============ KPT ================= TIME: Tue Apr 17 12:01:00 2012 USER: Todd Ansty ================================== Insert Spice File: /cas/ancillary/ops/NAIF/sp/110818AP_SE_11175_17265.bsp Insert Spice File: /cas/ancillary/ops/NAIF/sp/110317AP_RE_90165_18018.bsp Insert Spice File: /cas/ancillary/ops/NAIF/sp/110120BP_IRRE_00256_25017.bsp Insert Spice File: /cas/ancillary/ops/NAIF/sp/110818AP_PE_11175_17265.bsp Insert Spice File: /cas/ancillary/ops/NAIF/sp/110818AP_SK_11175_17265.bsp Insert Leap Seconds File: /cas/ancillary/ops/NAIF/lsk/naif0010.tls Insert Physical Constants File: /cas/ancillary/ops/NAIF/pck/cpck25Aug2011.tpc Insert Physical Constants File: /cas/ancillary/ops/NAIF/pck/cpck_rock_21Jan2011_merged.tpc Insert SCLK SCET File: /cas/ancillary/ops/NAIF/sclk/cas00152.tsc SPICE Successfully Opened Successfully Read BVH File: pdt_Run_4/input.bvh Successfully Read IVT File: pdt_Run_4/input.ivt Successfully Read TLF File: /export/home/eros/D14.2d_PDT-SWDepot/Input/KPT/kpt_default.tlf Successfully Read KPT Spice Identification File: /cas/ancillary/ops/SCO/ssid/09_131_param.ssid Successfully Read Input PEF File: pdt_Run_4/temp.pef NOTE: This File Supercedes Any Events held within the Input Configuration File. Successfully Read KPT CMT File: /cas/ancillary/ops/SCO/cmt_limits/POST_PROBE_V11.cmt Insert Spice File: /cas/ancillary/ops/NAIF/sp/110818AP_SE_11175_17265.bsp Insert Spice File: /cas/ancillary/ops/NAIF/sp/110317AP_RE_90165_18018.bsp Insert Spice File: /cas/ancillary/ops/NAIF/sp/110120BP_IRRE_00256_25017.bsp Insert Spice File: /cas/ancillary/ops/NAIF/sp/110818AP_PE_11175_17265.bsp Insert Spice File: /cas/ancillary/ops/NAIF/sp/110818AP_SK_11175_17265.bsp Insert Leap Seconds File: /cas/ancillary/ops/NAIF/lsk/naif0010.tls Insert Physical Constants File: /cas/ancillary/ops/NAIF/pck/cpck25Aug2011.tpc Insert Physical Constants File: /cas/ancillary/ops/NAIF/pck/cpck_rock_21Jan2011_merged.tpc Insert SCLK SCET File: /cas/ancillary/ops/NAIF/sclk/cas00152.tsc SPICE Successfully Opened Successfully Read BVH File: pdt_Run_4/input.bvh Successfully Read IVT File: pdt_Run_4/input.ivt Successfully Read TLF File: /export/home/eros/D14.2d_PDT-SWDepot/Input/KPT/kpt_default.tlf Successfully Read KPT Spice Identification File: /cas/ancillary/ops/SCO/ssid/09_131_param.ssid Successfully Read Input PEF File: pdt_Run_4/temp.pef NOTE: This File Supercedes Any Events held within the Input Configuration File. Successfully Read KPT CMT File: /cas/ancillary/ops/SCO/cmt_limits/POST_PROBE_V11.cmt ------------------------------ CSAS-KPT Version: V14.1 ------------------------------ SID Suspend Values Theta_1: 0.20 degrees Theta_2: 0.50 degrees Theta_3: 1.50 degrees T_1: 60.00 seconds T_2: 240.00 seconds T_3: 1800.00 seconds T_4: 2400.00 seconds NOTE: Primary Inertial Vector TITAN_LAT_VIEW_183 WILL be propagated by a Chebyshev Polynomial from the IVT. (INITIAL CONDITIONS) NOTE: Secondary Inertial Vector TITAN_FOV_LIMB_183 WILL be propagated by a Chebyshev Polynomial from the IVT. (INITIAL CONDITIONS) ************************************************************ NOTE: MANEUVER COMMANDS Cause Turning of the Spacecraft 1.125 -> 2.000 seconds following the Command Time - the times shown in this Run Log are times that the Spacecraft Actually Starts Turning. ************************************************************ ************************************************************ NOTE: CONSTRAINT MONITOR IS SELECTED FOR THIS RUN Initial CMT Dynamic Constraints: RCS Max Rates(rad/s): 1.43000000e-02 1.43000000e-02 1.43000000e-02 RCS Max Accel(rad/s/s): 1.52700000e-04 1.24200000e-04 3.24700000e-04 RWA Max Rates(rad/s): 2.46800000e-03 2.96200000e-03 4.88600000e-03 RWA Max Accel(rad/s/s): 1.35300000e-05 1.62300000e-05 2.67800000e-05 ************************************************************ ************************************************************ * * * NOTE: ALL ERRORS, REJECTED COMMANDS, WARNINGS, * * CMT VIOLATIONS, etc, MUST BE FIXED PRIOR * * TO FINAL SEQUENCE GENERATION and UPLINK * ************************************************************ Adding/Replacing Vector TITAN_LAT_VIEW_183 to the IVT at UTC Time: 2012-270T13:16:09.000 Adding/Replacing Vector TITAN_FOV_LIMB_183 to the IVT at UTC Time: 2012-270T13:16:24.000 Adding/Replacing Vector TITAN_LAT_VIEW_184 to the IVT at UTC Time: 2012-270T13:41:19.000 Adding/Replacing Vector TITAN_FOV_LIMB_184 to the IVT at UTC Time: 2012-270T13:41:24.000 PROCESSING Starting on PROFILE Command at 2084.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2012-270T13:46:33.000 ) This is Command #1 from the Event List TARGET / Command #2: Primary Inertial Vector: TITAN_LAT_VIEW_184 determined by an Evaluation of Chebyshev Polynomials, which originate from the IVT TARGET / Command #2: Secondary Inertial Vector: TITAN_FOV_LIMB_184 determined by an Evaluation of Chebyshev Polynomials, which originate from the IVT PROCESSING Starting on TARGET Command at 2085.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2012-270T13:46:34.000 ) This is Command #2 from the Event List PRIMARY BODY: CIRS_FP1; PRIMARY INERTIAL: TITAN_LAT_VIEW_184; SECONDARY BODY: NEG_Z; SECONDARY INERTIAL: TITAN_FOV_LIMB_184; Light Time Correction: NO_COR PROCESSING Starting on OFFSET Command at 2092.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2012-270T13:46:41.000 ) This is Command #3 from the Event List QUANTIZED ANGLES: 0.000 0.000 0.000 mrad Profiled Maneuver time (seconds): 34.6780 PROCESSING Starting on 89EXE_CMD_SEQ Command at 2090.004 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2012-270T13:46:39.000 ) This is Command #4 from the Event List Simulated Maneuver End Time (UTC): 2012-270T13:47:15.750 Turn Magnitude for 7OFFSET (milliradians): 29.7042 PROCESSING Starting on PROFILE Command at 2162.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2012-270T13:47:51.000 ) This is Command #5 from the Event List PROCESSING Starting on DELTA_BASE Command at 2166.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2012-270T13:47:55.000 ) This is Command #6 from the Event List QUANTIZED ANGLES: 27.995 0.000 0.000 mrad Profiled Maneuver time (seconds): 569.8691 Adding/Replacing Vector TITAN_LAT_VIEW_185 to the IVT at UTC Time: 2012-270T13:52:00.000 Adding/Replacing Vector TITAN_FOV_LIMB_185 to the IVT at UTC Time: 2012-270T13:52:15.000 PROCESSING Starting on PROFILE Command at 2735.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2012-270T13:57:24.000 ) This is Command #7 from the Event List Simulated Maneuver End Time (UTC): 2012-270T13:57:24.870 Turn Magnitude for 7DELTA_BASE (milliradians): 35.3221 TARGET / Command #8: Primary Inertial Vector: TITAN_LAT_VIEW_185 determined by an Evaluation of Chebyshev Polynomials, which originate from the IVT TARGET / Command #8: Secondary Inertial Vector: TITAN_FOV_LIMB_185 determined by an Evaluation of Chebyshev Polynomials, which originate from the IVT PROCESSING Starting on TARGET Command at 2736.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2012-270T13:57:25.000 ) This is Command #8 from the Event List PRIMARY BODY: CIRS_FP1; PRIMARY INERTIAL: TITAN_LAT_VIEW_185; SECONDARY BODY: NEG_Z; SECONDARY INERTIAL: TITAN_FOV_LIMB_185; Light Time Correction: NO_COR PROCESSING Starting on OFFSET Command at 2743.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2012-270T13:57:32.000 ) This is Command #9 from the Event List QUANTIZED ANGLES: 0.000 0.000 0.000 mrad Profiled Maneuver time (seconds): 81.0261 Simulated Maneuver End Time (UTC): 2012-270T13:58:53.120 Turn Magnitude for 7OFFSET (milliradians): 134.9491 PROCESSING Starting on PROFILE Command at 2863.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2012-270T13:59:32.000 ) This is Command #10 from the Event List PROCESSING Starting on DELTA_BASE Command at 2867.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2012-270T13:59:36.000 ) This is Command #11 from the Event List QUANTIZED ANGLES: 27.995 0.000 0.000 mrad Profiled Maneuver time (seconds): 569.8723 Adding/Replacing Vector TITAN_SC_RAM to the IVT at UTC Time: 2012-270T14:04:38.000 Adding/Replacing Vector TITAN to the IVT at UTC Time: 2012-270T14:04:40.000 Adding/Replacing Vector TITAN_FRAME_1 to the IVT at UTC Time: 2012-270T14:04:42.000 Adding/Replacing Vector TITAN_LAT_LON_176 to the IVT at UTC Time: 2012-270T14:04:44.000 Simulated Maneuver End Time (UTC): 2012-270T14:09:05.870 Turn Magnitude for 7DELTA_BASE (milliradians): 66.3538 PROCESSING Starting on PROFILE Command at 3464.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2012-270T14:09:33.000 ) This is Command #12 from the Event List NOTE: Primary Inertial Vector TITAN_LAT_LON_176 WILL be propagated by a ROTATE_VEC from the IVT. TARGET / Command #13: Secondary Inertial Vector: TITAN_SC_RAM determined by an Evaluation of Chebyshev Polynomials, which originate from the IVT PROCESSING Starting on TARGET Command at 3465.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2012-270T14:09:34.000 ) This is Command #13 from the Event List PRIMARY BODY: NEG_Z; PRIMARY INERTIAL: TITAN_LAT_LON_176; SECONDARY BODY: NEG_X; SECONDARY INERTIAL: TITAN_SC_RAM; Light Time Correction: NO_COR PROCESSING Starting on OFFSET Command at 3472.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2012-270T14:09:41.000 ) This is Command #14 from the Event List QUANTIZED ANGLES: 0.000 0.000 0.000 mrad Profiled Maneuver time (seconds): 434.9843 Adding/Replacing Vector CASSINI to the IVT at UTC Time: 2012-270T14:12:49.000 PROCESSING Starting on 89EXE_CMD_SEQ Command at 3890.004 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2012-270T14:16:39.000 ) This is Command #15 from the Event List Simulated Maneuver End Time (UTC): 2012-270T14:16:56.000 Turn Magnitude for 7OFFSET (milliradians): 1774.9629 EVENT SEQUENCE COMPLETED SUCCESSFULLY. (Save Checklist and Violations Summary Reports for more details) Created KPT Plot File: pdt_Run_4/kpt_eo.plt -----------------------------------