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FLIGHT DYNAMICS SUPPORT SYSTEM (FDSS) OPERATIONS READINESS REVIEW OCTOBER 11, 2000

EARTH OBSERVING-1 (EO-1). FLIGHT DYNAMICS SUPPORT SYSTEM (FDSS) OPERATIONS READINESS REVIEW OCTOBER 11, 2000. Prepared by: Bob DeFazio / GSFC / 572 Rich Luquette / GSFC / 572 Chad Mendelsohn / GSFC / 572 Seth Shulman / EO1 FOT / CSC Jennifer Sager / EO1 FOT/ HTSI Skip Owens / AI-Solutions.

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FLIGHT DYNAMICS SUPPORT SYSTEM (FDSS) OPERATIONS READINESS REVIEW OCTOBER 11, 2000

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  1. EARTH OBSERVING-1 (EO-1) FLIGHT DYNAMICS SUPPORT SYSTEM (FDSS)OPERATIONS READINESS REVIEWOCTOBER 11, 2000 Prepared by: Bob DeFazio / GSFC / 572 Rich Luquette / GSFC / 572 Chad Mendelsohn / GSFC / 572 Seth Shulman / EO1 FOT / CSC Jennifer Sager / EO1 FOT/ HTSI Skip Owens / AI-Solutions

  2. FLIGHT DYNAMICS TEAM FDAB (CODE 572) GN&CC MAB (CODE 583) ISC FOT RESPONSIBLE FOR DEFINING FUNCTIONAL REQUIREMENTS, TESTING, TRAINING AND OPERATIONS RESPONSIBLE FOR DEFINING FUNCTIONAL REQUIREMENTS, DEVELOPING, AND TESTING TOGETHER THE TEAM: COORDINATES WITH OUTSIDE INTERFACES, INTEGRATES SCHEDULE, BUILDS OPS CONCEPT FDF (CSOC) PROVIDES L & EO FLIGHT DYNAMICS INSTITUTIONAL SERVICES

  3. FDSS TEAM ROSTER Pre-Launch & L&EO

  4. FDSS TEAM ROSTER Normal Operations

  5. FDSS DOCUMENTATION LOCATIONS • MOST DOCUMENTATION IS ON THE FDSS SHARED DRIVE BETWEEN THE FDSS WORKSTATIONS & PCs: • FDSS Mission Procedures Handbook • ICD with Landsat-7 MOC • Software User’s Guides • Mission Timelines • SOME FDSS COTS DOCUMENTATION WILL BE AVAILABLE AS HARDCOPY IN THE MOC

  6. AGENDA • ORBIT • ATTITUDE • TEAM OPERATIONS READINESS • SYSTEM DESCRIPTION AND READINESS • ISSUES AND CONCERNS

  7. ORBIT AGENDA • MISSION ORBIT CHARACTERISTICS • LAUNCH AND INJECTION • BASELINE ASCENT PROFILE • ROUTINE MANEUVERS • ORBIT DETERMINATION

  8. MISSION ORBIT CHARACTERISTICS • FROZEN, SUN-SYNCHRONOUS • REPEAT CYCLE: 233 REVS/16 DAYS • 705 KM MEAN ALTITUDE OVER EQUATOR • 98.2 DEG INCLINATION • 10:03:38 AM (+/- 6 SEC) DESCENDING NODE MLT • +/- 5 KM GROUND TRACK CONTROL AT EQUATOR • +/- 10 TO 20 METERS RADIAL CONSTRAINT • MISSION DURATION: 1 YEAR

  9. FORMAT FLYING WITH LANDSAT-7 EO-1 Orbit Plane Landsat-7 Orbit Plane EO-1 Descending Node 1 Min. Behind Landsat-7 Descending Node 10:02 AM WRS Ground Track MLT Path 10:03AM MLT Equator Landsat-7 at Descending Node Mean Sun 12:00 MLT 1 min Earth Rotation

  10. LAUNCH • LAUNCH DATE: November 16, 2000 • LAUNCH VEHICLE: Delta II , 7920 • LAUNCH SITE: VANDENBERG AFB, CA • LAUNCH CO-MANIFEST: SAC-C • LAUNCH WINDOW: • 20 to 27 SECOND WINDOW EACH DAY IN NOV. AND DEC. 2000 • Window open: 18:24:16 UTC • Window close: Between 18:24:36 UTC • & • 18:24:43 UTC

  11. LAUNCH STATUS • AS OF 10/10/00, EO1/SAC-C ARE GO FOR LAUNCH ON 11/16/00 • EO-1 IS SEPARATED FIRST AT LAUNCH + 1 HOUR

  12. INJECTION • INJECTION TARGETS • MLT: 10:03:38 AM (+30 SECONDS, -18 SECONDS) • INCLINATION: 98.2 DEG. • ALTITUDE: • 705 KM. CIRCULAR, AT 1ST ASCENDING NODE • TARGET SPECIFICATION • PROVIDED TO BOEING 8/14/00 • VALID THROUGH 12/31/00 • WILL UPDATE BY 10/15/00 FOR LAUNCH LATER THAN 12/31/00

  13. EO-1 MLT 1 YEAR PREDICTION AT END OF ASCENT SEQUENCE

  14. EO-1 FORMATION FLYINGWITH LANDSAT-7 • AGREEMENT TO FLY SAME GROUND TRACK KEEPING EO-1 1 MINUTE (+ / - 6 SECONDS) BEHIND AND WITHIN +/- 3 KM CROSS TRACK OF LANDSAT-7 • SEPARATION WITHIN ORBIT TO FLY SAME GROUND TRACK IS DICTATED BY ORBIT PLANE MLT SEPARATION • MLT SEPARATION IS SET BY CHOOSING NEARLY INSTANTANEOUS LAUNCH WINDOW FOR EO-1. MLT DISPERSIONS WILL BE CORRECTED • ASCENT MANEUVERS WILL START 3 DAYS AFTER LAUNCH - ASCENT PHASE DURATION AND PROPELLANT USAGE WILL DEPEND ON THE INITIAL PHASING WITH LANDSAT-7 AT EO-1 INJECTION (MAY VARY BY A FACTOR OF 2) • FORMATION FLYING CONTROL WILL BE PERFORMED BY EO-1

  15. AM CONSTELLATION LANDSAT-7, EO-1, TERRA AND SAC-C ARE THE MEMBERS OF THE “AM CONSTELLATION” WHICH WILL PARTICIPATE IN IMAGING ACTIVITIES AND STUDIES The EO-1/SAC-C LAUNCH WILL DELIVER THE FINAL MEMBERS OF THE CONSTELLATION INTO ORBIT

  16. BASELINE ASCENT PLAN • 8 MANEUVERS SPACED EVERY 48 HOURS AFTER L+3 DAYS • START DATE NOMINALLY 3 DAYS AFTER INJECTION • GROUND STATION OR TDRS COVERAGE IS DESIRABLE FOR EACH ASCENT MANEUVERS • AFTER LAUNCH, FDSS WILL PREPARE AN UPDATED ASCENT PLAN AND BRIEF PROJECT MANAGEMENT ON AVAILABLE OPTIONS • MORE DETAILS REGARDING CONTINGENCY PLANS IN PROJECT DOCUMENT

  17. BASELINE ASCENT PLAN Assumes Propellant Load of 49.16 lbm (22.9 kg) Ascent Nominal Propellant Budget: 6.11 lbm (2.77 kg) Ascent Profile Duration: ~17 Days

  18. ROUTINE GTC MAINTENANCE MANEUVER PLAN • PLAN TO DO GROUND TRACK MAINTENANCE MANEUVERS TO MEET CO-FLY REQUIREMENTS WITH LANDSAT-7: • AS FREQUENTLY AS EVERY WEEK FOR HIGH SOLAR FLUX • AS INFREQUENTLY AS EVERY 3 WEEKS FOR LOW SOLAR FLUX • INCLINATION MAINTENANCE • FUEL BUDGET INCLUDES REMOVING ELV INCLINATION DISPERSIONS PLUS ONE MANEUVER ABOUT MID-OCTOBER 2001 FOLLOWING PLANNED LANDSAT-7 INCLINATION BURN • THE INITIAL INCLINATION WILL BE CHOSEN TO KEEP EO-1’s MLT AT THE DESCENDING NODE WITHIN 1 MINUTE OF LANDSAT-7’S MLT (+/- 6 SECONDS)

  19. ORBIT DETERMINATION • LAUNCH AND EARLY ORBIT • FDF PROVIDES EO-1 MOC - LAUNCH VEHICLE INSERTION VECTOR AND CODE 500 EPHEM FOR USE AS A PRIORI IN INITIAL OD SOLUTION AT EO-1 MOC - 46 CHARACTER C-BAND RADAR TRACKING DATA FILES - FDF’S INITIAL OD SOLUTION VECTOR AND EPHEM DURING FIRST FEW HOURS AFTER LAUNCH USING TDRS DOPPLER, GN S-BAND AND C-BAND RADAR TRACKING DATA • TDRS DOPPLER DATA WILL BE RECEIVED SOLELY AT FDF. WHILE EO-1 IS NON-COHERENT, DIFFERENCED 1-WAY DOPPLER FROM TWO TDRSs MAY BE RECEIVED. • EO-1 MOC WILL USE GN S-BAND AND C-BAND RADAR TRACKING DATA TO GET INITIAL OD SOLUTION

  20. ORBIT DETERMINATION • ON ORBIT • USING GPS ONBOARD NAVIGATION SYSTEM (PRIME); GN S-BAND DATA USED FOR GPS VALIDATION AND BACKUP OD • POSITION KNOWLEDGE REQUIREMENT IS BEST AVAILABLE, BUT EXPECTED TO BE 20-30 METERS, 3-SIGMA ON BOARD • GPS ORBIT SOLUTION COMES DOWN IN TELEMETRY IN SCIENCE AND HOUSEKEEPING PACKETS. • NO DEFINITIVE REQUIREMENT, BUT EPHEMERIS OVER DATA ARCS PROCESSED ON THE GROUND WILL BE ARCHIVED TO TAPE

  21. CSOC/FDF INTERFACE • FDF WILL PERFORM THE FOLLOWING FUNCTIONS: • LAUNCH VEHICLE SUPPORT • TRACKING DATA EVALUATION AND LOCAL OSCILLATOR FREQUENCY CALCULATIONS • DELIVERY OF ACQUISITION DATA TO C-BAND SITES • DELIVERY OF ACQUISITION DATA TO NCC FOR TDRS L&EO AND CONTINGENCY SUPPORT • SPACECRAFT ORBIT DETERMINATION (1ST 8 HOURS OF L&EO) • DELIVERY OF 46 CHARACTER C-BAND RADAR TRACKING DATA TO EO-1 MOC • DELIVERY OF LAUNCH VEHICLE INSERTION VECTOR AND EPHEM TO EO-1 MOC • DELIVERY OF INITIAL OD SOLUTION VECTOR AND EPHEM TO EO-1 MOC • LOF MAINTENANCE FOR LOCAL OSCILLATOR

  22. ATTITUDE AGENDA • ATTITUDE ORIENTATION AND SENSORS • ATTITUDE DETERMINATION SYSTEM • MOMENTUM MANAGEMENT • IRU & TAM SENSOR CALIBRATION • INSTRUMENT CALIBRATION MANEUVERS • AST FAILURE OPTIONS

  23. ATTITUDE ORIENTATION Expected ACS Performance < 60 arcsec per axis; Combined Knowledge & Control for Imaging

  24. SENSORS Litton SIRU (3 HRGs) Lockheed/Martin AST-201 Three-Axis Magnetometer (TAM) 4 Coarse Sun Sensors GPS ACTUATORS 3 Reaction Wheels 3 Magnetic Torquer Bars 4 Thrusters ATTITUDE CONTROL HARDWARE

  25. ATTITUDE DETERMINATION SYSTEM • PC based MATLAB/ADS with customized TP, RTADS interface to ASIST, and RTADS displays • TP is used processes GPS data into PCE tracking data format for use in PODS • Integrated with customized OBC Table Utilities to convert TAMCAL and IRUCAL results into ACS Flight Software Tables • MATLAB/ADS was tested using data generated using VSAT and ASIST

  26. MOMENTUM MANAGEMENT • Momentum Management and Attitude Planning (MMAP) is a MATLAB based utility that is integrated with the Mission Planning System (MOPSS) • Used to bias Reaction Wheels to avoid zero crossings during Imaging and also used to plan Pre-Image slews that include Yaw Steering and Instrument Offsets • MMAP was tested “End-to-End” using MOPSS and VSAT to verify proper Momentum and Attitude • Also runs in “Standalone” mode to plan Engineering Slews

  27. IRU SENSOR CALIBRATION • IRU calibration is performed during Spacecraft Checkout (and as needed thereafter) • IRU calibration slews are planned using MMAP and will consist of 3 pairs of “out and back” orbital referenced slews that occur on Mission Day 3 • IRU calibration sequence was tested “End-to-End” using VSAT for ACS simulation and error modeling, ADS for attitude determination, IRUCAL to solve for the G-Matrix (and biases), and the Flight S/W Lab to verify proper ACS Table phasing and magnitude

  28. TAM SENSOR CALIBRATION • TAM calibration is performed during the Spacecraft Checkout (and as needed thereafter) • TAM calibration will make use of the IRU calibration slews because of the high Torquer Bar activity • TAM calibration sequence was tested “End-to-End” using VSAT for ACS simulation and error modeling, ADS for attitude determination, TAMCAL to solve for the misalignment, scale factor, bias, and MTB coupling, and the Flight S/W Lab to verify proper ACS Table phasing and magnitude

  29. INSTRUMENT CALIBRATION MANEUVERS • Calibration Maneuver (CALMAN) is a MATLAB based utility that is used to plan all instrument calibration slews (Solar, Lunar, Deep Space) • CALMAN provides the capability to check the slews for AST and Instrument constraint violations • CALMAN was tested using VSAT to model slews and RTADS to verify proper attitude • Solar Calibrations involve a single slew to an inertial attitude to allow an individual instrument to view the Sun

  30. INSTRUMENT CALIBRATION MANEUVERS • Lunar Calibrations involve a series of slews to get the Moon to move through each instrument FOV at a specified rate:

  31. AST FAILURE OPTIONS • Short Term Option: Use RTADS to perform a TAM/IRU KF Solution and uplink a Delta-Quaternion near the end of a ground support. This solution is developed and tested using VSAT, ASIST, and RTADS. • Mid Term Option: Use ADS to perform a TAM/IRU Batch Solution and uplink a Delta-Quaternion on next available support. This solution would need minor modifications to the ADS. • Long Term Option: Modify ACS (TRMM Heritage) to use TAM (instead of AST) as input to the KF.

  32. FLIGHT DYNAMICS TEAMOPERATIONS READINESS • OPS CONCEPT • STAFFING • TRAINING • SIMULATIONS

  33. OPERATIONS CONCEPT • FDAB/FOT PERSONNEL OPERATE FDSS UNTIL EARLY MISSION CHECKOUT IS COMPLETE. ACTIVITIES SUPPORTED INCLUDE: • LAUNCH, INJECTION, AND ASCENT TO MISSION ORBIT • ATTITUDE SENSOR CALIBRATION MANEUVERS • FIRST TWO GROUND TRACK MAINTENANCE MANEUVERS (COMPLETED BY ~ L + 45 DAYS) • INITIAL INSTRUMENT CALIBRATION MANEUVERS • FDAB THEN HANDS OVER ALL RESPONSIBILITY FOR FUNCTIONS TO EO1 FOT FOR ROUTINE OPS.

  34. OPERATIONS CONCEPT • PRIOR TO HANDOVER: • FDAB WILL PROVIDE TRAINING TO FOT • FDAB WILL PROVIDE DOCUMENTATION OF PROCEDURES AND SYSTEM OPERATIONS • PARALLEL OPERATIONS WILL BE PERFORMED BY FOT AND FDSS TEAM • AFTER HANDOVER: • FOT PROVIDES ROUTINE OPERATIONS SUPPORT • FDAB ON CALL FOR CONTINGENCY, ANOMALY RESOLUTION NO HANDOVER UNTIL FDAB DETERMINES THAT FOT IS READY

  35. STAFFING PLAN - L&EO • TWO (2) TWELVE HOUR OPERATIONS SHIFTS (PLUS OVERLAP TIME FOR HANDOVER) • PRIME SHIFT, 9:00 AM TO 9:30 PM (CONTAINING ORBIT/ATTITUDE MANEUVERS) • -4 ENGINEERS COVERING THE FOLLOWING FUNCTIONS: • ATTITUDE SUPPORT, ORBIT DETERMINATION, ORBIT MANEUVERS AND PRODUCT GENERATION • OFF SHIFT, 9:00 PM TO 9:30 AM • - 2 ENGINEERS COVERING THE FOLLOWING FUNCTIONS: • ATTITUDE SUPPORT AND PRODUCT GENERATION • SOFTWARE SUPPORT PROVIDED ON CALL

  36. CALLUP PLAN • IF ADDITIONAL/ALTERNATIVE STAFFING IS NEEDED, THE OPS LEAD WILL: • CALL THE EMPLOYEE IDENTIFIED AS A SOLE SOURCE TO RESOLVE THE PROBLEM • CALL THE EMPLOYEE’S SUPERVISOR TO MAKE THEM AWARE OF THE PROBLEM AND THE STAFFING CHANGE

  37. MANAGEMENT NOTIFICATION • DURING NOMINAL OPERATIONS, FDAB MANAGEMENT WILL RECEIVE DAILY REPORTS OF ACTIVITES COMPLETED AND CURRENT STATUS. • IN THE EVENT OF A CONTINGENCY, FDAB MANAGEMENT WILL BE NOTIFIED AS SOON AS POSSIBLE BY THE FDE

  38. FDSS TEAM TRAINING Flight Dynamics Support System Team (FDSST) • TRAINING TRACKED BY AREAS OF SPECIALIZATION USING MATRIX • PROFICIENCY LEVELS DEFINED FOR EACH TEAM MEMBER, BASED ON SUPPORT ROLES Flight Operations Team (FOT) • CONTINUOUS TRAINING THROUGH HANDOVER • ALREADY PROVIDED SOME S/W TRAINING, MORE TO COME • OPS NOTEBOOK DESIGNED FOR EASY UPDATES

  39. FDSS TEAM TRAINING AREAS • ORBIT: Navigation and Maneuvers: • Pre-process Tracking Data, Orbit Determination, O. D. Quality Assurance, Tracking Data Archiving, EFF Orbit Maneuver Planning, Thruster Calibration, Est. of Propellant Remaining, EFF Table Generation • ATTITUDE : • Attitude Determination, IRU Calibration, TAM Calibration, Slew Planning, ADS Utilities • PRODUCTS: Generation and Delivery • DATABASE: Maintenance & Archiving

  40. FDSS TEAM TRAINING

  41. FDSS TEAM TRAINING STATUS • ALL TEAM MEMBERS HAVE ACHIEVED MINIMUM PROFICIENCY LEVELS SUFFICIENT TO SUPPORT LAUNCH • SUSTAINED TRAINING ACTIVITIES WILL ACHIEVE DESIRED GOALS PRIOR TO LAUNCH • IMPROVED TEAM PERFORMANCE • IMPROVED STAFF FLEXIBILITY

  42. COMPLETED: ATTITUDE CALIBRATION MANEUVER ASCENT MANEUVERS (IN & OUT OF PLANE) GROUND TRACK MAINTENANCE ATTITUDE TELEMETRY LAUNCH DAY & FDF INTERFACE NAVIGATION END-TO-END ACQ DATA TO WOTIS & NCC NON-NOMINAL MANEUVER LAUNCH VEHICLE OPM DELIVERY PRODUCT GENERATION ELECTRONIC INTERFACE TESTS AND BACKUPS WITH PIs, WOTIS, NCC, AND McMURDO INSTRUMENT CALIBRATION FUTURE: INCLINATION DELTA-V INTERNAL SIMULATIONS

  43. EXTERNAL SIMULATIONS • BETWEEN 10/99 AND 10/00, THE FDSS TEAM SUPPORTED THE EO-1 PROJECT DURING: • - MONTHLY LAUNCH & EARLY ORBIT SIMS • - MONTHLY SCIENCE DATA COLLECTION AND PROCESSING SIMS • - NETWORK SIMS WITH THE SN (4) AND THE WALLOPS GN (6)

  44. SYSTEM DESCRIPTIONAND READINESS • FACILITY CONFIGURATION • ARCHITECTURE OVERVIEW • SOFTWARE STATUS • TESTING STATUS • CERTIFICATION

  45. FDSS HARDWARE 2 Hewlett Packard workstations (1 prime; 1 backup) • software: Satellite Toolkit (STK), Ephemeris Utilities, Real Time Attitude Determination System (RTADS), MATLAB attitude tools, Precision Orbit Determination System (PODS), AutoProducts 4 Pentium Pro PCs (2 prime; 2 backup) • software: FreeFlyer, Microsoft Office, MATLAB attitude tools, NFS/MAESTRO; STK/PRO 4 Hewlett Packard workstations (2 prime; 2 backup) in FDF for initial EO-1 L & EO support ALL FDSS PLATFORMS CONNECTED TO SHARED DRIVES.

  46. FDSS INTERFACES MOPSS (P&S, CMS,DMS) Principal Investigators • • EPVs • Manv. Cmds. • Sci. Planning • & • Health & Safety • Products • FDSS Planning Products ASIST (Epoch 2000) • RT TLM Science Validation Facility • Mis-Align. Utility • RT TLM • Carry-Out Files Flight Operations Team • Pass Schedules FDF (bldg 28) • OPM (Post-Sep.) • C-Band Data • Ephemeris Files • Acquisition Data FDSS • UTC-UT1 • STK/PODS Files • JPL Files • FDF Files Internet • Acq Data NCC • • Acq Data • Tracking Data • Scheduling PSATs WOTIS

  47. FDSS MOC CONFIGURATION FOR L&EO

  48. L & EO PRODUCT GENERATION • ORBIT DETERMINATION (USING GPS) - DAILY; O.D. VERIFICATION (USING S-BAND) WEEKLY • 25 ORBIT & ATTITUDE PRODUCTS (IMAGE PLANNING & SCHEDULING, TABLE LOADS); • - FOLLOWING EVERY ASCENT MANEUVER PLAN - 8 DAY LENGTH • - FRIDAY: 35 DAY LENGTH • ORBIT MANEUVER COMMAND SHEETS - AS REQUIRED • RUN RTADS EVERY REALTIME PASS > 32 Kbps • INSTRUMENT CALIBRATION PLANS - AS REQUIRED

  49. NORMAL OPS PRODUCT GENERATION • ORBIT DETERMINATION (USING GPS) - M-W-F; O.D. VERIFICATION (USING S-BAND) WEEKLY • 25 ORBIT & ATTITUDE PRODUCTS (IMAGE PLANNING & SCHEDULING, TABLE LOADS); EVERY M-W-F • - MONDAY & WEDNESDAY: 8 DAY LENGTH • - FRIDAY: 35 DAY LENGTH • ORBIT MANEUVER COMMAND SHEETS - AS REQUIRED • RUN RTADS ON REQUEST • INSTRUMENT CALIBRATION PLANS - AS REQUIRED

  50. STK / PODS / executable: version 4.1.1, done - RFI sites may be added (not launch critical) AUTOCON-G / executable: version 4.3, done AutoProducts (STK/PODS), done AutoProducts (AUTOCON-G), final testing for retrofit to AUTOCON-G V4.3 (not launch critical) FreeFlyer/executable: version 4.8.0.6, done MATLAB ADS: version 2000.01, done MATLAB EO1MAN (MMAP & CALMAN): version 1.6, done MATLAB WRSSUN: version 1.0, done MATLAB ALI Mis-Alignment: version 1.2, done SOFTWARE STATUS

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