/*============================================================================*/ /***************************** MISSION TEMPLATE *******************************/ /* Template: Mission Template Rev: 1993-09-24 */ /* Note: Complete one template for each mission or campaign. Identify */ /* multiple hosts associated with the mission by repeating the */ /* lines beginning and ending with the MISSION_HOST values. For */ /* each instrument_host identified, repeat the 3 lines for the */ /* MISSION_TARGET object for each target associated with the host. */ /* Also complete a separate REFERENCE template for each new */ /* reference submitted to PDS. */ /* Hierarchy: MISSION */ /* MISSION_INFORMATION */ /* MISSION_HOST */ /* MISSION_TARGET */ /* MISSION_REFERENCE_INFORMATION */ /* MODIFICATIONS: */ /* 95-JUL-27 RMONARREZ */ /* Combined P12 and PVO into one template */ /* 98-MAY SJOY */ /* Re-did template */ OBJECT = MISSION MISSION_NAME = "PIONEER VENUS" OBJECT = MISSION_INFORMATION MISSION_START_DATE = 1968-06-01 MISSION_STOP_DATE = 1992-10-07 MISSION_ALIAS_NAME = "P12" MISSION_DESC = " \v Mission Overview ================ The Pioneer mission set the stage for U.S. space exploration. Pioneer 1 was the first manmade object to escape the Earth's gravitational field. Later Pioneer 4 was the first spacecraft to fly to the moon, Pioneer 10 was the first to Jupiter, Pioneer 11 was the first to Saturn and Pioneer 12 was the first U.S. spacecraft to orbit another planet, Venus. The following table summarizes the Pioneer spacecraft and scientific objectives of the Pioneer mission. Name Launch Mission Status (as of 1998) ----------------------------------------------------------------- Pioneer 1 1958-10-11 Moon Reached altitude of 72765 miles Pioneer 2 1958-11-08 Moon Reached altitude of 963 miles Pioneer 3 1958-12-02 Moon Reached altitude of 63580 miles Pioneer 4 1959-03-03 Moon Passed by moon into solar orbit Pioneer 5 1960-03-11 Solar Orbit Entered solar orbit Pioneer 6 1965-12-16 Solar Orbit Still operating Pioneer 7 1966-08-17 Solar Orbit Still operating Pioneer 8 1967-12-13 Solar Orbit Still operating Pioneer 9 1967-11-08 Solar Orbit Signal lost in 1983 Pioneer E 1969-08-07 Solar Orbit Launch failure Pioneer10 1972-03-02 Jupiter Communication terminated 1998 Pioneer11 1972-03-02 Jupiter/Saturn Communication terminated 1997 Pioneer12 1978-05-20 Venus Entered Venus atmos. 1992-10-08 The focus of this document is on Pioneer Venus (12), the last spacecraft in a mission of firsts in space exploration. Pioneer Venus separated into two spacecraft on Aug 8, 1978: an Orbiter (PVO) and a Multiprobe. The latter separated into five 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 encountered Venus on December 4, 1978, and 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 radio science investigations were planned using the S-band telemetry signal carrier and a special X-band beacon included as part of the Orbiter 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) with an orbital period of approximately 24 hours. At the end of the nominal mission (Aug 14, 1979), the spacecraft periapsis was raised from its 150-200 km altitude to more then 2000 km to conserve fuel for an extended mission. As fuel began to run out and periapsis began to drop back down into the Venusian atmosphere the end of the mission could no longer be avoided. On Oct 8, 1992 the Orbiter made its final encounter with the Venus atmosphere. More then 13 years had passed since the end of the nominal mission. During the nominal Orbiter mission all but two experiments operated 100% successfully. One, the Radar Mapper, produced unusable data for a 32-day period from December 18, 1978 to January 19, 1979. The radar instrument was successfully used during the extended mission until the periapsis altitude rose too high. The instrument was not used during the final re-entry phase of the mission at low periapsis due to the success of the Magellan radar mapping mission. The Infrared Radiometer was the other instrument to fail during the nominal mission. It stopped operating after February 14, 1979, but had collected an enormous quantity of valuable information prior to that date. Later in the mission (orbit 3601) the magnetometer data pickup failed such that data from only one of the three sensors (P sensor) was returned to Earth in the telemetry stream. The Multiprobe 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, Radio Science 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. Probe Anomalies: (Table 5-5, p146 Fimmel et al, 1995) ____________________________________________________________________ Anomaly Large North Day Night ____________________________________________________________________ Apparent failure of temperature sensors X X X X Apparent failure of net flux radiometer fluxplate temperature sensors X X X Abrupt changes and spikes in the data from the net flux radiometer X X X Change in the indicated deployment status of the atmospheric structure temperature sensor and net flux radiometer booms X X X Erratic data from two thermocouples embedded in the heat-shield X X X Erratic data from a thermistor measuring junction temperature of the heat-shield thermocouples. X X X Slight variation in the current and voltage levels in the power bus X X X Abrupt changes in the cloud particle size laser alignment monitor X N/A N/A N/A Decrease in the intensity of the beam returned to the cloud particle size spectrometer X N/A N/A N/A Noise spikes in the infrared radiometer X N/A N/A N/A Spikes in the data monitoring the ion pump current of the mass spectrometer analyzer X N/A N/A N/A Spurious reading from the thermocouples when the heat shield was dropped from the probe X N/A N/A N/A The long extended mission allowed the spacecraft controllers to make several comet observations that were never part of the original mission objectives. The tilt of the spacecraft was altered during these comet observations so that the Ultraviolet Spectrometer (OUVS) could view the comets rather than Venus. Comets Encke (April 13-16, 1984), Giacobini-Zinner (Sept 8-15, 1985), Halley (Dec 27, 1985 - Mar 9, 1986), Wilson (Mar 13 - May 2, 1987), NTT (April 8, 1987), and McNaught (Nov 19-24, 1987) were all observed in this way. Mission Phases ============== The Pioneer Venus Orbiter (PVO) phases are presented followed by the Pioneer Venus Multiprobe (PVMP) phases. PIONEER VENUS ORBITER PRELAUNCH ------------------------------- The spacecraft was delivered to the launch site at Kennedy Space Center on March 14, 1978. Spacecraft Id : PVO Target Name : VENUS Mission Phase Start Time : 1968-06-01 Mission Phase Stop Time : 1978-05-20T13:13 Spacecraft Operations Type : ORBITER PIONEER VENUS ORBITER LAUNCH ---------------------------- The spacecraft was launched atop an Atlas-Centaur from Kennedy Space Center. Spacecraft Id : PVO Target Name : VENUS Mission Phase Start Time : 1978-05-20T13:13:0 Mission Phase Stop Time : 1978-05-21 Spacecraft Operations Type : ORBITER PIONEER VENUS ORBITER CRUISE ---------------------------- Two small trajectory correction maneuvers were made on June 1 and November 2, 1978. Interplanetary cruise scientific data were collected. The Pioneer Venus Orbiter completed its 300-million-mile voyage in 6+ months and was placed into Venusian orbit on December 4, 1978. Spacecraft Id : PVO Target Name : VENUS Mission Phase Start Time : 1978-05-21 Mission Phase Stop Time : 1978-12-04 Spacecraft Operations Type : ORBITER VENUS ORBITAL OPERATIONS ----------------------------- The orbiter was placed into Venusian orbit on December 4, 1978, less than a week before the arrival of the Pioneer Venus Multiprobe. The planned mission ended August 4, 1979. The extended mission began August 5, 1979 and ended when the Orbiter entered the Venusian atmosphere on Oct. 8, 1992. Spacecraft Id : PVO Target Name : VENUS Mission Phase Start Time : 1978-12-04 Mission Phase Stop Time : 1992-10-08 Spacecraft Operations Type : ORBITER PIONEER VENUS ORBITER PHASE 1 ----------------------------- Orbiter Phase 1 was the primary mission which began on Dec 4, 1979 at orbital insertion and ended after 1 Venusian year (243 days) on Aug. 4, 1979. During Phase 1, the orbiter periapsis was maintained between 150-200 km altitude using the main thrusters. Spacecraft Id : PVO Target Name : VENUS Mission Phase Start Time : 1978-12-04 Mission Phase Stop Time : 1979-08-04 Spacecraft Operations Type : ORBITER PIONEER VENUS ORBITER PHASE 2 ----------------------------- Orbiter Phase 2 was the extended mission at high periapsis which began on Aug. 5, 1979, immediately following Phase 1. Phase 2 was the period where the project flight controllers did not control periapsis altitude. Periapsis altitude was allowed to rise and fall under the influence of solar perturbations to conserve fuel. Phase 2 ended when the periapsis altitude fell below the 1000 km level in early 1991. Spacecraft Id : PVO Target Name : VENUS Mission Phase Start Time : 1979-08-05 Mission Phase Stop Time : 1991-04-01 Spacecraft Operations Type : ORBITER PIONEER VENUS ORBITER COMETARY OBSERVING PHASE ---------------------------------------------- The long extended mission allowed the spacecraft controllers to make several comet observations that were never part of the original mission objectives. The tilt of the spacecraft was altered during these comet observations so that the Ultraviolet Spectrometer (OUVS) could view the comets rather than Venus. Comets Encke (April 13-16, 1984), Giacobini-Zinner (Sept 8-15, 1985), Halley (Dec 27, 1985 - Mar 9, 1986), Wilson (Mar 13 - May 2, 1987), NTT (April 8, 1987), and McNaught (Nov 19-24, 1987) were all observed in this way. Spacecraft Id : PVO Target Name : VENUS Mission Phase Start Time : 1984-04-13 Mission Phase Stop Time : 1987-11-24 Spacecraft Operations Type : ORBITER PIONEER VENUS ORBITER PHASE 3 (RE-ENTRY) ---------------------------------------- Orbiter Phase 3 describes the extended mission. Late in 1991, the periapsis began to penetrate the lower thermosphere and ionosphere. When it had fallen to about 1000 km, Phase 3 of the mission began. As the periapsis continued to fall, controllers again used the thrusters to maintain periapsis. This time they kept it within an altitude ranging from 140 km to 160 km. Also, the latitude of the periapsis continued moving southward to about 10 degrees below the planet's equator. During Phase 3, the spacecraft sampled the atmosphere to deeper levels than were prudent in Phase 1. Spacecraft Id : PVO Target Name : VENUS Mission Phase Start Time : 1991-04-01 Mission Phase Stop Time : 1992-10-08 Spacecraft Operations Type : ORBITER PIONEER VENUS MULTIPROBE LAUNCH ------------------------------- The spacecraft was launched atop an Atlas-Centaur from Kennedy Space Center. Spacecraft Id : PVMP Target Name : VENUS Mission Phase Start Time : 1978-08-08 Mission Phase Stop Time : 1978-08-08 Spacecraft Operations Type : ATMOSPHERIC PROBE PIONEER VENUS MULTIPROBE ENCOUNTER ---------------------------------- The Multiprobe 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 106 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, Radio Science 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. 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 \v " MISSION_OBJECTIVES_SUMMARY = " \v Mission Objectives Summary ========================== NASA established the Pioneer Venus Science Steering Group in Jan. 1972 in order to enlist widespread science community participation in designing the mission science requirements. This group concluded that a successful mission to Venus would answer the following list of scientific questions (Fimmel et al, 1995, Table 2-2, p25): 1) Cloud layers: What is their number and where are they located? Do they vary over the planet? 2) Cloud forms: Are they layered, turbulent, or merely hazes? 3) Cloud physics: Are the clouds opaque? What are the sizes of the cloud particles? What is the density of the cloud particles? 4) Cloud composition: What is the chemical composition of the clouds? Is it different in the different layers? 5) Solar heating: Where is the solar radiation deposited in the atmosphere? 6) Deep circulation: What is the nature of the wind in the lower regions of the atmosphere? Is there any measurable wind near the surface? 7) Deep driving forces: What are the horizontal differences in temperature in the deep atmosphere? 8) Driving force for the 4-day circulation: What are the horizontal temperature differences at the top of the cloud layer that could cause the high winds there? 9) Loss of water: Has water been lost from Venus? If so, how? 10) Carbon dioxide stability: Why is molecular CO2 stable in the upper atmosphere? 11) Surface composition: What is the composition of the crustal rocks? 12) Seismic activity: What is its level? 13) Earth tides: Do tidal effects from Earth exist at Venus, and if so, how strong are they? 14) Gravitational moments: What is the figure of the planet? What are the higher order gravitational moments? 15) Extent of the 4-day circulation: How does this circulation vary with latitude and depth in the Venusian atmosphere? 16) Vertical temperature structure: Is there an isothermal region? Are there other departures from adiabaticity? What is the structure near the cloud tops? 17) Ionospheric motions: Are these motions sufficient to transport ionization from the day to night hemisphere? 18) Turbulence: How much turbulence is there deep in the atmosphere? 19) Ion chemistry: What is the chemistry of the ionosphere? 20) Exospheric temperature: What is the temperature and does it vary over the planet? 21) Topography: What features exist on the surface of the planet? How do they relate to the thermal maps? 22) Magnetic moments: Does the planet have any internal magnetism? 23) Bulk atmospheric composition: What are the major gases in the Venus atmosphere? How do they vary with altitude? 24) Anemopause: How does the solar wind interact with the planet? The wide range of science questions to be answered by the Pioneer Venus mission could not be answered by an orbiter mission alone. An orbiter could address the questions regarding the upper atmosphere, ionosphere, solar wind, and surface topography, but a probe would be needed to make in situ measurements in the lower atmosphere. Likewise, a single probe would be inadequate to address the all of the questions posed about the lower atmosphere. Multiple probes targeting different parts of the planet simultaneously were required to meet the science objectives. Thus the Pioneer Venus mission developed into an Orbiter and Multiprobe spacecraft. A large number of scientific instruments were required on both the orbiter and the various probes in order to meet the mission science objectives. The orbiter carried 4 remote sensing instruments and 8 in situ experiments. In addition, several radio science experiments were performed using the S-band telemetry signal plus a special X-band beacon that was included on the Orbiter. The first letter of the instrument acronym designates which component of the spacecraft carried the instrument: O for Orbiter, L for Large Probe, S for the Small Probes, and B for the Bus. The remote sensing instruments were: 1) Cloud Photopolarimeter (OCPP), 2) Radar mapper (ORAD), 3) Ultraviolet Spectrometer (OUVS), and 4) Infrared Radiometer (OIR). The in situ instruments included 4 plasma and gamma ray detectors: 1) Ion Mass Spectrometer (OIMS), 2) Electron Temperature Probe (OETP), 3) Retarding Potential Analyzer (ORPA), 4) Plasma Analyzer (OPA), and 5) Gamma Burst Detector (OGBD). In addition, the neutral atmosphere composition was sampled by the Neutral Mass Spectrometer (ONMS), the magnetic field was measured by MAG (OMAG) and the wave electric fields were measured by the Electric Field Detector (OEFD). The large probe, bus, and small probes each carried slightly different instrumentation. The probe instruments were: Neutral Mass Spectrometers (LNMS, SNMS, BNMS), Gas Chromatograph (LGC), Atmospheric Structure experiment (LAS, SAS), Nephelometers (LN, SN), Cloud Particle Size (LCPS), Solar Flux Radiometer (LSFR), Infrared Radiometer (LIR), Net Flux Radiometer (SNFR), Finally, the spacecraft and probe telemetry signal distortions were used to probe the Venus atmosphere and ionosphere. The radio science experiments included the Atmospheric Propagation Experiment (OGPE), Atmospheric Drag (OAD), Differential Long Baseline Interferometry (DBLI), Doppler tracking of the probes (MWIN), Atmospheric Turbulence (MTUR/OTUR), Dual Frequency Occultation (ORO), Internal Density (OIDD), and finally, Celestial Mechanics experiments (OCM). \v " END_OBJECT = MISSION_INFORMATION OBJECT = MISSION_HOST INSTRUMENT_HOST_ID = "PVO" OBJECT = MISSION_TARGET TARGET_NAME = "VENUS" END_OBJECT = MISSION_TARGET END_OBJECT = MISSION_HOST OBJECT = MISSION_HOST INSTRUMENT_HOST_ID = "PVMP" OBJECT = MISSION_TARGET TARGET_NAME = "VENUS" END_OBJECT = MISSION_TARGET END_OBJECT = MISSION_HOST OBJECT = MISSION_REFERENCE_INFORMATION REFERENCE_KEY_ID = "COLIN1980B" END_OBJECT = MISSION_REFERENCE_INFORMATION OBJECT = MISSION_REFERENCE_INFORMATION REFERENCE_KEY_ID = "FIMMELETAL1995" END_OBJECT = MISSION_REFERENCE_INFORMATION END_OBJECT = MISSION /******************************************************************************/ /* Streamlined Instrument Host Template (combined Earthbase and Spacecraft) */ /******************************************************************************/ /* Template: Instrument Host Template Rev: 1993-09-24 */ /* Note: Complete one template for each instrument host. Identify each */ /* instrument host reference by repeating the 3 lines for the */ /* INSTRUMENT_HOST_REFERENCE_INFO object. Also complete a separate */ /* REFERENCE template for each new reference submitted to PDS. */ /* Hierarchy: INSTRUMENT_HOST */ /* INSTRUMENT_HOST_INFORMATION */ /* INSTRUMENT_HOST_REFERENCE_INFO */ /* MODIFICATIONS: */ /* 98-MAY SJOY */ /* Re-did template */ OBJECT = INSTRUMENT_HOST INSTRUMENT_HOST_ID = PVMP OBJECT = INSTRUMENT_HOST_INFORMATION INSTRUMENT_HOST_NAME = "PIONEER VENUS MULTIPROBE" INSTRUMENT_HOST_TYPE = "SPACECRAFT" INSTRUMENT_HOST_DESC = " \v Instrument Host Overview ======================== Mass: 290 kg (bus), 315 kg (large probe), 90 kg (each small probe) Power System: Solar Array of 241 W (bus), Batteries (probes) The Pioneer Venus Multiprobe consisted of a bus which carried one large and three small atmospheric probes. The large probe was released on November 16, 1978 and the three small probes on November 20. All four probes entered the Venus atmosphere on December 9, followed by the bus. The Pioneer Venus large probe was equipped with 7 science experiments, contained within a sealed spherical pressure vessel. This pressure vessel was encased in a nose cone and aft protective cover. After deceleration from initial atmospheric entry at about 11.5 km/s near the equator on the Venus night side, a parachute was deployed at 47 km altitude. The large probe was about 1.5 m in diameter and the pressure vessel itself was 73.2 cm in diameter. The science experiments were: * a neutral mass spectrometer to measure the atmospheric composition * a gas chromatograph to measure the atmospheric composition * a solar flux radiometer to measure solar flux penetration in the atmosphere * an infrared radiometer to measure distribution of infrared radiation * a cloud particle size spectrometer to measure particle size and shape * a nephelometer to search for cloud particles * temperature, pressure, and acceleration sensors The three small probes were identical to each other, 0.8 m in diameter. These probes also consisted of spherical pressure vessels surrounded by an aeroshell, but unlike the large probe, they had no parachutes and the aeroshells did not separate from the probe. Each small probe carried a nephelometer and temperature, pressure, and acceleration sensors, as well as a net flux radiometer experiment to map the distribution of sources and sinks of radiative energy in the atmosphere. The radio signals from all four probes were also used to characterize the winds, turbulence, and propagation in the atmosphere. The small probes were each targeted at different parts of the planet and were named accordingly. The North probe entered the atmosphere at about 60 degrees north latitude on the day side. The night probe entered on the night side. The day probe entered well into the day side, and was the only one of the four probes which continued to send radio signals back after impact, for over an hour. More detailed information on the probes is available. The Pioneer Venus bus also carried two experiments, a neutral mass spectrometer and an ion mass spectrometer to study the composition of the atmosphere. With no heat shield or parachute, the bus survived and made measurements only to about 110 km altitude before burning up. The bus was a 2.5 m diameter cylinder weighing 290 kg, and afforded us our only direct view of the upper Venus atmosphere, as the probes did not begin making direct measurements until they had decelerated lower in the atmosphere. Probe Entry Timing Events: (Table 5-2, p141, Fimmel et al, 1995) Time at Spacecraft, hr:min:sec* - PST - Dec 9, 1978 _______________________________________________________________ Parameter Large North Day Night _______________________________________________________________ End of coast 10:24:26 10:27:57 10:30:27 10:34:08 Initiate telemetry 10:29:27 10:32:55 10:35:27 10:39:08 200 km entry 10:45:32 10:49:40 10:52:18 10:56:13 Radio blackout begin 10:45:53 10:49:58 10:52:40 10:56:27 Signal locked on 10:46:55 10:50:55 10:53:46 10:57:48 Jettison parachute 11:03:28 N/A N/A N/A Impact with surface 11:39:53 11:42:40 11:47:59 11:52:05 Signal ended 11:39:53 11:42:40 12:55:34 11:52:07 Bus Entry 12:12:52 Bus signal ended 12:22:55 _______________________________________________________________ Event Duration _______________________________________________________________ Descent time 54:21 53:00 55:41 55:52 Blackout time 01:02 00:57 01:06 01:21 Time on parachute ~17:07 N/A N/A N/A Surface operations none none 01:07:37 00:02 * Earth receive times were approximately 3 minutes later Probe Entry Impacts: (Table 5-3, p144, Fimmel et al, 1995) _______________________________________________________________ Probe Latitude Longitude Solar-Zenith-Angle Venus Local deg E. deg (SZA) deg Time hr:mm _______________________________________________________________ Large 4.4 N 304.0 65.7 07:38 North 59.3 N 4.8 108.0 03:35 Day 31.3 S 317.0 79.9 06:46 Night 28.7 S 56.7 150.7 00:07 _______________________________________________________________ Bus Entry and Location of Sun and Earth: (Table 5-4, p144, Fimmel et al, 1995) _______________________________________________________________ Probe Lat E.Lon SZA Local Time deg deg deg hr:mm _______________________________________________________________ Bus entry at 200 km 37.9 S 290.9 60.7 08:30 Subsolar 0.5 S 328.5 0 12:00 Sub-Earth 1.6 S 1.7 123.1 03:47 ______________________________________________________________ Probe Anomalies: (Table 5-5, p146 Fimmel et al, 1995) ____________________________________________________________________ Anomaly Large North Day Night ____________________________________________________________________ Apparent failure of temperature sensors X X X X Apparent failure of net flux radiometer fluxplate temperature sensors X X X Abrupt changes and spikes in the data from the net flux radiometer X X X Change in the indicated deployment status of the atmospheric structure temperature sensor and net flux radiometer booms X X X Erratic data from two thermocouples embedded in the heat-shield X X X Erratic data from a thermistor measuring junction temperature of the heat-shield thermocouples. X X X Slight variation in the current and voltage levels in the power bus X X X Abrupt changes in the cloud particle size laser alignment monitor X N/A N/A N/A Decrease in the intensity of the beam returned to the cloud particle size spectrometer X N/A N/A N/A Noise spikes in the infrared radiometer X N/A N/A N/A Spikes in the data monitoring the ion pump current of the mass spectrometer analyzer X N/A N/A N/A Spurious reading from the thermocouples when the heat shield was dropped from the probe X N/A N/A N/A ____________________________________________________________________ \v " END_OBJECT = INSTRUMENT_HOST_INFORMATION OBJECT = INSTRUMENT_HOST_REFERENCE_INFO REFERENCE_KEY_ID = "N/A" END_OBJECT = INSTRUMENT_HOST_REFERENCE_INFO END_OBJECT = INSTRUMENT_HOST /******************************************************************************/ /* Streamlined Instrument Host Template (combined Earthbase and Spacecraft) */ /******************************************************************************/ /* Template: Instrument Host Template Rev: 1993-09-24 */ /* Note: Complete one template for each instrument host. Identify each */ /* instrument host reference by repeating the 3 lines for the */ /* INSTRUMENT_HOST_REFERENCE_INFO object. Also complete a separate */ /* REFERENCE template for each new reference submitted to PDS. */ /* Hierarchy: INSTRUMENT_HOST */ /* INSTRUMENT_HOST_INFORMATION */ /* INSTRUMENT_HOST_REFERENCE_INFO */ /* MODIFICATIONS: */ /* 98-MAY SJOY */ /* Re-did template */ OBJECT = INSTRUMENT_HOST INSTRUMENT_HOST_ID = PVO OBJECT = INSTRUMENT_HOST_INFORMATION INSTRUMENT_HOST_NAME = "PIONEER VENUS ORBITER" INSTRUMENT_HOST_TYPE = SPACECRAFT INSTRUMENT_HOST_DESC = " \v 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]. The main body of the spacecraft is a flat cylinder 2.5 meters in diameter and 1.2 meters high. In the upper end of this cylinder there is a circular equipment shelf with an area of 4.37 square meters on which all the scientific instruments and electronic subsystems are mounted. The shelf is mounted on the forward end of a thrust tube that connects the spacecraft to the launch vehicle. Below the shelf, 15 thermal louvers control heat radiation from an equipment compartment located between the shelf and the top of the spacecraft. A cylindrical solar array attached to the shelf by 24 brackets forms the circumference of the flat cylinder of the spacecraft. The spacecraft spins about its cylindrical axis wit ha nominal spin period of 12 seconds. On top of the spacecraft, a 1.09 meter diameter, despun, high-gain, parabolic dish antenna is mounted on a mast so that its line of sight clears equipment mounted outside the spacecraft. The despun design allows the antenna to be mechanically directed to Earth from the spinning spacecraft. The antenna operates at S- and X-bands. The spacecraft also carries a solid propellant rocket motor. Including the antenna mast, the Orbiter is almost 4.5 meters high, and it weighed 553 kg when launched. The launch weight included 45 kg of scientific instruments and 179 kg of rocket propellant. Orbital Characteristics: (Table 5-6, p150, Fimmel et al, 1995) Parameter Value __________________________________________________________ Periapsis, km (miles) 150-200 (93-124) Apoapsis, km (miles 66,900 (41,572) Eccentricity 0.842 Average period, hr 24.03 Inclination to Equator, deg 105.6 Periapsis Latitude 17.0 N Periapsis Longitude, deg (orbit 5) 170.2 E __________________________________________________________ Platform Descriptions ===================== MAGNETOMETER BOOM ----------------- An 4.8 meter long boom (188.9 inches) that was unfurled and extended automatically after launch. The magnetometer boom is located 240 degrees from the X-axis of the spacecraft coordinate system, measured in towards the Y-axis (in the spin direction) of the spin plane (XY). The total distance from the end of the boom to the orbiter spin axis is 5.94 meters (234.0 inches). \v " END_OBJECT = INSTRUMENT_HOST_INFORMATION OBJECT = INSTRUMENT_HOST_REFERENCE_INFO REFERENCE_KEY_ID = NOTHWANG1980 END_OBJECT = INSTRUMENT_HOST_REFERENCE_INFO OBJECT = INSTRUMENT_HOST_REFERENCE_INFO REFERENCE_KEY_ID = FIMMELETAL1995 END_OBJECT = INSTRUMENT_HOST_REFERENCE_INFO END_OBJECT = INSTRUMENT_HOST /******************** DATASET TEMPLATE ****************************************/ /* Template: Spacecraft Data Set Template Rev: 19890121 */ /* Note: The following templates form part of a standard set */ /* for the submission of a single dataset to the PDS. */ /* Hierarchy: SCDATASET */ /* DATASETINFO */ /* DATASETTARG */ /* DSPARMINFO */ /* SCDSHOST */ /* DSREFINFO */ /* REFERENCE */ /* REFAUTHORS */ OBJECT = SCDATASET DATA_SET_ID = "PVO-V-POS-6-SEDR-ORBITATTITUDE--V1.0" OBJECT = DATASETINFO DATA_SET_NAME = "PVO V SUPP EXPERIMENTER DATA RECORD SC ORBIT/ATTITUDE V1.0" DATA_SET_COLLECTION_MEMBER_FLG = N START_TIME = 1978-12-05T06:55:00.000Z STOP_TIME = 1992-10-08T18:14:07.018Z NATIVE_START_TIME = UNK NATIVE_STOP_TIME = UNK DATA_OBJECT_TYPE = TIME_SERIES DATA_SET_RELEASE_DATE = 1993-07-01 PROCESSING_LEVEL_ID = 6 PRODUCER_FULL_NAME = UNK PRODUCER_INSTITUTION_NAME = "NASA AMES RESEARCH CENTER" SOFTWARE_FLAG = N DETAILED_CATALOG_FLAG = N PROCESSING_START_TIME = UNK PROCESSING_STOP_TIME = UNK DATA_SET_DESC = " This dataset contains the Supplemental Experimenter Data Records (SEDR) as provided by the Pioneer project to the Magnetometer team (C.T. Russell - PI). The dataset covers the entire period of orbital operations, orbits 1-5055 (1978-12-05 to 1992-10-07). Each orbit was originally provided on a separate IBM 9-track 800 bpi tape which contained 6 files: 1) Standard Label file [sl] , 2) Ephemeris file [ep], 3) S/C Attitude file [at], 4) Pulse Time file [pt], 5) Selected Roll Reference file [sr], 6) Spin period file [sp]. The original structure has been preserved within the limitations of the CD-ROM media, and the PDS data archive rules. The data remain in individual orbit files in IBM binary and EBCDIC representations. One additional file has been provided by the UCLA Magnetometer team who have taken the primary responsibility for the SEDR archive. There is a ''corrected pulse time file'' which is identical to the original pulse time file in structure but which differs in content. The data in this file have been corrected using the OEFD phase information from the XXXXX channel. These data give a more accurate approximation of the actual Sun pulse than is contained in the raw SEDR data. When there are no OEFD data available to make this correction, there is no corrected pulse time file. This situation occurs near solar conjunctions." CONFIDENCE_LEVEL_NOTE = " The original SEDR data have not been altered or corrected in any way during the archive process. A ''corrected pulse time'' file has been included in this archive which was not a part of the original SEDR." END_OBJECT = DATASETINFO OBJECT = DATASETTARG TARGET_NAME = VENUS END_OBJECT = DATASETTARG OBJECT = DSPARMINFO SAMPLING_PARAMETER_NAME = "TIME" SAMPLING_PARAMETER_RESOLUTION = "N/A" MINIMUM_SAMPLING_PARAMETER = "N/A" MAXIMUM_SAMPLING_PARAMETER = "N/A" SAMPLING_PARAMETER_INTERVAL = "N/A" MINIMUM_AVAILABLE_SAMPLING_INT = "N/A" SAMPLING_PARAMETER_UNIT = "N/A" DATA_SET_PARAMETER_NAME = "S/C EPHEMERIDES" NOISE_LEVEL = "N/A" DATA_SET_PARAMETER_UNIT = "N/A" END_OBJECT = DSPARMINFO OBJECT = SCDSHOST INSTRUMENT_HOST_ID = PVO INSTRUMENT_ID = POS END_OBJECT = SCDSHOST OBJECT = DSREFINFO REFERENCE_KEY_ID = "PC-456.O4" OBJECT = REFERENCE DOCUMENT_TOPIC_TYPE = "DATA USER REQUIREMENTS" JOURNAL_NAME = "PIONEER VENUS PROJECT SPECIFICATION PC-456.O4" PUBLICATION_DATE = 1976-05-15 REFERENCE_DESC = " NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Ames Research Center Moffett Field, California PIONEER VENUS PROJECT SPECIFICATION PC-456.O4 PIONEER VENUS: DATA USER REQUIREMENTS FOR SUPPLEMENTARY EXPERIMENTER DATA RECORDS May 15, 1976" OBJECT = REFAUTHORS AUTHOR_FULL_NAME = "N/A" END_OBJECT = REFAUTHORS END_OBJECT = REFERENCE END_OBJECT = DSREFINFO END_OBJECT = SCDATASET /********************** PARAMETER CATALOG TEMPLATE ****************************/ /* Template: Parameter Template Rev: 19890121 */ /* Note: This template shall be completed for each combination */ /* of data set parameter name, instrument parameter */ /* name and instrument host id associated with a dataset. */ /* Hierarchy: PARAMETER */ OBJECT = PARAMETER INSTRUMENT_HOST_ID = PVO DATA_SET_PARAMETER_NAME = "S/C EPHEMERIDES" INSTRUMENT_PARAMETER_NAME = "S/C EPHEMERIDES" IMPORTANT_INSTRUMENT_PARMS = 1 END_OBJECT = PARAMETER /*************** DATASET INSTRUMENT PARAMETER DESCRIPTION TEMPLATE ************/ /* Template: Data Set Instrument Parameter Description Template Rev: 19890121 */ /* Note: This template shall be completed for any */ /* data set or instrument parameter description. */ /* Hierarchy: DSINSTPARMD */ OBJECT = DSINSTPARMD DATA_SET_OR_INSTRUMENT_PARM_NM = "S/C EPHEMERIDES" DATA_SET_OR_INST_PARM_DESC = "S/C EPHEMERIDES consist of the various spacecraft position and orientation parameters necessary to to locate the spacecraft in time and space." END_OBJECT = DSINSTPARMD /*********************** SC COORDS TEMPLATE ***********************************/ /* MODIFICATIONS: */ /* 930309 -- MKNIFFIN/SJOY modified with ctr and sjoy info. */ /* 930310 -- MKNIFFIN ran clean on jpl lvtool */ /* 930315 -- SJOY updated totally. */ /* 930526 -- SJOY added remaining coordinate systems for use in SEDR */ /* CD-ROM production. All PVO coordinate systems now defined. */ /* Template: Coordinate System Template Rev: 19890121 */ /* Note: The following templates form part of a standard */ /* set for the submission of a Coordinate System */ /* to the PDS. */ /* Hierarchy: COORDINATE */ /* COORDINFO */ /* VECTOR */ /* VECTORCOMP */ /* VECTORD */ /* /**************************************************************************** /* Spinning S/C Coordinates /**************************************************************************** /* OBJECT = COORDINATE COORDINATE_SYSTEM_ID = PVO_SSCC OBJECT = COORDINFO COORDINATE_SYSTEM_NAME = "PVO SPINNING SPACECRAFT COORDS" COORDINATE_SYSTEM_CENTER_NAME = PVO COORDINATE_SYSTEM_REF_EPOCH = "N/A" COORDINATE_SYSTEM_DESC = " Spacecraft coordinates (Xs, Ys, Zs) are used to describe the physical mounting locations of the Sun sensors, the star sensor, and the experiment sensors. The spacecraft coordinate system is centered at the spacecraft center of mass and rotates with the spacecraft. The Xs-Ys plane is parallel to the plane of the spacecraft equipment shelf. The positive Zs axis points out the top of the spacecraft. The positive Ys axis coincides with the split line of the equipment shelf. With no spacecraft wobble or nutation, the spacecraft positive Zs axis will coincide with the spin axis and the equipment shelf will thus be perpendicular to the spin axis." END_OBJECT = COORDINFO OBJECT = VECTOR VECTOR_COMPONENT_TYPE = SSCC_X OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = XS REFERENCE_OBJECT_NAME = "N/A" REFERENCE_TARGET_NAME = "N/A" VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " The +Xs axis of the PVO spacecraft coordinate system is defined to lie in a plane parallel to the equipment shelf at 90 degrees to the split-line of the equipment shelf measured in the direction opposing the spacecraft spin direction." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = SSCC_Y OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = YS REFERENCE_OBJECT_NAME = "N/A" REFERENCE_TARGET_NAME = SPACECRAFT VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " The +Ys axis of the PVO spacecraft coordinate system is defined to lie in a plane parallel to the equipment shelf and follow the split-line of the equipment shelf." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = SSCC_Z OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = ZS REFERENCE_OBJECT_NAME = "N/A" REFERENCE_TARGET_NAME = SPACECRAFT VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " The positive Zs axis points out the top of the spacecraft. With no spacecraft wobble or nutation, the spacecraft positive Zs axis will coincide with the spin axis and the equipment shelf will thus be perpendicular to the spin axis." END_OBJECT = VECTORD END_OBJECT = VECTOR END_OBJECT = COORDINATE /* /**************************************************************************** /* Inertial S/C Coordinates /**************************************************************************** /* OBJECT = COORDINATE COORDINATE_SYSTEM_ID = PVO_ISCC OBJECT = COORDINFO COORDINATE_SYSTEM_NAME = "PVO INERTIAL SPACECRAFT COORDS" COORDINATE_SYSTEM_CENTER_NAME = PVO COORDINATE_SYSTEM_REF_EPOCH = "N/A" COORDINATE_SYSTEM_DESC = " The inertial spacecraft coordinate system for the PVO spacecraft is same coordinate system as the spinning spacecraft coordinate system (SSCC) except that it does not spin with the spacecraft. Thus the Spin axis or positive Z axis direction is the same in both systems and it points out the top (toward the BAFTA assembly) of the spacecraft. The axes in the spin plane are defined as follows: The X-Z plane is defined to contain the spacecraft-Sun vector with the positive X direction being sunward, and the coordinate system is defined to be right-handed. The transformation from SSCC to ISCC is: _ _ | cos(p) -sin(p) 0 | | sin(p) cos(p) 0 | | 0 0 1 | _ _ where p is the spin phase angle measured in ISSC coordinates." END_OBJECT = COORDINFO OBJECT = VECTOR VECTOR_COMPONENT_TYPE = ISCC_X OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = PVO_X REFERENCE_OBJECT_NAME = "N/A" REFERENCE_TARGET_NAME = SPACECRAFT VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " The X component of the PVO spacecraft coordinate system lies in the sunward direction, such that the X-Z plane contains the sun. The X component is measured positive towards the sun." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = ISCC_Y OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = PVO_Y REFERENCE_OBJECT_NAME = "N/A" REFERENCE_TARGET_NAME = SPACECRAFT VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " The Y component is formed by the right-handed vector cross product of the X and Z unit vectors where the Z axis is defined as the spacecraft spin axis and the X-Z plane contains the Sun." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = ISCC_Z OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = PVO_Z REFERENCE_OBJECT_NAME = "N/A" REFERENCE_TARGET_NAME = SPACECRAFT VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " The Z axis is defined to be anti-parallel to the spacecraft spin axis during orbital operations." END_OBJECT = VECTORD END_OBJECT = VECTOR END_OBJECT = COORDINATE /**************************************************************************** /* VSO Coordinates /**************************************************************************** /* MODIFICATIONS: /* 930223 -- MKNIFFIN /* created template OBJECT = COORDINATE COORDINATE_SYSTEM_ID = VSO OBJECT = COORDINFO COORDINATE_SYSTEM_NAME = "VENUS SOLAR ORBITAL COORDS" COORDINATE_SYSTEM_CENTER_NAME = "VENUS" COORDINATE_SYSTEM_REF_EPOCH = "N/A" COORDINATE_SYSTEM_DESC = " The VSO coordinate system is a Cartesian coordinate system centered on Venus. The components of this coordinate system are as follows: The X axis direction points from the center of Venus to the Sun, taken positive towards the Sun, the Z axis is parallel to the northward pole of the Venus orbital plane, the Y axis completes the right-handed set and points towards dusk. Locations of bodies (spacecraft) given in VSO coordinates are usually represented in units of Venus radii where Rv = 6052 km." END_OBJECT = COORDINFO OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = VSO_X REFERENCE_OBJECT_NAME = SUN REFERENCE_TARGET_NAME = VENUS VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " The X component of the VSO coordinate system is taken to be positive in the direction of the Sun measured along the Venus- Sun line. The units are commonly given in Venus Radii where Rv = 6052 km" END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = VSO_Y REFERENCE_OBJECT_NAME = SUN REFERENCE_TARGET_NAME = VENUS VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " The Y component of the VSO coordinate system is taken to be positive in the direction opposing orbital motion (dusk) and lying in the orbital plane of Venus. The units are commonly given in Venus Radii where Rv = 6052 km" END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = VSO_Z REFERENCE_OBJECT_NAME = SUN REFERENCE_TARGET_NAME = VENUS VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " The Z component of the VSO coordinate system is taken to be parallel to the pole of the Venus orbital plane and positive in the northward direction (upward normal). The units are commonly given in Venus Radii where Rv = 6052 km" END_OBJECT = VECTORD END_OBJECT = VECTOR END_OBJECT = COORDINATE /**************************************************************************** /* Inertial Spherical Coordinates - Equatorial /**************************************************************************** OBJECT = COORDINATE COORDINATE_SYSTEM_ID = ISC_EQTR OBJECT = COORDINFO COORDINATE_SYSTEM_NAME = "EQUATORIAL INERT SPHRCL COORDS" COORDINATE_SYSTEM_CENTER_NAME = "EARTH" COORDINATE_SYSTEM_REF_EPOCH = 1950.0 COORDINATE_SYSTEM_DESC = " The EQUATORIAL INERTIAL SPHERICAL COORDINATE system is defined by the equatorial plane of the Earth for the reference epoch of 1950.0. The principal direction vectors of this system are the Earth's Equatorial Pole and the Vernal Equinox direction. The components of the coordinate system are: 1) Radius: Distance from the reference body to the spacecraft. 2) Declination: The angle between the reference body-spacecraft radius vector and the reference body equatorial plane, measured positive north of the equatorial plane. 3) Right Ascension: The angle between the Vernal Equinox line and the projection of the reference body-spacecraft radius vector onto the Earth equatorial plane, measured eastward from the Vernal Equinox line. 4) Inertial Speed (V): The magnitude of the inertial velocity of the spacecraft. 5) Inertial Flight Path Angle (GAMMA): The angle between the spacecraft inertial velocity vector and the plane perpendicular to the reference-body-to-spacecraft (radius) vector; positive when measured away from the reference body. 6) Inertial Azimuth Angle (SIGMA): The angle, measured in the plane perpendicular to the reference-body-to-spacecraft (radius) vector, from the projection of true north into that plane eastward to the projection of the inertial velocity vector into that plane. When the reference body is taken to be the Earth, this becomes the coordinate system EME-50. (FK-4)" END_OBJECT = COORDINFO OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = RADIUS REFERENCE_OBJECT_NAME = UNK REFERENCE_TARGET_NAME = SPACECRAFT VECTOR_COMPONENT_UNIT = "UNK" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " Radius: Distance from the reference body to the spacecraft." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = LATITUDE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = DECLNATN REFERENCE_OBJECT_NAME = UNK REFERENCE_TARGET_NAME = SPACECRAFT VECTOR_COMPONENT_UNIT = "UNK" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " Declination: The angle between the reference body-spacecraft radius vector and the reference body equatorial plane, measured positive north of the equatorial plane. " END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = LONGITUDE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = "R ASCNSN" REFERENCE_OBJECT_NAME = UNK REFERENCE_TARGET_NAME = SPACECRAFT VECTOR_COMPONENT_UNIT = "UNK" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " Right Ascension: The angle between the Vernal Equinox line and the projection of the reference body-spacecraft radius vector onto the Earth equatorial plane, measured eastward from the Vernal Equinox line." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = VELOCITY OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = "V" REFERENCE_OBJECT_NAME = UNK REFERENCE_TARGET_NAME = SPACECRAFT VECTOR_COMPONENT_UNIT = "UNK" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " Inertial Speed (V): The magnitude of the inertial velocity of the spacecraft." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = VELOCITY OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = GAMMA REFERENCE_OBJECT_NAME = UNK REFERENCE_TARGET_NAME = SPACECRAFT VECTOR_COMPONENT_UNIT = "UNK" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " Inertial Flight Path Angle (GAMMA): The angle between the spacecraft inertial velocity vector and the plane perpendicular to the reference-body-to-spacecraft (radius) vector; positive when measured away from the reference body." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = VELOCITY OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = SIGMA REFERENCE_OBJECT_NAME = UNK REFERENCE_TARGET_NAME = SPACECRAFT VECTOR_COMPONENT_UNIT = "UNK" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " Inertial Azimuth Angle (SIGMA): The angle, measured in the plane perpendicular to the reference-body-to-spacecraft (radius) vector, from the projection of true north into that plane eastward to the projection of the inertial velocity vector into that plane." END_OBJECT = VECTORD END_OBJECT = VECTOR END_OBJECT = COORDINATE /**************************************************************************** /* Inertial Spherical Coordinates - Ecliptic /**************************************************************************** OBJECT = COORDINATE COORDINATE_SYSTEM_ID = ISC_ECLP OBJECT = COORDINFO COORDINATE_SYSTEM_NAME = "ECLIPTIC INERTL SPHERCL COORDS" COORDINATE_SYSTEM_CENTER_NAME = "EARTH" COORDINATE_SYSTEM_REF_EPOCH = 1950.0 COORDINATE_SYSTEM_DESC = " The ECLIPTIC INERTIAL SPHERICAL COORDINATE system is defined by the ecliptic plane of the Earth for the reference epoch of 1950.0. The principal direction vectors of this system are the Earth's Ecliptic Pole and the Vernal Equinox direction. The components of the coordinate system are: 1) Radius: Distance from the reference body to the spacecraft. 2) Celestial Latitude: The angle between the reference body-spacecraft radius vector and the reference body ecliptic plane, measured positive north of the ecliptic plane. 3) Celestial Longitude: The angle between the Vernal Equinox line and the projection of the reference body-spacecraft radius vector onto the Earth ecliptic plane, measured eastward from the Vernal Equinox line. 4) Inertial Speed (V): The magnitude of the inertial velocity of the spacecraft. 5) Inertial Flight Path Angle (GAMMA): The angle between the spacecraft inertial velocity vector and the plane perpendicular to the reference-body-to-spacecraft (radius) vector; positive when measured away from the reference body. 6) Inertial Azimuth Angle (SIGMA): The angle, measured in the plane perpendicular to the reference-body-to-spacecraft (radius) vector, from the projection of true north into that plane eastward to the projection of the inertial velocity vector into that plane. When the reference body is taken to be the Earth, this becomes the coordinate system ECL-50." END_OBJECT = COORDINFO OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = RADIUS REFERENCE_OBJECT_NAME = UNK REFERENCE_TARGET_NAME = SPACECRAFT VECTOR_COMPONENT_UNIT = "UNK" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " Radius: Distance from the reference body to the spacecraft." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = LATITUDE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = "CLST LAT" REFERENCE_OBJECT_NAME = UNK REFERENCE_TARGET_NAME = SPACECRAFT VECTOR_COMPONENT_UNIT = "UNK" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " Celestial Latitude: The angle between the reference body-spacecraft radius vector and the reference body ecliptic plane, measured positive north of the ecliptic plane. " END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = LONGITUDE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = "CLST LNG" REFERENCE_OBJECT_NAME = UNK REFERENCE_TARGET_NAME = SPACECRAFT VECTOR_COMPONENT_UNIT = "UNK" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " Celestial Longitude: The angle between the Vernal Equinox line and the projection of the reference body-spacecraft radius vector onto the ecliptic plane, measured eastward from the Vernal Equinox line." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = VELOCITY OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = "V" REFERENCE_OBJECT_NAME = UNK REFERENCE_TARGET_NAME = SPACECRAFT VECTOR_COMPONENT_UNIT = "UNK" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " Inertial Speed (V): The magnitude of the inertial velocity of the spacecraft." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = VELOCITY OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = GAMMA REFERENCE_OBJECT_NAME = UNK REFERENCE_TARGET_NAME = SPACECRAFT VECTOR_COMPONENT_UNIT = "UNK" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " Inertial Flight Path Angle (GAMMA): The angle between the spacecraft inertial velocity vector and the plane perpendicular to the reference-body-to-spacecraft (radius) vector; positive when measured away from the reference body." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = VELOCITY OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = SIGMA REFERENCE_OBJECT_NAME = UNK REFERENCE_TARGET_NAME = SPACECRAFT VECTOR_COMPONENT_UNIT = "UNK" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " Inertial Azimuth Angle (SIGMA): The angle, measured in the plane perpendicular to the reference-body-to-spacecraft (radius) vector, from the projection of true north into that plane eastward to the projection of the inertial velocity vector into that plane." END_OBJECT = VECTORD END_OBJECT = VECTOR END_OBJECT = COORDINATE /**************************************************************************** /* Earth-Sun Line Cartesian Coordinates /**************************************************************************** OBJECT = COORDINATE COORDINATE_SYSTEM_ID = "ESL-CART" OBJECT = COORDINFO COORDINATE_SYSTEM_NAME = "EARTH-SUN LINE CARTES COORDS" COORDINATE_SYSTEM_CENTER_NAME = SUN COORDINATE_SYSTEM_REF_EPOCH = "N/A" COORDINATE_SYSTEM_DESC = " The Earth-Sun Line Cartesian coordinate system is defined to have the X-Y plane be the instantaneous ecliptic plane with the positive Z direction taken to be the Sun-centered, northward ecliptic normal. The positive X direction is away from the Sun along the Sun-Earth line. Y completes the righthanded set and is positive away from the Sun. Note: This system rotates with the Earth about the Sun." END_OBJECT = COORDINFO OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = ESL_X REFERENCE_OBJECT_NAME = SUN REFERENCE_TARGET_NAME = EARTH VECTOR_COMPONENT_UNIT = "UNK" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " The X component of the ESL coordinate system is taken to be positive in the direction away from the Sun measured along the Earth- Sun line." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = ESL_Y REFERENCE_OBJECT_NAME = SUN REFERENCE_TARGET_NAME = EARTH VECTOR_COMPONENT_UNIT = "UNK" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " The Y component of the ESL coordinate system is taken to be positive away from the Sun in the direction of orbital motion (dawn) and lying in the ecliptic plane." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = ESL_Z REFERENCE_OBJECT_NAME = SUN REFERENCE_TARGET_NAME = EARTH VECTOR_COMPONENT_UNIT = "UNK" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " The Z component of the ESL coordinate system is taken to be the Sun-centered pole of the ecliptic plane and positive in the northward direction (upward normal)." END_OBJECT = VECTORD END_OBJECT = VECTOR END_OBJECT = COORDINATE /**************************************************************************** /* Inertial Cartesian Coordinate System - Equatorial /**************************************************************************** OBJECT = COORDINATE COORDINATE_SYSTEM_ID = ICC_EQTL OBJECT = COORDINFO COORDINATE_SYSTEM_NAME = "EQUATORIAL INERTIAL CART COORD" COORDINATE_SYSTEM_CENTER_NAME = "UNK" COORDINATE_SYSTEM_REF_EPOCH = 1950.0 COORDINATE_SYSTEM_DESC = " The Equatorial Inertial Cartesian Coordinate System is defined for the reference epoch of 1950.0 The X-direction is positive away from the reference body towards the Vernal Equinox which is determined by the line of intersection between the mean Earth equatorial plane and the ecliptic plane of reference. The Y direction is measured outward from the center of the reference body, perpendicular to and east of the the X-axis, and lying in the equatorial plane of reference. The Z direction is positive toward the north equatorial pole of reference, from the center of the reference body." END_OBJECT = COORDINFO OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = ICC_X REFERENCE_OBJECT_NAME = "N/A" REFERENCE_TARGET_NAME = "N/A" VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = "The X-direction is positive away from the reference body towards the Vernal Equinox which is determined by the line of intersection between the mean Earth equatorial plane and the ecliptic plane of reference." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = ICC_Y REFERENCE_OBJECT_NAME = "N/A" REFERENCE_TARGET_NAME = "N/A" VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = "The Y direction is measured outward from the center of the reference body, perpendicular to and east of the the X-axis, and lying in the equatorial plane of reference." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = ICC_Z REFERENCE_OBJECT_NAME = "N/A" REFERENCE_TARGET_NAME = "N/A" VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = "The Z direction is positive toward the north equatorial pole of reference, from the center of the reference body." END_OBJECT = VECTORD END_OBJECT = VECTOR END_OBJECT = COORDINATE /**************************************************************************** /* Inertial Cartesian Coordinate System - Ecliptic /**************************************************************************** OBJECT = COORDINATE COORDINATE_SYSTEM_ID = ICC_ECLP OBJECT = COORDINFO COORDINATE_SYSTEM_NAME = "ECLIPTIC INERTIAL CART COORDS" COORDINATE_SYSTEM_CENTER_NAME = "UNK" COORDINATE_SYSTEM_REF_EPOCH = 1950.0 COORDINATE_SYSTEM_DESC = " The Equatorial Inertial Cartesian Coordinate System is defined for the reference epoch of 1950.0 The X-direction lies in the Ecliptic Plane and is positive away from the reference body towards the Vernal Equinox which is determined by the line of intersection between the mean Earth equatorial plane and the ecliptic plane of reference. The Y direction is measured outward from the center of the reference body, perpendicular to and east of the the X-axis, and lying in the ecliptic plane of reference. The Z direction is positive toward the north ecliptic pole of reference, from the center of the reference body." END_OBJECT = COORDINFO OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = ICC_X REFERENCE_OBJECT_NAME = "N/A" REFERENCE_TARGET_NAME = "N/A" VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = "The X-direction lies in the Ecliptic Plane and is positive away from the reference body towards the Vernal Equinox which is determined by the line of intersection between the mean Earth equatorial plane and the ecliptic plane of reference." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = ICC_Y REFERENCE_OBJECT_NAME = "N/A" REFERENCE_TARGET_NAME = "N/A" VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = "The Y direction is measured outward from the center of the reference body, perpendicular to and east of the the X-axis, and lying in the ecliptic plane of reference." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = ICC_Z REFERENCE_OBJECT_NAME = "N/A" REFERENCE_TARGET_NAME = "N/A" VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = "The Z direction is positive toward the north ecliptic pole of reference, from the center of the reference body." END_OBJECT = VECTORD END_OBJECT = VECTOR END_OBJECT = COORDINATE /**************************************************************************** /* Body-Fixed Spherical Coordinate System /**************************************************************************** /* MODIFICATIONS: /* 930223 -- MKNIFFIN /* created template OBJECT = COORDINATE COORDINATE_SYSTEM_ID = BFS_CRDS OBJECT = COORDINFO COORDINATE_SYSTEM_NAME = "BODY FIXED SPHERICAL COORDS" COORDINATE_SYSTEM_CENTER_NAME = "UNK" COORDINATE_SYSTEM_REF_EPOCH = "N/A" COORDINATE_SYSTEM_DESC = " The body-fixed spherical coordinate system is the familiar Geographic coordinate system at Earth generalized to other planets. The system consists of the components Radius, Latitude, Longitude. The definition of the prime meridian varies for each planet as does the rotation period. It is crucial to know the exact definition of these variables when changing the reference body. Note: This coordinate system rotates with the reference body." END_OBJECT = COORDINFO OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = RADIUS REFERENCE_OBJECT_NAME = "N/A" REFERENCE_TARGET_NAME = "SPACECRAFT" VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " Radius: Distance from the reference body to the spacecraft." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = LATITUDE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = PHI REFERENCE_OBJECT_NAME = "N/A" REFERENCE_TARGET_NAME = "SPACECRAFT" VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " phi = Latitude: The body-centered latitude of the spacecraft measured positive north of the reference body's equatorial plane." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = LONGITUDE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = THETA REFERENCE_OBJECT_NAME = "N/A" REFERENCE_TARGET_NAME = "SPACECRAFT" VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = " theta - Longitude: the longitude of the spacecraft measured eastward from the prime meridian of the reference body to the projection of the radius vector on the equatorial plane." END_OBJECT = VECTORD END_OBJECT = VECTOR END_OBJECT = COORDINATE /**************************************************************************** /* Spacecraft Centered Ecliptic Coordinates /**************************************************************************** /* MODIFICATIONS: /* 930223 -- MKNIFFIN /* created template OBJECT = COORDINATE COORDINATE_SYSTEM_ID = SCC_ECLP OBJECT = COORDINFO COORDINATE_SYSTEM_NAME = "SC CENTERED ECLIPTIC COORDS" COORDINATE_SYSTEM_CENTER_NAME = "SPACECRAFT" COORDINATE_SYSTEM_REF_EPOCH = 1950.0 COORDINATE_SYSTEM_DESC = " The Spacecraft Centered Ecliptic coordinates system (Xe, Ye, Ze) is used to describe the locations of the roll reference celestial objects (Sun or star) and the planet Venus. The coordinate system is centered at the spacecraft center of mass. The Xe-Ye plane is parallel to the Ecliptic Plane and the Ze axis points to the North Ecliptic Pole. The Xe axis points towards the Vernal Equinox. Directions in this coordinate system are described by Celestial Longitude and Celestial Latitude." END_OBJECT = COORDINFO OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = Xe REFERENCE_OBJECT_NAME = "SPACECRAFT" REFERENCE_TARGET_NAME = "N/A" VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = "The Xe-direction lies in the plane parallel to the Ecliptic Plane which passes through the spacecraft center of mass. It is positive away from the spacecraft towards the Vernal Equinox which is determined by the line of intersection between the mean Earth equatorial plane and the ecliptic plane of reference." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = Ye REFERENCE_OBJECT_NAME = "SPACECRAFT" REFERENCE_TARGET_NAME = "N/A" VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = "The Ye-direction is measured outward from the center of the spacecraft perpendicular to and east of the the X-axis, and lying in the plane parallel to the Ecliptic Plane which passes through the spacecraft center of mass." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = Ze REFERENCE_OBJECT_NAME = "SPACECRAFT" REFERENCE_TARGET_NAME = "N/A" VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = "The Ze-direction is positive toward the North Equatorial Pole of reference, measured from the center of mass of the spacecraft." END_OBJECT = VECTORD END_OBJECT = VECTOR END_OBJECT = COORDINATE /**************************************************************************** /* Non-Rotating Spin Coordinates /**************************************************************************** /* MODIFICATIONS: /* 930223 -- MKNIFFIN /* created template OBJECT = COORDINATE COORDINATE_SYSTEM_ID = NRSC OBJECT = COORDINFO COORDINATE_SYSTEM_NAME = "NON-ROTATING SPIN COORDINATES" COORDINATE_SYSTEM_CENTER_NAME = "SPACECRAFT" COORDINATE_SYSTEM_REF_EPOCH = 1950.0 COORDINATE_SYSTEM_DESC = " The roll angle of the roll reference object will be calculated in this coordinate system as well as the roll angles of the Fs, RIP, RAM, and NADIR signals. The non-rotating coordinate system (Wx, Wy, Wz) is centered at the spacecraft center of mass. The Wz-axis is parallel to the spacecraft spin axis. The Wx-Wy plane is perpendicular to the spacecraft spin axis. The Wx-Wz plane includes the Vernal Equinox of reference. Thus the Wx-axis is at the intersection of the plane perpendicular to the spacecraft spin axis and the plane containing the spin axis and the Vernal Equinox. Roll angles in this coordinate system are measured in the Wx-Wy plane from the roll reference direction." END_OBJECT = COORDINFO OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = Wx REFERENCE_OBJECT_NAME = "SPACECRAFT" REFERENCE_TARGET_NAME = "N/A" VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = "The Wx-direction is positive away from the spacecraft center of mass in the direction defined by the intersection of the plane perpendicular to the spin axis and the plane containing the Vernal Equinox and the spin axis." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = Wy REFERENCE_OBJECT_NAME = "SPACECRAFT" REFERENCE_TARGET_NAME = "N/A" VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = "The Wy-direction is measured outward from the center of mass of the spacecraft, perpendicular to and east of the the X-axis, and lying in the plane perpendicular to the spacecraft spin axis." END_OBJECT = VECTORD END_OBJECT = VECTOR OBJECT = VECTOR VECTOR_COMPONENT_TYPE = RANGE OBJECT = VECTORCOMP VECTOR_COMPONENT_ID = Wz REFERENCE_OBJECT_NAME = "SPACECRAFT" REFERENCE_TARGET_NAME = "N/A" VECTOR_COMPONENT_UNIT = "N/A" END_OBJECT = VECTORCOMP OBJECT = VECTORD VECTOR_COMPONENT_TYPE_DESC = "The Wz-direction is parallel to the spacecraft spin axis, measured from the spacecraft center of mass, positive in the direction of the spacecraft angular momentum." END_OBJECT = VECTORD END_OBJECT = VECTOR END_OBJECT = COORDINATE