API VERSION: 1.2 API SOURCE: NASA/JPL Horizons API ******************************************************************************* Revised: Oct 11, 2012 Deep Impact Flyby/EPOXI Spacecraft (DI) -140 http://deepimpact.jpl.nasa.gov/ http://www.nasa.gov/epoxi UPDATE: Contact was lost Aug 11-14, 2013. The mission was declared lost by NASA on Sep 19, 2013 after it was determined there were no plausible scenarios in which control of the spacecraft could be recovered. A software problem with date encodings extended beyond a supported range (due to the multiple mission extensions) resulted in a reboot loop when a fault was encountered. This would have eventually resulted in loss of power and subsequent freezing after a few days. The spacecraft was on target for a flyby of 2002 GT Jan 4, 2020 at the time and this will still occur ballistically, though without record. NOTE #1: The final post-Hartley 2 encounter reconstructed solution is used here. #2: The spacecraft trajectory (w/data to 2012-Jan-24) includes targeting maneuver #1 (to encounter 2002 GT in 2019) #3: Updated 2012-Sep-24 to include final planned 1.8 m/s maneuver on 2012-Oct-4 to target flyby of 2002 GT on Jan 4, 2020. After encountering 9P/Tempel 1 in 2005, the Deep Impact flyby spacecraft was retasked as the EPOXI mission to comet 103P/Hartley 2 (2007-2010). The two missions individual data-sheets are combined here. DEEP IMPACT (mission to 9P/Tempel 1): ------------------------------------- Initial post-encounter navigation trajectory solution "od189", produced 2005-Jul-07 16:55, is used here for the encounter. Launched : 2005-Jan-12 18:47:08 UTC (Delta II 7925) Encounter 9P/Tempel 1: 2005-Jul-04 05:44 UTC "End-of-mission" : 2005-Aug (end of data return) * Two component spacecraft: fly-by and impactor * 370 kg (~820 lb) impactor released from fly-by S/C approximately 24 hours before impact. Approach solar phase angle was 63 degrees. * Flyby spacecraft observed impact, crater development, ejecta and final crater with visible and IR multi-spectral instruments. Deep Impact flyby trajectory provided by OpNav (JPL) Sep 28, 2005. SPACECRAFT RETASKED: -------------------- Two proposals for the 2006 Discovery Program Announcement of Opportunity were merged so as to use the Deep Impact instruments for the study of a comet in our solar system and to investigate planets around other stars. EPOCh, the extrasolar planet investigation, observes three stars with known transiting giant planets to characterize those planets and to search for other planets in those systems. DIXI, the comet investigation, will observe 103P/Hartley 2 during a high-speed flyby to better understand the similarities and differences between cometary bodies and the implications on the formation and evolution of our solar system. Combined, the two proposals became ... EPOXI ----- TCM-9 : 2007-Nov-01 Earth flyby : 2007-Dec-31 EPOCh Science : 2008 Jan-May Earth flyby : 2008-Dec-30 Earth flyby : 2009-Dec-29 Earth flyby : 2010-Jun-27 Hartley 2 flyby : 2010-Nov-04 13:59:31 UTC B*R = 690.261 km B*T = -72.570 km Phase angle: 79.660 deg The formal uncertainty of the B-plane coordinates above is an ellipse with 1-sigma dimension of 117x98 m, with an orientation of the major axis of 95.7 deg clockwise from the T-axis. The formal uncertainty on the encounter time is 0.078 sec. EPOXI trajectories provided by navigation team (JPL) Oct 12, 2012. All final trajectory data has been merged in Horizons to provide time-continuous trajectory data from launch onward: USAGE NOTES: To access the 9P/Tempel 1 encounter trajectory estimated by the navigation team, available over 2005-2015, request pre-computed major body (MB) "1000093". To use it as a coordinate center, specify "@1000093" To access the 103P/Hartley 2 encounter trajectory estimated by the navigation team, available over 2010-2012, request pre-computed major body (MB) "1000041". To use it as a coordinate center, specify "@1000041" These precomputed trajectories are based on spacecraft tracking data and should be used when exact reconstruction or data-reduction is needed. By contrast, the standard solutions in the Horizons small-body (SB) database (accessed by including a semi-colon after the number or selecting the SB version and numerically integrating) include only ground-based optical data so are slightly different, but extend over longer time-spans and can include statistical uncertainties. Trajectory Name Start (TDB) Stop (TDB) ----------------------------- -------------------- -------------------- dif_preenc174_nav_v1 2005 JAN 12 19:23:32 2005 JUL 03 06:16:05 di_finalenc_nav_v3_to06048 2005 JUL 03 06:16:04 2005 JUL 05 05:45:34 (9P/Tempel 1 soln.: K051/17) di_flyby-od189 2005 JUL 05 05:45:34 2005 JUL 07 00:00:00 DI_050707_090115_050805 2005 JUL 07 00:00:00 2006 FEB 10 00:00:01 (undelivered) dif_epoch_nav_v1 2006 FEB 10 00:00:00 2009 FEB 20 00:00:00 spk_drm225-full.bsp 2009 FEB 20 00:00:00 2009 DEC 08 00:00:00 spk_drm226_WithBurn-full 2009 DEC 08 00:00:00 2010 MAR 29 00:00:00 140_drm228_WithBurn.bsp_V0.1 2010 MAR 29 00:00:00 2010 MAY 29 00:00:01 140_od229.bsp_V0.1 2010 MAY 29 00:00:00 2010 JUL 10 00:00:00 140_drm230_WithBurn-full 2010 JUL 10 00:00:00 2010 SEP 29 19:01:07 spk_drm237_WithBurn-full 2010 SEP 29 19:01:07 2011 AUG 02 00:00:00 di3_epoxi_extended_od120124 2011 AUG 02 00:00:00 2020 JAN 30 00:00:00 140_od240_WithBurn.bsp 2012 AUG 14 00:00:01 2020 JAN 10 00:00:00 *******************************************************************************