observed with the Mars Exploration
+ Rovers, J. Geophys. Res., 113, E06S22, doi:10.1029/2007JE002990, 2008.
+
+ Meteorites on Mars observed with the Mars Exploration Rovers
+
+
+
+ Seidelmann, P.K., V.K. Abalakin, M. Bursa, M.E. Davies, C. de Bergh, J.H.
+ Lieske, J. Oberst, J.L. Simon, E.M. Standish, P. Stooke, and P.C. Thomas,
+ Report of the IAU/IAG working group on cartographic coordinates and rotational
+ elements of the planets and satellites: 2000, Celestial Mechanics and Dynamical
+ Astronomy, 82, 83-111, 2002.
+
+
+
+ 10.1029/2007JE003003
+
+ Soderblom, J.M., J.F. Bell III, J.R. Johnson, J. Joseph, and M.J. Wolff (2008)
+ Mars Exploration Rover Navigation Camera (Navcam) in-flight calibration, J.
+ Geophys. Res., 113, E06S19, doi:10.1029/2007JE003003.
+
+ Mars Exploration Rover Navigation Camera (Navcam) in-flight calibration
+
+
+ 10.1029/2008JE003101
+
+ Sullivan, R., et al., Wind-driven particle mobility on Mars: Insights from Mars
+ Exploration Rover observations at 'El Dorado' and surroundings at Gusev Crater, J. Geophys. Res., 113, E06S07, doi:10.1029/2008JE003101, 2008.
+
+ Wind-driven particle mobility on Mars
+
+
+ 10.1029/2007JE002978
+
+ Yen, A.S., et al., Hydrothermal processes at Gusev Crater: An evaluation of
+ Paso Robles class soils, J. Geophys. Res., 113, E06S10,
+ doi:10.1029/2007JE002978, 2008.
+
+ Hydrothermal processes at Gusev Crater
+
+
+ https://science.nasa.gov/mission/mars-exploration-rovers-spirit-and-opportunity/
+ NASA Mission Website, Mars Exploration Rovers: Spirit and Opportunity
+
+
+
+
+ Mars Exploration Rover
+ Mission
+ 2000-05-08
+
+
+ NASA’s twin rovers, Spirit and Opportunity, landed on Mars on Jan. 3 and Jan. 24, 2004 PST (Jan. 4 and Jan. 25 UTC). The rovers were planned as 90-day missions to search for geological clues regarding environmental conditions on early Mars, and assess whether those environments were conducive to life. Spirit lasted 20 times longer than its original design, concluding its mission on March 22, 2010. Opportunity worked for nearly 15 years on Mars and broke the driving record for putting the most miles on its odometer, ending its mission on Feb. 13, 2019.
+
+
+
+ Opportunity
+ 1
+
+
+ Spirit
+ 1
+
+
+ Mer
+ 2
+
+
+
+
+ Mer1
+ 1
+
+
+ Mer2
+ 1
+
+
+
+
diff --git a/data/pds4/context-pds4/investigation/mission.mars_express_1.1.xml b/data/pds4/context-pds4/investigation/mission.mars_express_1.1.xml
new file mode 100644
index 00000000..bbd70807
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/mission.mars_express_1.1.xml
@@ -0,0 +1,190 @@
+
+
+
+
+
+ urn:esa:psa:context:investigation:mission.mars_express
+ 1.1
+ Mars Express
+ 1.21.0.0
+ Product_Context
+
+
+
+ 2024-03-04
+ 1.1
+
+ Added instruments. Added terse description, acronym, alias. Added NASA website.
+
+
+ 2021-02-24
+ 1.0
+
+ Changed LIDs from urn:nasa:pds: to urn:esa:psa:
+ And per "Guide toPDS4 Context Products" v1.7,
+ changed all lidvid_reference to lid_reference
+
+
+
+
+
+
+
+ urn:esa:psa:context:instrument_host:spacecraft.mex
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:target:planet.mars
+ investigation_to_target
+
+
+ urn:nasa:pds:context:target:plasma_stream.solar_wind
+ investigation_to_target
+
+
+ urn:nasa:pds:context:instrument:aspera-3.mex
+ investigation_to_instrument
+
+
+ urn:esa:psa:context:instrument:mex.hrsc
+ investigation_to_instrument
+
+
+ urn:esa:psa:context:instrument:mex.marsis
+ investigation_to_instrument
+
+
+ urn:esa:psa:context:instrument:mex.mrs
+ investigation_to_instrument
+
+
+ urn:esa:psa:context:instrument:mex.omega
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:pfs.mex
+ investigation_to_instrument
+
+
+ urn:esa:psa:context:instrument:mex.spicam
+ investigation_to_instrument
+
+
+
+ Bibring, J-P, et. al., OMEGA: Observatoire pour la Mineralogie, l'Eau, les
+ Glaces et l'Activite, ESA SP-1240, September 2004
+
+ Observatoire pour la Mineralogie
+
+
+
+ Deep Space Network / Flight Project Interface Design Book, Document 810-5, Jet
+ Propulsion Laboratory, Pasadena, CA.
+
+ Flight Project Interface Design Book
+
+
+
+ Formisano, V., et. al., The Planetary Fourier Spectrometer(PFS) for Mars
+ Express, ESA SP-1240, September 2004
+
+ he Planetary Fourier Spectrometer(PFS) for Mars Express
+
+
+
+ MEX-ESC-PL-5500, 'Mars Express Mission Implementation Plan', Issue 1.0,
+ September 1999
+
+ Mars Express Mission Implementation Plan
+
+
+
+ MEX-ESC-RP-5500, 'Mars Express Consolidated Report on Mission Analysis
+ (CREMA)', M. Hechler, Arturo Yanez, Issue 3.1, 6 May 2003.
+
+ Mars Express Consolidated Report on Mission Analysis
+
+
+
+ MEX-EST-PL-13128, 'Mars Express, Master Science Plan', ESA Project
+ Documentation, Patrick Martin, Version 1.5, July 2004
+
+ Mars Express, Master Science Plan
+
+
+
+ Mars Express, Spacecraft User Manual, Issue 4, Revision 0, 15 May 2003, Volume
+ 1: Mission and Spacecraft Design
+
+ Mars Express, Spacecraft User Manual
+
+
+
+ MEX-MMT-RP-0221, 'Mars Express Mission Plan', Issue 4.0, July 2000.
+
+ Mars Express Mission Plan
+
+
+
+ Neukum, G. and Jaumann, R., HRSC: the High Resolution Stereo Camera of Mars
+ Express, ESA SP-1240, September 2004
+
+ High Resolution Stereo Camera of Mars Express
+
+
+
+ Paetzold, M., F.M. Neubauer, L. Carone, A. Hagermann, C. Stanzel, B. Haeusler,
+ S. Remus, J. Selle, D. Hagl, D.P. Hinson, R.A. Simpson, G.L. Tyler, S.W. Asmar,
+ W.I. Axford, T. Hagfors, J.-P. Barriot, J.-C. Cerisier, T. Imamura, K.-I.
+ Oyama, P. Janle, G. Kirchengast, and V. Dehant, MaRS: Mars Express Radio
+ Science, in Mars Express: The Scientific Payload, European Space Agency
+ SP-1240, 141-163, August 2004.
+
+ Mars Express: The Scientific Payload
+
+
+
+ Picardi, G. et. al., MARSIS: Mars Advanced Radar for Subsurface and Ionosphere
+ Sounding, ESA-SP-1240, September 2004
+
+ MARSIS: Mars Advanced Radar for Subsurface and Ionosphere Sounding
+
+
+
+ Pullan, D., et. al., Beagle 2: the Exobiological Lander of Mars Express, ESA
+ SP-1240, September 2004
+
+ The Exobiological Lander of Mars Express
+
+
+ https://science.nasa.gov/mission/mars-express/
+ NASA Mission Website, Mars Express
+
+
+
+
+ Mars Express
+ Mission
+ 1997-10-31
+
+
+ In partnership with their European colleagues, U.S. scientists are participating in the scientific instrument teams of the Mars Express mission. NASA's involvement with the mission includes joint development of a radar instrument called the Mars Advanced Radar for Subsurface and Ionospheric Sounding (MARSIS) with the Italian Space Agency.
+ The specific science objectives for MARSIS are to detect, map, and characterize subsurface material discontinuities in the upper crust of Mars, including liquid water-bearing zones, icy layers, and other geologic units and structures. As well as characterize and map the elevation, roughness, and electromagnetic properties of the surface. And probe the ionosphere of Mars to characterize the interaction of the atmosphere and the solar wind.
+ To date, MARSIS has already provided information about features beneath the Martian surface, including buried impact craters, layered deposits, and hints of deep underground water ice. NASA's involvement also includes coordination of radio relay systems to make sure that different spacecraft operate together; a hardware contribution to the energetic neutral atoms analyzer instrument; and backup tracking support from NASA's Deep Space Network during critical mission phases.
+
+
+
+ Express
+ 1
+
+
+
+
+ MEX
+ 1
+
+
+
+
\ No newline at end of file
diff --git a/data/pds4/context-pds4/investigation/mission.mars_global_surveyor_1.2.xml b/data/pds4/context-pds4/investigation/mission.mars_global_surveyor_1.2.xml
new file mode 100644
index 00000000..e1f89bc6
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/mission.mars_global_surveyor_1.2.xml
@@ -0,0 +1,257 @@
+
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.mars_global_surveyor
+ 1.2
+ Mars Global Surveyor
+ 1.21.0.0
+ Product_Context
+
+
+ 2024-06-04
+ 1.2
+
+ Added instruments. Added terse description, acronym, alias. Added NASA website. Fixed titles.
+
+
+
+ 2019-01-03
+ 1.1
+
+ Per "Guide toPDS4 Context Products" v1.3,
+ - changed all lidvid_reference to lid_reference
+ - changed target LIDs to new formation rule
+
+
+
+ 2016-10-01
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.mgs
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:target:planet.mars
+ investigation_to_target
+
+
+ urn:nasa:pds:context:target:satellite.mars.phobos
+ investigation_to_target
+
+
+ urn:nasa:pds:context:target:sun.sun
+ investigation_to_target
+
+
+ urn:nasa:pds:context:instrument:mgs.accel
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mgs.er
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mgs.mag
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mgs.moc
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mgs.mola
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mgs.rss
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mgs.tes
+ investigation_to_instrument
+
+
+
+ Acuna, M.H., J.E.P. Connerney, P. Wasilewski, R.P. Lin, K.A. Anderson, C.W.
+ Carlson, J. McFadden, D.W. Curtis, H. Reme, A. Cros, J.L. Medale, J.A. Sauvaud,
+ C. d'Uston, S.J. Bauer, P. Cloutier, M. Mayhew, and N.F. Ness, Mars Observer
+ Magnetic Fields Investigation, J. Geophys. Res., 97, 7799-7814, 1992.
+
+ reference.ACUNAETAL1992
+
+
+
+ Acuna, M.H., J.E.P. Connerney, P. Wasilewski, R.P. Lin, D. Mitchell, K.A.
+ Anderson, C.W. Carlson, J. McFadden, H. Reme, C. Mazelle, D. Vignes, S.J.
+ Bauer, P. Cloutier, and N.F. Ness, The Magnetic Field of Mars: Summary of
+ Results from the Aerobraking and Mapping Orbits, Journal of Geophysical
+ Research, 106, E10, 23403-23417, 2001.
+
+ reference.ACUNAETAL2001
+
+
+
+ Albee, A., Introduction to the special section: the Mars Global Surveyor
+ mission, J. Geophys. Res., 106, E10, 23289, 2001.
+
+ reference.ALBEE2001
+
+
+
+ Albee, A.L., R.E. Arvidson, and F.D. Palluconi, Mars Observer Mission, J.
+ Geophys. Res., 97, 7665-7680, 1992.
+
+ reference.ALBEEETAL1992
+
+
+
+ Albee, A.L., F.D. Palluconi, and R.E. Arvidson, Mars Global Surveyor Mission:
+ Overview and Status, Science, 279, 1671-1672, 1998.
+
+ reference.ALBEEETAL1998
+
+
+
+ Albee, A.L., R.E. Arvidson, F.D. Palluconi, and T. Thorpe, Overview of the Mars
+ Global Surveyor mission, J. Geophys. Res., 106, E10, 23291-23316, 2001.
+
+ reference.ALBEEETAL2001
+
+
+
+ Bougher, S.W., and G.M. Keating, Mars Global Surveyor aerobraking: atmospheric
+ trends and model interpretation, Adv. Space Res., 23(11), 1887-1897, 1999.
+
+ reference.BOUGHER-KEATING1999
+
+
+
+ Christensen, P.R., D.L. Anderson, S.C. Chase, R.N. Clark, H.H. Kieffer, M.C.
+ Malin, J.C. Pearl, J. Carpenter, N. Bandiera, F.G. Brown, and S. Silverman,
+ Thermal emission spectrometer experiment: Mars Observer mission, J. Geophys.
+ Res., 97, (E5) 7719-7734, 1992.
+
+ reference.CHRISTENSENETAL1992
+
+
+
+ Christensen, P.R., J.L. Bandfield, V.E. Hamilton, S.W. Ruff, H.H. Kieffer, T.N.
+ Titus, M.C. Malin, R.V. Morris, M.D. Lane, R.L. Clark, B.M. Jakosky, M.T.
+ Mellon, J.C. Pearl, B.J. Conrath, M.D. Smith, R.T. Clancy, R.O. Kuzmin, T.
+ Roush, G.L. Mehall, N. Gorelick, K. Bender, K. Murray, S. Dason, E. Greene, S.
+ Silverman, and M. Greenfield, Mars Global Surveyor Thermal Emission
+ Spectrometer experiment: investigation description and surface science results,
+ J. Geophys. Res., 106, E10, 23823-23871, 2001.
+
+ reference.CHRISTENSENETAL2001
+
+
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+ Estabrook, F.B., and H.D. Wahlquist, Response of Doppler Spacecraft Tracking to
+ Gravitational Radiation, Gen. Rel. Grav., 6, 439-447, 1995.
+
+ reference.ESTABROOKETAL1995
+
+
+
+ Mars Global Surveyor Project, Mission Plan, Final Version (MGS 542-405), JPL
+ Document D-12088, Jet Propulsion Laboratory, Pasadena, CA, 1995.
+
+ reference.JPLD-12088
+
+
+
+ Malin, M.C., and K.S. Edgett, Mars Global Surveyor Mars Orbiter Camera:
+ interplanetary cruise through primary mission, J. Geophys. Res., 106, E10,
+ 23429-23570, 2001.
+
+ reference.MALIN-EDGETT2001
+
+
+
+ Malin, M.C., G.E. Danielson, A.P. Ingersoll, H. Masursky, J. Veverka, M.A.
+ Ravine, and T.A. Soulanille, Mars Observer Camera, J. Geophys. Res., 97,
+ 7699-7718, 1992.
+
+ reference.MALINETAL1992
+
+
+
+ Martin, T.Z., and J.R. Murphy, A martian year of mapping by the MGS Horizon
+ Science Experiment, Bull. Amer. Astro. Soc., 33, 3, 1072-1073, 2001.
+
+ reference.MARTIN-MURPHY2001
+
+
+
+ Smith, D.E., M.T. Zuber, H.V. Frey, J.B. Garvin, J.W. Head, D.O. Muhleman, G.H.
+ Pettengill, R.J. Phillips, S.C. Solomon, H.J. Zwally, W.B. Banerdt, T.C.
+ Duxbury, M.P. Golombek, F.G. Lemoine, G.A. Neumann, D.D. Rowlands, O.
+ Aharonson, P.G. Ford, A.B. Ivanov, C.L. Johnson, P.J. McGovern, J.B. Abshire,
+ R.S. Afzal, and X. Sun, Mars Orbiter Laser Altimeter: Experiment summary after
+ the first year of global mapping of Mars, J. Geophys. Res., 106, E10,
+ 23689-23722, 2001.
+
+ reference.SMITHETAL2001B
+
+
+
+ Tyler, G.L., G. Balmino, D.P. Hinson, W.L. Sjogren, D.E. Smith, R. Woo, S.W.
+ Asmar, M.J. Connally, C.L. Hamilton, and R.A. Simpson, Radio Science
+ Investigations with Mars Observer, Journal of Geophysical Research, 97,
+ 7759-7779, 1992.
+
+ reference.TYLERETAL1992
+
+
+
+ Woo, R., Spacecraft Radio Scintillation and Solar System Exploration, Wave
+ Propagation in Random Media (Scintillation), Society of Photo-Optical
+ Instrumentation Engineers, Bellingham, WA, 1993.
+
+ reference.WOO1993
+
+
+
+ Zuber, M.T., D.E. Smith, S.C. Solomon, D.O. Muhleman, J.W. Head, J.B. Garvin,
+ J.B. Abshire, and J.L. Bufton, The Mars Observer Laser Altimeter Investigation,
+ J. Geophys. Res., 97, 7781-7797, 1992.
+
+ reference.ZUBERETAL1992
+
+
+ https://science.nasa.gov/mission/mars-global-surveyor/
+ NASA Mission Website, Mars Global Surveyor
+
+
+
+
+ Mars Global Surveyor
+ Mission
+ 1994-10-12
+ 2007-09-30
+
+ Mars Global Surveyor was an orbiting spacecraft that looped around the Red Planet for a decade. The mission overhauled scientists' understanding of Mars by studying the entire Martian surface, atmosphere, and interior. Major findings included dramatic evidence that water still flows on Mars in short bursts down hillside gullies, and the identification of water-related mineral deposits leading to selection of a Mars rover landing site for a subsequent mission.
+ The mission continued sending images and other data until November 2006, when it went silent due to a series of events linked to a computer error likely caused by battery failure.
+
+
+
+ MGS
+ 1
+
+
+
+
diff --git a/data/pds4/context-pds4/investigation/mission.mars_pathfinder_1.2.xml b/data/pds4/context-pds4/investigation/mission.mars_pathfinder_1.2.xml
new file mode 100644
index 00000000..2d477ddf
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/mission.mars_pathfinder_1.2.xml
@@ -0,0 +1,121 @@
+
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.mars_pathfinder
+ 1.2
+ Mars Pathfinder
+ 1.21.0.0
+ Product_Context
+
+
+
+ 2024-04-09
+ 1.2
+ Added instruments. Added terse description, acronym, alias. Added NASA website.
+
+
+ 2019-01-03
+ 1.1
+
+ Per "Guide toPDS4 Context Products" v1.3,
+ - changed all lidvid_reference to lid_reference
+ - changed target LIDs to new formation rule
+
+
+
+ 2016-10-01
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.mpfl
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.mpfr
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:target:planet.mars
+ investigation_to_target
+
+
+ urn:nasa:pds:context:target:satellite.mars.deimos
+ investigation_to_target
+
+
+ urn:nasa:pds:context:target:satellite.mars.phobos
+ investigation_to_target
+
+
+ urn:nasa:pds:context:target:sun.sun
+ investigation_to_target
+
+
+ urn:nasa:pds:context:instrument:mpfr.apxs
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mpfr.rclt
+ investigation_to_instrument
+
+
+
+ urn:nasa:pds:context:instrument:mpfr.rcrr
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mpfr.rcrt
+ investigation_to_instrument
+
+
+
+ Cook, R., P. Katemeyn, and C. Salvo, Mars Pathfinder Project Mission Plan,
+ JPL Document 11355, PF-100-MP-02, 90 pp., 1995.
+
+ reference.COOKETAL1995
+
+
+
+ Golombek, M.P., The Mars Pathfinder Mission, J. Geophys. Res., 102,
+ 3953-3965, 1997.
+
+ reference.GOLOMBEK1997
+
+
+
+ Golombek, M.P., R.A. Cook, T. Economou, W.M. Folkner, A.F.C. Haldemann,
+ P.H. Kallemeyn, J.M. Knudsen, R.M. Manning, H.J. Moore, T.J. Parker, R.
+ Rieder, J.T. Schofield, P.H. Smith, and R.M. Vaughan, Overview of the Mars
+ Pathfinder Mission and Assessment of Landing Site Predictions, Science,
+ 278, 1743-1748, 1997.
+
+ reference.GOLOMBEKETAL1997B
+
+
+ https://science.nasa.gov/mission/mars-pathfinder/
+ NASA Mission Website, Mars Pathfinders
+
+
+
+
+ Mars Pathfinder
+ Mission
+ 1993-11-01
+ 1998-03-10
+
+ Mars Pathfinder launched Dec. 4, 1996 and landed on Mars' Ares Vallis on July 4, 1997. It successfully delivered an instrumented lander and the Sojourner rover, the first-ever robotic rover to land and operate on the Martian surface. Pathfinder also returned a then-unprecedented amount of data and outlived its primary design life. At a time when the Internet was still in its infancy, the mission's activities captured millions of eyes as people remained glued to their computers to watch anxious and excited engineers and scientists in Mission Control, and to view Mars images transmitted down to Earth.
+
+
+
diff --git a/data/pds4/context-pds4/investigation/mission.mars_reconnaissance_orbiter_1.1.xml b/data/pds4/context-pds4/investigation/mission.mars_reconnaissance_orbiter_1.1.xml
new file mode 100644
index 00000000..e66b8f3d
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/mission.mars_reconnaissance_orbiter_1.1.xml
@@ -0,0 +1,98 @@
+
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.mars_reconnaissance_orbiter
+ 1.1
+ Mars Reconnaissance Orbiter
+ 1.21.0.0
+ Product_Context
+
+
+ 2024-06-21
+ 1.1
+
+ Added instruments. Added terse description, acronym, alias. Added NASA website. Fixed titles.
+
+
+
+ 2016-10-01
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.mro::1.0
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:target:planet.mars::1.0
+ investigation_to_target
+
+
+ urn:nasa:pds:context:instrument:accel.mro
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:crism.mro
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:ctx.mro
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:hirise.mro
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:marci.mro
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mcs.mro
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:rss.mro
+ investigation_to_instrument
+
+
+
+ urn:nasa:pds:context:instrument:sharad.mro
+ investigation_to_instrument
+
+
+
+ https://science.nasa.gov/mission/mars-reconnaissance-orbiter/
+
+ NASA Mission Website, Mars Reconnaissance Orbiter
+
+
+
+
+ Mars Reconnaissance Orbiter
+ Mission
+ 2005-08-12
+
+
+ The Mars Reconnaissance Orbiter, or MRO, has studied the Red Planet's atmosphere and terrain from orbit since 2006 and also serves as a key data relay station for other Mars missions, including the Mars Exploration Rover Opportunity.
+ Equipped with a powerful camera called HiRISE that has aided in a number of discoveries, the Mars Reconnaissance Orbiter has sent back thousands of stunning images of the Martian surface that are helping scientists learn more about Mars, including the history of water flows on or near the planet's surface.
+
+
+
+ MRO
+ 1
+
+
+
+
diff --git a/data/pds4/context-pds4/investigation/mission.mars_science_laboratory_1.1.xml b/data/pds4/context-pds4/investigation/mission.mars_science_laboratory_1.1.xml
new file mode 100644
index 00000000..abef6787
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/mission.mars_science_laboratory_1.1.xml
@@ -0,0 +1,206 @@
+
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.mars_science_laboratory
+ 1.1
+ Mars Science Laboratory
+ 1.22.0.0
+ Product_Context
+
+
+
+ 2024-03-20
+ 1.1
+
+ Added instruments, descriptions, acronym and alias. Added NASA website.
+
+
+
+ 2016-10-01
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.msl::1.0
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:target:planet.mars::1.0
+ investigation_to_target
+
+
+ urn:nasa:pds:context:instrument:mahli.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mardi.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:apxs.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:chemcam_libs.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:chemcam_soh.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:chemcam_rmi.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:chemin.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:sam.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:rad.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:dan.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:rems.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:hazcam.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mast_right.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mast_left.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:nav_right_a.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:nav_right_b.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:nav_left_a.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:nav_left_b.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:rhaz_left_a.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:rhaz_left_b.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:rhaz_right_a.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:rhaz_right_b.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:fhaz_right_a.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:fhaz_right_b.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:fhaz_left_a.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:fhaz_left_b.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:navcam.msl
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:accel.msl
+ investigation_to_instrument
+
+
+ 10.1038/ngeo480
+
+ Grotzinger, J., Beyond water on Mars, Nature Geoscience 2, 231-233,
+ doi:10.1038/ngeo480, 2009.
+
+ Beyond Water on Mars
+
+
+ 10.1007/s11214-012-9892-2
+
+ Grotzinger, J.P., J. Crisp, A.R. Vasavada, R.C. Anderson, C.J. Baker, R. Barry,
+ D.F. Blake, P. Conrad, K.S. Edgett, B. Ferdowsi, R. Gellert, J.B. Gilbert, M.
+ Golombek, J.Gomez-Elvira, D.M. Hassler, L. Jandura, M. Litvak, P. Mahaffy, J.
+ Maki, M. Meyer, M.C. Malin, I. Mitrofanov, J.J. Simmonds, D. Vaniman, R.V.
+ Welch, and R.C. Wiens, Mars Science Laboratory mission and science
+ investigation, Space Science Reviews, 170, 5-56, doi:
+ 10.1007/s11214-012-9892-2, 2012.
+
+ MSL Mission and Science Investigation
+
+
+
+ https://science.nasa.gov/mission/msl-curiosity/
+
+ Nasa Mission Website, Mars Science Laboratory: Curiosity Rover
+
+
+
+
+ Mars Science Laboratory
+ Mission
+ 2003-10-01
+
+
+ The Mars Science Laboratory (MSL) project, initiated in 2003, marked a significant advancement in Mars exploration with the successful deployment of the Curiosity rover. Launched on November 26, 2011, and landing in Gale Crater on August 6, 2012, the MSL mission has broadened our understanding of Martian environments and their potential habitability. Throughout its journey to Mars, and during its primary mission which concluded on September 28, 2014, Curiosity undertook comprehensive scientific investigations. These included routine instrument health checks and data collection by the Radiation Assessment Detector (RAD) during transit.
+ On the Martian surface, Curiosity's primary objectives were to assess the biological potential of the landing site, characterize the landing region's geology, study planetary processes relevant to habitability, and quantify the spectrum of surface radiation. The rover gathered crucial data through imaging, spectroscopy, and other analytic techniques to evaluate the composition of Martian soils, rocks, and the atmosphere. These efforts have provided vital insights into Mars' habitability and environmental history.
+ The continuation of these scientific objectives into Curiosity’s first extended mission aims to deepen the exploration of potentially habitable environments that could also preserve organic compounds. Additionally, the mission focuses on exploring and characterizing significant geological transitions in the region surrounding the foothills of Mt. Sharp. This ongoing research is pivotal for understanding the past and present potential for life on Mars and informs future exploratory missions to the Red Planet.
+
+
+
+ Curiosity
+ 1
+
+
+
+
+ MSL
+ 1
+
+
+
+
diff --git a/data/pds4/context-pds4/investigation/mission.maven_1.2.xml b/data/pds4/context-pds4/investigation/mission.maven_1.2.xml
new file mode 100644
index 00000000..a41f3e9e
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/mission.maven_1.2.xml
@@ -0,0 +1,124 @@
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.maven
+ 1.1
+ Mars Atmosphere and Volatile EvolutioN
+ 1.21.0.0
+ Product_Context
+
+
+
+ 2024-07-08
+ 1.1
+ Added instrument host, target, instruments, terse description, and acronym. Fixed titles.
+
+
+ 2015-03-16
+ 1.0
+
+ Initial version.
+
+
+
+
+
+
+
+ urn:nasa:pds:context:target:planet.mars
+ investigation_to_target
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.maven
+ instrument_to_instrument_host
+
+
+ urn:nasa:pds:context:instrument:acc.maven
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:euv.maven
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:iuvs.maven
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:lpw.maven
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:mag.maven
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:ngims.maven
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:rss.maven
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:sep.maven
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:static.maven
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:swea.maven
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:swia.maven
+ investigation_to_instrument
+
+
+ https://science.nasa.gov/mission/maven/
+ NASA Mission Website, MAVEN
+
+
+
+ Mars Atmosphere and Volatile EvolutioN
+ Mission
+ 2013-11-13
+
+
+ The MAVEN mission launched on an Atlas V between November 18, 2013. Mars orbit insertion
+ occured on September 22, 2014, after a ten-month ballistic cruise phase. Following a 5-week
+ transition phase, the spacecraft entered Mars orbit at a 75 degree inclination, with a 4.5
+ hour period and periapsis altitude of 140-170 km (density corridor of 0.05-0.15 kg/km3). Over
+ a one-Earth-year period, periapsis precessed over a wide range of latitude and local time,
+ while MAVEN obtained detailed measurements of the upper atmosphere, ionosphere, planetary
+ corona, solar wind, interplanetary/Mars magnetic fields, solar EUV and solar energetic
+ particles, thus defining the interactions between the Sun and Mars. MAVEN explored down to
+ the homopause during a series of five 5-day “deep dip” campaigns for which periapsis was
+ lowered to an atmospheric density of 2 kg/km3 (~125 km altitude) in order to sample the
+ transition from the collisional lower atmosphere to the collisionless upper atmosphere.
+ These five campaigns were interspersed though the mission to sample the subsolar region, the
+ dawn and dusk terminators, the anti-solar region, and the north pole.
+
+
+
+ MAVEN
+ 1
+
+
+
+
\ No newline at end of file
diff --git a/data/pds4/context-pds4/investigation/mission.pioneer_venus_2.1.xml b/data/pds4/context-pds4/investigation/mission.pioneer_venus_2.1.xml
new file mode 100644
index 00000000..57ba98ed
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/mission.pioneer_venus_2.1.xml
@@ -0,0 +1,185 @@
+
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.pioneer_venus
+ 2.1
+ Pioneer Venus (PV)
+ 1.20.0.0
+ Product_Context
+
+
+ P12
+ P12
+
+
+
+
+ 2016-10-01
+ 1.0
+
+ extracted metadata from PDS3 catalog and
+ modified to comply with PDS4 Information Model
+
+
+
+ 2023-12-05
+ 2.0
+
+ Adding references for Pioneer Venus Multiprobe.
+
+
+
+ 2024-09-06
+ 2.1
+
+ Edited title and name.
+
+
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.pvo
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.pvmp.lp
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.pvmp.sp-day
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.pvmp.sp-night
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.pvmp.sp-north
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.pvmp.bus
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:target:planet.venus
+ investigation_to_target
+
+
+
+ Colin, L., Pioneer Venus Overview, IEEE Transactions on Geoscience and
+ Remote Sensing, Vol GE-18, No. 1, pp. 5-10, 1980.
+
+ reference.COLIN1980B
+
+
+
+
+ Pioneer Venus (PV)
+ Mission
+ 1978-05-20
+ 1992-10-07
+
+
+
+ Mission Overview
+ ================
+
+ [From COLIN1980B]
+
+ Pioneer Venus consists of two basic spacecraft: Orbiter and
+ Multiprobe [1]. The latter was separated into five separate
+ vehicles near Venus. These were the probe transporter (called
+ the Bus), a large atmospheric entry probe (dubbed Sounder) and
+ three identical smaller probes (called North, Day, and Night in
+ accordance with their entry locations). At Venus all six
+ spacecraft communicated directly back to the Earth-based Deep
+ Space Network (DSN) and, in the case of the Multiprobe mission,
+ to two special receiving sites near Guam and Santiago (Chile).
+
+ The Orbiter was launched on May 20, 1978, encountered Venus on
+ December 4, 1978, was inserted into orbit on that same day
+ after a Type II interplanetary cruise trajectory lasting 198
+ days and covering more than 500 x 10^6 km. Twelve scientific
+ experiments were included in the instrumentation payload and a
+ few radioscience investigations were planned using the S-band
+ telemetry signal carrier and a special X-band beacon included
+ as part of the spacecraft hardware. Scientific observations
+ were made both in-cruise and in-orbit. The nominal in-orbit
+ mission was designed to extend for one Venus year (243 days).
+
+ During the nominal mission all but two experiments operated 100
+ percent successfully. One, the Radar Mapper, produced unusable
+ data for a 32-day period from December 18, 1978 to January 19,
+ 1979. The data lost [were to] be acquired during the extended
+ Orbiter mission. The other, the Infrared Radiometer, failed to
+ operate after February 14, 1979, but had collected an enormous
+ quantity of valuable information prior to that date.
+
+ The Multiprobe was launched on August 8, 1978, encountered
+ Venus on December 9, 1978 (just five days following the Orbiter
+ insertion) after a Type I interplanetary cruise trajectory
+ lasting 123 days and covering 330 x 10^6 km. The Sounder was
+ released from the Bus on November 15, 1978, and the three small
+ probes were released simultaneously on November 19, 1978. All
+ probes entered (200-km altitude) the Venus upper atmosphere
+ within a time span of about 11 min and descended to the surface
+ in a period from 53 to 56 min, all the time performing
+ scientific observations. The Bus made a delayed (~90 min)
+ entry relative to the probes into Venus' upper atmosphere and
+ burned up at about 110-km altitude since it was not protected,
+ as were the probes, with entry heat shields. Scientific
+ observations were made during the one-minute interval from 700
+ to 110 km. Although not designed for `survival' after impact,
+ the Day probe managed to transmit for over 67 min on the
+ surface (it in fact continued to transmit after the Bus
+ transmission ceased). Seven scientific experiments were
+ included in the Sounder instrumentation payload, three
+ identical experiments in each small probe, and two in the Bus.
+ Again, radioscience experiments were performed using,
+ separately or together, the S-band telemetry signal carriers
+ emanating from the spacecraft and received at the Earth-based
+ tracking stations. In general, all instruments performed
+ nominally, although certain instruments behaved anomalously on
+ all four probes near the surface.
+
+ References:
+
+ [1] L. Colin and C.F. Hall, Space Sci. Rev., vol. 20,
+ no. 3, p. 283, May 1977.
+
+ Mission Phases
+ ==============
+
+ PIONEER VENUS ORBITER VENUS ORBITAL OPERATIONS
+ ----------------------------------------------
+ This mission phase 'orbiter operations' describes the entire
+ mission of the Orbiter spacecraft.
+
+ Spacecraft Id : PVO
+ Target Name : VENUS
+ Mission Phase Start Time : 1978-12-05
+ Mission Phase Stop Time : 1992-10-02
+ Spacecraft Operations Type : ORBITER OPERATIONS
+
+
+ PIONEER VENUS ORBITER VENUS ENCOUNTER
+ -------------------------------------
+ This mission phase 'encounter' describes all operations of
+ the 5 separate probe components of the Multiprobe component
+ of the Pioneer Venus mission.
+
+ Spacecraft Id : PVMP
+ Target Name : VENUS
+ Mission Phase Start Time : 1978-12-07
+ Mission Phase Stop Time : 1992-12-07
+ Spacecraft Operations Type : ATMOSPHERIC PROBE
+
+
+
diff --git a/data/pds4/context-pds4/investigation/mission.psyche_1.1.xml b/data/pds4/context-pds4/investigation/mission.psyche_1.1.xml
new file mode 100644
index 00000000..4411a3dc
--- /dev/null
+++ b/data/pds4/context-pds4/investigation/mission.psyche_1.1.xml
@@ -0,0 +1,76 @@
+
+
+
+
+ urn:nasa:pds:context:investigation:mission.psyche
+ 1.1
+ Psyche
+ 1.21.0.0
+ Product_Context
+
+
+
+ 2024-03-20
+ 1.1
+
+ Added terse description, acronym, alias. Added instruments. Added NASA website. Fixed titles.
+
+
+
+ 2022-01-12
+ 1.0
+ Initial version
+
+
+
+
+
+ urn:nasa:pds:context:instrument_host:spacecraft.psyche
+ investigation_to_instrument_host
+
+
+ urn:nasa:pds:context:target:asteroid.16_psyche
+ investigation_to_target
+
+
+ urn:nasa:pds:context:instrument:psyche.grs
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:psyche.imager
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:psyche.mag
+ investigation_to_instrument
+
+
+ urn:nasa:pds:context:instrument:psyche.ns
+ investigation_to_instrument
+
+
+ 10.2514/6.2016-4541
+
+ Oh, D. Y., Goebel, D., Polanskey, C., Snyder, S., Carr, G., Collins, S. M., Lantoine, G.,
+ Landau, D., Elkins-Tanton, L., Lord, P., and Tilley, S. (2016). Psyche: Journey to a Metal
+ World. 52nd AIAA/SAE/ASEE Joint Propulsion Conference. https://doi.org/10.2514/6.2016-4541
+
+ Psyche: Journey to a Metal World
+
+
+ https://www.jpl.nasa.gov/missions/psyche
+ NASA Mission Website, Psyche
+
+
+
+ Psyche
+ Mission
+ 2022-08-01
+
+
+ The Psyche mission is a journey to a unique metal-rich asteroid orbiting the Sun between Mars and Jupiter. What makes the asteroid Psyche unique is that it appears to be the exposed nickel-iron core of an early planet, one of the building blocks of our solar system.
+ Deep within rocky, terrestrial planets - including Earth - scientists infer the presence of metallic cores, but these lie unreachably far below the planets' rocky mantles and crusts. Because we cannot see or measure Earth's core directly, Psyche offers a unique window into the violent history of collisions and accretion that created terrestrial planets.
+ The mission is led by Arizona State University. NASA's Jet Propulsion Laboratory is responsible for mission management, operations and navigation. The spacecraft's solar-electric propulsion chassis will be built by Maxar (formerly SSL) with a payload that includes an imager, magnetometer, and a gamma-ray spectrometer.
+
+
+
diff --git a/data/pds4/context_support/document/description/ody.accel_description_1.0.md b/data/pds4/context_support/document/description/ody.accel_description_1.0.md
new file mode 100644
index 00000000..993e923c
--- /dev/null
+++ b/data/pds4/context_support/document/description/ody.accel_description_1.0.md
@@ -0,0 +1,61 @@
+# Instrument Overview
+
+During aerobraking, the accelerometers measure the change in velocity of
+the spacecraft due to aerodynamic forces. The dominant force is along the
+spacecraft y-direction. The spacecraft y-axis is approximately into the
+wind. Data are provided at 1 second intervals and recorded in units of
+m/s^2.
+
+
+# Scientific Objectives
+
+Accelerometer data were used to characterize the nature of the atmosphere,
+to determine the effect of the atmosphere on each orbit, and to predict
+the effect of the atmosphere on future orbits.
+
+
+# Calibration
+
+The instrument was calibrated on each orbit to determine drift in
+instrument bias. Bias is determined by monitoring the accelerometer
+instrument during periods of inactivity before and after entering the
+atmosphere. The bias acceleration is then estimated over the entire pass
+by trending the data from the pre- and post-atmospheric entry periods.
+The pre- and post-atmospheric periods were defined by instrument turn-on
+and turn-off times and a lower limit on the altitude of data used for
+calibration, typically 250 km.
+
+
+# Operational Considerations
+
+The instrument readings are affected by changes in temperature. The
+instrument is mounted in the inertial measurement unit (IMU) and the
+temperature of the IMU is by temperature sensors.
+
+
+# Operational Modes
+
+The data from the accelerometer are passed to the telemetry deck during an
+aerobraking pass from the time the s/c reaches aerobraking orientation
+until the s/c returns to nominal orbit attitude.
+
+
+# Measured Parameters
+
+An accelerometer is an instrument that measures the acceleration of the
+case of the sensor due to external forces. All accelerometers have a
+'proof mass' and it is the tendency of the proof mass to move relative to
+the case that is a measure of the acceleration of the case. Early
+accelerometers produced output that was directly related to acceleration;
+but modern sensors integrate the internally measured signal to reduce
+noise and the output is proportional to the change in velocity over the
+integration time. In high precision accelerometers, like those on ODY,
+the proof mass is an electronically floating mass. The electromagnetic
+field is varied to keep the proof mass stationary relative to the case.
+The current required to accomplish this is proportional to the
+acceleration. The accelerometers on ODY are sensitive to acceleration of
+the center of mass (c.m.) of the s/c, pseudo-accelerations (i.e.
+centrifugal) due to rigid motion of the s/c about the c.m., and
+differences in gravitational force at the proof mass and the c.m. of the
+s/c (gravity gradient).
+
diff --git a/data/pds4/context_support/document/description/ody.mar_description_1.0.md b/data/pds4/context_support/document/description/ody.mar_description_1.0.md
new file mode 100644
index 00000000..e8fefbcc
--- /dev/null
+++ b/data/pds4/context_support/document/description/ody.mar_description_1.0.md
@@ -0,0 +1,275 @@
+# Scientific Objectives and Overview
+
+Mars is substantially exposed to the harshest elements of space
+weather. Unlike Earth, which sits inside a protective magnetic field
+called the magnetosphere, Mars does not have a global magnetic field
+to shield it from solar flares and cosmic rays. Another factor is
+the lack of atmosphere. Mars' atmosphere is less than 1% as thick as
+Earth. These two factors make Mars vulnerable to space radiation.
+The Marie instrument was designed to measure the amount of harmful
+radiation in the Mars environment.
+
+The particles which are thought to be most harmful to humans fall
+mostly in the energy range of 30 MeV to thousands of MeV per
+nucleon. These are the particles with enough energy to damage human
+DNA. The MARIE instrument is designed to measure particles in the
+range of 15 MeV to 500 MeV/n. The data gathered in several detector
+elements is combined to identify the species of the incident
+particles and their energies in this range. The MARIE Instrument was
+developed by NASA Johnson Space Center. The development process was
+a coordinated effort of NASA/JSC, Lockheed-Martin and Battelle.
+Battelle developed the CPU, power boards, A detector, B detector and
+C detector boards. Lockheed was tasked with development of the
+position sensor devices (PSD), the instrument packaging, system
+integration, software development and certifying the instrument for
+flight. NASA/JSC provided the project management and coordination of
+the contractors.
+
+If a particle enters the MARIE detector telescope within the 60
+degree cone defined by the A1 and A2 detectors, and has enough
+energy to reach the A2 detector, it is considered a coincident
+event. On coincident events, all detector boards are polled by the
+CPU and the data for this event is recorded. The readout for each
+detector records a pulse height that is proportional to the amount
+of energy deposited in the detector. The PSD's also record the
+position of the strike within the detector.
+
+The minimum proton energy required to form an A1A2 coincidence
+corresponds to a proton with range greater than the sum of the
+thickness of A1, PSD1, PSD2, and a minuscule part of the A2
+thickness. This adds up to 0.374 g/cm2 of Si and corresponds to a
+proton energy of 19.8 MeV. So protons above this energy will be
+recorded by the telescope; more energy per nucleon is required for
+higher-charged particles. If one takes into account the thin
+aluminum case that surrounds MARIE, the minimum proton energy is 30
+MeV. The angular response functions are calculated for those
+particles that give an A1A2 coincidence and also pass through PSD1
+and PSD2 detectors, since they are the only particles that can
+provide the incidence angle of the charged particle. Note that not
+all particles that give rise to A1A2 coincidence pass through PSD1
+and PSD2 because the position sensitive detector are slightly
+smaller in size. A new particle identification algorithm is being
+developed to determine incident angles for particles that miss the
+PSDs or have their positions mis-reported by the PSDs. (The latter
+are common, owing to spurious detector noise.)
+
+If a particle hits only one of the A-detectors, the event is
+discarded because the angle of impact and energy loss in the other
+detector boards is not known. Also, any particle entering the bottom
+of the telescope will not register an event on the C-detector due to
+the directional properties of the C-detector.
+
+The chassis box of MARIE is made from machined aluminum with an
+alodine coating. The exterior surfaces are painted white. Input
+voltage to MARIE is 28 VDC and power requirements are 3 watts for
+survival mode and 7 watts for nominal operation.There are no
+external controls. All control is from the orbiter through an RS-422
+interface.
+
+
+# Calibration
+
+Data obtained during the cruise phase of the 2001 Mars Odyssey
+mission have been used to calibrate the data. Pulse height spectra
+in the range 0 to 4096 have been scaled to yield distributions of
+apparent charge, Z. Calibration factors for each detector were
+determined by forcing the obvious high-energy proton peak in each
+distribution to have its center at Z = 1.
+
+
+# Operational Considerations
+
+During Odyssey's daily DSN session, MARIE is off for 1-2 hours,
+causing small gaps in coverage. When the recorded data volume
+approaches the capacity of MARIE's local storage, data acquisition
+is halted until the next download opportunity. When all data have
+been downloaded, the storage area is erased and the instrument
+reset. This sequence of events causes relatively long outages, on
+the order of 1 to 2 days.
+
+
+# Detectors
+
+Each of the two A detector assemblies contains a 25.4 x 25.4 x 1 mm
+ion-implanted silicon solid state detector, detector signal
+amplifiers, detector high voltage supply and the interface circuitry
+between the detector and the MARIE CPU. The MARIE CPU controls the
+interface circuitry including high voltage control, collecting
+digitized signal amplitude data and controlling signal coincidence
+timing sources. The two A-detectors are used to define a coincidence
+event. These detectors are operated near 160 V.
+
+Each of the four B-detector assemblies contains a 5 mm thick
+lithium-drifted silicon solid state detector, detector signal
+amplifiers, detector high voltage supply and the interface circuitry
+between the detector and the MARIE CPU. The MARIE CPU controls the
+interface circuitry including high voltage control and collecting
+digitized signal amplitude data. These detectors are operated near
+350 V.
+
+The C detector consists of a Schott-glass Cherenkov detector and a
+Hamamatsu photo multiplier tube (PMT). When a charged particle with
+a velocity greater than [velocity of light / glass refractive index]
+hits the Cherenkov detector, the detector releases a photon light
+burst proportional to the energy of the particle which struck it.
+The photo multiplier tube receives the light pulse and translates it
+into an electronic pulse which is amplified by the tube and read by
+the electronics on the C-detector board. The C-detector assembly
+contains the PMT, detector signal amplifiers, detector high voltage
+supply and the interface circuitry between the detector and the
+MARIE CPU. The MARIE CPU controls the interface circuitry including
+high voltage control and collecting digitized signal amplitude data.
+
+Each of the two position sensitive detector (PSD) assemblies
+contains 25.4 X 25.4 mm position sensitive detector. These are
+double-sided silicon strip detectors with 24 strips on each side,
+with a 1 mm pitch. The strips on one side are oriented so as to be
+orthogonal to the strips on the other side. The active area of these
+detectors is 24 mm x 24 mm. Hits from all four strip planes define
+the particle's incident angle.
+
+From the front of the device, particles entering the detector pass
+through detector A1, PSD1, PSD2, A2, B1, B2, B3, B4, and C.
+Depending on the angle of incidence and scattering within the
+detector, some of the downstream detectors (B's and C) may be missed
+on any given event.
+
+
+# Electronics
+
+The Central Processing Unit (CPU) board has an Intel 80C188
+microprocessor, detector interface circuitry and data communication
+hardware for transferring data to the spacecraft from the 80 MB
+flash memory. The flash memory holds the program code and any data
+which has not been transferred to the spacecraft. The power from the
+spacecraft is nominally 28 volts. The Marie instrument has
+Interpoint DC-DC converters to convert the power to a usable level.
+
+Each detector has its own card, with all of the electronics
+associated with the detector on it, including a 12 bit
+analog-to-digital (ADC) converter, and Field Programmable Gate
+Array (FPGA)
+
+The power, mode control and data download of the MARIE instrument
+are controlled by the Odyssey spacecraft. Commands are sent from the
+ground to the spacecraft central processing unit (CPU) to power on
+MARIE and to change modes.
+
+
+# Location
+
+The MARIE instrument frame is illustrated by this diagram:
+
+```
+ _______________ HGA
+ \ /
+ .. `._________.'
+ Science || ._______________.Science deck
+ Orbit || | ^+Xsc |
+ Velocity || | | |
+ ^. || | | ^+Xmarie .' MARIE FOV
+ `. || | |+Zsc /|| .' (68 deg cone)
+ `. ||@| <-----o ..'._|_. .'
+ || +Ysc / | | |.'
+ || | _.' <----o o--------> MARIE FOV
+ || | _.' +Ymarie _.`. boresight
+ Solar || ..'_____________. `.
+ Array .. Bottom Deck `.
+ `.
+ /
+ / -------->
+ / Aerobraking
+ V Nadir Velocity
+```
+
+Actual keywords defining MARIE instrument frame and incorporating
+MARIE mounting alignment information are provided in reference [1].
+
+The MARIE FOV (field of view), as defined in [2], is a 68-degree
+cone centered around the -Y axis of the MARIE instrument frame.
+
+The set of keywords in the data section above defines MARIE FOV
+as a circle with a half-angle of 34 degrees and boresight direction
+along the -Y axis of the MARIE instrument frame.
+
+The following data for the FOV geometry were extracted from the
+SPICE instrument kernel for MARIE, provided by the NAIF Node of
+the Planetary Data System [3]. (The text of this section also was
+adapted from that SPICE kernel.) These data are included here for
+the benefit of those familiar with the use of SPICE kernels.
+
+```
+INS-53040_FOV_FRAME = 'M01_MARIE'
+INS-53040_FOV_SHAPE = 'CIRCLE'
+INS-53040_BORESIGHT = (
+ 0.0000000000000000
+ -1.0000000000000000
+ 0.0000000000000000
+ )
+
+INS-53040_FOV_BOUNDARY_CORNERS = (
+ 0.0000000000000000
+ -0.8290375725550400
+ +0.5591929034707500
+ )
+```
+
+# Operational Modes
+
+The instrument has only two modes, Science Mode and Survival Mode.
+
+Science Mode: When placed in Science mode, the MARIE acts as an
+ autonomous data acquisition device. Data is collected until the
+ spacecraft issues a mode change command to move to survival mode.
+
+Survival Mode: From survival mode, the spacecraft can issue commands
+ to download data, change parameters, power down or return to
+ Science Mode. During the data download, the spacecraft controls
+ the download process and downlinks the data to the ground.
+
+
+# Measured Parameters
+
+The detector is composed primarily of three types of silicon
+detectors: the A detectors, which are square in cross-section (25.4
+mm on a side) and 1 mm in depth; the B detectors, circular, 63.5 mm
+diameter and 5 mm thick; and the PSDs, or position-sensitive
+detectors. The PSDs are square double-sided strip detectors with 24
+1 mm strips on each side (the strips on one side are orthogonal to
+those on the other side), and have a thickness of 0.3 mm. There are
+two A detectors, A1 and A2; sandwiched in between them are PSD1 and
+PSD2; behind A2, there are the B detectors, B1 through B4.
+Downstream of B4 is a circular piece of quartz, 10 mm thick, that
+radiates photons (Cerenkov radiation) generated by the passage of
+high-velocity particles through it. The photons are reflected by a
+45 deg mirror into a photo multiplier tube that sits out of the path
+of particles that hit the detectors.
+
+MARIE is triggered by a coincidence of hits in detectors A1 and
+A2. Once triggered, the data acquisition system records 12-bit
+digitized outputs which are proportional to the energies deposited
+in the A and B detectors. A two-byte data word is stored for each of
+these channels. The pulse height from the phototube is similarly
+digitized in 12 bits and stored.
+
+Readout of the PSDs is more complex. Each PSD has two orthogonal
+sides, referred to as columns and rows. The following description
+applies to each side of each detector. Onboard hardware analyzes the
+signals from each of the 24 strips and finds the two largest pulse
+heights. For each, the pulse height is digitized in 8 bits (256
+channels) and stored, along with the strip number. The largest pulse
+height and position are referred to as 'event1', the second-largest
+as 'event2.' The event2 data are usually noise. Four quantities are
+stored for each side of each detector, so that a total of sixteen
+words (thirty-two bytes) of PSD data are stored on each event. The
+eight-bit pulse heights are referred to as 'magnitudes', the
+positions are valid only when in the range 1 to 24.
+
+
+# References
+
+1. M'01 Frames Definition Kernel (FK), latest version as of March 6,
+ 2001
+2. 'MARIE ICD', MSP01-98-0016, June 23, 1999
+3. MARIE Instrument Kernel (TI), March 6, 2001
+
diff --git a/data/pds4/context_support/document/description/ody.rss_description_1.0.md b/data/pds4/context_support/document/description/ody.rss_description_1.0.md
new file mode 100644
index 00000000..e84da96f
--- /dev/null
+++ b/data/pds4/context_support/document/description/ody.rss_description_1.0.md
@@ -0,0 +1,1338 @@
+# Instrument Overview
+
+There were no recognized radio science investigations on
+the 2001 Mars Odyssey (ODY) mission. But investigators on
+Mars Global Surveyor (MGS) requested access to ODY radio
+tracking data. To support them and future proposers to
+Mars data analysis programs (MDAPs), the Planetary Data
+System (PDS) accepted responsibility for archiving the ODY
+data with initial activities funded jointly by MGS.
+
+Radio science investigations utilize instrumentation with
+elements both on a spacecraft and at ground stations -- in
+this case, at the NASA Deep Space Network (DSN). For ODY
+much of this was equipment used for routine telecommunications.
+The performance and calibration of both the spacecraft and
+tracking stations directly affected the radio science data
+accuracy, and they played a major role in determining the
+quality of the results. The spacecraft part of the radio
+science instrument is described immediately below; that is
+followed by a description of the DSN (ground) part of the
+instrument. For more information, see [MAKOVSKY2001].
+
+
+# Instrument Specifications - Spacecraft
+
+The 2001 Mars Odyssey spacecraft telecommunications
+subsystem served as part of a radio science subsystem for
+investigations of Mars. Many details of the subsystem are
+unknown; its 'build date' is taken to be 2001-04-01, which
+was near the end of the Prelaunch Phase of the ODY mission.
+```
+Instrument Id : RSS
+Instrument Host Id : ODY
+Pi Pds User Id : UNK
+Instrument Name : RADIO SCIENCE SUBSYSTEM
+Instrument Type : RADIO SCIENCE
+Build Date : 2001-04-01
+Instrument Mass : UNK
+Instrument Length : UNK
+Instrument Width : UNK
+Instrument Height : UNK
+Instrument Manufacturer Name : UNK
+```
+
+# Instrument Overview - Spacecraft
+
+The spacecraft radio system was constructed around a
+redundant pair of X-band Small Deep Space Transponders (SDSTs).
+Other components included one low-gain receive antenna (LGA);
+one medium-gain transmit antenna (MGA); one steerable
+high-gain antenna (HGA) for both transmitting (Tx) and receiving
+(Rx); two redundant solid state power amplifiers (SSPAs); a
+diplexer; several switches; and cabling. The SDSTs were
+connected to redundant Command and Data Handling (C&DH) units
+in such a way that any pairing could be chosen. A functional
+block diagram is shown below.
+
+```
+ DIPLEXER . .
+ --- . / .
+ ---------------------| |------------/ .
+ | --- . \ HGA .
+ | _ BPF1 | . \ .
+ ----------|_| | . .
+ | | / \ | . / .
+ | |_____| S1 |________________________/ .
+ | \ / . \ MGA .
+ | \_/ | . \ .
+ | |_| | . .
+ | | BPF2 | . .
+ |\| |\| | . HGA ASSEMBLY.
+ | \ | \ | . . . . . . . .
+ | / SSPA_1 | / SSPA_2 | /
+ |/| |/| | /
+ | | | HGA GIMBAL
+ | | | ASSEMBLY
+ --------------- |
+ | 3 dB HYBRID | |
+ | COUPLER | |
+ --------------- |
+ | | |
+ | | |
+ ------ ------ |
+ |SDST_1| |SDST_2| |
+ ------ ------ |
+ | \ / | |
+ | X | |
+ | / \ | -
+ ------ ------ _ / \ _ NF1
+ ---|C&DH_A| |C&DH_B|-------|_| S2 |_|--
+ | ------ ------ NF2 \ / |
+ | - |
+ | | | /
+ | ----------/
+ | | \ LGA
+ ---------------------------------------- \
+```
+
+S1 was a waveguide transfer switch with positions:
+1. SSPA_1 to HGA and SSPA_2 to MGA
+2. SSPA_1 to MGA and SSPA_2 to HGA
+(Insertion loss, <0.05 dB)
+S2 was a coaxial transfer switch with positions:
+1. SDST_1 to LGA and SDST_2 to HGA
+2. SDST_1 to HGA and SDST_2 to LGA
+(insertion loss, <0.3 dB)
+BPF_1 and BPF_2 were bandpass filters
+(<0.2 dB insertion loss over 8400-8450 MHz)
+NF1 and NF2 were notch filters
+(>70 dB rejection over 8400-8450 MHz)
+The X-Band Diplexer insertion loss was 0.1 DB (Tx), 0.2 dB (Rx)
+
+End-to-end circuit losses are given in the following table:
+
+```
+========================================================
+| Link/Direction | Elements | Value |
++------------------+---------------+-------------------+
+| X-Band Transmit | SSPA to HGA | -0.25 +/- 0.11 dB |
++------------------+---------------+-------------------+
+| X-Band Transmit | SSPA to MGA | -0.52 +/- 0.35 dB |
++------------------+---------------+-------------------+
+| X-Band Receive | HGA to SDST | -8.13 +/- 0.03 dB |
++------------------+---------------+-------------------+
+| X-Band Receive | LGA to SDST | -2.43 +/- 0.02 dB |
+========================================================
+```
+
+SSPA output power design was for 15 W (41.8 dBm) at end of life.
+
+The ODY telecommunications system was designed to perform the
+following functions:
+
+1) Receive an X-band uplink carrier from a DSN station and
+demodulate the command data and ranging signal if either
+were present;
+2) Generate an X-band downlink carrier either by coherently
+multiplying the frequency of the uplink carrier by the
+turn-around ratio of 880/749 or by utilizing an
+auxiliary crystal oscillator (AUX OSC);
+3) Phase modulate the downlink carrier with either (or both)
+of the following:
+a composite telemetry signal, consisting of a square
+wave subcarrier (25 kHz or 375 kHz) that was BPSK
+(binary phase shift keying) modulated by telemetry data
+provided by the C&DH subsystem;
+the ranging signal that was demodulated from the uplink
+(this is referred to as two-way, or turn-around,
+ranging);
+4) Permit control of the telecom subsystem through commands
+to select signal routing and the operational mode of the
+subsystem either from the ground or from command
+sequences previously loaded on the spacecraft;
+5) Provide telecom status for monitoring operating
+conditions of the subsystem;
+6) Provide ON/OFF power control for all RF transmitters;
+7) Assume a single well-defined operating mode (a known
+baseline state) after a Power-On-Reset (POR).
+
+The X-band capability reduced plasma effects on radio
+signals by a factor of 10 compared with older S-band
+systems, but absence of a dual-frequency capability (both
+S- and X-band) meant that plasma effects could not be
+estimated and removed from radio data.
+
+The spacecraft also carried redundant ultra-high frequency (UHF)
+transceivers for communication and relay with future missions.
+Since the UHF equipment was not used for radio science, it is
+not described here.
+
+
+# Science Objectives
+
+There were no radio science objectives for the 2001 Mars Odyssey
+mission. The radio tracking data could be used by others to
+improve knowledge of the Mars gravity field .
+
+
+# Operational Considerations - Spacecraft
+
+Descriptions given here are for nominal performance. The
+spacecraft transponder system comprised redundant units,
+each with slightly different characteristics. As
+transponder units age, their performance changes slightly.
+More importantly, the performance for radio science depended
+on operational factors such as the modulation state for the
+transmitters, which cannot be predicted in advance. The
+performance also depended on factors which were not always
+under the control of the 2001 Mars Odyssey Project.
+
+The telecom subsystem relied on C&DH to control its operating
+mode; that control could be done via real-time commands from
+the ground or via a stored sequence onboard the spacecraft.
+The only exception was the POR state, which would be entered
+directly after a Power-On-Reset.
+
+C&DH provided the data to be downlinked, it carried out the
+frame and packet formatting and the Reed-Solomon encoding,
+and it provided the clock to drive the encoding. The clock was
+either
+data clock X 2 for (7,1/2) encoding or
+data clock X 6 for (15,1/6) encoding
+C&DH also handled error control for the uplink data stream.
+
+
+# Calibration Description - Spacecraft
+
+All measurements below were made during the Prelaunch Phase of
+The mission.
+
+Antenna characteristics are listed below. Masses of MGA and
+HGA are combined. Gain and axial ratio are given for boresight.
+Beamwidth is between the 3 dB points.
+
+```
+=========================================================
+| Antenna Characteristics - 2001 Mars Odyssey |
++-----------------+---------+--------+--------+---------+
+| | MGA | HGA | LGA |
+| Parameter +---------+--------+--------+---------|
+| | Tx Only | Tx | Rx | Rx Only |
++-----------------+---------+--------+--------+---------+
+|Frequency (MHz) | 8406.851852 | 7155.377315 |
++-----------------+---------+--------+--------+---------+
+|Diameter (m) | N/A | 1.3 | N/A |
++-----------------+---------+--------+--------+---------+
+|Mass (kg) | 3.150 | 0.040 |
++-----------------+---------+--------+--------+---------+
+|Gain (dBi) | 16.5 | 38.3 | 36.6 | 7+/-4 |
++-----------------+---------+--------+--------+---------+
+|Axial Ratio (dB) | N/A | 1.35 | 1.24 | 3 |
++-----------------+---------+--------+--------+---------+
+|Beamwidth (deg) | 28 | 1.9 | 2.3 | 82 |
+=========================================================
+```
+Receiver Carrier Loop characteristics were as follows:
+```
+=========================================================
+| Parameter | Value |
++------------------+------------------------------------+
+|Noise Figure | 2.70 +0.60/-0.73 dB averaged over |
+| | lifetime aging, temperature,|
+| | and radiation |
++------------------+------------------------------------|
+|Tracking | -155 to -156 dBm |
+| Threshold | |
++------------------+------------------------------------|
+|Tracking Rate | 200 Hz/s for uplink Pt <= -120 dBm |
++------------------+------------------------------------|
+|Capture Range | +/-1.3 kHz |
++------------------+------------------------------------|
+|Tracking Range | +100 kHz/-200 kHz relative to best |
+| | lock frequency |
++------------------+------------------------------------|
+|Carrier Loop | 20 Hz |
+| Threshold | |
+| Bandwidth | |
++------------------+------------------------------------|
+|Strong Signal Open| 2.0e+07 |
+| Loop Gain | |
++------------------+------------------------------------|
+|Predetection Noise| 12500 Hz |
+| Bandwidth | |
++------------------+------------------------------------|
+|Loop Pole Time | 2258.6 s |
+| Constant | |
++------------------+------------------------------------|
+|Loop Zero Time | 0.050 s |
+| Constant | |
++------------------+------------------------------------|
+|Strong Signal Loop| 231.306 Hz two-sided at Pc/No = |
+| Noise Bandwidth | 100 dB-Hz |
+=========================================================
+```
+The SDST ranging performance is listed in the table below.
+One range unit was 0.947 nanoseconds for 2001 Mars Odyssey.
+```
+==========================================================
+| Parameter | Value (average over 3 devices) |
++---------------------+----------------------------------+
+|Range Delay | 1417.2 range units |
++---------------------+----------------------------------+
+|Temperature Variation| +/-4.0 ru (-25C to +30C) |
++---------------------+----------------------------------+
+|Carrier Suppression | 0.5 dB (17.5 deg range mod index)|
+| | 1.9 dB (35.0 deg range mod index)|
++---------------------+----------------------------------+
+|3 dB Bandwidth | 1.4 MHz |
++---------------------+----------------------------------+
+|Noise Equivalent | 2.0 MHz |
+| Bandwidth | |
+==========================================================
+```
+
+
+# Platform Mounting Descriptions - Spacecraft
+
+During the Launch, Cruise, Orbit Insertion, and Aerobraking
+phases of the mission, the HGA was stowed so that its
+boresight and the MGA boresight were along the +X axis. After
+aerobraking, the HGA was deployed and tracked the
+Earth using a pair of gimbals (azimuth and elevation) at the
+end of a boom.
+The MGA was mounted on the HGA dish so that the MGA and HGA
+boresights were equal. The SSPAs were mounted behind the HGA
+reflector to minimize circuit losses.
+
+
+# Investigators
+
+None.
+
+
+# Instrument Section / Operating Mode Descriptions - Spacecraft
+
+Redundant components could be configured as desired. Each
+configuration had slightly different performance, but the
+quantitative differences are unknown.
+
+
+# Instrument Overview - DSN
+
+Three Deep Space Communications Complexes (DSCCs) (near
+Barstow, CA; Canberra, Australia; and Madrid, Spain) comprise
+the DSN tracking network. Each complex is equipped with
+several antennas [including at least one each 70-m, 34-m High
+Efficiency (HEF), and 34-m Beam WaveGuide (BWG)], associated
+electronics, and operational systems. Primary activity
+at each complex is radiation of commands to and reception of
+telemetry data from active spacecraft. Transmission and
+reception is possible in several radio-frequency bands, the
+most common being S-band (nominally a frequency of 2100-2300 MHz
+or a wavelength of 14.2-13.0 cm) and X-band (7100-8500 MHz or
+4.2-3.5 cm). Transmitter output powers of up to 400 kW are
+available.
+
+Ground stations have the ability to transmit coded and uncoded
+waveforms which can be echoed by distant spacecraft. Analysis
+of the received coding allows navigators to determine the
+distance to the spacecraft; analysis of Doppler shift on the
+carrier signal allows estimation of the line-of-sight
+spacecraft velocity. Range and Doppler measurements are used
+to calculate the spacecraft trajectory and to infer gravity
+fields of objects near the spacecraft.
+
+Ground stations can record spacecraft signals that have
+propagated through or been scattered from target media.
+Measurements of signal parameters after wave interactions with
+surfaces, atmospheres, rings, and plasmas are used to infer
+physical and electrical properties of the target.
+
+Principal investigators vary from experiment to experiment.
+See the corresponding section of the spacecraft instrument
+description or the data set description for specifics.
+
+The Deep Space Network is managed by the Jet Propulsion
+Laboratory of the California Institute of Technology for the
+U.S. National Aeronautics and Space Administration.
+Specifications include:
+
+Instrument Id : RSS
+Instrument Host Id : DSN
+Pi Pds User Id : N/A
+Instrument Name : RADIO SCIENCE SUBSYSTEM
+Instrument Type : RADIO SCIENCE
+Build Date : N/A
+Instrument Mass : N/A
+Instrument Length : N/A
+Instrument Width : N/A
+Instrument Height : N/A
+Instrument Manufacturer Name : N/A
+
+For more information on the Deep Space Network and its use in
+radio science see reports by [ASMAR&RENZETTI1993],
+[ASMAR&HERRERA1993], and [ASMARETAL1995]. For design
+specifications on DSN subsystems see [DSN810-5]. For DSN use
+with MGS Radio Science see [TYLERETAL1992], [TYLERETAL2001],
+and [JPLD-14027].
+
+
+# Subsystems - DSN
+
+The Deep Space Communications Complexes (DSCCs) are an integral
+part of Radio Science instrumentation, along with the spacecraft
+Radio Frequency Subsystem. Their system performance directly
+determines the degree of success of Radio Science
+investigations, and their system calibration determines the
+degree of accuracy in the results of the experiments. The
+following paragraphs describe the functions performed by the
+individual subsystems of a DSCC. This material has been adapted
+from [ASMAR&HERRERA1993] and [JPLD-14027]; for additional
+information, consult [DSN810-5].
+
+Each DSCC includes a set of antennas, a Signal Processing
+Center (SPC), and communication links to the Jet Propulsion
+Laboratory (JPL). The general configuration is illustrated
+below; antennas (Deep Space Stations, or DSS -- a term carried
+over from earlier times when antennas were individually
+instrumented) are listed in the table.
+
+```
+ -------- -------- -------- -------- --------
+ | DSS 25 | | DSS 27 | | DSS 14 | | DSS 15 | | DSS 16 |
+ |34-m BWG| |34-m HSB| | 70-m | |34-m HEF| | 26-m |
+ -------- -------- -------- -------- --------
+ | | | | |
+ | v v | v
+ | --------- | ---------
+ --------->|GOLDSTONE|<---------- |EARTH/ORB|
+ | SPC 10 |<-------------->| LINK |
+ --------- ---------
+ | SPC |<-------------->| 26-M |
+ | COMM | ------>| COMM |
+ --------- | ---------
+ | | |
+ v | v
+ ------ --------- | ---------
+ | NOCC |<--->| JPL |<------- | |
+ ------ | CENTRAL | | GSFC |
+ ------ | COMM | | NASCOMM |
+ | MCCC |<--->| TERMINAL|<-------------->| |
+ ------ --------- ---------
+ ^ ^
+ | |
+ CANBERRA (SPC 40) <---------------- |
+ |
+ MADRID (SPC 60) <----------------------
+
+ GOLDSTONE CANBERRA MADRID
+ Antenna SPC 10 SPC 40 SPC 60
+ -------- --------- -------- --------
+ 26-m DSS 16 DSS 46 DSS 66
+ 34-m HEF DSS 15 DSS 45 DSS 65
+ 34-m BWG DSS 24 DSS 34 DSS 54
+ DSS 25
+ DSS 26
+ 34-m HSB DSS 27
+ DSS 28
+ 70-m DSS 14 DSS 43 DSS 63
+ Developmental DSS 13
+```
+
+
+Subsystem interconnections at each DSCC are shown in the
+diagram below, and they are described in the sections that
+follow. The Monitor and Control Subsystem is connected to all
+other subsystems; the Test Support Subsystem can be.
+
+```
+ ----------- ------------------ --------- ---------
+ |TRANSMITTER| | | | TRACKING| | COMMAND |
+ | SUBSYSTEM |-| RECEIVER/EXCITER |-|SUBSYSTEM|-|SUBSYSTEM|-
+ ----------- | | --------- --------- |
+ | | SUBSYSTEM | | | |
+ ----------- | | --------------------- |
+ | MICROWAVE | | | | TELEMETRY | |
+ | SUBSYSTEM |-| |-| SUBSYSTEM |-
+ ----------- ------------------ --------------------- |
+ | |
+ ----------- ----------- --------- -------------- |
+ | ANTENNA | | MONITOR | | TEST | | DIGITAL | |
+ | SUBSYSTEM | |AND CONTROL| | SUPPORT | |COMMUNICATIONS|-
+ ----------- | SUBSYSTEM | |SUBSYSTEM| | SUBSYSTEM |
+ ----------- --------- --------------
+```
+
+## DSCC Monitor and Control Subsystem
+
+The DSCC Monitor and Control Subsystem (DMC) is part of the
+Monitor and Control System (MON) which also includes the
+ground communications Central Communications Terminal and the
+Network Operations Control Center (NOCC) Monitor and Control
+Subsystem. The DMC is the center of activity at a DSCC. The
+DMC receives and archives most of the information from the
+NOCC needed by the various DSCC subsystems during their
+operation. Control of most of the DSCC subsystems, as well
+as the handling and displaying of any responses to control
+directives and configuration and status information received
+from each of the subsystems, is done through the DMC. The
+effect of this is to centralize the control, display, and
+archiving functions necessary to operate a DSCC.
+Communication among the various subsystems is done using a
+Local Area Network (LAN) hooked up to each subsystem via a
+network interface unit (NIU).
+
+
+## DSCC Antenna Mechanical Subsystem
+
+Multi-mission Radio Science activities require support from
+the 70-m, 34-m HEF, and 34-m BWG antenna subnets. The
+antennas at each DSCC function as large-aperture collectors
+which, by double reflection, cause the incoming radio
+frequency (RF) energy to enter the feed horns. The large
+collecting surface of the antenna focuses the incoming energy
+onto a subreflector, which is adjustable in both axial and
+angular position. These adjustments are made to correct for
+gravitational deformation of the antenna as it moves between
+zenith and the horizon; the deformation can be as large as
+5 cm. The subreflector adjustments optimize the channeling
+of energy from the primary reflector to the subreflector
+and then to the feed horns. The 70-m and 34-m HEF antennas
+have 'shaped' primary and secondary reflectors, with forms
+that are modified paraboloids. This customization allows
+more uniform illumination of one reflector by another. The
+BWG reflector shape is ellipsoidal.
+
+On the 70-m antennas, the subreflector directs
+received energy from the antenna onto a dichroic plate, a
+device which reflects S-band energy to the S-band feed horn
+and passes X-band energy through to the X-band feed horn. In
+the 34-m HEF, there is one 'common aperture feed,' which
+accepts both frequencies without requiring a dichroic plate.
+In the 34-m BWG, a series of small mirrors (approximately 2.5
+meters in diameter) directs microwave energy from the
+subreflector region to a collection area at the base of
+the antenna -- typically in a pedestal room. A retractable
+dichroic reflector separates S- and X-band on some BWG
+antennas or X- and Ka-band on others. RF energy to be
+transmitted into space by the horns is focused by the
+reflectors into narrow cylindrical beams, pointed with high
+precision (either to the dichroic plate or directly to the
+subreflector) by a series of drive motors and gear trains
+that can rotate the movable components and their support
+structures.
+
+The different antennas can be pointed by several means. Two
+pointing modes commonly used during tracking passes are
+CONSCAN and 'blind pointing.' With CONSCAN enabled and a
+closed loop receiver locked to a spacecraft signal, the
+system tracks the radio source by conically scanning around
+its position in the sky. Pointing angle adjustments are
+computed from signal strength information (feedback) supplied
+by the receiver. In this mode the Antenna Pointing Assembly
+(APA) generates a circular scan pattern which is sent to the
+Antenna Control System (ACS). The ACS adds the scan pattern
+to the corrected pointing angle predicts. Software in the
+receiver-exciter controller computes the received signal
+level and sends it to the APA. The correlation of scan
+position with the received signal level variations allows the
+APA to compute offset changes which are sent to the ACS.
+Thus, within the capability of the closed-loop control
+system, the scan center is pointed precisely at the apparent
+direction of the spacecraft signal source. An additional
+function of the APA is to provide antenna position angles and
+residuals, antenna control mode/status information, and
+predict-correction parameters to the Area Routing Assembly
+(ARA) via the LAN, which then sends this information to JPL
+via the Ground Communications Facility (GCF) for antenna
+status monitoring.
+
+During periods when excessive signal level dynamics or low
+received signal levels are expected (e.g., during an
+occultation experiment), CONSCAN should not be used. Under
+these conditions, blind pointing (CONSCAN OFF) is used, and
+pointing angle adjustments are based on a predetermined
+Systematic Error Correction (SEC) model.
+
+Independent of CONSCAN state, subreflector motion in at least
+the z-axis may introduce phase variations into the received
+Radio Science data. For that reason, during certain
+experiments, the subreflector in the 70-m and 34-m HEFs may
+be frozen in the z-axis at a position (often based on
+elevation angle) selected to minimize phase change and signal
+degradation. This can be done via Operator Control Inputs
+(OCIs) from the LMC to the Subreflector Controller (SRC)
+which resides in the alidade room of the antennas. The SRC
+passes the commands to motors that drive the subreflector to
+the desired position.
+
+Pointing angles for all antenna types are computed by
+the NOCC Support System (NSS) from an ephemeris provided by
+the flight project. These predicts are received and archived
+by the CMC. Before each track, they are transferred to the
+APA, which transforms the direction cosines of the predicts
+into AZ-EL coordinates. The LMC operator then downloads the
+antenna predict points to the antenna-mounted ACS computer
+along with a selected SEC model. The pointing predicts
+consist of time-tagged AZ-EL points at selected time intervals
+along with polynomial coefficients for interpolation between
+points.
+
+The ACS automatically interpolates the predict points,
+corrects the pointing predicts for refraction and
+subreflector position, and adds the proper systematic error
+correction and any manually entered antenna offsets. The ACS
+then sends angular position commands for each axis at the
+rate of one per second. In the 70-m and 34-m HEF, rate
+commands are generated from the position commands at the
+servo controller and are subsequently used to steer the
+antenna.
+
+When not using binary predicts (the routine mode for
+spacecraft tracking), the antennas can be pointed using
+'planetary mode' -- a simpler mode which uses right ascension
+(RA) and declination (DEC) values. These change very slowly
+with respect to the celestial frame. Values are provided to
+the station in text form for manual entry. The ACS
+quadratically interpolates among three RA and DEC points
+which are on one-day centers.
+
+A third pointing mode -- sidereal -- is available for
+tracking radio sources fixed with respect to the celestial
+frame.
+
+Regardless of the pointing mode being used, a 70-m antenna
+has a special high-accuracy pointing capability called
+'precision' mode. A pointing control loop derives the
+main AZ-EL pointing servo drive error signals from a two-
+axis autocollimator mounted on the Intermediate Reference
+Structure. The autocollimator projects a light beam to a
+precision mirror mounted on the Master Equatorial drive
+system, a much smaller structure, independent of the main
+antenna, which is exactly positioned in HA and DEC with shaft
+encoders. The autocollimator detects elevation/cross-
+elevation errors between the two reference surfaces by
+measuring the angular displacement of the reflected light
+beam. This error is compensated for in the antenna servo by
+moving the antenna in the appropriate AZ-EL direction.
+Pointing accuracies of 0.004 degrees (15 arc seconds) are
+possible in 'precision' mode. The 'precision' mode is not
+available on 34-m antennas -- nor is it needed, since their
+beamwidths are twice as large as on the 70-m antennas.
+
+
+## DSCC Antenna Microwave Subsystem
+
+70-m Antennas: Each 70-m antenna has three feed cones
+installed in a structure at the center of the main reflector.
+The feeds are positioned 120 degrees apart on a circle.
+Selection of the feed is made by rotation of the
+subreflector. A dichroic mirror assembly, half on the S-band
+cone and half on the X-band cone, permits simultaneous use of
+the S- and X-band frequencies. The third cone is devoted to
+R&D and more specialized work.
+
+The Antenna Microwave Subsystem (AMS) accepts the received S-
+and X-band signals at the feed horn and transmits them
+through polarizer plates to an orthomode transducer. The
+polarizer plates are adjusted so that the signals are
+directed to a pair of redundant amplifiers for each
+frequency, thus allowing simultaneous reception of signals in
+two orthogonal polarizations. For S-band these are two Block
+IVA S-band Traveling Wave Masers (TWMs); for X-band the
+amplifiers are Block IIA TWMs.
+
+34-m HEF Antennas: The 34-m HEF uses a single feed for both
+S- and X-band. Simultaneous S- and X-band receive as well as
+X-band transmit is possible thanks to the presence of an S/X
+'combiner' which acts as a diplexer. For S-band, RCP or LCP
+is user selected through a switch so neither a polarizer nor
+an orthomode transducer is needed. X-band amplification
+options include two Block II TWMs or an HEMT Low Noise
+Amplifier (LNA). S-band amplification is provided by an FET
+LNA.
+
+34-m BWG Antennas: These antennas use feeds and low-noise
+amplifiers (LNA) in the pedestal room, which can be switched
+in and out as needed. Typically the following modes are
+available:
+
+1. downlink non-diplexed path (RCP or LCP) to LNA-1, with
+uplink in the opposite circular polarization;
+2. downlink non-diplexed path (RCP or LCP) to LNA-2, with
+uplink in the opposite circular polarization
+3. downlink diplexed path (RCP or LCP) to LNA-1, with
+uplink in the same circular polarization
+4. downlink diplexed path (RCP or LCP) to LNA-2, with
+uplink in the same circular polarization
+For BWG antennas with dual-band capabilities (e.g., DSS 25)
+and dual LNAs, each of the above four modes can be used in a
+single-frequency or dual-frequency configuration. Thus, for
+antennas with the most complete capabilities, there are
+sixteen possible ways to receive at a single frequency
+(2 polarizations, 2 waveguide path choices, 2 LNAs, and 2
+bands).
+
+
+## DSCC Receiver-Exciter Subsystem
+
+The Receiver-Exciter Subsystem is composed of two groups of
+equipment: the closed-loop receiver group and the open-loop
+receiver group. This subsystem is controlled by the
+Receiver-Exciter Controller (REC) which communicates
+directly with the DMC for predicts and OCI reception and
+status reporting.
+
+The exciter generates the S-band signal (or X-band for the
+34-m HEF only) which is provided to the Transmitter Subsystem
+for the spacecraft uplink signal. It is tunable under
+command of the Digitally Controlled Oscillator (DCO) which
+receives predicts from the Metric Data Assembly (MDA).
+
+The diplexer in the signal path between the transmitter and
+the feed horn for all three antennas (used for simultaneous
+transmission and reception) may be configured such that it is
+out of the received signal path (in listen-only or bypass
+mode) in order to improve the signal-to-noise ratio in the
+receiver system.
+
+Closed Loop Receivers: The Block V receiver-exciter at the
+70-m stations allows for two receiver channels, each capable
+of L-Band (e.g., 1668 MHz frequency or 18 cm wavelength),
+S-band, or X-band reception, and an S-band exciter for
+generation of uplink signals through the low-power or
+high-power transmitter.
+
+The closed-loop receivers provide the capability for rapid
+acquisition of a spacecraft signal and telemetry lockup. In
+order to accomplish acquisition within a short time, the
+receivers are predict driven to search for, acquire, and
+track the downlink automatically. Rapid acquisition
+precludes manual tuning though that remains as a backup
+capability. The subsystem utilizes FFT analyzers for rapid
+acquisition. The predicts are NSS generated, transmitted to
+the CMC which sends them to the Receiver-Exciter Subsystem
+where two sets can be stored. The receiver starts
+acquisition at uplink time plus one round-trip-light-time or
+at operator specified times. The receivers may also be
+operated from the LMC without a local operator attending
+them. The receivers send performance and status data,
+displays, and event messages to the LMC.
+
+Either the exciter synthesizer signal or the simulation
+(SIM) synthesizer signal is used as the reference for the
+Doppler extractor in the closed-loop receiver systems,
+depending on the spacecraft being tracked (and Project
+guidelines). The SIM synthesizer is not ramped; instead it
+uses one constant frequency, the Track Synthesizer Frequency
+(TSF), which is an average frequency for the entire pass.
+
+The closed-loop receiver AGC loop can be configured to one
+of three settings: narrow, medium, or wide. It will be
+configured such that the expected amplitude changes are
+accommodated with minimum distortion. The loop bandwidth
+(2BLo) will be configured such that the expected phase
+changes can be accommodated while maintaining the best
+possible loop SNR.
+
+Open-Loop Receivers (OLR): The OLR utilized a fixed first
+Local Oscillator (LO) frequency and a tunable second LO
+frequency to minimize phase noise and improve frequency
+stability. The OLR consisted of an RF-to-IF downconverter
+located at the feed , an IF selection switch (IFS), and a
+Radio Science Receiver (RSR). The RF-IF downconverters
+in the 70-m antennas were equipped for four IF channels:
+S-RCP, S-LCP, X-RCP, and X-LCP. The 34-m HEF stations
+were equipped with a two-channel RF-IF: S-band and X-band.
+The IFS switched the IF input among the antennas.
+
+
+## DSCC Transmitter Subsystem
+
+The Transmitter Subsystem accepts the S-band frequency
+exciter signal from the Receiver-Exciter Subsystem exciter
+and amplifies it to the required transmit output level. The
+amplified signal is routed via the diplexer through the feed
+horn to the antenna and then focused and beamed to the
+spacecraft.
+
+The Transmitter Subsystem power capabilities range from 18 kW
+to 400 kW. Power levels above 18 kW are available only at
+70-m stations.
+
+
+## DSCC Tracking Subsystem
+
+The Tracking Subsystem primary functions are to acquire and
+maintain communications with the spacecraft and to generate
+and format radiometric data containing Doppler and range.
+
+The DSCC Tracking Subsystem (DTK) receives the carrier
+signals and ranging spectra from the Receiver-Exciter
+Subsystem. The Doppler cycle counts are counted, formatted,
+and transmitted to JPL in real time. Ranging data are also
+transmitted to JPL in real time. Also contained in these
+blocks is the AGC information from the Receiver-Exciter
+Subsystem. The Radio Metric Data Conditioning Team (RMDCT)
+at JPL produces an Archival Tracking Data File (ATDF) which
+contains Doppler and ranging data.
+
+In addition, the Tracking Subsystem receives from the CMC
+frequency predicts (used to compute frequency residuals and
+noise estimates), receiver tuning predicts (used to tune the
+closed-loop receivers), and uplink tuning predicts (used to
+tune the exciter). From the LMC, it receives configuration
+and control directives as well as configuration and status
+information on the transmitter, microwave, and frequency and
+timing subsystems.
+
+The Metric Data Assembly (MDA) controls all of the DTK
+functions supporting the uplink and downlink activities. The
+MDA receives uplink predicts and controls the uplink tuning
+by commanding the DCO. The MDA also controls the Sequential
+Ranging Assembly (SRA). It formats the Doppler and range
+measurements and provides them to the GCF for transmission to
+NOCC.
+
+The Sequential Ranging Assembly (SRA) measures the round trip
+light time (RTLT) of a radio signal traveling from a ground
+tracking station to a spacecraft and back. From the RTLT,
+phase, and Doppler data, the spacecraft range can be
+determined. A coded signal is modulated on an uplink carrier
+and transmitted to the spacecraft where it is detected and
+transponded back to the ground station. As a result, the
+signal received at the tracking station is delayed by its
+round trip through space and shifted in frequency by the
+Doppler effect due to the relative motion between the
+spacecraft and the tracking station on Earth.
+
+
+## DSCC Frequency and Timing Subsystem
+
+The Frequency and Timing Subsystem (FTS) provides all
+frequency and timing references required by the other DSCC
+subsystems. It contains four frequency standards of which
+one is prime and the other three are backups. Selection of
+the prime standard is done via the CMC. Of these four
+standards, two are hydrogen masers followed by clean-up loops
+(CUL) and two are cesium standards. These four standards all
+feed the Coherent Reference Generator (CRG) which provides
+the frequency references used by the rest of the complex. It
+also provides the frequency reference to the Master Clock
+Assembly (MCA) which in turn provides time to the Time
+Insertion and Distribution Assembly (TID) which provides UTC
+and SIM-time to the complex.
+
+JPL's ability to monitor the FTS at each DSCC is limited to
+the MDA calculated Doppler pseudo-residuals, the Doppler
+noise, the SSI, and to a system which uses the Global
+Positioning System (GPS). GPS receivers at each DSCC receive
+a one-pulse-per-second pulse from the station's (hydrogen
+maser referenced) FTS and a pulse from a GPS satellite at
+scheduled times. After compensating for the satellite signal
+delay, the timing offset is reported to JPL where a database
+is kept. The clock offsets stored in the JPL database are
+given in microseconds; each entry is a mean reading of
+measurements from several GPS satellites and a time tag
+associated with the mean reading. The clock offsets provided
+include those of SPC 10 relative to UTC (NIST), SPC 40
+relative to SPC 10, etc.
+
+
+## Radio Science Receiver (RSR)
+
+A radio frequency (RF) spacecraft signal at S-band, X-band,
+or Ka-band is captured by a receiving antenna on Earth, down
+converted to an intermediate frequency (IF) near 300 MHz and
+then fed via a distribution network to one input of an IF
+Selector Switch (IFS). The IFS allows each RSR to select any
+of the available input signals for its RSR Digitizer (DIG).
+Within the RSR the digitized signal is then passed to the
+Digitial Down Converter (DDC), VME Data Processor (VDP), and
+Data Processor (DP) [JPLD-16765].
+
+```
+ \ ----------- ------ ----- ----- -----
+ \ | RF TO IF | | |----| | | | | |
+ |----| DOWN |----| |----| |----| DIG | | DP |
+ / | CONVERTER | | |----| | | | | |
+ / ----------- | IF |----| IFS | ----- -----
+ ANTENNA --| DIST |----| | | |
+ 300 MHz IF --| | .. | | ----- -----
+ FROM OTHER --| |----| | | | | |
+ ANTENNAS --| | ----- | DDC | | VDP |
+ ------ | | | |
+ ----- -----
+ | |
+ -------
+```
+
+In the DIG the IF signal is passed through a programmable
+attenuator, adjusted to provide the proper level to the Analog
+to Digital Converter (ADC). The attenuated signal is then
+passed through a Band Pass Filter (BPF) which selects a
+frequency band in the range 265-375 MHz. The filtered output
+from the BPF is then mixed with a 256 MHz Local Oscillator
+(LO), low pass filtered (LPF), and sampled by the ADC. The
+output of the ADC is a stream of 8-bit real samples at 256
+Msamples/second (Msps). DIG timing is derived from the
+station FTS 5 MHz clock and 1 pulse per second (1PPS)
+reference; the DIG generates a 256 MHz clock signal for later
+processing. The 1PPS signal marks the data sample taken at
+the start of each second.
+
+The DDC selects one 16 MHz subchannel from the possible 128
+MHz bandwidth available from the DIG by using Finite Impulse
+Response (FIR) filters with revolving banks of filter
+coefficients. The sample stream from the DIG is separated
+into eight decimated streams, each of which is fed into two
+sets of FIR filters. One set of filters produces in-phase (I)
+8-bit data while the other produces quadrature-phase (Q) 8-bit
+data. The center frequency of the desired 16 MHz channel is
+adjustable in 1 MHz steps and is usually chosen to be near the
+spacecraft carrier frequency. After combining the I and Q
+sample streams, the DDC feeds the samples to the VDP. The DDC
+also converts the 256 MHz data clock and 1PPS signals into a
+msec time code, which is also passed to the VDP.
+
+The VDP contains a quadruply-redundant set of custom boards
+which are controlled by a real-time control computer (RT).
+Each set of boards comprises a numerically controlled
+oscillator (NCO), a complex multiplier, a decimating FIR
+filter, and a data packer. The 16 Msps complex samples
+from the DDC are digitally mixed with the NCO signal in the
+complex multiplier. The NCO phase and frequency are updated
+every millisecond by the RT and are selected so that the
+center frequency of the desired portion of the 16 MHz channel
+is down-converted to 0 Hz. The RT uses polynomials derived
+from frequency predictions. The output of the complex
+multiplier is sent to the decimating FIR filter where its
+bandwidth and sample rate are reduced (see table below). The
+decimating FIR filter also allows adjustment of the
+sub-channel gain to take full advantage of the dynamic range
+available in the hardware. The data packer truncates samples
+to 1, 2, 4, 8, or 16 bits by dropping the least significant
+bits and packs them into 32-bit data words. Q-samples are
+packed into the first 16 bits of the word, and I-samples into
+the least significant 16 bits (see below). In 'narrow band'
+operation all four sets of sets of custom boards can be
+supported simultaneously. In 'medium band' operation no more
+than two channels can be supported simultaneously. In
+'wide band' operation, only one sub-channel can be recorded.
+
+```
+|============================================================|
+| RSR Sample Rates and Sample Sizes Supported |
+|================+=======+======+=================+==========|
+| Category | Rate | Size | Data Rate |Rec Length|
+| | (ksps)|(bits)|(bytes/s) (rec/s)| (bytes) |
+|================+=======+======+=========+=======+==========|
+|Narrow Band (NB)| 1 | 8 | 2000 | 1 | 2000 |
+| | 2 | 8 | 4000 | 1 | 4000 |
+| | 4 | 8 | 8000 | 1 | 8000 |
+| | 8 | 8 | 16000 | 1 | 16000 |
+| | 16 | 8 | 32000 | 2 | 16000 |
+| | 25 | 8 | 50000 | 2 | 25000 |
+| | 50 | 8 | 100000 | 4 | 25000 |
+| | 100 | 8 | 200000 | 10 | 20000 |
+| | 1 | 16 | 4000 | 1 | 4000 |
+| | 2 | 16 | 8000 | 1 | 8000 |
+| | 4 | 16 | 16000 | 1 | 16000 |
+| | 8 | 16 | 32000 | 2 | 16000 |
+| | 16 | 16 | 64000 | 4 | 16000 |
+| | 25 | 16 | 100000 | 4 | 25000 |
+| | 50 | 16 | 200000 | 10 | 20000 |
+| | 100 | 16 | 400000 | 20 | 20000 |
+|Medium Band (MB)| 250 | 1 | 62500 | 5 | 12500 |
+| | 500 | 1 | 125000 | 5 | 25000 |
+| | 1000 | 1 | 250000 | 10 | 25000 |
+| | 2000 | 1 | 500000 | 20 | 25000 |
+| | 4000 | 1 | 1000000 | 40 | 25000 |
+| | 250 | 2 | 125000 | 5 | 25000 |
+| | 500 | 2 | 250000 | 10 | 25000 |
+| | 1000 | 2 | 500000 | 20 | 25000 |
+| | 2000 | 2 | 1000000 | 40 | 25000 |
+| | 4000 | 2 | 2000000 | 100 | 20000 |
+| | 250 | 4 | 250000 | 10 | 25000 |
+| | 500 | 4 | 500000 | 20 | 25000 |
+| | 1000 | 4 | 1000000 | 40 | 25000 |
+| | 2000 | 4 | 2000000 | 100 | 20000 |
+| | 250 | 8 | 500000 | 20 | 25000 |
+| | 500 | 8 | 1000000 | 40 | 25000 |
+| | 1000 | 8 | 2000000 | 100 | 20000 |
+|Wide Band (WB) | 8000 | 1 | 2000000 | 100 | 20000 |
+| | 16000 | 1 | 4000000 | 200 | 20000 |
+| | 8000 | 2 | 4000000 | 200 | 20000 |
+|============================================================|
+
+|============================================================|
+| Sample Packing |
+|=================+==========================================|
+| Bits per Sample | Contents of 32-bit Packed Data Register |
+|=================+==========================================|
+| 16 | (Q1),(I1) |
+| 8 | (Q2,Q1),(I2,I1) |
+| 4 | (Q4,Q3,Q2,Q1),(I4,I3,I2,I1) |
+| 2 | (Q8,Q7,...Q1),(I8,I7,...I1) |
+| 1 | (Q16,Q15,...Q1),(I16,I15,...I1) |
+|============================================================|
+```
+
+Once per second the RT sends the accumulated data records from
+each sub-channel to the Data Processor (DP) over a 100 Mbit/s
+ethernet connection. In addition to the samples, each data
+record includes header information such as time tags and NCO
+frequency and phase that are necessary for analysis. The DP
+processes the data records to provide monitor data, such as
+power spectra. If recording has been enabled, the records are
+stored by the DP.
+
+# NCO Phase and Frequency
+
+At the start of each DSN pass, the RSR is provided with a
+file containing a list of predicted frequencies. Using these
+points, the RT computes expected sky frequencies at the
+beginning, middle, and end of each one second time interval.
+Based on the local oscillator frequencies selected and any
+offsets entered, the RT computes the coefficients of a
+frequency polynomial fitted to the DDC channel frequencies
+at these three times. The RT also computes a phase
+polynomial by integrating the frequency polynomial and
+matching phases at the one second boundaries.
+
+The phase and frequency of the VDP NCO's are computed every
+millisecond (000-999) from the polynomial coefficients as
+follows:
+
+```
+nco_phase(msec) = phase_coef_1 +
+phase_coef_2 * (msec/1000) +
+phase_coef_3 * (msec/1000)**2 +
+phase_coef_4 * (msec/1000)**3
+
+nco_freq(msec) = freq_coef_1 +
+freq_coef_2 * ((msec + 0.5)/1000) +
+freq_coef_3 * ((msec + 0.5)/1000)**2
+```
+
+The sky frequency may be reconstructed using
+
+```
+sky_freq = RF_to_IF_LO +
+DDC_LO -
+nco_freq +
+reside_freq
+```
+
+where RF_to_IF_LO is the down conversion from the
+microwave frequency to IF (bytes 42-43
+in the data record header)
+DDC_LO is the down-conversion applied in the
+DIG and DDC (bytes 40-41 in the data
+record header)
+Resid_Freq is the frequency of the signal in the
+VDP output
+
+
+# Detectors - DSN
+
+Nominal carrier tracking loop threshold noise bandwidth at
+X-band is 10 Hz. Coherent (two-way) closed-loop
+system stability is shown in the table below:
+
+```
+ integration time Doppler uncertainty
+ (secs) (one sigma, microns/sec)
+ ------ ------------------------
+ 10 50
+ 60 20
+ 1000 4
+```
+
+For the open-loop subsystem, signal detection is done in
+software.
+
+
+# Calibration - DSN
+
+Calibrations of hardware systems are carried out periodically
+by DSN personnel; these ensure that systems operate at required
+performance levels -- for example, that antenna patterns,
+receiver gain, propagation delays, and Doppler uncertainties
+meet specifications. No information on specific calibration
+activities is available. Nominal performance specifications
+are shown in the tables above. Additional information may be
+available in [DSN810-5].
+
+Prior to each tracking pass, station operators perform a series
+of calibrations to ensure that systems meet specifications for
+that operational period. Included in these calibrations is
+measurement of receiver system temperature in the configuration
+to be employed during the pass. Results of these calibrations
+are recorded in (hard copy) Controller's Logs for each pass.
+
+The nominal procedure for initializing open-loop receiver
+attenuator settings is described below. In cases where widely
+varying signal levels are expected, the procedure may be
+modified in advance or real-time adjustments may be made to
+attenuator settings.
+
+
+# Operational Considerations - DSN
+
+The DSN is a complex and dynamic 'instrument.' Its performance
+for Radio Science depends on a number of factors from equipment
+configuration to meteorological conditions. No specific
+information on 'operational considerations' can be given here.
+
+
+# Operational Modes - DSN
+
+
+## DSCC Antenna Mechanical Subsystem
+
+Pointing of DSCC antennas may be carried out in several ways.
+For details see the subsection 'DSCC Antenna Mechanical
+Subsystem' in the 'Subsystem' section. Binary pointing is
+the preferred mode for tracking spacecraft; pointing
+predicts are provided, and the antenna simply follows those.
+With CONSCAN, the antenna scans conically about the optimum
+pointing direction, using closed-loop receiver signal
+strength estimates as feedback. In planetary mode, the
+system interpolates from three (slowly changing) RA-DEC
+target coordinates; this is 'blind' pointing since there is
+no feedback from a detected signal. In sidereal mode, the
+antenna tracks a fixed point on the celestial sphere. In
+'precision' mode, the antenna pointing is adjusted using an
+optical feedback system. It is possible on most antennas to
+freeze z-axis motion of the subreflector to minimize phase
+changes in the received signal.
+
+
+## DSCC Receiver-Exciter Subsystem
+
+The diplexer in the signal path between the transmitter and
+the feed horns on all antennas may be configured so
+that it is out of the received signal path in order to
+improve the signal-to-noise ratio in the receiver system.
+This is known as the 'listen-only' or 'bypass' mode.
+
+
+## Closed-Loop Receiver AGC Loop
+
+The closed-loop receiver AGC loop can be configured to one of
+three settings: narrow, medium, or wide. Ordinarily it is
+configured so that expected signal amplitude changes are
+accommodated with minimum distortion. The loop bandwidth is
+ordinarily configured so that expected phase changes can be
+accommodated while maintaining the best possible loop SNR.
+
+
+## Coherent vs. Non-Coherent Operation
+
+The frequency of the signal transmitted from the spacecraft
+can generally be controlled in two ways -- by locking to a
+signal received from a ground station or by locking to an
+on-board oscillator. These are known as the coherent (or
+'two-way') and non-coherent ('one-way') modes, respectively.
+Mode selection is made at the spacecraft, based on commands
+received from the ground. When operating in the coherent
+mode, the transponder carrier frequency is derived from the
+received uplink carrier frequency with a 'turn-around ratio'
+typically of 880/749. In the non-coherent mode, the
+downlink carrier frequency is derived from the spacecraft
+on-board crystal-controlled oscillator. Either closed-loop
+or open-loop receivers (or both) can be used with either
+spacecraft frequency reference mode. Closed-loop reception
+in two-way mode is usually preferred for routine tracking.
+Occasionally the spacecraft operates coherently while two
+ground stations receive the 'downlink' signal; this is
+sometimes known as the 'three-way' mode.
+
+
+# Location - DSN
+
+Station locations are documented in [GEO-10REVD]. Geocentric
+coordinates are summarized here.
+
+```
+ Geocentric Geocentric Geocentric
+ Station Radius (km) Latitude (N) Longitude (E)
+ --------- ----------- ------------ -------------
+ Goldstone
+ DSS 13 (34-m R&D) 6372.125125 35.0660185 243.2055430
+ DSS 14 (70-m) 6371.993286 35.2443527 243.1104638
+ DSS 15 (34-m HEF) 6371.966540 35.2403133 243.1128069
+ DSS 24 (34-m BWG) 6371.973553 35.1585349 243.1252079
+ DSS 25 (34-m BWG) 6371.983060 35.1562594 243.1246384
+ DSS 26 (34-m BWG) 6371.993032 35.1543411 243.1269849
+
+ Canberra
+ DSS 34 (34-m BWG) 6371.693561 -35.2169868 148.9819620
+ DSS 43 (70-m) 6371.689033 -35.2209234 148.9812650
+ DSS 45 (34-m HEF) 6371.675906 -35.2169652 148.9776833
+
+ Madrid
+ DSS 45 (34-m BWG) 6370.025429 40.2357708 355.7459008
+ DSS 63 (70-m) 6370.051221 40.2413537 355.7519890
+ DSS 65 (34-m HEF) (see next paragraph)
+
+ The coordinates for DSS 65 until 1 February 2005 were
+ 6370.021697 40.2373325 355.7485795
+ In cartesian coordinates (x, y, z) this was
+ (+4849336.6176, -0360488.6349, +4114748.9218)
+ Between February and September 2005, the antenna was
+ physically moved to
+ (+4849339.6448, -0360427.6560, +4114750.7428)
+```
+
+# Measurement Parameters - DSN
+
+Closed-loop data are recorded in Archival Tracking Data Files
+(ATDFs), as well as certain secondary products such as the
+Orbit Data File (ODF). The ATDF Tracking Logical Record
+contains 150 entries including status information and
+measurements of ranging, Doppler, and signal strength.
+
+
+# ACRONYMS AND ABBREVIATIONS - DSN
+
+```
+ACS Antenna Control System
+ADC Analog-to-Digital Converter
+AGC Automatic Gain Control
+AMS Antenna Microwave System
+APA Antenna Pointing Assembly
+ARA Area Routing Assembly
+ATDF Archival Tracking Data File
+AUX Auxiliary
+AZ Azimuth
+BPF Band Pass Filter
+bps bits per second
+BWG Beam WaveGuide (antenna)
+CDU Command Detector Unit
+CMC Complex Monitor and Control
+CONSCAN Conical Scanning (antenna pointing mode)
+CRG Coherent Reference Generator
+CUL Clean-up Loop
+DANA a type of frequency synthesizer
+dB deciBel
+dBi dB relative to isotropic
+dBm dB relative to one milliwatt
+DCO Digitally Controlled Oscillator
+DDC Digital Down Converter
+DEC Declination
+deg degree
+DIG RSR Digitizer
+DMC DSCC Monitor and Control Subsystem
+DOR Differential One-way Ranging
+DP Data Processor
+DSCC Deep Space Communications Complex
+DSN Deep Space Network
+DSP DSCC Spectrum Processing Subsystem
+DSS Deep Space Station
+DTK DSCC Tracking Subsystem
+E east
+EIRP Effective Isotropic Radiated Power
+EL Elevation
+FET Field Effect Transistor
+FFT Fast Fourier Transform
+FIR Finite impulse Response
+FTS Frequency and Timing Subsystem
+GCF Ground Communications Facility
+GHz Gigahertz
+GPS Global Positioning System
+HA Hour Angle
+HEF High-Efficiency (as in 34-m HEF antennas)
+HEMT High Electron Mobility Transistor (amplifier)
+HGA High-Gain Antenna
+HSB High-Speed BWG
+IF Intermediate Frequency
+IFS IF Selector Switch
+IVC IF Selection Switch
+JPL Jet Propulsion Laboratory
+K Kelvin
+Ka-Band approximately 32 GHz
+KaBLE Ka-Band Link Experiment
+kbps kilobits per second
+kHz kilohertz
+km kilometer
+kW kilowatt
+LAN Local Area Network
+LCP Left-Circularly Polarized
+LGR Low-Gain Receive (antenna)
+LGT Low-Gain Transmit (antenna)
+LMA Lockheed Martin Astronautics
+LMC Link Monitor and Control
+LNA Low-Noise Amplifier
+LO Local Oscillator
+LPF Low Pass Filter
+m meters
+MCA Master Clock Assembly
+MCCC Mission Control and Computing Center
+MDA Metric Data Assembly
+MGS Mars Global Surveyor
+MHz Megahertz
+MOLA Mars Orbiting Laser Altimeter
+MON Monitor and Control System
+MOT Mars Observer Transponder
+MSA Mission Support Area
+N north
+NAR Noise Adding Radiometer
+NBOC Narrow-Band Occultation Converter
+NCO Numerically Controlled Oscillator
+NIST SPC 10 time relative to UTC
+NIU Network Interface Unit
+NOCC Network Operations and Control System
+NRV NOCC Radio Science/VLBI Display Subsystem
+NSS NOCC Support System
+OCI Operator Control Input
+ODF Orbit Data File
+ODR Original Data Record
+ODS Original Data Stream
+OLR Open Loop Receiver
+OSC Oscillator
+PDS Planetary Data System
+POCA Programmable Oscillator Control Assembly
+PPM Precision Power Monitor
+RA Right Ascension
+REC Receiver-Exciter Controller
+RCP Right-Circularly Polarized
+RF Radio Frequency
+RIC RIV Controller
+RIV Radio Science IF-VF Converter Assembly
+RMDCT Radio Metric Data Conditioning Team
+RMS Root Mean Square
+RSR Radio Science Receiver
+RSS Radio Science Subsystem
+RT Real-Time (control computer)
+RTLT Round-Trip Light Time
+S-band approximately 2100-2300 MHz
+sec second
+SEC System Error Correction
+SIM Simulation
+SLE Signal Level Estimator
+SNR Signal-to-Noise Ratio
+SNT System Noise Temperature
+SOE Sequence of Events
+SPA Spectrum Processing Assembly
+SPC Signal Processing Center
+sps samples per second
+SRA Sequential Ranging Assembly
+SRC Sub-Reflector Controller
+SSI Spectral Signal Indicator
+TID Time Insertion and Distribution Assembly
+TLM Telemetry
+TSF Tracking Synthesizer Frequency
+TWM Traveling Wave Maser
+TWNC Two-Way Non-Coherent
+TWTA Traveling Wave Tube Amplifier
+UNK unknown
+USO UltraStable Oscillator
+UTC Universal Coordinated Time
+VCO Voltage-Controlled Oscillator
+VDP VME Data Processor
+VF Video Frequency
+X-band approximately 7800-8500 MHz
+```
diff --git a/data/pds4/context_support/document/description/ody.rss_description_1.0.rst b/data/pds4/context_support/document/description/ody.rss_description_1.0.rst
new file mode 100644
index 00000000..89a6d1cc
--- /dev/null
+++ b/data/pds4/context_support/document/description/ody.rss_description_1.0.rst
@@ -0,0 +1,1318 @@
+Instrument Overview
+===================
+There were no recognized radio science investigations on
+the 2001 Mars Odyssey (ODY) mission. But investigators on
+Mars Global Surveyor (MGS) requested access to ODY radio
+tracking data. To support them and future proposers to
+Mars data analysis programs (MDAPs), the Planetary Data
+System (PDS) accepted responsibility for archiving the ODY
+data with initial activities funded jointly by MGS.
+
+Radio science investigations utilize instrumentation with
+elements both on a spacecraft and at ground stations -- in
+this case, at the NASA Deep Space Network (DSN). For ODY
+much of this was equipment used for routine telecommunications.
+The performance and calibration of both the spacecraft and
+tracking stations directly affected the radio science data
+accuracy, and they played a major role in determining the
+quality of the results. The spacecraft part of the radio
+science instrument is described immediately below; that is
+followed by a description of the DSN (ground) part of the
+instrument. For more information, see [MAKOVSKY2001].
+
+
+Instrument Specifications - Spacecraft
+======================================
+The 2001 Mars Odyssey spacecraft telecommunications
+subsystem served as part of a radio science subsystem for
+investigations of Mars. Many details of the subsystem are
+unknown; its 'build date' is taken to be 2001-04-01, which
+was near the end of the Prelaunch Phase of the ODY mission.
+
+Instrument Id : RSS
+Instrument Host Id : ODY
+Pi Pds User Id : UNK
+Instrument Name : RADIO SCIENCE SUBSYSTEM
+Instrument Type : RADIO SCIENCE
+Build Date : 2001-04-01
+Instrument Mass : UNK
+Instrument Length : UNK
+Instrument Width : UNK
+Instrument Height : UNK
+Instrument Manufacturer Name : UNK
+
+
+Instrument Overview - Spacecraft
+================================
+The spacecraft radio system was constructed around a
+redundant pair of X-band Small Deep Space Transponders (SDSTs).
+Other components included one low-gain receive antenna (LGA);
+one medium-gain transmit antenna (MGA); one steerable
+high-gain antenna (HGA) for both transmitting (Tx) and receiving
+(Rx); two redundant solid state power amplifiers (SSPAs); a
+diplexer; several switches; and cabling. The SDSTs were
+connected to redundant Command and Data Handling (C&DH) units
+in such a way that any pairing could be chosen. A functional
+block diagram is shown below.
+
+ . . . . . . . .
+ DIPLEXER . .
+ --- . / .
+ ---------------------| |------------/ .
+ | --- . \ HGA .
+ | _ BPF1 | . \ .
+ ----------|_| | . .
+ | | / \ | . / .
+ | |_____| S1 |________________________/ .
+ | \ / . \ MGA .
+ | \_/ | . \ .
+ | |_| | . .
+ | | BPF2 | . .
+ |\| |\| | . HGA ASSEMBLY.
+ | \ | \ | . . . . . . . .
+ | / SSPA_1 | / SSPA_2 | /
+ |/| |/| | /
+ | | | HGA GIMBAL
+ | | | ASSEMBLY
+ --------------- |
+ | 3 dB HYBRID | |
+ | COUPLER | |
+ --------------- |
+ | | |
+ | | |
+ ------ ------ |
+ |SDST_1| |SDST_2| |
+ ------ ------ |
+ | \ / | |
+ | X | |
+ | / \ | -
+ ------ ------ _ / \ _ NF1
+ ---|C&DH_A| |C&DH_B|-------|_| S2 |_|--
+ | ------ ------ NF2 \ / |
+ | - |
+ | | | /
+ | ----------/
+ | | \ LGA
+ ---------------------------------------- \
+
+S1 was a waveguide transfer switch with positions:
+1. SSPA_1 to HGA and SSPA_2 to MGA
+2. SSPA_1 to MGA and SSPA_2 to HGA
+ (Insertion loss, <0.05 dB)
+S2 was a coaxial transfer switch with positions:
+1. SDST_1 to LGA and SDST_2 to HGA
+2. SDST_1 to HGA and SDST_2 to LGA
+ (insertion loss, <0.3 dB)
+BPF_1 and BPF_2 were bandpass filters
+ (<0.2 dB insertion loss over 8400-8450 MHz)
+NF1 and NF2 were notch filters
+ (>70 dB rejection over 8400-8450 MHz)
+The X-Band Diplexer insertion loss was 0.1 DB (Tx), 0.2 dB (Rx)
+
+End-to-end circuit losses are given in the following table:
+
+========================================================
+| Link/Direction | Elements | Value |
++------------------+---------------+-------------------+
+| X-Band Transmit | SSPA to HGA | -0.25 +/- 0.11 dB |
++------------------+---------------+-------------------+
+| X-Band Transmit | SSPA to MGA | -0.52 +/- 0.35 dB |
++------------------+---------------+-------------------+
+| X-Band Receive | HGA to SDST | -8.13 +/- 0.03 dB |
++------------------+---------------+-------------------+
+| X-Band Receive | LGA to SDST | -2.43 +/- 0.02 dB |
+========================================================
+
+SSPA output power design was for 15 W (41.8 dBm) at end of life.
+
+The ODY telecommunications system was designed to perform the
+following functions:
+
+1) Receive an X-band uplink carrier from a DSN station and
+ demodulate the command data and ranging signal if either
+ were present;
+2) Generate an X-band downlink carrier either by coherently
+ multiplying the frequency of the uplink carrier by the
+ turn-around ratio of 880/749 or by utilizing an
+ auxiliary crystal oscillator (AUX OSC);
+3) Phase modulate the downlink carrier with either (or both)
+ of the following:
+ a composite telemetry signal, consisting of a square
+ wave subcarrier (25 kHz or 375 kHz) that was BPSK
+ (binary phase shift keying) modulated by telemetry data
+ provided by the C&DH subsystem;
+ the ranging signal that was demodulated from the uplink
+ (this is referred to as two-way, or turn-around,
+ ranging);
+4) Permit control of the telecom subsystem through commands
+ to select signal routing and the operational mode of the
+ subsystem either from the ground or from command
+ sequences previously loaded on the spacecraft;
+5) Provide telecom status for monitoring operating
+ conditions of the subsystem;
+6) Provide ON/OFF power control for all RF transmitters;
+7) Assume a single well-defined operating mode (a known
+ baseline state) after a Power-On-Reset (POR).
+
+The X-band capability reduced plasma effects on radio
+signals by a factor of 10 compared with older S-band
+systems, but absence of a dual-frequency capability (both
+S- and X-band) meant that plasma effects could not be
+estimated and removed from radio data.
+
+The spacecraft also carried redundant ultra-high frequency (UHF)
+transceivers for communication and relay with future missions.
+Since the UHF equipment was not used for radio science, it is
+not described here.
+
+
+Science Objectives
+==================
+There were no radio science objectives for the 2001 Mars Odyssey
+mission. The radio tracking data could be used by others to
+improve knowledge of the Mars gravity field .
+
+
+Operational Considerations - Spacecraft
+=======================================
+Descriptions given here are for nominal performance. The
+spacecraft transponder system comprised redundant units,
+each with slightly different characteristics. As
+transponder units age, their performance changes slightly.
+More importantly, the performance for radio science depended
+on operational factors such as the modulation state for the
+transmitters, which cannot be predicted in advance. The
+performance also depended on factors which were not always
+under the control of the 2001 Mars Odyssey Project.
+
+The telecom subsystem relied on C&DH to control its operating
+mode; that control could be done via real-time commands from
+the ground or via a stored sequence onboard the spacecraft.
+The only exception was the POR state, which would be entered
+directly after a Power-On-Reset.
+
+C&DH provided the data to be downlinked, it carried out the
+frame and packet formatting and the Reed-Solomon encoding,
+and it provided the clock to drive the encoding. The clock was
+either
+ data clock X 2 for (7,1/2) encoding or
+ data clock X 6 for (15,1/6) encoding
+C&DH also handled error control for the uplink data stream.
+
+
+Calibration Description - Spacecraft
+====================================
+All measurements below were made during the Prelaunch Phase of
+The mission.
+
+Antenna characteristics are listed below. Masses of MGA and
+HGA are combined. Gain and axial ratio are given for boresight.
+Beamwidth is between the 3 dB points.
+
+=========================================================
+| Antenna Characteristics - 2001 Mars Odyssey |
++-----------------+---------+--------+--------+---------+
+| | MGA | HGA | LGA |
+| Parameter +---------+--------+--------+---------|
+| | Tx Only | Tx | Rx | Rx Only |
++-----------------+---------+--------+--------+---------+
+|Frequency (MHz) | 8406.851852 | 7155.377315 |
++-----------------+---------+--------+--------+---------+
+|Diameter (m) | N/A | 1.3 | N/A |
++-----------------+---------+--------+--------+---------+
+|Mass (kg) | 3.150 | 0.040 |
++-----------------+---------+--------+--------+---------+
+|Gain (dBi) | 16.5 | 38.3 | 36.6 | 7+/-4 |
++-----------------+---------+--------+--------+---------+
+|Axial Ratio (dB) | N/A | 1.35 | 1.24 | 3 |
++-----------------+---------+--------+--------+---------+
+|Beamwidth (deg) | 28 | 1.9 | 2.3 | 82 |
+=========================================================
+
+Receiver Carrier Loop characteristics were as follows:
+
+=========================================================
+| Parameter | Value |
++------------------+------------------------------------+
+|Noise Figure | 2.70 +0.60/-0.73 dB averaged over |
+| | lifetime aging, temperature,|
+| | and radiation |
++------------------+------------------------------------|
+|Tracking | -155 to -156 dBm |
+| Threshold | |
++------------------+------------------------------------|
+|Tracking Rate | 200 Hz/s for uplink Pt <= -120 dBm |
++------------------+------------------------------------|
+|Capture Range | +/-1.3 kHz |
++------------------+------------------------------------|
+|Tracking Range | +100 kHz/-200 kHz relative to best |
+| | lock frequency |
++------------------+------------------------------------|
+|Carrier Loop | 20 Hz |
+| Threshold | |
+| Bandwidth | |
++------------------+------------------------------------|
+|Strong Signal Open| 2.0e+07 |
+| Loop Gain | |
++------------------+------------------------------------|
+|Predetection Noise| 12500 Hz |
+| Bandwidth | |
++------------------+------------------------------------|
+|Loop Pole Time | 2258.6 s |
+| Constant | |
++------------------+------------------------------------|
+|Loop Zero Time | 0.050 s |
+| Constant | |
++------------------+------------------------------------|
+|Strong Signal Loop| 231.306 Hz two-sided at Pc/No = |
+| Noise Bandwidth | 100 dB-Hz |
+=========================================================
+
+The SDST ranging performance is listed in the table below.
+One range unit was 0.947 nanoseconds for 2001 Mars Odyssey.
+
+==========================================================
+| Parameter | Value (average over 3 devices) |
++---------------------+----------------------------------+
+|Range Delay | 1417.2 range units |
++---------------------+----------------------------------+
+|Temperature Variation| +/-4.0 ru (-25C to +30C) |
++---------------------+----------------------------------+
+|Carrier Suppression | 0.5 dB (17.5 deg range mod index)|
+| | 1.9 dB (35.0 deg range mod index)|
++---------------------+----------------------------------+
+|3 dB Bandwidth | 1.4 MHz |
++---------------------+----------------------------------+
+|Noise Equivalent | 2.0 MHz |
+| Bandwidth | |
+==========================================================
+
+
+
+Platform Mounting Descriptions - Spacecraft
+===========================================
+During the Launch, Cruise, Orbit Insertion, and Aerobraking
+phases of the mission, the HGA was stowed so that its
+boresight and the MGA boresight were along the +X axis. After
+aerobraking, the HGA was deployed and tracked the
+Earth using a pair of gimbals (azimuth and elevation) at the
+end of a boom.
+The MGA was mounted on the HGA dish so that the MGA and HGA
+boresights were equal. The SSPAs were mounted behind the HGA
+reflector to minimize circuit losses.
+
+
+Investigators
+=============
+None.
+
+
+Instrument Section / Operating Mode Descriptions - Spacecraft
+=============================================================
+Redundant components could be configured as desired. Each
+configuration had slightly different performance, but the
+quantitative differences are unknown.
+
+
+Instrument Overview - DSN
+=========================
+Three Deep Space Communications Complexes (DSCCs) (near
+Barstow, CA; Canberra, Australia; and Madrid, Spain) comprise
+the DSN tracking network. Each complex is equipped with
+several antennas [including at least one each 70-m, 34-m High
+Efficiency (HEF), and 34-m Beam WaveGuide (BWG)], associated
+electronics, and operational systems. Primary activity
+at each complex is radiation of commands to and reception of
+telemetry data from active spacecraft. Transmission and
+reception is possible in several radio-frequency bands, the
+most common being S-band (nominally a frequency of 2100-2300 MHz
+or a wavelength of 14.2-13.0 cm) and X-band (7100-8500 MHz or
+4.2-3.5 cm). Transmitter output powers of up to 400 kW are
+available.
+
+Ground stations have the ability to transmit coded and uncoded
+waveforms which can be echoed by distant spacecraft. Analysis
+of the received coding allows navigators to determine the
+distance to the spacecraft; analysis of Doppler shift on the
+carrier signal allows estimation of the line-of-sight
+spacecraft velocity. Range and Doppler measurements are used
+to calculate the spacecraft trajectory and to infer gravity
+fields of objects near the spacecraft.
+
+Ground stations can record spacecraft signals that have
+propagated through or been scattered from target media.
+Measurements of signal parameters after wave interactions with
+surfaces, atmospheres, rings, and plasmas are used to infer
+physical and electrical properties of the target.
+
+Principal investigators vary from experiment to experiment.
+See the corresponding section of the spacecraft instrument
+description or the data set description for specifics.
+
+The Deep Space Network is managed by the Jet Propulsion
+Laboratory of the California Institute of Technology for the
+U.S. National Aeronautics and Space Administration.
+Specifications include:
+
+Instrument Id : RSS
+Instrument Host Id : DSN
+Pi Pds User Id : N/A
+Instrument Name : RADIO SCIENCE SUBSYSTEM
+Instrument Type : RADIO SCIENCE
+Build Date : N/A
+Instrument Mass : N/A
+Instrument Length : N/A
+Instrument Width : N/A
+Instrument Height : N/A
+Instrument Manufacturer Name : N/A
+
+For more information on the Deep Space Network and its use in
+radio science see reports by [ASMAR&RENZETTI1993],
+[ASMAR&HERRERA1993], and [ASMARETAL1995]. For design
+specifications on DSN subsystems see [DSN810-5]. For DSN use
+with MGS Radio Science see [TYLERETAL1992], [TYLERETAL2001],
+and [JPLD-14027].
+
+
+Subsystems - DSN
+================
+The Deep Space Communications Complexes (DSCCs) are an integral
+part of Radio Science instrumentation, along with the spacecraft
+Radio Frequency Subsystem. Their system performance directly
+determines the degree of success of Radio Science
+investigations, and their system calibration determines the
+degree of accuracy in the results of the experiments. The
+following paragraphs describe the functions performed by the
+individual subsystems of a DSCC. This material has been adapted
+from [ASMAR&HERRERA1993] and [JPLD-14027]; for additional
+information, consult [DSN810-5].
+
+Each DSCC includes a set of antennas, a Signal Processing
+Center (SPC), and communication links to the Jet Propulsion
+Laboratory (JPL). The general configuration is illustrated
+below; antennas (Deep Space Stations, or DSS -- a term carried
+over from earlier times when antennas were individually
+instrumented) are listed in the table.
+
+ -------- -------- -------- -------- --------
+ | DSS 25 | | DSS 27 | | DSS 14 | | DSS 15 | | DSS 16 |
+ |34-m BWG| |34-m HSB| | 70-m | |34-m HEF| | 26-m |
+ -------- -------- -------- -------- --------
+ | | | | |
+ | v v | v
+ | --------- | ---------
+ --------->|GOLDSTONE|<---------- |EARTH/ORB|
+ | SPC 10 |<-------------->| LINK |
+ --------- ---------
+ | SPC |<-------------->| 26-M |
+ | COMM | ------>| COMM |
+ --------- | ---------
+ | | |
+ v | v
+ ------ --------- | ---------
+ | NOCC |<--->| JPL |<------- | |
+ ------ | CENTRAL | | GSFC |
+ ------ | COMM | | NASCOMM |
+ | MCCC |<--->| TERMINAL|<-------------->| |
+ ------ --------- ---------
+ ^ ^
+ | |
+ CANBERRA (SPC 40) <---------------- |
+ |
+ MADRID (SPC 60) <----------------------
+
+ GOLDSTONE CANBERRA MADRID
+ Antenna SPC 10 SPC 40 SPC 60
+ -------- --------- -------- --------
+ 26-m DSS 16 DSS 46 DSS 66
+ 34-m HEF DSS 15 DSS 45 DSS 65
+ 34-m BWG DSS 24 DSS 34 DSS 54
+ DSS 25
+ DSS 26
+ 34-m HSB DSS 27
+ DSS 28
+ 70-m DSS 14 DSS 43 DSS 63
+ Developmental DSS 13
+
+
+Subsystem interconnections at each DSCC are shown in the
+diagram below, and they are described in the sections that
+follow. The Monitor and Control Subsystem is connected to all
+other subsystems; the Test Support Subsystem can be.
+
+----------- ------------------ --------- ---------
+|TRANSMITTER| | | | TRACKING| | COMMAND |
+| SUBSYSTEM |-| RECEIVER/EXCITER |-|SUBSYSTEM|-|SUBSYSTEM|-
+----------- | | --------- --------- |
+ | | SUBSYSTEM | | | |
+----------- | | --------------------- |
+| MICROWAVE | | | | TELEMETRY | |
+| SUBSYSTEM |-| |-| SUBSYSTEM |-
+----------- ------------------ --------------------- |
+ | |
+----------- ----------- --------- -------------- |
+| ANTENNA | | MONITOR | | TEST | | DIGITAL | |
+| SUBSYSTEM | |AND CONTROL| | SUPPORT | |COMMUNICATIONS|-
+----------- | SUBSYSTEM | |SUBSYSTEM| | SUBSYSTEM |
+ ----------- --------- --------------
+
+
+DSCC Monitor and Control Subsystem
+----------------------------------
+The DSCC Monitor and Control Subsystem (DMC) is part of the
+Monitor and Control System (MON) which also includes the
+ground communications Central Communications Terminal and the
+Network Operations Control Center (NOCC) Monitor and Control
+Subsystem. The DMC is the center of activity at a DSCC. The
+DMC receives and archives most of the information from the
+NOCC needed by the various DSCC subsystems during their
+operation. Control of most of the DSCC subsystems, as well
+as the handling and displaying of any responses to control
+directives and configuration and status information received
+from each of the subsystems, is done through the DMC. The
+effect of this is to centralize the control, display, and
+archiving functions necessary to operate a DSCC.
+Communication among the various subsystems is done using a
+Local Area Network (LAN) hooked up to each subsystem via a
+network interface unit (NIU).
+
+
+DSCC Antenna Mechanical Subsystem
+---------------------------------
+Multi-mission Radio Science activities require support from
+the 70-m, 34-m HEF, and 34-m BWG antenna subnets. The
+antennas at each DSCC function as large-aperture collectors
+which, by double reflection, cause the incoming radio
+frequency (RF) energy to enter the feed horns. The large
+collecting surface of the antenna focuses the incoming energy
+onto a subreflector, which is adjustable in both axial and
+angular position. These adjustments are made to correct for
+gravitational deformation of the antenna as it moves between
+zenith and the horizon; the deformation can be as large as
+5 cm. The subreflector adjustments optimize the channeling
+of energy from the primary reflector to the subreflector
+and then to the feed horns. The 70-m and 34-m HEF antennas
+have 'shaped' primary and secondary reflectors, with forms
+that are modified paraboloids. This customization allows
+more uniform illumination of one reflector by another. The
+BWG reflector shape is ellipsoidal.
+
+On the 70-m antennas, the subreflector directs
+received energy from the antenna onto a dichroic plate, a
+device which reflects S-band energy to the S-band feed horn
+and passes X-band energy through to the X-band feed horn. In
+the 34-m HEF, there is one 'common aperture feed,' which
+accepts both frequencies without requiring a dichroic plate.
+In the 34-m BWG, a series of small mirrors (approximately 2.5
+meters in diameter) directs microwave energy from the
+subreflector region to a collection area at the base of
+the antenna -- typically in a pedestal room. A retractable
+dichroic reflector separates S- and X-band on some BWG
+antennas or X- and Ka-band on others. RF energy to be
+transmitted into space by the horns is focused by the
+reflectors into narrow cylindrical beams, pointed with high
+precision (either to the dichroic plate or directly to the
+subreflector) by a series of drive motors and gear trains
+that can rotate the movable components and their support
+structures.
+
+The different antennas can be pointed by several means. Two
+pointing modes commonly used during tracking passes are
+CONSCAN and 'blind pointing.' With CONSCAN enabled and a
+closed loop receiver locked to a spacecraft signal, the
+system tracks the radio source by conically scanning around
+its position in the sky. Pointing angle adjustments are
+computed from signal strength information (feedback) supplied
+by the receiver. In this mode the Antenna Pointing Assembly
+(APA) generates a circular scan pattern which is sent to the
+Antenna Control System (ACS). The ACS adds the scan pattern
+to the corrected pointing angle predicts. Software in the
+receiver-exciter controller computes the received signal
+level and sends it to the APA. The correlation of scan
+position with the received signal level variations allows the
+APA to compute offset changes which are sent to the ACS.
+Thus, within the capability of the closed-loop control
+system, the scan center is pointed precisely at the apparent
+direction of the spacecraft signal source. An additional
+function of the APA is to provide antenna position angles and
+residuals, antenna control mode/status information, and
+predict-correction parameters to the Area Routing Assembly
+(ARA) via the LAN, which then sends this information to JPL
+via the Ground Communications Facility (GCF) for antenna
+status monitoring.
+
+During periods when excessive signal level dynamics or low
+received signal levels are expected (e.g., during an
+occultation experiment), CONSCAN should not be used. Under
+these conditions, blind pointing (CONSCAN OFF) is used, and
+pointing angle adjustments are based on a predetermined
+Systematic Error Correction (SEC) model.
+
+Independent of CONSCAN state, subreflector motion in at least
+the z-axis may introduce phase variations into the received
+Radio Science data. For that reason, during certain
+experiments, the subreflector in the 70-m and 34-m HEFs may
+be frozen in the z-axis at a position (often based on
+elevation angle) selected to minimize phase change and signal
+degradation. This can be done via Operator Control Inputs
+(OCIs) from the LMC to the Subreflector Controller (SRC)
+which resides in the alidade room of the antennas. The SRC
+passes the commands to motors that drive the subreflector to
+the desired position.
+
+Pointing angles for all antenna types are computed by
+the NOCC Support System (NSS) from an ephemeris provided by
+the flight project. These predicts are received and archived
+by the CMC. Before each track, they are transferred to the
+APA, which transforms the direction cosines of the predicts
+into AZ-EL coordinates. The LMC operator then downloads the
+antenna predict points to the antenna-mounted ACS computer
+along with a selected SEC model. The pointing predicts
+consist of time-tagged AZ-EL points at selected time intervals
+along with polynomial coefficients for interpolation between
+points.
+
+The ACS automatically interpolates the predict points,
+corrects the pointing predicts for refraction and
+subreflector position, and adds the proper systematic error
+correction and any manually entered antenna offsets. The ACS
+then sends angular position commands for each axis at the
+rate of one per second. In the 70-m and 34-m HEF, rate
+commands are generated from the position commands at the
+servo controller and are subsequently used to steer the
+antenna.
+
+When not using binary predicts (the routine mode for
+spacecraft tracking), the antennas can be pointed using
+'planetary mode' -- a simpler mode which uses right ascension
+(RA) and declination (DEC) values. These change very slowly
+with respect to the celestial frame. Values are provided to
+the station in text form for manual entry. The ACS
+quadratically interpolates among three RA and DEC points
+which are on one-day centers.
+
+A third pointing mode -- sidereal -- is available for
+tracking radio sources fixed with respect to the celestial
+frame.
+
+Regardless of the pointing mode being used, a 70-m antenna
+has a special high-accuracy pointing capability called
+'precision' mode. A pointing control loop derives the
+main AZ-EL pointing servo drive error signals from a two-
+axis autocollimator mounted on the Intermediate Reference
+Structure. The autocollimator projects a light beam to a
+precision mirror mounted on the Master Equatorial drive
+system, a much smaller structure, independent of the main
+antenna, which is exactly positioned in HA and DEC with shaft
+encoders. The autocollimator detects elevation/cross-
+elevation errors between the two reference surfaces by
+measuring the angular displacement of the reflected light
+beam. This error is compensated for in the antenna servo by
+moving the antenna in the appropriate AZ-EL direction.
+Pointing accuracies of 0.004 degrees (15 arc seconds) are
+possible in 'precision' mode. The 'precision' mode is not
+available on 34-m antennas -- nor is it needed, since their
+beamwidths are twice as large as on the 70-m antennas.
+
+
+DSCC Antenna Microwave Subsystem
+--------------------------------
+70-m Antennas: Each 70-m antenna has three feed cones
+installed in a structure at the center of the main reflector.
+The feeds are positioned 120 degrees apart on a circle.
+Selection of the feed is made by rotation of the
+subreflector. A dichroic mirror assembly, half on the S-band
+cone and half on the X-band cone, permits simultaneous use of
+the S- and X-band frequencies. The third cone is devoted to
+R&D and more specialized work.
+
+The Antenna Microwave Subsystem (AMS) accepts the received S-
+and X-band signals at the feed horn and transmits them
+through polarizer plates to an orthomode transducer. The
+polarizer plates are adjusted so that the signals are
+directed to a pair of redundant amplifiers for each
+frequency, thus allowing simultaneous reception of signals in
+two orthogonal polarizations. For S-band these are two Block
+IVA S-band Traveling Wave Masers (TWMs); for X-band the
+amplifiers are Block IIA TWMs.
+
+34-m HEF Antennas: The 34-m HEF uses a single feed for both
+S- and X-band. Simultaneous S- and X-band receive as well as
+X-band transmit is possible thanks to the presence of an S/X
+'combiner' which acts as a diplexer. For S-band, RCP or LCP
+is user selected through a switch so neither a polarizer nor
+an orthomode transducer is needed. X-band amplification
+options include two Block II TWMs or an HEMT Low Noise
+Amplifier (LNA). S-band amplification is provided by an FET
+LNA.
+
+34-m BWG Antennas: These antennas use feeds and low-noise
+amplifiers (LNA) in the pedestal room, which can be switched
+in and out as needed. Typically the following modes are
+available:
+ 1. downlink non-diplexed path (RCP or LCP) to LNA-1, with
+ uplink in the opposite circular polarization;
+ 2. downlink non-diplexed path (RCP or LCP) to LNA-2, with
+ uplink in the opposite circular polarization
+ 3. downlink diplexed path (RCP or LCP) to LNA-1, with
+ uplink in the same circular polarization
+ 4. downlink diplexed path (RCP or LCP) to LNA-2, with
+ uplink in the same circular polarization
+For BWG antennas with dual-band capabilities (e.g., DSS 25)
+and dual LNAs, each of the above four modes can be used in a
+single-frequency or dual-frequency configuration. Thus, for
+antennas with the most complete capabilities, there are
+sixteen possible ways to receive at a single frequency
+(2 polarizations, 2 waveguide path choices, 2 LNAs, and 2
+bands).
+
+
+DSCC Receiver-Exciter Subsystem
+-------------------------------
+The Receiver-Exciter Subsystem is composed of two groups of
+equipment: the closed-loop receiver group and the open-loop
+receiver group. This subsystem is controlled by the
+Receiver-Exciter Controller (REC) which communicates
+directly with the DMC for predicts and OCI reception and
+status reporting.
+
+The exciter generates the S-band signal (or X-band for the
+34-m HEF only) which is provided to the Transmitter Subsystem
+for the spacecraft uplink signal. It is tunable under
+command of the Digitally Controlled Oscillator (DCO) which
+receives predicts from the Metric Data Assembly (MDA).
+
+The diplexer in the signal path between the transmitter and
+the feed horn for all three antennas (used for simultaneous
+transmission and reception) may be configured such that it is
+out of the received signal path (in listen-only or bypass
+mode) in order to improve the signal-to-noise ratio in the
+receiver system.
+
+Closed Loop Receivers: The Block V receiver-exciter at the
+70-m stations allows for two receiver channels, each capable
+of L-Band (e.g., 1668 MHz frequency or 18 cm wavelength),
+S-band, or X-band reception, and an S-band exciter for
+generation of uplink signals through the low-power or
+high-power transmitter.
+
+The closed-loop receivers provide the capability for rapid
+acquisition of a spacecraft signal and telemetry lockup. In
+order to accomplish acquisition within a short time, the
+receivers are predict driven to search for, acquire, and
+track the downlink automatically. Rapid acquisition
+precludes manual tuning though that remains as a backup
+capability. The subsystem utilizes FFT analyzers for rapid
+acquisition. The predicts are NSS generated, transmitted to
+the CMC which sends them to the Receiver-Exciter Subsystem
+where two sets can be stored. The receiver starts
+acquisition at uplink time plus one round-trip-light-time or
+at operator specified times. The receivers may also be
+operated from the LMC without a local operator attending
+them. The receivers send performance and status data,
+displays, and event messages to the LMC.
+
+Either the exciter synthesizer signal or the simulation
+(SIM) synthesizer signal is used as the reference for the
+Doppler extractor in the closed-loop receiver systems,
+depending on the spacecraft being tracked (and Project
+guidelines). The SIM synthesizer is not ramped; instead it
+uses one constant frequency, the Track Synthesizer Frequency
+(TSF), which is an average frequency for the entire pass.
+
+The closed-loop receiver AGC loop can be configured to one
+of three settings: narrow, medium, or wide. It will be
+configured such that the expected amplitude changes are
+accommodated with minimum distortion. The loop bandwidth
+(2BLo) will be configured such that the expected phase
+changes can be accommodated while maintaining the best
+possible loop SNR.
+
+Open-Loop Receivers (OLR): The OLR utilized a fixed first
+Local Oscillator (LO) frequency and a tunable second LO
+frequency to minimize phase noise and improve frequency
+stability. The OLR consisted of an RF-to-IF downconverter
+located at the feed , an IF selection switch (IFS), and a
+Radio Science Receiver (RSR). The RF-IF downconverters
+in the 70-m antennas were equipped for four IF channels:
+S-RCP, S-LCP, X-RCP, and X-LCP. The 34-m HEF stations
+were equipped with a two-channel RF-IF: S-band and X-band.
+The IFS switched the IF input among the antennas.
+
+
+DSCC Transmitter Subsystem
+--------------------------
+The Transmitter Subsystem accepts the S-band frequency
+exciter signal from the Receiver-Exciter Subsystem exciter
+and amplifies it to the required transmit output level. The
+amplified signal is routed via the diplexer through the feed
+horn to the antenna and then focused and beamed to the
+spacecraft.
+
+The Transmitter Subsystem power capabilities range from 18 kW
+to 400 kW. Power levels above 18 kW are available only at
+70-m stations.
+
+
+DSCC Tracking Subsystem
+-----------------------
+The Tracking Subsystem primary functions are to acquire and
+maintain communications with the spacecraft and to generate
+and format radiometric data containing Doppler and range.
+
+The DSCC Tracking Subsystem (DTK) receives the carrier
+signals and ranging spectra from the Receiver-Exciter
+Subsystem. The Doppler cycle counts are counted, formatted,
+and transmitted to JPL in real time. Ranging data are also
+transmitted to JPL in real time. Also contained in these
+blocks is the AGC information from the Receiver-Exciter
+Subsystem. The Radio Metric Data Conditioning Team (RMDCT)
+at JPL produces an Archival Tracking Data File (ATDF) which
+contains Doppler and ranging data.
+
+In addition, the Tracking Subsystem receives from the CMC
+frequency predicts (used to compute frequency residuals and
+noise estimates), receiver tuning predicts (used to tune the
+closed-loop receivers), and uplink tuning predicts (used to
+tune the exciter). From the LMC, it receives configuration
+and control directives as well as configuration and status
+information on the transmitter, microwave, and frequency and
+timing subsystems.
+
+The Metric Data Assembly (MDA) controls all of the DTK
+functions supporting the uplink and downlink activities. The
+MDA receives uplink predicts and controls the uplink tuning
+by commanding the DCO. The MDA also controls the Sequential
+Ranging Assembly (SRA). It formats the Doppler and range
+measurements and provides them to the GCF for transmission to
+NOCC.
+
+The Sequential Ranging Assembly (SRA) measures the round trip
+light time (RTLT) of a radio signal traveling from a ground
+tracking station to a spacecraft and back. From the RTLT,
+phase, and Doppler data, the spacecraft range can be
+determined. A coded signal is modulated on an uplink carrier
+and transmitted to the spacecraft where it is detected and
+transponded back to the ground station. As a result, the
+signal received at the tracking station is delayed by its
+round trip through space and shifted in frequency by the
+Doppler effect due to the relative motion between the
+spacecraft and the tracking station on Earth.
+
+
+DSCC Frequency and Timing Subsystem
+-----------------------------------
+The Frequency and Timing Subsystem (FTS) provides all
+frequency and timing references required by the other DSCC
+subsystems. It contains four frequency standards of which
+one is prime and the other three are backups. Selection of
+the prime standard is done via the CMC. Of these four
+standards, two are hydrogen masers followed by clean-up loops
+(CUL) and two are cesium standards. These four standards all
+feed the Coherent Reference Generator (CRG) which provides
+the frequency references used by the rest of the complex. It
+also provides the frequency reference to the Master Clock
+Assembly (MCA) which in turn provides time to the Time
+Insertion and Distribution Assembly (TID) which provides UTC
+and SIM-time to the complex.
+
+JPL's ability to monitor the FTS at each DSCC is limited to
+the MDA calculated Doppler pseudo-residuals, the Doppler
+noise, the SSI, and to a system which uses the Global
+Positioning System (GPS). GPS receivers at each DSCC receive
+a one-pulse-per-second pulse from the station's (hydrogen
+maser referenced) FTS and a pulse from a GPS satellite at
+scheduled times. After compensating for the satellite signal
+delay, the timing offset is reported to JPL where a database
+ is kept. The clock offsets stored in the JPL database are
+ given in microseconds; each entry is a mean reading of
+ measurements from several GPS satellites and a time tag
+ associated with the mean reading. The clock offsets provided
+ include those of SPC 10 relative to UTC (NIST), SPC 40
+ relative to SPC 10, etc.
+
+
+ Radio Science Receiver (RSR)
+ ----------------------------
+ A radio frequency (RF) spacecraft signal at S-band, X-band,
+ or Ka-band is captured by a receiving antenna on Earth, down
+ converted to an intermediate frequency (IF) near 300 MHz and
+ then fed via a distribution network to one input of an IF
+ Selector Switch (IFS). The IFS allows each RSR to select any
+ of the available input signals for its RSR Digitizer (DIG).
+ Within the RSR the digitized signal is then passed to the
+ Digitial Down Converter (DDC), VME Data Processor (VDP), and
+ Data Processor (DP) [JPLD-16765].
+
+ \ ----------- ------ ----- ----- -----
+ \ | RF TO IF | | |----| | | | | |
+ |----| DOWN |----| |----| |----| DIG | | DP |
+ / | CONVERTER | | |----| | | | | |
+ / ----------- | IF |----| IFS | ----- -----
+ ANTENNA --| DIST |----| | | |
+ 300 MHz IF --| | .. | | ----- -----
+ FROM OTHER --| |----| | | | | |
+ ANTENNAS --| | ----- | DDC | | VDP |
+ ------ | | | |
+ ----- -----
+ | |
+ -------
+
+ In the DIG the IF signal is passed through a programmable
+ attenuator, adjusted to provide the proper level to the Analog
+ to Digital Converter (ADC). The attenuated signal is then
+ passed through a Band Pass Filter (BPF) which selects a
+ frequency band in the range 265-375 MHz. The filtered output
+ from the BPF is then mixed with a 256 MHz Local Oscillator
+ (LO), low pass filtered (LPF), and sampled by the ADC. The
+ output of the ADC is a stream of 8-bit real samples at 256
+ Msamples/second (Msps). DIG timing is derived from the
+ station FTS 5 MHz clock and 1 pulse per second (1PPS)
+ reference; the DIG generates a 256 MHz clock signal for later
+ processing. The 1PPS signal marks the data sample taken at
+ the start of each second.
+
+ The DDC selects one 16 MHz subchannel from the possible 128
+ MHz bandwidth available from the DIG by using Finite Impulse
+ Response (FIR) filters with revolving banks of filter
+ coefficients. The sample stream from the DIG is separated
+ into eight decimated streams, each of which is fed into two
+ sets of FIR filters. One set of filters produces in-phase (I)
+ 8-bit data while the other produces quadrature-phase (Q) 8-bit
+ data. The center frequency of the desired 16 MHz channel is
+ adjustable in 1 MHz steps and is usually chosen to be near the
+ spacecraft carrier frequency. After combining the I and Q
+ sample streams, the DDC feeds the samples to the VDP. The DDC
+ also converts the 256 MHz data clock and 1PPS signals into a
+ msec time code, which is also passed to the VDP.
+
+ The VDP contains a quadruply-redundant set of custom boards
+ which are controlled by a real-time control computer (RT).
+ Each set of boards comprises a numerically controlled
+ oscillator (NCO), a complex multiplier, a decimating FIR
+ filter, and a data packer. The 16 Msps complex samples
+ from the DDC are digitally mixed with the NCO signal in the
+ complex multiplier. The NCO phase and frequency are updated
+ every millisecond by the RT and are selected so that the
+ center frequency of the desired portion of the 16 MHz channel
+ is down-converted to 0 Hz. The RT uses polynomials derived
+ from frequency predictions. The output of the complex
+ multiplier is sent to the decimating FIR filter where its
+ bandwidth and sample rate are reduced (see table below). The
+ decimating FIR filter also allows adjustment of the
+ sub-channel gain to take full advantage of the dynamic range
+ available in the hardware. The data packer truncates samples
+ to 1, 2, 4, 8, or 16 bits by dropping the least significant
+ bits and packs them into 32-bit data words. Q-samples are
+ packed into the first 16 bits of the word, and I-samples into
+ the least significant 16 bits (see below). In 'narrow band'
+ operation all four sets of sets of custom boards can be
+ supported simultaneously. In 'medium band' operation no more
+ than two channels can be supported simultaneously. In
+ 'wide band' operation, only one sub-channel can be recorded.
+
+ |============================================================|
+ | RSR Sample Rates and Sample Sizes Supported |
+ |================+=======+======+=================+==========|
+ | Category | Rate | Size | Data Rate |Rec Length|
+ | | (ksps)|(bits)|(bytes/s) (rec/s)| (bytes) |
+ |================+=======+======+=========+=======+==========|
+ |Narrow Band (NB)| 1 | 8 | 2000 | 1 | 2000 |
+ | | 2 | 8 | 4000 | 1 | 4000 |
+ | | 4 | 8 | 8000 | 1 | 8000 |
+ | | 8 | 8 | 16000 | 1 | 16000 |
+ | | 16 | 8 | 32000 | 2 | 16000 |
+ | | 25 | 8 | 50000 | 2 | 25000 |
+ | | 50 | 8 | 100000 | 4 | 25000 |
+ | | 100 | 8 | 200000 | 10 | 20000 |
+ | | 1 | 16 | 4000 | 1 | 4000 |
+ | | 2 | 16 | 8000 | 1 | 8000 |
+ | | 4 | 16 | 16000 | 1 | 16000 |
+ | | 8 | 16 | 32000 | 2 | 16000 |
+ | | 16 | 16 | 64000 | 4 | 16000 |
+ | | 25 | 16 | 100000 | 4 | 25000 |
+ | | 50 | 16 | 200000 | 10 | 20000 |
+ | | 100 | 16 | 400000 | 20 | 20000 |
+ |Medium Band (MB)| 250 | 1 | 62500 | 5 | 12500 |
+ | | 500 | 1 | 125000 | 5 | 25000 |
+ | | 1000 | 1 | 250000 | 10 | 25000 |
+ | | 2000 | 1 | 500000 | 20 | 25000 |
+ | | 4000 | 1 | 1000000 | 40 | 25000 |
+ | | 250 | 2 | 125000 | 5 | 25000 |
+ | | 500 | 2 | 250000 | 10 | 25000 |
+ | | 1000 | 2 | 500000 | 20 | 25000 |
+ | | 2000 | 2 | 1000000 | 40 | 25000 |
+ | | 4000 | 2 | 2000000 | 100 | 20000 |
+ | | 250 | 4 | 250000 | 10 | 25000 |
+ | | 500 | 4 | 500000 | 20 | 25000 |
+ | | 1000 | 4 | 1000000 | 40 | 25000 |
+ | | 2000 | 4 | 2000000 | 100 | 20000 |
+ | | 250 | 8 | 500000 | 20 | 25000 |
+ | | 500 | 8 | 1000000 | 40 | 25000 |
+ | | 1000 | 8 | 2000000 | 100 | 20000 |
+ |Wide Band (WB) | 8000 | 1 | 2000000 | 100 | 20000 |
+ | | 16000 | 1 | 4000000 | 200 | 20000 |
+ | | 8000 | 2 | 4000000 | 200 | 20000 |
+ |============================================================|
+
+ |============================================================|
+ | Sample Packing |
+ |=================+==========================================|
+ | Bits per Sample | Contents of 32-bit Packed Data Register |
+ |=================+==========================================|
+ | 16 | (Q1),(I1) |
+ | 8 | (Q2,Q1),(I2,I1) |
+ | 4 | (Q4,Q3,Q2,Q1),(I4,I3,I2,I1) |
+ | 2 | (Q8,Q7,...Q1),(I8,I7,...I1) |
+ | 1 | (Q16,Q15,...Q1),(I16,I15,...I1) |
+ |============================================================|
+
+ Once per second the RT sends the accumulated data records from
+ each sub-channel to the Data Processor (DP) over a 100 Mbit/s
+ ethernet connection. In addition to the samples, each data
+ record includes header information such as time tags and NCO
+ frequency and phase that are necessary for analysis. The DP
+ processes the data records to provide monitor data, such as
+ power spectra. If recording has been enabled, the records are
+ stored by the DP.
+
+ NCO Phase and Frequency
+ -----------------------
+ At the start of each DSN pass, the RSR is provided with a
+ file containing a list of predicted frequencies. Using these
+ points, the RT computes expected sky frequencies at the
+ beginning, middle, and end of each one second time interval.
+ Based on the local oscillator frequencies selected and any
+ offsets entered, the RT computes the coefficients of a
+ frequency polynomial fitted to the DDC channel frequencies
+ at these three times. The RT also computes a phase
+ polynomial by integrating the frequency polynomial and
+ matching phases at the one second boundaries.
+
+ The phase and frequency of the VDP NCO's are computed every
+ millisecond (000-999) from the polynomial coefficients as
+ follows:
+
+ nco_phase(msec) = phase_coef_1 +
+ phase_coef_2 * (msec/1000) +
+ phase_coef_3 * (msec/1000)**2 +
+ phase_coef_4 * (msec/1000)**3
+
+ nco_freq(msec) = freq_coef_1 +
+ freq_coef_2 * ((msec + 0.5)/1000) +
+ freq_coef_3 * ((msec + 0.5)/1000)**2
+
+ The sky frequency may be reconstructed using
+
+ sky_freq = RF_to_IF_LO +
+ DDC_LO -
+ nco_freq +
+ reside_freq
+
+ where RF_to_IF_LO is the down conversion from the
+ microwave frequency to IF (bytes 42-43
+ in the data record header)
+ DDC_LO is the down-conversion applied in the
+ DIG and DDC (bytes 40-41 in the data
+ record header)
+ Resid_Freq is the frequency of the signal in the
+ VDP output
+
+
+Detectors - DSN
+===============
+ Nominal carrier tracking loop threshold noise bandwidth at
+ X-band is 10 Hz. Coherent (two-way) closed-loop
+ system stability is shown in the table below:
+
+ integration time Doppler uncertainty
+ (secs) (one sigma, microns/sec)
+ ------ ------------------------
+ 10 50
+ 60 20
+ 1000 4
+
+ For the open-loop subsystem, signal detection is done in
+ software.
+
+
+Calibration - DSN
+=================
+ Calibrations of hardware systems are carried out periodically
+ by DSN personnel; these ensure that systems operate at required
+ performance levels -- for example, that antenna patterns,
+ receiver gain, propagation delays, and Doppler uncertainties
+ meet specifications. No information on specific calibration
+ activities is available. Nominal performance specifications
+ are shown in the tables above. Additional information may be
+ available in [DSN810-5].
+
+ Prior to each tracking pass, station operators perform a series
+ of calibrations to ensure that systems meet specifications for
+ that operational period. Included in these calibrations is
+ measurement of receiver system temperature in the configuration
+ to be employed during the pass. Results of these calibrations
+ are recorded in (hard copy) Controller's Logs for each pass.
+
+ The nominal procedure for initializing open-loop receiver
+ attenuator settings is described below. In cases where widely
+ varying signal levels are expected, the procedure may be
+ modified in advance or real-time adjustments may be made to
+ attenuator settings.
+
+
+Operational Considerations - DSN
+================================
+ The DSN is a complex and dynamic 'instrument.' Its performance
+ for Radio Science depends on a number of factors from equipment
+ configuration to meteorological conditions. No specific
+ information on 'operational considerations' can be given here.
+
+
+Operational Modes - DSN
+=======================
+
+ DSCC Antenna Mechanical Subsystem
+ ---------------------------------
+ Pointing of DSCC antennas may be carried out in several ways.
+ For details see the subsection 'DSCC Antenna Mechanical
+ Subsystem' in the 'Subsystem' section. Binary pointing is
+ the preferred mode for tracking spacecraft; pointing
+ predicts are provided, and the antenna simply follows those.
+ With CONSCAN, the antenna scans conically about the optimum
+ pointing direction, using closed-loop receiver signal
+ strength estimates as feedback. In planetary mode, the
+ system interpolates from three (slowly changing) RA-DEC
+ target coordinates; this is 'blind' pointing since there is
+ no feedback from a detected signal. In sidereal mode, the
+ antenna tracks a fixed point on the celestial sphere. In
+ 'precision' mode, the antenna pointing is adjusted using an
+ optical feedback system. It is possible on most antennas to
+ freeze z-axis motion of the subreflector to minimize phase
+ changes in the received signal.
+
+
+ DSCC Receiver-Exciter Subsystem
+ -------------------------------
+ The diplexer in the signal path between the transmitter and
+ the feed horns on all antennas may be configured so
+ that it is out of the received signal path in order to
+ improve the signal-to-noise ratio in the receiver system.
+ This is known as the 'listen-only' or 'bypass' mode.
+
+
+ Closed-Loop Receiver AGC Loop
+ -----------------------------
+ The closed-loop receiver AGC loop can be configured to one of
+ three settings: narrow, medium, or wide. Ordinarily it is
+ configured so that expected signal amplitude changes are
+ accommodated with minimum distortion. The loop bandwidth is
+ ordinarily configured so that expected phase changes can be
+ accommodated while maintaining the best possible loop SNR.
+
+
+ Coherent vs. Non-Coherent Operation
+ -----------------------------------
+ The frequency of the signal transmitted from the spacecraft
+ can generally be controlled in two ways -- by locking to a
+ signal received from a ground station or by locking to an
+ on-board oscillator. These are known as the coherent (or
+ 'two-way') and non-coherent ('one-way') modes, respectively.
+ Mode selection is made at the spacecraft, based on commands
+ received from the ground. When operating in the coherent
+ mode, the transponder carrier frequency is derived from the
+ received uplink carrier frequency with a 'turn-around ratio'
+ typically of 880/749. In the non-coherent mode, the
+ downlink carrier frequency is derived from the spacecraft
+ on-board crystal-controlled oscillator. Either closed-loop
+ or open-loop receivers (or both) can be used with either
+ spacecraft frequency reference mode. Closed-loop reception
+ in two-way mode is usually preferred for routine tracking.
+ Occasionally the spacecraft operates coherently while two
+ ground stations receive the 'downlink' signal; this is
+ sometimes known as the 'three-way' mode.
+
+
+Location - DSN
+==============
+ Station locations are documented in [GEO-10REVD]. Geocentric
+ coordinates are summarized here.
+
+ Geocentric Geocentric Geocentric
+ Station Radius (km) Latitude (N) Longitude (E)
+ --------- ----------- ------------ -------------
+ Goldstone
+ DSS 13 (34-m R&D) 6372.125125 35.0660185 243.2055430
+ DSS 14 (70-m) 6371.993286 35.2443527 243.1104638
+ DSS 15 (34-m HEF) 6371.966540 35.2403133 243.1128069
+ DSS 24 (34-m BWG) 6371.973553 35.1585349 243.1252079
+ DSS 25 (34-m BWG) 6371.983060 35.1562594 243.1246384
+ DSS 26 (34-m BWG) 6371.993032 35.1543411 243.1269849
+
+ Canberra
+ DSS 34 (34-m BWG) 6371.693561 -35.2169868 148.9819620
+ DSS 43 (70-m) 6371.689033 -35.2209234 148.9812650
+ DSS 45 (34-m HEF) 6371.675906 -35.2169652 148.9776833
+
+ Madrid
+ DSS 45 (34-m BWG) 6370.025429 40.2357708 355.7459008
+ DSS 63 (70-m) 6370.051221 40.2413537 355.7519890
+ DSS 65 (34-m HEF) (see next paragraph)
+
+ The coordinates for DSS 65 until 1 February 2005 were
+ 6370.021697 40.2373325 355.7485795
+ In cartesian coordinates (x, y, z) this was
+ (+4849336.6176, -0360488.6349, +4114748.9218)
+ Between February and September 2005, the antenna was
+ physically moved to
+ (+4849339.6448, -0360427.6560, +4114750.7428)
+
+
+Measurement Parameters - DSN
+============================
+ Closed-loop data are recorded in Archival Tracking Data Files
+ (ATDFs), as well as certain secondary products such as the
+ Orbit Data File (ODF). The ATDF Tracking Logical Record
+ contains 150 entries including status information and
+ measurements of ranging, Doppler, and signal strength.
+
+
+ACRONYMS AND ABBREVIATIONS - DSN
+================================
+ ACS Antenna Control System
+ ADC Analog-to-Digital Converter
+ AGC Automatic Gain Control
+ AMS Antenna Microwave System
+ APA Antenna Pointing Assembly
+ ARA Area Routing Assembly
+ ATDF Archival Tracking Data File
+ AUX Auxiliary
+ AZ Azimuth
+ BPF Band Pass Filter
+ bps bits per second
+ BWG Beam WaveGuide (antenna)
+ CDU Command Detector Unit
+ CMC Complex Monitor and Control
+ CONSCAN Conical Scanning (antenna pointing mode)
+ CRG Coherent Reference Generator
+ CUL Clean-up Loop
+ DANA a type of frequency synthesizer
+ dB deciBel
+ dBi dB relative to isotropic
+ dBm dB relative to one milliwatt
+ DCO Digitally Controlled Oscillator
+ DDC Digital Down Converter
+ DEC Declination
+ deg degree
+ DIG RSR Digitizer
+ DMC DSCC Monitor and Control Subsystem
+ DOR Differential One-way Ranging
+ DP Data Processor
+ DSCC Deep Space Communications Complex
+ DSN Deep Space Network
+ DSP DSCC Spectrum Processing Subsystem
+ DSS Deep Space Station
+ DTK DSCC Tracking Subsystem
+ E east
+ EIRP Effective Isotropic Radiated Power
+ EL Elevation
+ FET Field Effect Transistor
+ FFT Fast Fourier Transform
+ FIR Finite impulse Response
+ FTS Frequency and Timing Subsystem
+ GCF Ground Communications Facility
+ GHz Gigahertz
+ GPS Global Positioning System
+ HA Hour Angle
+ HEF High-Efficiency (as in 34-m HEF antennas)
+ HEMT High Electron Mobility Transistor (amplifier)
+ HGA High-Gain Antenna
+ HSB High-Speed BWG
+ IF Intermediate Frequency
+ IFS IF Selector Switch
+ IVC IF Selection Switch
+ JPL Jet Propulsion Laboratory
+ K Kelvin
+ Ka-Band approximately 32 GHz
+ KaBLE Ka-Band Link Experiment
+ kbps kilobits per second
+ kHz kilohertz
+ km kilometer
+ kW kilowatt
+ LAN Local Area Network
+ LCP Left-Circularly Polarized
+ LGR Low-Gain Receive (antenna)
+ LGT Low-Gain Transmit (antenna)
+ LMA Lockheed Martin Astronautics
+ LMC Link Monitor and Control
+ LNA Low-Noise Amplifier
+ LO Local Oscillator
+ LPF Low Pass Filter
+ m meters
+ MCA Master Clock Assembly
+ MCCC Mission Control and Computing Center
+ MDA Metric Data Assembly
+ MGS Mars Global Surveyor
+ MHz Megahertz
+ MOLA Mars Orbiting Laser Altimeter
+ MON Monitor and Control System
+ MOT Mars Observer Transponder
+ MSA Mission Support Area
+ N north
+ NAR Noise Adding Radiometer
+ NBOC Narrow-Band Occultation Converter
+ NCO Numerically Controlled Oscillator
+ NIST SPC 10 time relative to UTC
+ NIU Network Interface Unit
+ NOCC Network Operations and Control System
+ NRV NOCC Radio Science/VLBI Display Subsystem
+ NSS NOCC Support System
+ OCI Operator Control Input
+ ODF Orbit Data File
+ ODR Original Data Record
+ ODS Original Data Stream
+ OLR Open Loop Receiver
+ OSC Oscillator
+ PDS Planetary Data System
+ POCA Programmable Oscillator Control Assembly
+ PPM Precision Power Monitor
+ RA Right Ascension
+ REC Receiver-Exciter Controller
+ RCP Right-Circularly Polarized
+ RF Radio Frequency
+ RIC RIV Controller
+ RIV Radio Science IF-VF Converter Assembly
+ RMDCT Radio Metric Data Conditioning Team
+ RMS Root Mean Square
+ RSR Radio Science Receiver
+ RSS Radio Science Subsystem
+ RT Real-Time (control computer)
+ RTLT Round-Trip Light Time
+ S-band approximately 2100-2300 MHz
+ sec second
+ SEC System Error Correction
+ SIM Simulation
+ SLE Signal Level Estimator
+ SNR Signal-to-Noise Ratio
+ SNT System Noise Temperature
+ SOE Sequence of Events
+ SPA Spectrum Processing Assembly
+ SPC Signal Processing Center
+ sps samples per second
+ SRA Sequential Ranging Assembly
+ SRC Sub-Reflector Controller
+ SSI Spectral Signal Indicator
+ TID Time Insertion and Distribution Assembly
+ TLM Telemetry
+ TSF Tracking Synthesizer Frequency
+ TWM Traveling Wave Maser
+ TWNC Two-Way Non-Coherent
+ TWTA Traveling Wave Tube Amplifier
+ UNK unknown
+ USO UltraStable Oscillator
+ UTC Universal Coordinated Time
+ VCO Voltage-Controlled Oscillator
+ VDP VME Data Processor
+ VF Video Frequency
+ X-band approximately 7800-8500 MHz
+
diff --git a/data/pds4/context_support/document/description/ody.themis_description_1.0.md b/data/pds4/context_support/document/description/ody.themis_description_1.0.md
new file mode 100644
index 00000000..69cb0997
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@@ -0,0 +1,404 @@
+# Instrument Overview
+
+The THEMIS flight instrument is a combined infrared and visible
+multi-spectral pushbroom imager [CHRISTENSENETAL2002]. It has a
+12-cm effective aperature telescope and co-aligned infrared and
+visible area arrays. The imaging system is comprised of a
+three-mirror anastigmat telescope in a rugged enclosure, a
+visible/infrared beamsplitter, a silicon focal plane for visible
+detection, and a microbolometer for infrared detection. A major
+feature of this instrument is the use of an uncooled IR
+microbolometer array operated at ambient temperature, eliminating
+the need for complex passive or active cryogenic coolers. A small
+thermal electric cooler is used to stabilize the detector
+temperature to 0.001K. A calibration flag, the only moving part in
+the instrument, provides thermal calibration and a DC restore
+capability, and will also be used to protect the detectors from
+unintentional direct illumination from the Sun when the instrument
+is not in use. The electronics provide digital data collection and
+processing as well as the instrument control and data interface to
+the spacecraft. Infrared data will be collected in 9 wavelengths
+centered from 6.6 to 15.0 microns at 100 meter per pixel resolution;
+the 6.6 micron band is collected twice to result in a 10 band image.
+Visible data will be collected in 5 spectral bands at a resolution
+of 18 meters per pixel. The instrument weighs 11.2 kg, is 29 cm by
+37 cm by 55 cm in size, and consumes an orbital average power of
+14W.
+
+
+## Optical Design
+
+In order to integrate the visible and IR bands into a single
+telescope, a fast, wide field-of-view reflective telescope has
+been used. The 3.5 degree (down-track) by 4.6 degree
+(cross-track) field of view is achieved with a 3 mirror f/1.6
+anastigmat telescope with an effective aperature of 12 cm and a
+20-cm effective focal length. The design allows for excellent
+baffling to minimize scattered light. It is based on a
+diamond-turned bolt-together approach to telescope design,
+fabrication, alightment and testing. The manufacture utilized
+high-precision machining capabilities that allowed the entire
+optical stage to be machined and assembled without manual optical
+component adjustments, and achieved diffraction-limited
+performance in both the visible and infrared. The optical
+surfaces were machined with extremely tight tolerances (0.0002in).
+The optical surfaces were machined directly from high order
+aspheric equations. The telescope was manufactured with aluminum
+to reduce cost and to be significantly light-weight. Nickel
+plating and automated post polishing were used to keep the surface
+scatter to levels unobtainable with conventional diamond turning
+techniques. The system was optimized to match the high signal
+performance required for the IR imager and the spatial resolution
+needed for the visible camera. The 9 micron pitch of the visible
+array maps to a ground sample distance (GSD) of 18 meters with an
+MTF of approximately 0.1 at Nyquist. Similarly, the 50 micron
+pitch of the IR focal plane array maps to a GSD of 100 meters.
+
+
+## Focal Plane Assemblies
+
+The THEMIS infrared design is based on a Raytheon hand-held
+imager developed for rugged military use. The microbolometer
+array contains 320 pixels cross track by 240 pixels along track,
+with a square 50 micron pixel pitch. The microbolometer arrays
+were grown directly on the surface of Readout Integrated Circuits
+(ROIC) which are designed by Raytheon Santa Barbara Research
+Center (SBRC) and utilize custom Digital Signal Processing
+electronics. Spectral discrimination in the infrared is achieved
+with ten narrowband stripe filters. Each filter covers 16 lines
+in the along track directiona with an 8-line 'dead-space' between
+filters. The stripe filters were fabricated as separate stripe
+filters butted together on the focal plane. The along-track
+detectors under a common spectral filter are combined by the use
+of time-delay and integration (TDI) to improve the instrument's
+signal-to-noise performatnce. The calculated dwell time for a
+single pixel, at a martian orbit of 400km and a 100-meter
+footprint is 29.9 msec, which closely matches the 30Hz frame rate
+for the standard microbolometer. The ten stripe filter produces
+nine ~1 micron wide wavelength bands from 6.6 to 15 microns. Two
+filters (bands 1 and 2) cover the same spectral region centered at
+6.6 microns. The nine IR wavelengths include eight surface-
+sensing wavelengths (bands 1 - 9) and one atmospheric wavelength
+(band 10).
+
+The visible camera was supplied by Malin Space Science Systems
+(MSSS) and is a derivative of the MS'98 MARDI camera. It consists
+of a small (5.5 x 8.5 x 6.5 cm, <500 gm) unit incorporating a
+focal plane assembly with five color filters superimposed on the
+CCD detector, a timing board, a data acquisition subsystem and a
+power supply. The visible sensor utilizes a Kodak KAI-1001 CCD.
+This detector has 1024 by 1024 9-micrometer pixels (1018 x 1008
+photoactive). The visible imager used a filter plate mounted
+directly over the area-array detector on the focal plane. On the
+plate are multiple narrowband filter strips, each covering the
+entire cross-track width of the detector, but only a fraction of
+the along-track portion of the detector. The five filter bands
+are centered near 425, 550, 650, 750, and 860 nanometers. Band
+selection is accomplished by selectively reading out only part of
+the resulting frame for transmission to the spacecraft computer.
+The imager uses 5 stripes each 192 pixels in along-track extent.
+The entire detector is read out every 1.3 seconds.
+
+
+## Electronics Design
+
+Both the visible and infrared cameras utilized commercial,
+off-the-shelf electonics with modifications to accommodate space
+environmental requirements. Dedicated, miniaturized electronics
+provide ultra-stable, low-noise clock and bias signals to the
+focal planes, stabilize IR focal plane temperature with 0.001
+degree C, and perform analog and digital processing of the output
+signals.
+
+The microbolometer readout electronics includes an initial 8-bit
+analog DC offset correction which occurs on the focal plane, an
+Analog-to-Digital Converter (ADC) coverts the signals to 12-bit
+words, which are then corrected for gain and offsets. The
+correction is provided by the electronics of the IR camera and
+consists of a 12-bit fine offset and 8-bit gain and responsivity
+adjustment, performed in real time on a pixel-by-pixel basis.
+This process eliminates all the significant noise elements with
+the exception of the fundamental random noise term. This noise is
+reduced by applying TDI to the corrected digital data. Internal
+THEMIS data processing in firnmware includes a 16:1 TDI processing
+and lossless data compression for the IR bands using a hardware
+Rice data compression algorithm chip.
+
+The visible sensor requires 7 clock signals: a two-phase
+vertical clock (V1/V2), a two-phase horizontal clock (H1/H2), a
+sub-state clear clock (S), a reset clock (R), and a fast-dump
+clock (F). In addition, the ADC requires a convert clock. The
+amplified CCD signal is digitized by an Analog Devices AD1672
+12-bit ADC running at its maximum rate of 3 MSPS. For each pixel,
+both reset and video levels are digitized and then subtracted in
+the digital domain to perform correlated double sampling (CDS).
+The digital electronics are responsible for clock generation,
+sampling of the CCD signal, conversion of the 12-bit samples to
+8-bit encoded pixels, storage of the pixels, and finally readout
+of the pixels to the spacecraft. The zero reference ('reset')
+level for each pixel is digitized and stored in a register. The
+sum of the video plus zero reference ('video') level is then
+digitized, and an arithmetic subtraction is performed to produce
+the final result. The CCD output only requires scaling to the
+ADC range; no analog sampling, delay or differencing is required.
+The digital signal processor within the visible sensor generates
+the CCD clocks, reads the reset and video levels from the ADC,
+performs the correlated double sampling subtraction, reduces the
+pixel from 12 to 8 bits, applies lossless (2:1) first-difference
+Huffman compression, and transmits it digitally with handshaking
+over the serial communications interface to the spacecraft CPU.
+
+The spacecraft interface electronics supply final processing of
+the focal plane data, a data and command interface to the
+spacecraft, and overall instrument power conditioning. The bulk
+of the interface electronics is performed using Actel Field
+Programmable Gate Arrays (FPGAs), that are packaged using a
+mixture of conventional, and Sealed Chip-On-Board, High-Density
+Multiple Interconnect technology and chip stack memory. The
+visible and IR subsystems have independent power supplies, the IR
+power supply uses off-the-shelf modules and requires only a few
+discrete components for input filtering to assure electromagnetic
+compatibility with the rest of the spacecraft. The spacecraft
+processor performas final data stream formatting for both the IR
+and the visible data.
+
+
+## Mechanical Design
+
+The THEMIS main frame is composed of aluminum and provides the
+mounting interface to the spacecraft as well as the telescope
+assembly, thermal blankets, and thermal control surface. The
+focal plane assemblies are mounted in the main frame using
+brackets that provide for the necessary degrees of freedom for
+alignment to the telescope. The calibration shutter flag is
+stored against a side wall that will maintain a known termperature
+of the flag for calibration purposes. Aluminum covers are
+installed over the electronics circuit cards to provide EMI, RFI,
+and radiation shielding as required. There is no reliance on the
+spacecraft for thermal control of THEMIS, other than the
+application of replacement heater power when the instrument is
+off. The themal control plan includes the use of multi-layer
+insulation blankets and appropriate thermal control surfaces to
+provide a stable thermal environment and a heatsink for the
+electronics and the TE termperature controller on the focal plane
+arrays.
+
+
+## Performance Characteristics
+
+The predicted performance for the infrared bands produced noise
+equivalent delta emissivity values ranging from 0.007 to 0.038
+when viewing Mars at surface temperatures of 245K to 270K. The
+measured SNR values for each band at a reference surface
+temperature of 245K are as follows:
+
+ band 1,2 = 45
+ band 3 = 107
+ band 4 = 169
+ band 5 = 193
+ band 6 = 187
+ band 7 = 194
+ band 8 = 167
+ band 9 = 128
+ band 10 = 120
+
+SNR ratios for the visible imager were computed for a low albedo
+(0.25), flat-lying surface viewed at an incidence angle of 67.5
+degrees under aphelion conditions. The SNR values for this case
+vary from 200 to 400.
+
+
+## Software
+
+The flight software for the IR imager resides on the spacecraft
+computer and performs the formatting and data packetization.
+Instrument commanding will be done using discrete spacecraft
+commands to the THEMIS instrument over an RS-232 command line.
+These commands will consist of:
+
+ 1) IR camera on/off/standby;
+ 2) visible camera on/off/stand-by;
+ 3) calibration flag shutter control and electronics
+ synchronization;
+ 4) instrument parameter settings (gain, offset, integration
+ time, etc.).
+
+The visible imager software runs on two processors: the main
+spacecraft CPU and the internal DSP. The CPU will be responsible
+for instrument operational commands and image post-processing and
+compression. The DSP is responsible for generating the CCD
+clocks, emulating the required analog processing and transmitting
+the data output to the CPU. Lossless predictive compression is
+implemented as part of the DSP firmware. The algorithm employed
+compresses each image line independently by encoding first
+differences with a single, fixed Huffman table. Selective readout
+and pixel summing can also be performed by the DSP software. The
+result of an imaging command is a stream of raw or compressed
+8-bit pixels.
+
+Experience has shown that the volume of data likely to be
+returned from a spacecraft often evolves during a mission.
+Implementing data compression in software on the spacecraft
+computer provides the maximum flexibility for the science and
+spacecraft team to trade-off data return and buffer space usage.
+The compression nodes developed are:
+
+ 1) lossless predictive (capable of applications by the SDP in
+ real-time);
+ 2) a relatively fast discrete cosine transform compression
+ (applied by the spacecraft CPU in 'near realtime' a few
+ tens of seconds);
+ 3) high-quality lossy wavelet compression (applied by the CPU
+ on a longer timescale).
+
+Each compression node has optional pixel summing.
+
+
+# Scientific Objectives
+
+The objectives of the THEMIS experiment are:
+
+ 1) to determine the mineralogy and petrology of localized
+ deposits associated with hydrothermal or sub-aqueous
+ environments, and to identify future landing sites likely to
+ represent these environments.
+
+ 2) to search for pre-dawn thermal anomalies associated with
+ active sub-surface hydrothermal systems.
+
+ 3) to study small-scale geologic processes and landing site
+ characteristics using morphologic and thermophysical
+ properties.
+
+ 4) to investigate polar cap processes at all seasons using
+ infrared observations at high spatial resolution.
+
+ 5) to provide a direct link to the global hyperspectral
+ mineral mappingfrom the Mars Global Surveyor TES
+ investigation by utilizing the same infrared spectral region
+ at high (100m) spatial resolution.
+
+
+# Calibration
+
+The THEMIS instrument was radiometrically, spectrally, and
+spatially calibrated prior to delivery. Three categories of
+calibration were performed: 1) spatial calibration; 2) spectral
+calibration; and 3) radiometric calibration. The radiometric
+calibration included the absolute rediometry, the relative precision
+(SNR), and the calibration stability during an image aquisition.
+The data returned from the instrument in-flight will be converted
+to scene radiance by:
+
+ 1) adjusting for the gain and offset that were applied in the
+ instrument to optimize the dynamic range and signal
+ resolution for each scene;
+
+ 2) correcting for drift or offest that occur between
+ observations of the calibrations flag;
+
+ 3) converting signal to radiance using the instrument response
+ function determined prior to launch.
+
+The response functions necessary to perform this calibration were
+acquired prior to instrument delivery using a thermal vacuum chamber
+at the SBRS facility. See calibration report for details on IR and
+visible image calibration methodologies [CHRISTENSEN2002]
+
+THEMIS images will be calibrated using periodic views of the
+internal calibration flag. This flag will be closed, imaged, and
+reopened at selectable intervals throughout each orbit. Calibration
+data are expected to be acquired every 3-5 minutes. However, the
+optimum spacing of these observations that meets the calibration
+accuracy requirements, while minimizing the loss of surface
+observations, will be determined in Mars orbit.
+
+
+# Operation of THEMIS
+
+The THEMIS instrument is operated from ASU, building on the
+facility and staff developed and in place for the MGS TES
+investigation. No special spacecraft operation or orientation is
+required to obtain THEMIS data. The instrument alternates between
+data collection (<3.5 hours per day) and idle modes based on
+available DSN downlink rates. These modes will fall within
+allocated resources (e.g. power), and will not require power
+cycling of the instrument. All instrument commands are generated
+at ASU, delivered electronically to the Odyssey Project, and
+transmitted to the spacecraft.
+
+
+## Image Collection
+
+IR images can be acquired at selectable image lengths, in
+multiples of 256 lines (25.6 km). The image width is 320 pixels
+(32 km from the nominal mapping orbit) and the length is variable,
+as given by ((#frames)*256 lines) - 240.
+The allowable number of frames varies from 2 to 256, giving
+minimum and maximum image lengths of 272 and 65,296 lines
+respectively (27.2 km and 6,530 km from the nominal mapping
+orbit). The bands returned to the ground are selectable. THEMIS
+visible images can be acquired simultaneously with IR images, but
+the spacecraft can only transfer data from one of the two THEMIS
+imagers at a time. The IR image transfers data as it is being
+collected, while the visible images are stroed within an internal
+THEMIS buffer for later transfer to the spacecraft CPU.
+
+Visible images can be acquired in framelets that are 1024 samples
+crosstrack by 192 lines downtrack in size. The images can be
+composed of any selectable combination of bands and image length
+that can be stored within the 3.734 Mbytes THEMIS internal buffer.
+The size of an image is given by:
+
+ (1024 * 192) * #framelets * #bands < 3.734 Mbytes.
+Thus, for example, either a single-band, 19 framelet (65.6 km)
+image or a 5-band 3-framelet (10.3 km) image can be collected.
+This buffer must be emptied to the spacecraft before a subsequent
+image can be acquired.
+
+
+## Data Allocation
+
+THEMIS data collection will be distributed between the
+mineralogic, temperature, and morphologic science objectives in
+both targeted and global mapping modes. A baseline observing plan
+has been developed to prioritize the total data volume returned by
+THEMIS between the different objectives. This plan currently
+devotes 62% of the total data to the IR imager and 38% to the
+visible, averaged over the course of the Primary Mission. In the
+baselne plane the IR data will be further sub-divided into
+9-wavelength daytime mineralogic observations (47% of total data
+return) and 2-wavelength nighttime and polar temperature mapping
+(15% of total data). The visible data will be sub-divided into
+monochromatic images (36% of total data) and 5-band multi-spectral
+images (2%).
+
+We have assumed a lossless data compression factor of 1.7 for
+the IR imager and a combination of lossless (40%), and lossy with
+compression factors of 4 (30%) and 6(30%) for the visible imager.
+With these allocations, the Science and Relay phases of the
+mission will fully map Mars in daytime IR and will map the planet
+1.5 times in nighttime IR. The visible imaging will cover 60% of
+the planet at 18 meter resolution in one band (80,000 18x50Km
+frames) and <1% in 5-band color. Tradeoffs between monochromatic
+and multi-spectral imaging, as well as variations in the degree of
+lossy compression , will be made to maximize the science return
+from the visible imager.
+
+THEMIS data volume return varies significantly will mission
+phase due to variations n the Earth-Mars distance. In addition,
+the equator crossing local time will vary between ~15.5 H (24 H
+equals one martian day) and 18 H over the course of the mission.
+The first ~180-day phase of the mission provides some of the best
+viewing conditions for the IR imager and will allow ~40% of the
+planet to be observed. IR images acquried during this period will
+be carefully selected using the TES global mineral maps to focus
+on the sites of highest mineralogical or morphological interest.
+During a second IR mapping phase, when the data rates are again
+high and the local time close to 16.5 H, the remaining ~60% of the
+planet will be mapped.
+
+# Principal Investigator
+
+Philip R. Christensen
+Arizona State University
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