============ KPT ================= TIME: Fri Aug 14 12:06:22 2009 USER: Todd Ansty ================================== Insert Spice File: /cas/ancillary/ops/NAIF/sp/080806AP_SE_08138_10182.bsp Insert Spice File: /cas/ancillary/ops/NAIF/sp/090507AP_RE_90165_18018.bsp Insert Spice File: /cas/ancillary/ops/NAIF/sp/090202BP_IRRE_00256_50017.bsp Insert Spice File: /cas/ancillary/ops/NAIF/sp/080806AP_PE_08138_10182.bsp Insert Spice File: /cas/ancillary/ops/NAIF/sp/080806AP_SK_08138_10182.bsp Insert Leap Seconds File: /cas/ancillary/ops/NAIF/lsk/naif0009.tls Insert Physical Constants File: /cas/ancillary/ops/NAIF/pck/cpck15May2008.tpc Insert Physical Constants File: /cas/ancillary/ops/NAIF/pck/cpck_rock_11May2009_merged.tpc Insert SCLK SCET File: /cas/ancillary/ops/NAIF/sclk/cas00133.tsc SPICE Successfully Opened Successfully Read BVH File: pdt_Run_3/input.bvh Successfully Read IVT File: pdt_Run_3/input.ivt Successfully Read TLF File: /export/home/eros/PDT13.3d/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_3/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/080806AP_SE_08138_10182.bsp Insert Spice File: /cas/ancillary/ops/NAIF/sp/090507AP_RE_90165_18018.bsp Insert Spice File: /cas/ancillary/ops/NAIF/sp/090202BP_IRRE_00256_50017.bsp Insert Spice File: /cas/ancillary/ops/NAIF/sp/080806AP_PE_08138_10182.bsp Insert Spice File: /cas/ancillary/ops/NAIF/sp/080806AP_SK_08138_10182.bsp Insert Leap Seconds File: /cas/ancillary/ops/NAIF/lsk/naif0009.tls Insert Physical Constants File: /cas/ancillary/ops/NAIF/pck/cpck15May2008.tpc Insert Physical Constants File: /cas/ancillary/ops/NAIF/pck/cpck_rock_11May2009_merged.tpc Insert SCLK SCET File: /cas/ancillary/ops/NAIF/sclk/cas00133.tsc SPICE Successfully Opened Successfully Read BVH File: pdt_Run_3/input.bvh Successfully Read IVT File: pdt_Run_3/input.ivt Successfully Read TLF File: /export/home/eros/PDT13.3d/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_3/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: V13.1 ------------------------------ 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_135 WILL be propagated by a Chebyshev Polynomial from the IVT. (INITIAL CONDITIONS) NOTE: Secondary Inertial Vector TITAN_FOV_LIMB_135 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_135 to the IVT at UTC Time: 2010-028T20:36:19.000 Adding/Replacing Vector TITAN_FOV_LIMB_135 to the IVT at UTC Time: 2010-028T20:36:34.000 Adding/Replacing Vector TITAN_LAT_VIEW_136 to the IVT at UTC Time: 2010-028T21:01:29.000 Adding/Replacing Vector TITAN_FOV_LIMB_136 to the IVT at UTC Time: 2010-028T21:01:34.000 PROCESSING Starting on PROFILE Command at 2084.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2010-028T21:06:43.000 ) This is Command #1 from the Event List TARGET / Command #2: Primary Inertial Vector: TITAN_LAT_VIEW_136 determined by an Evaluation of Chebyshev Polynomials, which originate from the IVT TARGET / Command #2: Secondary Inertial Vector: TITAN_FOV_LIMB_136 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): 2010-028T21:06:44.000 ) This is Command #2 from the Event List PRIMARY BODY: CIRS_FP1; PRIMARY INERTIAL: TITAN_LAT_VIEW_136; SECONDARY BODY: POS_Z; SECONDARY INERTIAL: TITAN_FOV_LIMB_136; Light Time Correction: NO_COR PROCESSING Starting on OFFSET Command at 2092.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2010-028T21:06:51.000 ) This is Command #3 from the Event List QUANTIZED ANGLES: 0.000 0.000 0.000 mrad Profiled Maneuver time (seconds): 1.6598 PROCESSING Starting on 89EXE_CMD_SEQ Command at 2090.004 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2010-028T21:06:49.000 ) This is Command #4 from the Event List Simulated Maneuver End Time (UTC): 2010-028T21:06:52.870 Turn Magnitude for 7OFFSET (milliradians): 0.1547 PROCESSING Starting on PROFILE Command at 2182.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2010-028T21:08:21.000 ) This is Command #5 from the Event List PROCESSING Starting on DELTA_BASE Command at 2186.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2010-028T21:08:25.000 ) This is Command #6 from the Event List QUANTIZED ANGLES: -50.046 0.000 0.000 mrad Profiled Maneuver time (seconds): 1121.3437 Adding/Replacing Vector TITAN_FOV_LIMB_137 to the IVT at UTC Time: 2010-028T21:22:05.000 Adding/Replacing Vector SKY_RA_DEC_130 to the IVT at UTC Time: 2010-028T21:22:25.000 Simulated Maneuver End Time (UTC): 2010-028T21:27:06.500 Turn Magnitude for 7DELTA_BASE (milliradians): 169.3689 PROCESSING Starting on PROFILE Command at 3315.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2010-028T21:27:14.000 ) This is Command #7 from the Event List TARGET / Command #8: Secondary Inertial Vector: TITAN_FOV_LIMB_137 determined by an Evaluation of Chebyshev Polynomials, which originate from the IVT PROCESSING Starting on TARGET Command at 3316.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2010-028T21:27:15.000 ) This is Command #8 from the Event List PRIMARY BODY: VIMS_IR; PRIMARY INERTIAL: SKY_RA_DEC_130; SECONDARY BODY: POS_Z; SECONDARY INERTIAL: TITAN_FOV_LIMB_137; Light Time Correction: NO_COR PROCESSING Starting on OFFSET Command at 3323.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2010-028T21:27:22.000 ) This is Command #9 from the Event List QUANTIZED ANGLES: 0.000 0.000 0.000 mrad Profiled Maneuver time (seconds): 244.4001 Simulated Maneuver End Time (UTC): 2010-028T21:31:26.620 Turn Magnitude for 7OFFSET (milliradians): 174.9419 Adding/Replacing Vector TITAN_LAT_VIEW_138 to the IVT at UTC Time: 2010-028T21:31:49.000 Adding/Replacing Vector TITAN_FOV_LIMB_138 to the IVT at UTC Time: 2010-028T21:31:54.000 Adding/Replacing Vector CASSINI to the IVT at UTC Time: 2010-028T21:35:29.000 PROCESSING Starting on PROFILE Command at 3904.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2010-028T21:37:03.000 ) This is Command #10 from the Event List TARGET / Command #11: Primary Inertial Vector: TITAN_LAT_VIEW_138 determined by an Evaluation of Chebyshev Polynomials, which originate from the IVT TARGET / Command #11: Secondary Inertial Vector: TITAN_FOV_LIMB_138 determined by an Evaluation of Chebyshev Polynomials, which originate from the IVT PROCESSING Starting on TARGET Command at 3905.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2010-028T21:37:04.000 ) This is Command #11 from the Event List PRIMARY BODY: CIRS_FP1; PRIMARY INERTIAL: TITAN_LAT_VIEW_138; SECONDARY BODY: POS_Z; SECONDARY INERTIAL: TITAN_FOV_LIMB_138; Light Time Correction: NO_COR PROCESSING Starting on OFFSET Command at 3912.000 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2010-028T21:37:11.000 ) This is Command #12 from the Event List QUANTIZED ANGLES: 0.000 0.000 0.000 mrad Profiled Maneuver time (seconds): 142.8979 PROCESSING Starting on 89EXE_CMD_SEQ Command at 4040.004 Seconds Into the Simulated Maneuver Sequence. ( Spacecraft Event Time (UTC): 2010-028T21:39:19.000 ) This is Command #13 from the Event List Simulated Maneuver End Time (UTC): 2010-028T21:39:34.120 Turn Magnitude for 7OFFSET (milliradians): 81.9457 EVENT SEQUENCE COMPLETED SUCCESSFULLY. (Save Checklist and Violations Summary Reports for more details) Created KPT Plot File: pdt_Run_3/kpt_eo.plt -----------------------------------