/*============================================================================*/ /***************************** MISSION TEMPLATE *******************************/ /* MODIFICATIONS: */ /* 920929 RMONARREZ */ /* Generated from database */ /* Template: Mission Template Rev: 19890121 */ /* Note: The following templates form part of a standard set */ /* for the submission of a mission to the PDS. */ /* Hierarchy: MISSION */ /* MSNINFO */ /* MSNPHSINFO */ /* MSNREFINFO */ /* REFERENCE */ /* REFAUTHORS */ OBJECT = MISSION MISSION_NAME = "PIONEER VENUS" OBJECT = MSNINFO MISSION_START_DATE = 1978-05-20 MISSION_STOP_DATE = 1992-10-07 MISSION_ALIAS_NAME = "P12" MISSION_DESC = " Pioneer Venus Overview 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 106 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). At the time this Special Issue was submitted for publication the nominal mission was complete and the Orbiter was continuing into an extended mission phase. It appears that sufficient fuel remains to permit full operation through calendar year 1980, at least. 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 will be acquired during the extended Orbiter mission. The other, the Infrared Radiometer, failed to operate after February 14, 1979, but had collected and 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 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, 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. The scientific payload, Principal Investigator, and his affiliation are listed in Table I for each Pioneer Venus spacecraft. This Special Issue is primarily devoted to short descriptions of the instruments listed. All are contained herein with one exception: Orbiter Cloud Photopolarimeter. Detailed instrument descriptions for this experiment have been published [2]. Before proceeding with descriptions of the individual instruments, four special archival-type reports are included. The first deals with spacecraft design and operation [3]. The Pioneer Venus spacecraft were unique and very special design features and operational modes needed to be incorporated. These are summarized therein. Similarly, telemetry recovery, particularly for the Multiprobe mission, was unusually demanding and unique techniques were developed and employed. The Orbiter and Multiprobe systems are described in two papers [4], [5]. Finally, a special ground data handling and distribution system, developed after an Atmospheric Explorer program model, was developed and is described [6]. Only one radioscience experiment description is specifically presented [7]. The necessary information for the others are contained in the telemetry recovery papers [3], [4]. It should be noted that neither the scientific objectives nor the scientific results for the Pioneer Venus program are described or discussed in detail. The objectives have been published elsewhere [8], [9]. The reader is referred to two special journal issues devoted to initial scientific results published to data [10], [11]. References [1] L. Colin and C.F. Hall, Space Sci. Rev., vol. 20, no. 3, p. 283, May 1977. [2] E.E. Russell, L. A. Watts, S. F. Pellicori, and D. L. Coffeen, 'Orbiter cloud photopolarimeter for the Pioneer Venus mission,' Proc. Soc. Photo-Optical Instrum. Eng., vol. 112, Aug. 1977. L. D. Travis, 'Imaging and polarimetry with the Pioneer Venus orbiter cloud photopolarimeter,' Proc. Photo-Optical Instrum. Eng., vol. 183, 1979. [3] G. J. Nothwang, 'Pioneer Venus Spacecraft Design and Operation,' IEEE Trans. on Geosci. and Remote Sensing, vol. GE-18, no. 1 pp 5-10, January, 1980. [4] A. L. Berman and R. Ramos, 'Pioneer Venus Occultation Radio Science Data Generation,' IEEE Trans. on Geosci. and Remote Sensing, vol. GE-18, no. 1 pp 11-14. [5] R. B. Miller and R. Ramos, 'Pioneer Multiprobe Entry Telemetry Recovery,' IEEE Trans. on Geosci. and Remote Sensing, vol. GE-18, no. 1 pp 15-19, January, 1980. [6] J. A. Ferandin, J. Brownwood, C. Weeks, and R. Pak, 'Pioneer Venus Unified Abstract Data Library and Quick Look Data Delivery System,' IEEE Trans. on Geosci. and Remote Sensing, vol. GE-18, no. 1 pp 19-27, January, 1980. [7] J. R. Smith and R. Ramos, 'Data Acquisition for Measuring the Wind on Venus from Pioneer Venus', IEEE Trans. on Geosci. and Remote Sensing, vol. GE-18, no. 1 pp 126-130, January, 1980. [8] Space Sci. Rev., vol. 20 no. 3, May 1977. [9] Space Sci. Rev., vol. 20 no. 4, June 1977. [10] Science, vol. 203 no. 4382, Feb. 23 1979. [11] Science, vol. 205 no. 4401, July 6 1979." MISSION_OBJECTIVES_SUMMARY = " The two Pioneer flights to Venus were intended to explore the atmosphere of the planet, to study its surface using radar, and to determine its global shape and internal density distribution. The Pioneer Venus Orbiter was designed to operate for 8 months or more making direct and remote sensing measurements. The Pioneer Venus Multiprobe spacecraft was designed to separate into 5 separate atmospheric entry craft some 12.9 million km (8 million miles) before reaching Venus. Each probe craft was designed to make measurements of the characteristics of the atmosphere from its highest regions to the surface of the planet in a period of a little more than 2 hours at points spread over the Earth-facing hemisphere of the planet." OBJECT = MSNPHSINFO SPACECRAFT_ID = PVO TARGET_NAME = VENUS MISSION_PHASE_TYPE = "ORBITAL OPERATIONS" SPACECRAFT_OPERATIONS_TYPE = "ORBITER OPERATIONS" MISSION_PHASE_START_TIME = 1978-12-05 MISSION_PHASE_STOP_TIME = 1992-10-02 MISSION_PHASE_DESC = " This mission phase 'orbiter operations' describes the entire mission of the Orbiter spacecraft." END_OBJECT = MSNPHSINFO OBJECT = MSNPHSINFO SPACECRAFT_ID = PVMP TARGET_NAME = VENUS MISSION_PHASE_TYPE = ENCOUNTER SPACECRAFT_OPERATIONS_TYPE = "ATMOSPHERIC PROBE" MISSION_PHASE_START_TIME = 1978-12-07 MISSION_PHASE_STOP_TIME = 1978-12-07 MISSION_PHASE_DESC = " This mission phase 'encounter' describes all operations of the 5 separate probe components of the Multiprobe component of the Pioneer Venus mission." END_OBJECT = MSNPHSINFO END_OBJECT = MSNINFO OBJECT = MSNREFINFO REFERENCE_KEY_ID = "COLIN1980B" OBJECT = REFERENCE DOCUMENT_TOPIC_TYPE = "MISSION DESCRIPTION" JOURNAL_NAME = "IEEE TRANSACTIONS ON GEOSCIENCE AND REMOTE SENSING" PUBLICATION_DATE = 1980 REFERENCE_DESC = " Colin, L., 'Pioneer Venus Overview', IEEE Transactions on Geoscience and Remote Sensing, January 1980, Vol GE-18, No. 1, p5-10" OBJECT = REFAUTHORS AUTHOR_FULL_NAME = "LAWRENCE COLIN" END_OBJECT = REFAUTHORS END_OBJECT = REFERENCE END_OBJECT = MSNREFINFO END_OBJECT = MISSION /*============================================================================*/ /*********************** SPACECRAFT TEMPLATE **********************************/ /* MODIFICATIONS: */ /* Template: Spacecraft Template Rev: 19890121 */ /* Note: The following templates form part of a standard */ /* set for the submission of a spacecraft to the PDS. */ /* Hierarchy: SPACECRAFT */ /* SCINFO */ /* PLATFORM */ /* SCREFINFO */ /* REFERENCE */ /* REFAUTHORS */ OBJECT = SPACECRAFT SPACECRAFT_ID = "PVO" OBJECT = SCINFO LAUNCH_DATE = 1978-05-20 INSTRUMENT_HOST_NAME = "PIONEER VENUS ORBITER" INSTRUMENT_HOST_TYPE ="SPACECRAFT" SPACECRAFT_DESC = " Extracted from: `Pioneer Venus Spacecraft Design and Operation' IEEE Transactions on Geoscience and Remote Sensing, vol. GE-18, No. 1, January 1980 By George J. Nothwang I. Introduction 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. A photograph of the Multiprobe (foreground) and Orbiter in the manufacturer's facility (Hughes Aircraft Company, El Segundo, CA) is shown on the cover. II. Spacecraft Design and Operation The design and operation of the orbiter will be described first and the Multiprobe second. The Multiprobe description and operation will then be separated into the Bus, Large Probe, and Small Probe segments. A. Orbiter The general configuration of the Orbiter after launch by an Atlas SLV-3D/Centaur D-1 AR is shown in Fig. 1. The weight of the spacecraft and 12 scientific instruments immediately after separation from the launch vehicle was 553 kg (1220 lbs) which included 32 kg (70 lbs) of hydrazine for trajectory correction maneuvers and spin axis orientation and 179 kg (398 lbs) of orbit insertion motor solid propellant and inserts. Immediately after separation from the Centaur launch vehicle, the spacecraft was automatically spun up to approximately 6.5 rpm and after establishing satisfactory ground communications with the Deep Space Network (DSN), commands to deploy the magnetometer boom and to orient the spacecraft spin axis perpendicular to the ecliptic were transmitted. The nominal spin rate was increased to 15 rpm with the spin axis (+Z axis) pointed in a northerly direction and this attitude was maintained in the cruise phase of the mission except during short periods for trajectory corrections. Communications were normally maintained through the despun high-gain antenna to maximize the data rates. Two days before reaching Venus, the spacecraft was configured for orbit insertion. Communications were transferred to the omni antennas and the spacecraft including the high- gain antenna spun up to 52 rpm to provide acceptable gyroscopic stiffness during motor burn. Since the motor burn had to occur while the spacecraft was being occulted by Venus, commands were loaded and subsequently executed from the on-board stored command logic without real-time communication. Orbit insertion was achieved with an orbit inclination of 105 degrees with respect to the equator and a nominal orbit period of 24 h. After reacquisition of the spacecraft from occultation, a series of maneuvers were performed to point the spacecraft spin axis (=Z axis) perpendicular to the ecliptic in a southerly direction, despin the high-gain antenna, and slow the spacecraft spin rate to about 5 rpm, the preferred rate for scientific data. Nominal orbital operations were then begun which include orbit periapsis and period adjustments and spacecraft attitude adjustments. 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 Subsystem, Data Handling subsystem, Command Subsystem, Communications Subsystem, and Power Subsystem. 1) Mechanical: The mechanical features of the spacecraft can be described by six basic assemblies, as seen in Fig. 1. 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. 2) 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 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 and 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. 3) 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 and star sensors), science roll reference signals generation, and spin period measurements; 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. 4) 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. 5) 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 16 384-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). 6) 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. 7) 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 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. 8) Power: The power subsystem provides semiregulated 28 V 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 over-current 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." END_OBJECT = SCINFO OBJECT = PLATFORM PLATFORM_OR_MOUNTING_NAME = "MAGNETOMETER BOOM" PLATFORM_OR_MOUNTING_DESC = " 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)" END_OBJECT = PLATFORM OBJECT = SCREFINFO REFERENCE_KEY_ID = NOTHWANG1980 OBJECT = REFERENCE DOCUMENT_TOPIC_TYPE = "SPACECRAFT DESIGN" JOURNAL_NAME = "IEEE TRANSACTIONS ON GEOSCIENCE AND REMOTE SENSING" PUBLICATION_DATE = 1980 REFERENCE_DESC = " Nothwang, G.T., `Pioneer Venus Spacecraft Design and Operation', IEEE Transactions on Geoscience and Remote Sensing, January 1980, Vol GE-18, No. 1, p5-10" OBJECT = REFAUTHORS AUTHOR_FULL_NAME = "GEORGE J. NOTHWANG" END_OBJECT = REFAUTHORS END_OBJECT = REFERENCE END_OBJECT = SCREFINFO END_OBJECT = SPACECRAFT /******************** 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 = "UNK" /*1950.0*/ 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 = "UNK" /* 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 = "UNK" /* 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 = "UNK" /* 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 = "UNK" /* 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 = "UNK" 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 = "UNK" /* 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 = "UNK" /* 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