1. Post-Fall AGU SWT Meeting1Dec. 18, 2010 THEMIS ARTEMIS Constellation Status, Plans for Future Manfred Bester University of California - Berkeley

2. Post-Fall AGU SWT Meeting2Dec. 18, 2010 THEMIS ARTEMIS Outline Mission Status Summary Mission Networks Flight Systems Performance Anomaly Status ARTEMIS P1 Dynamics Anomaly Science Operations Metrics ARTEMIS Navigation Status Summary

3. Post-Fall AGU SWT Meeting3Dec. 18, 2010 THEMIS ARTEMIS 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. Post-Fall AGU SWT Meeting4Dec. 18, 2010 THEMIS ARTEMIS Berkeley Multi-mission Operations Center White Sands Complex GSFC GCC THEMIS Probes Secure Intranet TDRS O pen IONet T1 Line HBK Isolated Dial-up ISDN Line AGO, MILA, WGS USNHI, USNAU BGS JPL DSN GDSCCDSS-15, 24, 27 CDSCCDSS-34, 45 MDSCCDSS-54, 65 USN NMC Mission Networks

5. Post-Fall AGU SWT Meeting5Dec. 18, 2010 THEMIS ARTEMIS Spacecraft Bus Systems Status Flight Systems Status Summary – Spacecraft Bus SystemSubsystemProbeStatusComments Spacecraft Bus Bus SubsystemsA - ENominal BAU FSWA - ENominalAll probes are running BAU FSW version 0x3701; upload completed on Nov. 7, 2009 TelecomA - EAntennas weaker than expected Degraded operational link budgets (B: -3 dB; A,C,D: -4 dB; E: -5 dB) PowerA - ENominalPower systems allow operation through 4-h shadows; longest penumbra ~8 h ThermalA - ENominalNo issues in nominal mission attitude EThermal leak near Service Valve 2 Analysis shows no risk of freezing fuel lines RCSA - ENominalAll RCS thrusters & valves function well, no leaks ACSA - ENominalAll ACS sensors nominal

6. Post-Fall AGU SWT Meeting6Dec. 18, 2010 THEMIS ARTEMIS Instrument Status Flight Systems Status Summary – Instruments SystemSubsystemProbeStatusComments InstrumentsInstrument SuiteA - ENominal IDPU FSWA - ENominalAll probes are running IDPU FSW version 0x56; upload completed on Nov. 19, 2010 EFIBLost -X sensor sphere and part of the fine wire due to melting of the fine wire, likely as a result of micrometeorite impact, possibly from the Orionids (Oct. 14, 2010) Reconfigured instrument to use ±Y sensors to obtain spin-fit DC electric field measurements and to trigger bursts; ±X pair continues to provide wave measurements; no significant science loss ESAA - ESmall degradation in sensitivity of electron sensor below 30 eV 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 SSTA – ENoticeable degradation of sensitivity in all ion detectors Caused by ion implantation; Increased sensor bias once to restore nominal sensitivity DAttenuator B stuck in closed position due to a failure of the actuator mechanism (April 9, 2010) While attenuator A is still functioning, both attenuators will likely be left in the closed position for the remainder of the mission; no significant science loss

7. Post-Fall AGU SWT Meeting7Dec. 18, 2010 THEMIS ARTEMIS Sequence of Events On October 15, both GSFC/FDF and UCB/SSL observed an unexplained range and range rate bias in their OD solutions. THB/P1 Dynamics Anomaly 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. Post-Fall AGU SWT Meeting8Dec. 18, 2010 THEMIS ARTEMIS Deployed Instruments THEMIS Probe with Deployed Instruments Electric Field Instrument (EFI): Spin plane booms (SPBs): X: ±25 m end-to-end (1-2) Y: ±20 m end-to-end (3-4) Axial booms (AXBs): (5-6) Preamplifier, fine wire and sphere sensor (−X) Preliminary analysis indicates the EFI −X sphere actually departed from the spacecraft.

9. Post-Fall AGU SWT Meeting9Dec. 18, 2010 THEMIS ARTEMIS EFI Dimensions Engineering unit of preamplifier, fine wire, sphere and key reel 3.5 m X: 24.39 m

10. Post-Fall AGU SWT Meeting10Dec. 18, 2010 THEMIS ARTEMIS ∆V sphere = 51.032 m/s ω = 2 π / 3.0 s Sun Sensor Expected ∆V from Sphere Loss ∆V spacecraft = 0.056 m/s EFI Preamp −X Sphere Note: This figure is not to scale. Spin plane boom length: 24.39 m from s/c center to sphere, 21.39 m from s/c center to preamp

11. Post-Fall AGU SWT Meeting11Dec. 18, 2010 THEMIS ARTEMIS Observed ∆V Targeting Method∆V [m/s]Azimuth [deg]Elevation [deg] Position only0.0565479.751-0.945 Velocity only0.0692578.33831.277 Position and Velocity0.0577577.3790.679 Reference: D. Folta, NASA/GSFC/NMDB 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

12. Post-Fall AGU SWT Meeting12Dec. 18, 2010 THEMIS ARTEMIS Thrust Maneuver Summary * ARTEMIS Probes Maneuver and Fuel Budget Summary to Date Parameter THEMIS A P5 THEMIS B P1* THEMIS C P2* THEMIS D P3 THEMIS E P4 Initial Fuel Load [kg]48.80048.78048.810 48.820 Expended Fuel [kg]32.48639.37340.24022.64722.467 Remaining Fuel [kg]16.3149.4078.57026.16326.353 Remaining Fuel [%]33.419.317.653.654.0 Total Expended ΔV [m/s]654.536838.075849.600442.761430.354 Total executed thrust operations by end of prime mission: 296 Total executed thrust operations to date: 430

13. Post-Fall AGU SWT Meeting13Dec. 18, 2010 THEMIS ARTEMIS Geostationary Conjunctions THD: Dec. 24 - 30, 2010 THE: Feb. 25 - Mar. 5, 2011 THA: Apr. 27 - May 8, 2011

14. Post-Fall AGU SWT Meeting14Dec. 18, 2010 THEMIS ARTEMIS 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. Post-Fall AGU SWT Meeting15Dec. 18, 2010 THEMIS ARTEMIS ARTEMIS Data Recovery Metrics

16. Post-Fall AGU SWT Meeting16Dec. 18, 2010 THEMIS ARTEMIS THEMIS / ARTEMIS Trajectories on 21-Sep-2009 THEMIS C orbit after ORM 13 THEMIS B orbit after ORM 5 and first lunar approach: 347,000 x 19,300 km 16

17. Post-Fall AGU SWT Meeting17Dec. 18, 2010 THEMIS ARTEMIS 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 17

18. Post-Fall AGU SWT Meeting18Dec. 18, 2010 THEMIS ARTEMIS THEMIS B / ARTEMIS P1 – Second Lunar Approach 18 07/08-Dec-2009 Second lunar approach (the knee) within 18,800 km, causing inclination change from 10 to 58 deg 02-Dec-2009 Flyby Targeting Maneuver (FTM 2) near perigee of last equatorial orbit 02-Dec-2009 Contingency options for executing missed FTM 2 Moon 19-Dec-2009 Trajectory Correction Maneuver (TCM 1) near end of first high- inclination orbit

19. Post-Fall AGU SWT Meeting19Dec. 18, 2010 THEMIS ARTEMIS THEMIS B / ARTEMIS P1 – First and Second Lunar Flyby 19 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 Back flip The knee Moon 08-Dec-2009 − 31-Jan-2010 5 high-inclination orbits with 11-day periods

20. Post-Fall AGU SWT Meeting20Dec. 18, 2010 THEMIS ARTEMIS THEMIS B / ARTEMIS P1 – Largest Range from Earth 20 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. Post-Fall AGU SWT Meeting21Dec. 18, 2010 THEMIS ARTEMIS THEMIS B / ARTEMIS P1 – Libration Orbit Insertion 21 23-Aug-2010 Libration orbit insertion (LL2)

22. Post-Fall AGU SWT Meeting22Dec. 18, 2010 THEMIS ARTEMIS 22 THEMIS B / ARTEMIS P1 Orbit Evolution

23. Post-Fall AGU SWT Meeting23Dec. 18, 2010 THEMIS ARTEMIS 23 THEMIS C / ARTEMIS P2 – Final Earth Orbits 24-Mar-2010 Flyby targeting maneuver (FTM 1) 22-Mar-2010 Long partial Earth shadow Lunar orbit 28-Mar-2010 Lunar flyby within 10,200 km of center, resulting in trans- lunar trajectory 15-Mar-2010 Shadow deflection maneuver (SDM 2) 27-Feb-2010 Shadow deflection maneuver (SDM 1) 26-Feb-2010 Last orbit raise maneuver (ORM 27) Moon 26-Mar-2010 Trajectory correction maneuver (TCM 1)

24. Post-Fall AGU SWT Meeting24Dec. 18, 2010 THEMIS ARTEMIS 24 THEMIS C / ARTEMIS P2 Orbit Evolution

25. Post-Fall AGU SWT Meeting25Dec. 18, 2010 THEMIS ARTEMIS THEMIS B & C / ARTEMIS P1 & P2 – Libration Orbits 25 Libration orbit (LL2) Libration orbit (LL1) Moon

26. Post-Fall AGU SWT Meeting26Dec. 18, 2010 THEMIS ARTEMIS 26 THEMIS B / ARTEMIS P1 Libration Orbits – Moon Centered Coordinates Credit: NASA/GSFC

27. Post-Fall AGU SWT Meeting27Dec. 18, 2010 THEMIS ARTEMIS 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 Summary