DAF/SPK SPKMERGE !FBIG-IEEEFTPSTR: : : : :::ENDFTP\beginlabelPDS_VERSION_ID = PDS3RECORD_TYPE = FIXED_LENGTHRECORD_BYTES = 1024^SPICE_KERNEL = "dii_preenc174_nav_v1.bsp"MISSION_NAME = "DEEP IMPACT"SPACECRAFT_NAME = "DEEP IMPACT IMPACTOR SPACECRAFT"DATA_SET_ID = "DI-C-SPICE-6-V1.0"KERNEL_TYPE_ID = SPKPRODUCT_ID = "dii_preenc174_nav_v1.bsp"PRODUCT_CREATION_TIME = 2006-03-01T14:14:33PRODUCER_ID = "DI NAV/JPL"MISSION_PHASE_NAME = { "9P CRUISE", "9P ENCOUNTER", "9P POST-ENCOUNTER CRUISE" }PRODUCT_VERSION_TYPE = ACTUALPLATFORM_OR_MOUNTING_NAME = "N/A"START_TIME = 2005-01-12T19:22:28STOP_TIME = 2006-01-19T23:58:54SPACECRAFT_CLOCK_START_COUNT = "N/A"SPACECRAFT_CLOCK_STOP_COUNT = "N/A"TARGET_NAME = "9P/TEMPEL 1 (1867 G1)"INSTRUMENT_NAME = "N/A"NAIF_INSTRUMENT_ID = "N/A"SOURCE_PRODUCT_ID = "N/A"NOTE = "See comments in the file for details"OBJECT = SPICE_KERNEL INTERCHANGE_FORMAT = BINARY KERNEL_TYPE = EPHEMERIS DESCRIPTION = "DII SPICE SP-Kernel file containing DIIspacecraft trajectory reconstructed from radio tracking data as wellplanetary ephemerides and ephemerides for the DI mission targets, created byDI Navigation Team, JPL, covering the whole mission. "END_OBJECT = SPICE_KERNEL\endlabelDII SPK file, Complete Mission, Last Pre-Encounter Solution (174)=========================================================================== Created by Boris Semenov, NAIF/JPL, September 20, 2005 from SPK files produced by the Deep Impact (DI) Navigation (NAV) team during mission operations.Objects in the Ephemeris-------------------------------------------------------- This file contains ephemeris data for Deep Impact Impactor (DII) spacecraft (NAIF ID -70), DI primary mission target comet Tempel 1 (NAIF ID 1000093), Sun, and planets and planet barycenters.Approximate Time Coverage-------------------------------------------------------- The DII trajectory and comet and planetary ephemerides provided in this file cover the whole DI primary mission, from launch through the beginning of 2006: COVERAGE BEGIN TIME (TDB): 2005 JAN 12 19:23:32.068 COVERAGE END TIME (TDB): 2006 JAN 19 23:59:59.000Status-------------------------------------------------------- This file was created by merging regular OD SPK files produced during the mission for into a single file intended for archiving with the Planetary Data System (PDS).Pedigree-------------------------------------------------------- The original regular NAV OD solution SPK files used to produce this file were created and delivered to the DI project data base (DOM) by the DI NAV Team. At the end of the mission the NAV team identified a subset of the files containing the best trajectory and providing complete coverage for the whole mission. NAIF merged selected data from these files to create this SPK, using SPKMERGE program. The DII spacecraft trajectory data provided in this file came from the following source SPKs (name extension for all files in the table is .bsp): SPK File Name Start UTC Stop UTC ------------------------ -------------------- -------------------- spk_od004-radio (*) 2005 JAN 12 19:22:27 2005 JAN 22 04:00:00 spk_od007-radio (*) 2005 JAN 22 04:00:00 2005 FEB 12 00:00:00 spk_od019 (*) 2005 FEB 12 00:00:00 2005 MAY 06 00:00:00 spk_od039-radio (*) 2005 MAY 06 00:00:00 2005 JUN 01 00:00:00 spk_od174_dtumble_impact 2005 JUN 01 00:00:00 2005 JUL 04 05:46:00 dii_fixed_to_comet 2005 JUL 04 05:46:00 2006 JAN 19 23:58:54 (*) The first four source SPKs in the list provided trajectory for the DI Flyby (DIF) spacecraft rather than for the DII spacecraft; this trajectory was for the s/c with -140. Since during all that time DII was attached to the DIF and no DII SPK were made, these DIF files were used to get trajectory from the beginning of the mission. After merging, the Flyby ID was changed from -140 to -70 using DAFMOD utility program. Note that the source SPK ``spk_od174_dtumble_impact.bsp'' containing spacecraft trajectory for encounter period was created prior to the encounter (on July 3, 2005 around 15:00 UTC); therefore, it provides predicted DII spacecraft trajectory for the encounter that is not accurate enough to be used in the encounter data processing. The trajectory in this source SPK did not end at the time of closest approach to the comet center (2005 JUL 04 05:44:48.500 UTC, determined from DII and comet trajectories stored in this file, NOT the actual impact time). Instead, the DII went right through the comet as if it was continuing to fly on on a ballistic path. In merging process, this data was cut off not exactly at the closest approach time but at about a minute after it -- at 2005 JUL 04 05:46 -- to allow more flexibility in using this file as a starting point in any process that would attempt to perform a DII trajectory adjustment. The ``dii_fixed_to_comet'' SPK providing trajectory past the cut-off time of the ``spk_od174_dtumble_impact.bsp'' (2005 JUL 04 05:46) was prepared by NAIF. It contains DII position as zero offset from the comet center. The comet Tempel 1 ephemerides provided in this file were extracted from the source SPK file ``sb-9p-od174.bsp'' that contained the comet ephemeris used in producing the spacecraft SPK covering the encounter (``spk_od174_dtumble_impact.bsp''.) The planetary ephemerides provided in this file were extracted from the ``de405s.bsp'' SPK file containing DE405 ephemerides used by the NAV team during the whole primary mission. The Appendix 1 of these comments contains the complete log generated by SPKMERGE/DAFMOD run that created this SPK.Segment Boundary Discontinuities-------------------------------------------------------- This SPK file contains a number of spacecraft trajectory SPK segments that came from original individual SPK files. Although, each segment provides continuous trajectory within the interval that it covers, in general a position and velocity discontinuity exists at the boundary of the segment and the segments whose coverage immediately precede and follow it. The times and magnitudes of these discontinuities are provided in the Appendix 2 of these comments.Contacts-------------------------------------------------------- If you have questions regarding this data contact Boris V. Semenov (818)-354-8136 Boris.Semenov@jpl.nasa.gov or DI NAV Team: Mark S. Ryne (818)-354-8101 Mark.S.Ryne@jpl.nasa.govAppendix 1: SPKMERGE Log--------------------------------------------------------; dii_preenc174_nav_v1.bsp LOG FILE; Created 2005-09-16/16:00:00.00.;; BEGIN SPKMERGE COMMANDSLEAPSECONDS_KERNEL = /kernels/gen/lsk/naif0007.tlsSPK_KERNEL = dii_preenc174_nav_v1.bsp SOURCE_SPK_KERNEL = /ftp/pub/naif/DEEPIMPACT/kernels/spk/spk_od004-radio.bsp INCLUDE_COMMENTS = NO BODIES = -140 BEGIN_TIME = 2005 JAN 12 19:22:27.884 END_TIME = 2005 JAN 22 04:00:00.000 SOURCE_SPK_KERNEL = /ftp/pub/naif/DEEPIMPACT/kernels/spk/spk_od007-radio.bsp INCLUDE_COMMENTS = NO BODIES = -140 BEGIN_TIME = 2005 JAN 22 04:00:00.000 END_TIME = 2005 FEB 12 00:00:00.000 SOURCE_SPK_KERNEL = /ftp/pub/naif/DEEPIMPACT/kernels/spk/spk_od019.bsp INCLUDE_COMMENTS = NO BODIES = -140 BEGIN_TIME = 2005 FEB 12 00:00:00.000 END_TIME = 2005 MAY 06 00:00:00.000 SOURCE_SPK_KERNEL = /ftp/pub/naif/DEEPIMPACT/kernels/spk/spk_od039-radio.bsp INCLUDE_COMMENTS = NO BODIES = -140 BEGIN_TIME = 2005 MAY 06 00:00:00.000 END_TIME = 2005 JUN 01 00:00:00.000SOURCE_SPK_KERNEL = /ftp/pub/naif/DEEPIMPACT/kernels/spk/spk_od174_dtumble_impact.bsp INCLUDE_COMMENTS = NO BODIES = -70 BEGIN_TIME = 2005 JUN 01 00:00:00.000 END_TIME = 2005 JUL 04 05:46:00.000 SOURCE_SPK_KERNEL = dii_fixed_to_comet.bsp INCLUDE_COMMENTS = NO BODIES = -70 BEGIN_TIME = 2005 JUL 04 05:46:00.000 END_TIME = 2006 JAN 19 23:58:54.816 SOURCE_SPK_KERNEL = sb-9p-od174.bsp INCLUDE_COMMENTS = NO BODIES = 1000093 BEGIN_TIME = 2005 JAN 12 19:22:27.884 END_TIME = 2006 JAN 19 23:58:54.816 SOURCE_SPK_KERNEL = /ftp/pub/naif/DEEPIMPACT/kernels/spk/de405s.bsp INCLUDE_COMMENTS = NO BODIES = 499, 299, 199, 399, 301, 10, 9, 8, 7, 6, 5, 4, 3, 2, 1 BEGIN_TIME = 2005 JAN 12 19:22:27.884 END_TIME = 2006 JAN 19 23:58:54.816; END SPKMERGE COMMANDS===================================================== !!!!!!!!!!!!!!!!!!!Warning !!!!!!!!!!!!!!!!!=====================================================This file was modified by the SPICE program "DAFMOD" ona PC running Linux.Date and time modified: 2005-SEP-16 16:01:19Every occurrence of a body (target or center) in a segment descriptorwith idcode -140 was changed to the value -70. This changewas performed on the segments in the following list.Segments: 1 2 3 4 5Appendix 2: Spacecraft Trajectory Segment Boundary Discontinuity Summary-------------------------------------------------------- This SPK file contains a number of spacecraft trajectory SPK segments that came from original individual SPK files. Although, each segment provides continuous trajectory within the interval that it covers, in general a position and velocity discontinuity exists at the boundary of the segment and the segments whose coverage immediately precede and follow it. The times and magnitudes of these discontinuities are provided in the table included in this Appendix. The top portion of the table contains the name of this SPK file. All descriptive lines in the top portion of the file start with the ``#'' character to allow direct plotting of the data in the freeware ``gnuplot'' application. The table consists of 4 columns. The first column contains the UTC time of that segment boundary. The last three columns (2..4) contain view coordinate frame components -- ``down track'' (this direction is parallel to the velocity vector), ``normal to plane'' (this direction is computed as cross product of position vector by velocity vector) and ``in plane'' (this direction is computed as a cross product of ``down track'' by ``normal to plane'') -- of the difference between the state vectors computed at that UTC time defining segment boundary at which a discontinuity exists. The pairs of segments and discontinuity times are determined using an algorithm that emulates the standard SPK loading priority -- ``last loaded segment takes precedence''. Therefore, the discontinuities summarized in the file are those which a user reading file would actually see. The difference components in the view coordinate frame were computed for each discontinuity using the following algorithm: -- A single state was computed from each pair of segment the J2000 frame at the time of discontinuity. -- For this pair of states, a position difference vector was computed by subtracting the state computed from the segment with higher priority from the state computed from segment with lower priority. Then, a frame transformation matrix rotating these difference vectors from J2000 to the view coordinate frame defined by the state obtained from the higher priority segment was computed, and the position difference vector was rotated to the view frame coordinates using this matrix. 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