urn:nasa:pds:magellan_losapdr:data_calibrated:los_06207_001 1.0 1.20.0.0 Product_Observational 2024-02-27 1.0 Initial PDS4 version 1992-11-15T07:55:32.269Z 1992-11-15T09:07:12.269Z Magellan Mission urn:nasa:pds:context:investigation:mission.magellan data_to_investigation Magellan Host urn:nasa:pds:context:instrument_host:spacecraft.mgn is_instrument_host Radio Science Subsystem for MGN Instrument urn:nasa:pds:context:instrument:mgn.rss is_instrument Venus Planet urn:nasa:pds:context:target:planet.venus data_to_target LOSAPDR 4 6207 Mapping Cycle 4 Jet Propulsion Laboratory los_06207_001 processing_information_to_data_object LOSRES.1996.4.1 l06207.001 los_06207_001 1996-06-12T15:46:13 The LOSAPDR (Line of Sight Acceleration Profile Data Record) is a set of three tables represented in ASCII character format that summarize the analysis of radio tracking data of orbiting planetary spacecraft (specifically, Magellan). The first table identifies input parameters and conditions; the second table gives times between which spline fits to data points are valid; and the third table gives times, Doppler residuals, spline fit residuals, and inferred values of spacecraft acceleration with respect to the nominal gravity field (MGN120PSAAP) and orbit. The LOSAPDR was produced at the Jet Propulsion Laboratory under the supervision of W.L. Sjogren.

0 30502 PDS3 Original attached PDS3 label

LOSAPDR_HEADER_TABLE 30502 1 The LOSAPDR header includes input data and summary results from initial ODP and LUNRES calculations. It is a single-row table with 42 columns, two of which have three elements each. The data are represented as ASCII characters; entries are delimited by commas. The total of the data plus delimiters is 1030 characters, followed by 180 padding characters and a carriage-return line-feed pair. The row thus has 1212 characters. Carriage-Return Line-Feed 46 0 1212 Planetary_Radius 1 1 ASCII_Real 23 km The assumed radius of the spherical planet (program mnemonic RADIUS). GM 2 25 ASCII_Real 23 km^3/sec^2 Assumed gravitational constant for the planet. Calendar_Epoch 3 49 ASCII_Date_Time_YMD 23 The calendar epoch in ephemeris time of the initial state vector at the spacecraft. The initial state vector is given by the spacecraft position and velocity (program mnemonic CEPOCH). Julian_Ephemeris_Days 4 73 ASCII_Real 23 day The Julian date corresponding to CEPOCH (ephemeris time at the spacecraft) (program mnemonic JED). Spacecraft_Position_X 5 97 ASCII_Real 23 km >The X component of the spacecraft position vector at CEPOCH, calculated in program ODP (program mnemonic XS). Spacecraft_Position_Y 6 121 ASCII_Real 23 km >The Y component of the spacecraft position vector at CEPOCH, calculated in program ODP (program mnemonic YS). Spacecraft_Position_Z 7 145 ASCII_Real 23 km >The Z component of the spacecraft position vector at CEPOCH, calculated in program ODP (program mnemonic ZS). Spacecraft_Velocity_X 8 169 ASCII_Real 23 km/sec >The X component of the spacecraft velocity vector at CEPOCH, calculated in program ODP (program mnemonic DXS). Spacecraft_Velocity_Y 9 193 ASCII_Real 23 km/sec >The Y component of the spacecraft velocity vector at CEPOCH, calculated in program ODP (program mnemonic DYS). Spacecraft_Velocity_Z 10 217 ASCII_Real 23 km/sec >The Z component of the spacecraft velocity vector at CEPOCH, calculated in program ODP (program mnemonic DZS). Spacecraft_Longitude 11 241 ASCII_Real 23 degree Planetocentric longitude of the spacecraft corresponding to the spacecraft position at CEPOCH (program mnemonic LONEP). Spacecraft_Hour_Angle 12 265 ASCII_Real 23 degree The hour angle of the spacecraft corresponding to spacecraft position at CEPOCH (program mnemonic HANG). DOBKS 13 289 ASCII_Integer 2 Flag for constant (-1) or variable (+1) time spacing in spline fits. If DOBKS=+1, the time intervals in BKTIMX will be unequal. Record_Spacing 14 292 ASCII_Real 23 minute Time spacing of the output records in the RESULTS_TABLE (program mnemonic DTACC). Large values may mean that spacing defaults to the spacing of the data points (no interpolated data). MINBKS 15 316 ASCII_Integer 10 Minimum number of data points in each spline interval (used only if DOBKS=+1). MAXBKS 16 327 ASCII_Integer 10 Maximum number of data points in each spline interval (used only if DOBKS=+1). Band 17 338 ASCII_Real 23 mm/sec Conversion factor from Doppler to acceleration. Nominally 0.2955 for X-band data and 1.0833 for S-band data. TADD 18 362 ASCII_Real 23 minute Time from CEPOCH to first data point (at the spacecraft). TFIT 19 386 ASCII_Real 23 minute Time from TADD to last data point (at the spacecraft). DFIT 20 410 ASCII_Real 23 minute Length of each spline interval (used only when DOBKS=-1). Reject 21 434 ASCII_Real 23 Hz Threshold for rejection of bad data points. Earth_Longitude 22 458 ASCII_Real 23 degree Planetocentric longitude of Earth at CEPOCH (program mnemonic LNE). Earth_Latitude 23 482 ASCII_Real 23 degree Planetocentric north latitude of Earth at CEPOCH (program mnemonic LTE). TRANSA 24 506 ASCII_Real 23 sec One-way downlink light-time for a photon leaving the spacecraft at CEPOCH. TRANSB 25 530 ASCII_Real 23 sec/sec Rate of change of TRANSA. DUTSEC 26 554 ASCII_Real 23 sec Difference between ephemeris time (ET) and universal time (UT). REFEP 27 578 ASCII_Date_Time_YMD 23 Reference epoch for TRANSA and TRANSB at the spacecraft (same time system, and often the same value, as CEPOCH). Orbital_Semimajor_Axis 28 602 ASCII_Real 23 km Semi-major axis of spacecraft orbit. Obtained in the orbit solution of program ODP (program mnemonic SMA). Orbital_Eccentricity 29 626 ASCII_Real 23 Eccentricity of spacecraft orbit. Obtained in the orbit solution of program ODP (program mnemonic ECC). Orbital_Inclination 30 650 ASCII_Real 23 degree Inclination of spacecraft orbit. Obtained in the orbit solution of program ODP (program mnemonic INC). Ascending_Node_Longitude 31 674 ASCII_Real 23 degree Ascending node of spacecraft orbit. Obtained in the orbit solution of program ODP (program mnemonic NODE). Periapsis_Argument_Angle 32 698 ASCII_Real 23 degree Argument of periapsis for spacecraft orbit. Obtained in the orbit solution of program ODP (program mnemonic ARG). True_Anomaly_Angle 33 722 ASCII_Real 23 degree True anomaly of spacecraft orbit. Obtained in the orbit solution of program ODP (program mnemonic F). Mean_Anomaly_Angle 34 746 ASCII_Real 23 degree Mean anomaly of spacecraft orbit. Obtained in the orbit solution of program ODP (program mnemonic M). Eccentric_Anomaly_Angle 35 770 ASCII_Real 23 degree Eccentric anomaly of spacecraft orbit. Obtained in the orbit solution of program ODP (program mnemonic E). Orbital_period 36 794 ASCII_Real 23 hour Period of spacecraft orbit. Obtained in the orbit solution of program ODP (program mnemonic P). Periapsis_Latitude 37 818 ASCII_Real 23 degree Planetocentric north latitude at periapsis for spacecraft orbit (program mnemonic LATPER). Periapsis_Longitude 38 842 ASCII_Real 23 degree Planetocentric longitude of periapsis for spacecraft orbit (program mnemonic LONPER). Periapsis_Radius 39 866 ASCII_Real 23 km Spacecraft distance from target center of mass at periapsis (program mnemonic RPER). Periapsis_Velocity 40 890 ASCII_Real 23 km/sec Spacecraft velocity at peripasis (program mnemonic VPER). Periapsis_Altitude 41 914 ASCII_Real 23 km Spacecraft altitude over reference surface at periapsis (program mnemonic APER). Apoapsis_Radius 42 938 ASCII_Real 23 km Spacecraft distance from target center of mass at apoapsis (program mnemonic RAPO). Apoapsis_Velocity 43 962 ASCII_Real 23 km/sec Spacecraft velocity at apoapsis (program mnemonic VAPO). Apoapsis_Altitude 44 986 ASCII_Real 23 km Spacecraft altitude over reference surface at apoapsis (program mnemonic AAPO). NBKS 45 1010 ASCII_Integer 10 Number of times in the Times Table defining spline intervals. NPOINT 46 1021 ASCII_Integer 10 Number of data points used to make this file. LOSAPDR_TIMES_TABLE 31714 87 The LOSAPDR times table contains exact times bounding each spline interval. Each row contains one 23-digit number, 177 spaces, and a carriage-return line-feed pair. Carriage-Return Line-Feed 1 0 202 Spline_Break_Times 1 1 ASCII_Real 23 minute The exact times of spline interval boundaries measured from midnight at the spacecraft (program mnemonic BKTIMX). LOSAPDR_RESULTS_TABLE 49288 1838 The LOSAPDR Results Table contains the results from spline fits to Doppler tracking residuals. Each row in the table contains times, Doppler residuals, spacecraft position information, residuals to spline fits, and inferred spacecraft acceleration with respect to the nominal orbit. Each row has length 202 bytes; the first 200 are column data delimited by commas; the last two are a carriage-return line-feed pair. Carriage-Return Line-Feed 11 0 202 HH 1 1 ASCII_Integer 2 hour The hour of a Doppler residual data point at the spacecraft. MM 2 4 ASCII_Integer 2 minute The minute of a Doppler residual data point at the spacecraft. ss 3 7 ASCII_Integer 2 sec The whole seconds of a Doppler residual data point at the spacecraft. Note that there are generally fractional seconds; for full time accuracy use OFFSET TIME. Offset_Time 4 10 ASCII_Real 23 minute Offset from CEPOCH to the time of the Doppler residual data point or interpolation (program mnemonic DMIN). Doppler_Residual 5 34 ASCII_Real 23 Hz Doppler residual from input data (program mnemonic DATA_RESID). Spacecraft_Altitude 6 58 ASCII_Real 23 km Spacecraft altitude over reference surface (program mnemonic SC_ALT). Spacecraft_Latitude 7 82 ASCII_Real 23 degree Spacecraft planetocentric north latitude (program mnemonic SC_LAT). Spacecraft_Longitude 8 106 ASCII_Real 23 degree Spacecraft planetocentric longitude (program mnemonic SC_LON). Fit_Residual 9 130 ASCII_Real 23 Hz Doppler residual from fitted spline at HHMMSS (program mnemonic FIT_RESID). Acceleration 10 154 ASCII_Real 23 mm/sec^2 Acceleration from fitted Doppler residual (program mnemonic ACCEL). Harmonic_Acceleration 11 178 ASCII_Real 23 mm/sec^2 The acceleration in the line-of-sight direction due to the spherical harmonic gravity field (MGN120PSAAP). This acceleration is to be added to the acceleration from the Doppler residual to obtain the total line-of-sight acceleration.