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

Constellation Status, Plans for Future Manfred Bester University of California - Berkeley. Outline. Outline Mission Status Summary Mission Networks Flight Systems Performance Anomaly Status ARTEMIS P1 Dynamics Anomaly Science Operations Metrics ARTEMIS Navigation Status Summary.

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

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  1. Constellation Status, Plans for Future Manfred Bester University of California - Berkeley

  2. Outline • Outline • Mission Status Summary • Mission Networks • Flight Systems Performance • Anomaly Status • ARTEMIS P1 Dynamics Anomaly • Science Operations Metrics • ARTEMIS Navigation Status • Summary

  3. Mission Status Summary • Constellation Status • All five probes are very healthy in general and continue to collect high quality science data after 3.75 years of successful on-orbit operations • In general none of the five probes show any sign of degradation in any of the spacecraft subsystems • One spacecraft lost an EFI sensor sphere • Few other minor issues with no impact to mission success • Fuel reserves continue to allow for ambitious mission extensions • Ground Systems & Operations Status • All ground systems are processing nominally • Hardware, software and procedures are kept up to date • Executed 430 individual thrust operations to date • Completed more than 23,000 passes to date (DSN: nearly 900) • All routine passes supported in lights-out mode

  4. Mission Networks THEMIS Probes TDRS GDSCC DSS-15, 24, 27 CDSCC DSS-34, 45 MDSCC DSS-54, 65 AGO, MILA, WGS BGS Secure Intranet JPL DSN White Sands Complex USNHI, USNAU USN NMC GSFC GCC Open IONet T1 Line Isolated Dial-up ISDN Line Berkeley Multi-mission Operations Center HBK

  5. Spacecraft BusSystems Status

  6. Instrument Status

  7. THB/P1 Dynamics Anomaly Sequence of Events • On October 15, both GSFC/FDF and UCB/SSL observed an unexplained range and range rate bias in their OD solutions. Note the range rate bias of -5.6 cm/s in the last two tracks (DS45, BRKS)! This bias prevailed during subsequent tracks, i.e. the effect appeared to be real and suggested a ΔV event had occurred. Reference: P. Morinelli, NASA/GSFC/FDF

  8. Deployed Instruments THEMIS Probe with Deployed Instruments Preamplifier, fine wire and sphere sensor (−X) • Electric Field Instrument(EFI): Spinplane booms (SPBs): X: ±25 m end-to-end (1-2) Y: ±20 m end-to-end (3-4) Axial booms (AXBs): (5-6) Preliminary analysis indicates the EFI −X sphere actually departed from the spacecraft.

  9. EFI Dimensions 3.5 m X: 24.39 m Engineering unit of preamplifier, fine wire, sphere and key reel

  10. Expected ∆V from Sphere Loss Sun Sensor ∆Vspacecraft = 0.056 m/s EFI Preamp −X Sphere ∆Vsphere = 51.032 m/s ω = 2 π / 3.0 s Spin plane boom length: 24.39 m from s/c center to sphere, 21.39 m from s/c center to preamp Note: This figure is not to scale.

  11. Observed ∆V Elevation of the impulse should be near the spin plane, which may indicate the velocity-only targeting is an outlier. Analysis based on post-event orbit solution Reference: D. Folta, NASA/GSFC/NMDB

  12. Thrust Maneuver Summary * ARTEMIS Probes Total executed thrust operations by end of prime mission: 296 Total executed thrust operations to date: 430

  13. Geostationary Conjunctions • THD: Dec. 24 - 30, 2010 THE: Feb. 25 - Mar. 5, 2011 THA: Apr. 27 - May 8, 2011

  14. Science Operations Metrics • Science Instrument Commanding • Configuration changes discussed in weekly operations meetings • All instruments command sequences typically tested on FlatSat prior to upload (FlatSat was moved from cleanroom to operations area) • Operations team implemented 117 Instrument Configuration Change Requests (ICCRs) to date, based on input from the science team • Science Data Recovery Metrics • Data dumps near perigee typically at 128K, 512K or 1024K • Tohban monitors data quality and completeness • Required data volumes: 591-751 Mbits/orbit, varying with compression • Actual recovered data volumes (mostly with >99% completeness): • 2007: 453 – 486 Mbits/orbit • 2008: 664 – 924 Mbits/orbit • 2009: 837 – 1050 Mbits/orbit • 2010: 907 – 919 Mbits/orbit (THEMIS-Low probes)

  15. ARTEMIS Data Recovery Metrics

  16. THEMIS / ARTEMIS Trajectories on 21-Sep-2009 THEMIS B orbit after ORM 5 and first lunar approach: 347,000 x 19,300 km THEMIS C orbit after ORM 13

  17. THEMIS B / ARTEMIS P1 – First Lunar Approach 17-Sep-2009 THEMIS B orbit after ORM 5 and first lunar approach within 46,000 km, causing orbit to increase to 347,000 x 19,300 km Moon

  18. THEMIS B / ARTEMIS P1 – Second Lunar Approach 02-Dec-2009 Flyby Targeting Maneuver (FTM 2) near perigee of last equatorial orbit 02-Dec-2009 Contingency options for executing missed FTM 2 19-Dec-2009 Trajectory Correction Maneuver (TCM 1) near end of first high-inclination orbit 07/08-Dec-2009 Second lunar approach (the knee) within 18,800 km, causing inclination change from 10 to 58 deg Moon

  19. THEMIS B / ARTEMIS P1 – First and Second Lunar Flyby 13-Feb-2010 Second lunar flyby within 5,000 km, resulting in trans-lunar trajectory 31-Jan-2010 First lunar flyby within 14,300 km, resulting in back flip The knee Moon 08-Dec-2009 − 31-Jan-2010 5 high-inclination orbits with 11-day periods Back flip

  20. THEMIS B / ARTEMIS P1 – Largest Range from Earth 13-Feb-2010 - 23-Aug-2010 Weak stability boundary trajectory with two large excursions and one Earth flyby in between 06-Jun-2010 Largest range from Earth: 1,500,000 km

  21. THEMIS B / ARTEMIS P1 – Libration Orbit Insertion 23-Aug-2010 Libration orbit insertion (LL2)

  22. THEMIS B / ARTEMIS P1 Orbit Evolution

  23. THEMIS C / ARTEMIS P2 – Final Earth Orbits Lunar orbit Moon 27-Feb-2010 Shadow deflection maneuver (SDM 1) 26-Mar-2010 Trajectory correction maneuver (TCM 1) 24-Mar-2010 Flyby targeting maneuver (FTM 1) 28-Mar-2010 Lunar flyby within 10,200 km of center, resulting in trans- lunar trajectory 26-Feb-2010 Last orbit raise maneuver (ORM 27) 15-Mar-2010 Shadow deflection maneuver (SDM 2) 22-Mar-2010 Long partial Earth shadow

  24. THEMIS C / ARTEMIS P2 Orbit Evolution

  25. THEMIS B & C / ARTEMIS P1 & P2 – Libration Orbits Libration orbit (LL1) Moon Libration orbit (LL2)

  26. THEMIS B / ARTEMIS P1 Libration Orbits – Moon Centered Coordinates Credit: NASA/GSFC

  27. Summary Summary • Overall Mission Status • Completed THEMIS prime mission on November 19, 2009 • Encountered 50 anomalies since launch - 39 closed • None of the anomalies caused a serious risk to mission success • Operations team staffing adequate for THEMIS & ARTEMIS support • Flight Systems • All bus flight subsystems continued to perform very well • All science instruments are working very well in general • Ground Systems • All ground systems continue to function well • Software tools are continually refined and extended as required • ARTEMIS Mission Extension • Initiated Earth departure on July 20, 2009 • Lissajous science phase started on October 22, 2010 • Lunar orbit insertion likely delayed until July 2011 (details are TBD) • P1 to date: 5 ORMs, 2 FTMs, 8 TCMs, 1 DSM, 13 SKMs • P2 to date: 27 ORMs, 1 FTM, 2 SDMs, 5 TCMs, 3 DSMs, 8 SKMs

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