THEMIS ARTEMIS Constellation Status Plans for Future Manfred

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THEMIS ARTEMIS Constellation Status, Plans for Future Manfred Bester University of California - Berkeley

THEMIS ARTEMIS Constellation Status, Plans for Future Manfred Bester University of California - Berkeley Post-Fall AGU SWT Meeting 1 UCB/SSL – Dec. 20, 2008

THEMIS ARTEMIS Overview • • • Prime Mission Constellation Status Science Operations Maneuver Summary

THEMIS ARTEMIS Overview • • • Prime Mission Constellation Status Science Operations Maneuver Summary Fuel Budget Extended Mission ARTEMIS Concept of Operations Top Level Schedule Network Communications Roles and Responsibilities Navigation Plans Summary of Future Plans Post-Fall AGU SWT Meeting 2 UCB/SSL – Dec. 20, 2008

THEMIS ARTEMIS Prime Mission Time History of Events and Macroscale Interactions during Substorms (THEMIS)

THEMIS ARTEMIS Prime Mission Time History of Events and Macroscale Interactions during Substorms (THEMIS) NASA Medium-class explorer mission Managed in PI Mode by UCLA/UCB http: //themis. ssl. berkeley. edu http: //www. nasa. gov/themis 5 Probes in synchronized Earth orbits with periods of 4, 2 and 1 days Conjunctions are formed in magnetospheric tail every 4 days Post-Fall AGU SWT Meeting 3 UCB/SSL – Dec. 20, 2008

THEMIS ARTEMIS Successful Launch Campaign Probe Release: L + 70 min Responsibility for Constellation

THEMIS ARTEMIS Successful Launch Campaign Probe Release: L + 70 min Responsibility for Constellation Operations Transitioned to MOC at UCB Launch: February 17, 2007 Post-Fall AGU SWT Meeting 4 UCB/SSL – Dec. 20, 2008

THEMIS Prime Mission Status Summary ARTEMIS • Prime Mission Status • Completed LEOP, coast

THEMIS Prime Mission Status Summary ARTEMIS • Prime Mission Status • Completed LEOP, coast phase, tail 1 and dayside 1 • Upcoming tail 2 and dayside 2 seasons • Answered primary scientific questions already • Constellation Status • All probes very healthy and collecting science data • Fuel reserves allow for ambitious mission extension • Ground Systems & Operations Status • • All ground systems processing nominally Executed 248 individual thrust operations to date Completed 10, 000 passes on December 3, 2008 All routine passes supported in lights-out mode Post-Fall AGU SWT Meeting 5 UCB/SSL – Dec. 20, 2008

THEMIS ARTEMIS Post-Fall AGU SWT Meeting Constellation Status Page 6 UCB/SSL – Dec. 20,

THEMIS ARTEMIS Post-Fall AGU SWT Meeting Constellation Status Page 6 UCB/SSL – Dec. 20, 2008

THEMIS ARTEMIS Science Operations • Science Instrument Commanding • Configuration changes discussed in ops

THEMIS ARTEMIS Science Operations • Science Instrument Commanding • Configuration changes discussed in ops meetings • All instruments command sequences typically tested on Flat. Sat prior to upload • Ops team implemented 75 ICCRs to date • Science Data Recovery Metrics • • • Data dumps near perigee at 512 K or 1024 K Outer probes get two passes whenever possible Recovered / acquired data volume: 98 - 99% Recovered / required data volume: 111 - 147% Tohban monitors data quality and completeness Post-Fall AGU SWT Meeting 7 UCB/SSL – Dec. 20, 2008

THEMIS Flight Systems Status ARTEMIS Flight Systems Status System Spacecraft Bus Subsystem Probe Bus

THEMIS Flight Systems Status ARTEMIS Flight Systems Status System Spacecraft Bus Subsystem Probe Bus Subsystems BAU FSW A-E Nominal Occasional glitches in onboard spin rate calculation Telecom A-E Power A-E Antennas weaker than expected Nominal Degraded operational link budgets (B: -3 d. B; A, C, D: -4 d. B; E: -5 d. B) Power systems allow operation through 4 -h shadows Thermal A-E Nominal No issues in nominal mission attitude Analysis shows no risk of freezing fuel lines E Instruments Status Comments New BAU FSW version 0 x 3500 currently tested on Flat. Sat, upload scheduled for early 2009 Instrument Suite A-E Thermal leak near Service Valve 2 Thermistor on Solar Array 3 has open circuit in shadow Nominal IDPU FSW A-E Nominal All probes run IDPU FSW version 0 x 50 ESA A-E Small degradation in sensitivity of electron sensor below 30 e. V in certain angle sectors Localized MCP degradation in angle sectors looking along the spin axis may be caused by emission of photo electrons from axial booms – probes A and B have least amount of degradation, had booms deployed later SST A-E Small degradation of 8 sensitivity Increased sensor bias once to restore UCB/SSL – Dec. 20, 2008 nominal sensitivity Post-Fall AGU SWT Meeting Thermistors on SA 1, 2, 4 provide redundant information

THEMIS ARTEMIS Anomaly Tracking • Anomaly Tracking & Resolution • Tiger Team assigned for

THEMIS ARTEMIS Anomaly Tracking • Anomaly Tracking & Resolution • Tiger Team assigned for each flight system or major ground system anomaly • Investigate and determine cause of anomaly • Recommend solutions, work-arounds and/or mitigations • Provide final report • Anomaly Tracking List • Items closed out when anomaly report released and recommended actions were performed • Currently tracking 29 items (20 closed) Post-Fall AGU SWT Meeting 9 UCB/SSL – Dec. 20, 2008

THEMIS ARTEMIS THEMIS Orbit Determination • Orbit determination (OD) for the THEMIS constellation is

THEMIS ARTEMIS THEMIS Orbit Determination • Orbit determination (OD) for the THEMIS constellation is based on two-way Doppler tracking data and the Goddard Trajectory Determination System (GTDS). • Tests are underway to characterize the THEMIS ranging capabilities for use during ARTEMIS. Parameter THEMIS A/P 5 THEMIS B/P 1 THEMIS C/P 2 THEMIS D/P 3 THEMIS E/P 4 Arc Length [d] 7 12 9 7 7 Number of Passes in Arc 25 40 32 25 25 Pass Duration [min] 20 - 30 20 - 30 Typical Achieved Accuracy < 50 m < 5 mm/s < 50 m < 5 mm/s Number of Orbit Solutions as of 11/24/2008 328 344 342 326 330 Post-Fall AGU SWT Meeting 10 UCB/SSL – Dec. 20, 2008

THEMIS ARTEMIS Executed Maneuver Summary THEMIS A P 5 THEMIS B P 1* THEMIS

THEMIS ARTEMIS Executed Maneuver Summary THEMIS A P 5 THEMIS B P 1* THEMIS C P 2* THEMIS D P 3 THEMIS E P 4 Initial Fuel Load [kg] 48. 800 48. 780 48. 810 48. 820 Expended Fuel [kg] 23. 412 33. 508 27. 029 20. 208 19. 944 Remaining Fuel [kg] 25. 388 15. 272 21. 781 28. 602 28. 876 Total Expended ΔV [m/s] 452. 600 694. 618 537. 979 390. 927 377. 661 Attitude Precessions 20 21 9 11 10 Spin Rate Changes 16 17 16 10 10 ΔV Maneuvers 23 22 27 17 19 Total Executed Maneuvers 59 60 52 38 39 Parameter * ARTEMIS Probes Total executed thrust operations: 248 Post-Fall AGU SWT Meeting 11 UCB/SSL – Dec. 20, 2008

THEMIS ARTEMIS P 1 Large Plane Change Maneuver ΔV: 296. 5 m/s Fuel: 13.

THEMIS ARTEMIS P 1 Large Plane Change Maneuver ΔV: 296. 5 m/s Fuel: 13. 2 kg Post-Fall AGU SWT Meeting 12 UCB/SSL – Dec. 20, 2008

THEMIS ARTEMIS P 2 Large Plane Change Maneuver ΔV: 227. 7 m/s Fuel: 10.

THEMIS ARTEMIS P 2 Large Plane Change Maneuver ΔV: 227. 7 m/s Fuel: 10. 5 kg Post-Fall AGU SWT Meeting 13 UCB/SSL – Dec. 20, 2008

THEMIS P 1 Planned Maneuvers ARTEMIS THEMIS B/P 1 Time (UTC) ΔV [m/s] Fuel

THEMIS P 1 Planned Maneuvers ARTEMIS THEMIS B/P 1 Time (UTC) ΔV [m/s] Fuel Used [kg] Purpose M 03_T 2 2008/347 23: 58: 04. 658 1. 417 0. 058 Apogee - 1463 km M 03_T 2 Spin Control Post M 03_T 2 0. 020 0. 001 Spin Control* M 04_T 2 2009/017 05: 50: 00. 028 4. 581 0. 188 Apogee - 4721 km M 04_T 2 Attitude Change 2009/017 10: 06: 26. 055 0. 333 0. 014 Attitude Change to Nominal M 04_T 2 Spin Control Post M 04_T 2 0. 033 0. 001 Spin Control* M 05_T 2 2009/062 16: 37: 09. 413 6. 428 0. 263 Apogee + 6388 km M 05_T 2 Spin Control Post M 05_T 2 0. 040 0. 002 Spin Control* M 1 A_D 2 2009/130 06: 43. 412 2. 567 0. 105 Apogee + 2494 km M 1 A_D 2 Attitude Change 2009/130 10: 52: 58. 172 0. 315 0. 013 Attitude Change to Nominal M 1 A_D 2 Spin Control Post M 1 A_D 2 0. 047 0. 002 Spin Control* M 03_D 2 2009/158 14: 33: 14. 154 3. 444 0. 141 Apogee - 3392 km M 03_D 2 Spin Control Post M 03_D 2 0. 073 0. 003 Spin Control* Contingency 10. 674 0. 5 Total 19. 298 1. 291 * Spin target is 20. 2105 ± 0. 0130 rpm Post-Fall AGU SWT Meeting 14 UCB/SSL – Dec. 20, 2008

THEMIS P 2 Planned Maneuvers ARTEMIS THEMIS C/P 2 Time (UTC) ΔV [m/s] Fuel

THEMIS P 2 Planned Maneuvers ARTEMIS THEMIS C/P 2 Time (UTC) ΔV [m/s] Fuel Used [kg] Purpose M 03_T 2 2008/346 01: 30: 27. 968 3. 664 0. 164 Apogee +1384 km M 03_T 2 Spin Control Post M 03_T 2 0. 033 0. 001 Spin Control* M 04_T 2 2009/015 16: 05: 40. 741 1. 641 0. 074 Apogee - 644 km M 04_T 2 Spin Control Post M 04_T 2 0. 020 0. 001 Spin Control* M 05_T 2 2009/062 19: 23: 31. 781 2. 468 0. 110 Apogee + 957 km M 05_T 2 Spin Control Post M 05_T 2 0. 033 0. 001 Spin Control* M 1 A_D 2 2009/128 07: 33: 27. 684 4. 581 0. 205 Apogee + 1730 km M 1 A_D 2 Attitude Change 2009/128 11: 43: 39. 382 0. 247 0. 011 Attitude Change to Nominal M 1 A_D 2 Spin Control Post M 1 A_D 2 0. 053 0. 002 Spin Control* M 03_D 2 2009/156 15: 24: 45. 789 4. 634 0. 207 Apogee - 1761 km M 03_D 2 Spin Control Post M 03_D 2 0. 053 0. 002 Spin Control* Contingency 10. 046 0. 500 Total 27. 473 1. 278 * Spin target is 20. 2105 ± 0. 0130 rpm Post-Fall AGU SWT Meeting 15 UCB/SSL – Dec. 20, 2008

THEMIS ARTEMIS THEMIS B/P 1 & P 2 Remaining Fuel Remaining ΔV [m/s] Remaining

THEMIS ARTEMIS THEMIS B/P 1 & P 2 Remaining Fuel Remaining ΔV [m/s] Remaining Fuel [kg] End of THEMIS D 2 326. 0 14. 0 ARTEMIS ACS / Contingency 21. 5 1. 0 Net Remaining 304. 5 13. 0 Remaining ΔV [m/s] Remaining Fuel [kg] End of THEMIS D 2 468. 1 20. 5 ARTEMIS ACS / Contingency 20. 2 1. 0 Net Remaining 447. 9 19. 5 THEMIS C/P 2 Post-Fall AGU SWT Meeting 16 UCB/SSL – Dec. 20, 2008

THEMIS ARTEMIS Extended Mission Time History of Events and Macroscale Interactions during Substorms (THEMIS)

THEMIS ARTEMIS Extended Mission Time History of Events and Macroscale Interactions during Substorms (THEMIS) 3 Probes (A/P 5, D/P 3, E/P 4) in synchronized Earth orbits with 1 -day periods Acceleration, Reconnection, Turbulence and Electrodynamics of the Moon’s Interaction with the Sun (ARTEMIS) 2 Probes (B/P 1, C/P 2) in lunar orbits Post-Fall AGU SWT Meeting 17 UCB/SSL – Dec. 20, 2008

THEMIS ARTEMIS Con. Ops • ARTEMIS Concept of Operations • Transfer of outer two

THEMIS ARTEMIS Con. Ops • ARTEMIS Concept of Operations • Transfer of outer two probes (B/P 1 and C/P 2) into lunar orbits via Weak Stability Boundary trajectory using Earth and lunar gravity assist • Communications with these two probes via DSN • Data recovery from lunar distances up to 128 K • Attitude determination with sun sensor data only • No required flight software changes • THEMIS Concept of Operations • THEMIS mission continues with inner three probes (A/P 5, D/P 3, E/P 4) in tighter formation NOTES: For all operational purposes all five probes shall continue to be referred to as THEMIS A-E. New capabilities at the MOC shall be considered an upgrade, not a transition. Post-Fall AGU SWT Meeting 18 UCB/SSL – Dec. 20, 2008

THEMIS Network Communications ARTEMIS THEMIS Probes TDRS GDSCC DSS-24, 27 CDSCC DSS-34, 45 MDSCC

THEMIS Network Communications ARTEMIS THEMIS Probes TDRS GDSCC DSS-24, 27 CDSCC DSS-34, 45 MDSCC DSS-54, 65 BGS Secure Intranet WS 1, AGO, MILA, WGS JPL DSN White Sands Complex USN NMC USNHI, USNAU GSFC NMC Open IONet T 1 Line Isolated Dial-up ISDN Line Berkeley Multi-mission Operations Center Post-Fall AGU SWT Meeting THEMIS/ARTEMIS Network Links 19 HBK UCB/SSL – Dec. 20, 2008

THEMIS Spacecraft Constraints ARTEMIS Spacecraft Constraints Impacting ARTEMIS Operations Constraint Operational Impact / Risks

THEMIS Spacecraft Constraints ARTEMIS Spacecraft Constraints Impacting ARTEMIS Operations Constraint Operational Impact / Risks Work-around / Mitigation Thruster locations on spacecraft Thrust direction only in one hemisphere Insert bias maneuvers into navigation plan No thrust operations in shadow due to RCS design Cannot execute maneuvers in Earth or lunar shadows Shift maneuvers outside of shadows Survival of long shadows Spacecraft designed for maximum shadow duration of 180 min. Power systems performance allows shadows up to 240 min duration. Design trajectory to avoid shadows longer than 240 min EIRP of spacecraft transmitter with omni antenna Spacecraft telecomm subsystem designed to work with 11 -m class ground stations Utilize DSN 34 -m antennas and adjust telemetry rates to close link with positive margin, based on range and spacecraft attitude Available sensor data for attitude determination ACS and ADS designed to work with sun sensor and FGM data, requiring Earth’s magnetic field Implement ADS based only on sun sensor data Post-Fall AGU SWT Meeting 20 UCB/SSL – Dec. 20, 2008

THEMIS Thruster Firing Modes ARTEMIS Thruster Firing Modes Maneuver Type Thrusters Involved Depiction of

THEMIS Thruster Firing Modes ARTEMIS Thruster Firing Modes Maneuver Type Thrusters Involved Depiction of Operational Mode Purpose of Maneuver Axial Thrust A 1 and A 2 continuous firing Perigee or apogee change or combined in-plane and out-of-plane orbit change with stowed EFI booms Side Thrust T 1 and T 2 pulsed firing Perigee or apogee change with deployed EFI booms Beta Thrust A 1 and A 2 continuous firing alternating with T 1 and T 2 pulsed firing In-plane and out-of-plane orbit change with deployed EFI booms Attitude Precession A 1 or A 2 pulsed firing Attitude change Spin-up / Spin-down T 1 or T 2 continuous or pulsed firing Spin rate adjustment Post-Fall AGU SWT Meeting 21 UCB/SSL – Dec. 20, 2008

THEMIS Roles and Responsibilities ARTEMIS • ARTEMIS Navigation Team • Mission Design & Baseline

THEMIS Roles and Responsibilities ARTEMIS • ARTEMIS Navigation Team • Mission Design & Baseline Trajectories • JPL/GNC • Trajectory Verification & Validation • GSFC/FDAB • Navigation Plans & Error Analysis • GSFC/FDAB • Maneuver Targeting & Operations • GSFC/FDAB & UCB/SSL • Orbit Determination & Error Analysis • GSFC/FDF & UCB/SSL • Attitude Determination • UBC/SSL with software provided by GSFC/FDAB and a. i. solutions Post-Fall AGU SWT Meeting 22 UCB/SSL – Dec. 20, 2008

THEMIS ARTEMIS Post-Fall AGU SWT Meeting Top Level Schedule 23 UCB/SSL – Dec. 20,

THEMIS ARTEMIS Post-Fall AGU SWT Meeting Top Level Schedule 23 UCB/SSL – Dec. 20, 2008

THEMIS ARTEMIS P 1 Impulsive ORM Sequence THEMIS D 2 ORM 8 ORM 1

THEMIS ARTEMIS P 1 Impulsive ORM Sequence THEMIS D 2 ORM 8 ORM 1 Post-Fall AGU SWT Meeting 24 UCB/SSL – Dec. 20, 2008

THEMIS ARTEMIS Post-Fall AGU SWT Meeting P 1 Lunar Approaches 25 UCB/SSL – Dec.

THEMIS ARTEMIS Post-Fall AGU SWT Meeting P 1 Lunar Approaches 25 UCB/SSL – Dec. 20, 2008

THEMIS ARTEMIS Finite Trajectory Design JPL/NAV Initial Trajectory Verification and Correction GSFC/FDAB Validated Trajectory

THEMIS ARTEMIS Finite Trajectory Design JPL/NAV Initial Trajectory Verification and Correction GSFC/FDAB Validated Trajectory Navigation Work Flow Orbit Determination Predictive Ephemeris GSFC/FDF Maneuver Operations UCB Ephemeris Products Telemetry Data Maneuver Planning GSFC/FDAB Maneuver Reconstruction UCB GMAN/GMAT Config Post Execution State Maneuver Verification UCB Orbit Determination Definitive Ephemeris GSFC/FDF Thruster CMD Sheets Acquisition Data Planning Products Post-Fall AGU SWT Meeting 26 Ephemeris Products Maneuver Calibration GSFC/FDAB & UCB/SSL – Dec. 20, 2008

THEMIS ARTEMIS Summary • Near Term Plans • Complete second tail season by April

THEMIS ARTEMIS Summary • Near Term Plans • Complete second tail season by April 2009 • Outer probes maneuvered close to neutral sheet • Finalize ARTEMIS mission design • Mid Term Plans • Complete second dayside season by July 2009 • Start orbit raise maneuver sequence for P 1 & P 2 • Long Term Plans • Execute translunar trajectory phase for ARTEMIS (P 1 & P 2) • Operate THEMIS (P 3, P 4, P 5) in closer formation Post-Fall AGU SWT Meeting 27 UCB/SSL – Dec. 20, 2008

THEMIS ARTEMIS Going Back to the Moon Landing: July 20, 1969 40 Years Later

THEMIS ARTEMIS Going Back to the Moon Landing: July 20, 1969 40 Years Later … Launch: July 16, 1969 Post-Fall AGU SWT Meeting 28 UCB/SSL – Dec. 20, 2008