LEO and Normal Operations Manfred Bester THEMIS FDMO

L&EO and Normal Operations Manfred Bester THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 1 June 1 -2, 2004

L&EO and Normal Operations Overview • • • Launch Early Orbit Checkout Maneuver Operations Instrument Commissioning Normal Science Operations THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 2 June 1 -2, 2004

L&EO Operations Launch & Early Orbit Operations • • • Delta II Launch Sequence with Release of Probes Probe A Radiating During Separation, Monitored Via TDRSS Subsequent Round Robin State-of-Health Monitoring Initial Attitude and Orbit Determination Uplink of First Set of Command Loads to Each Probe Change Attitude from Release to Commissioning Attitude Systematic Instrument Power-up and Check-out Decision of Probe Placement − Based on Functional Check-out Orbit Placement Maneuvers Critical Operations Performed Real-time Contact Approval to Proceed via Command Authorization Meetings (CAMs) THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 3 June 1 -2, 2004

Launch Configuration Delta II 7925 -10 Third Stage and Probe Carrier Assembly THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 4 June 1 -2, 2004

Probe Exterior and Interior View Probe Bus – Exterior View with Magnetometer Booms Stowed Probe Bus – Interior View THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 5 June 1 -2, 2004

Probe Separation from PCA • • • Monitoring of Separation via TDRSS One Probe Will Be Transmitting (THEMIS A, Top of PCA) All Probes Will Be Recording Data Round-robin Status Polling After Separation Each Probe Will Be Contacted for 5 Minutes Initially THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 6 June 1 -2, 2004

Dispersion Analysis Post-launch Probe Dispersion Analysis • • Use Relative Separation Velocities Perform Inter-probe Range Analysis (Not Yet Completed) Relative Separation Velocities X [m/s] Y [m/s] Radial [m/s] Z [m/s] PCA + LV 0. 0000 0. 01600 -0. 2700 Probe A 0. 0084 -0. 0349 0. 03590 0. 2563 Probe B 1. 5726 -0. 9411 1. 83269 0. 1549 Probe C 0. 9456 1. 5864 1. 84684 0. 1416 Probe D -1. 5818 0. 9589 1. 84975 0. 1326 Probe E -0. 9545 1. 5681 1. 83576 0. 1460 THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 7 June 1 -2, 2004

Mission Profile THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 8 June 1 -2, 2004

Post-launch Scenario Power Profile • • Probes Are Power Positive with Minimum Loads Need to Perform Attitude Maneuver to Orient Probe +Z Axis Perpendicular to Probe-sun Line to Allow for Check-out Activities Thermal Profile • Worst Case Is Top or Bottom Deck to Sun Communications Coverage • • • Scenario Based on Launch Trajectory Provided by KSC Modeled Probe Antenna Pattern Dynamic Link Margin Calculated for Telemetry Data Rate of 4. 096 kbps THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 9 June 1 -2, 2004

Launch Scenario THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 10 June 1 -2, 2004

Launch Scenario THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 11 June 1 -2, 2004

Launch Scenario THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 12 June 1 -2, 2004

Launch Scenario THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 13 June 1 -2, 2004

Probe Antenna Pattern Calculated Probe Antenna Pattern Specification: -3 d. B Points at 90° ± 45° Polarization: LHCP Pattern: Toroidal, Centered in X−Y Plane Top Deck of Probe Body Affects Gain Pattern: Blockage at −Z Ripples at +Z THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 14 June 1 -2, 2004

Launch Scenario Data Rate: 4. 096 kbps THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 15 June 1 -2, 2004

Launch Scenario Data Rate: 4. 096 kbps THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 16 June 1 -2, 2004

Launch Scenario Polar Plot of First Two BGS View Periods THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 17 June 1 -2, 2004

L&EO Timeline THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 18 June 1 -2, 2004

L&EO Timeline THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 19 June 1 -2, 2004

L&EO Timeline THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 20 June 1 -2, 2004

L&EO Timeline THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 21 June 1 -2, 2004

Maneuver Planning & Execution Maneuver Planning • • • Determine Pre-maneuver State Vector and Attitude with Required Accuracy Perform Maneuver Analysis with Current and Target State Vectors Verify Delta V Budget Perform Contact Schedule and Shadow Analysis Develop Detailed Thruster Firing Sequence Validate Probe Configuration and Maneuver Sequence on Probe Simulator Maneuver Execution • • • Establish Two-way Communications with Probe Ramp Down ESA High-voltage Supply, Place SST into Attenuated Mode Uplink Command Sequence to Perform Reorientation and Orbit Maneuvers Download and Verify Command Buffer and Verify Firing Attitude Monitor Maneuver Execution in Real-time De-configure Probe Systems and Monitor Health and Safety Maneuver Calibration • • • Determine Post-maneuver Orbit and Attitude Calibrate Thrusters and Analyze Overall Maneuver Efficiency and Accuracy Perform Accurate Bookkeeping of Fuel Usage THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 22 June 1 -2, 2004

Pre-launch Testing & Validation Pre-launch Testing and Validation of Maneuvers • Develop Representative Command Profile – Required to Perform End-to-end Tests for All Operational Scenarios for Each Probe • Post-test Analysis of Captured Virtual. Sat Telemetry Data – Validate ACS Flight Software for Thruster Control, On-orbit Attitude Determination and Fault Protection – Validate Ground-based Attitude Determination Software THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 23 June 1 -2, 2004

Typical Maneuver Sequence Probe Operations Functions Turn Off Gyros Turn Off Transmitter Determin e New Orbit and Attitude, and Calibrate Maneuver Execute Burn Sequence Turn Off Catalyst Bed Heaters On-board Failure Detection & Correction (FDC) Logic (Gyro Rates, Sun Sensor Attitude Limits, etc. ) Aborts Sequence if Anomaly Detected Perform Long-term Calibration of Pulse Timing and Thruster Efficiency Perform Mission Design to Determine Target Probe Orbit and Attitude Perform GMAN Run with Current and Target Orbit and Attitude Downlink On-board CMD Buffer Verify CMD & TLM Link Via BGS, WGS or TDRSS Monitor Key Temperature s, Tank Pressure, Attitude and State Vector Verify Tank Pressure, General Probe Health and Safety, and Perform Twoway Ranging Turn On Gyros and Catalyst Bed Heaters (Preheat) Formulate Specific Maneuver Events, Attitudes and Durations Verify Gyro Performance, Catalyst Bed Heater Functionality, Propellant Tank Pressure, Valve and Fuel Line Temperatures and States, and Pre-Maneuver Attitude Verify Current Attitude Via Sun Sensor Data Generate Discrete Thruster Profile and Pulse Firing Sequence Compare Flight and Ground Reference Image to Verify Load Generate Discrete Stored Command Sequence Via MPS Upload TLM Table, Firing Sequence and Downlink Data Rate Perform Off-line Validation of Entire Stored Command Sequence on Hifidelity Probe Simulator Ground Operations Functions THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 24 June 1 -2, 2004

Maneuver Types Maneuver Type Thrusters Involved Purpose, Requirements and Fuel Efficiency Orbit Position for Maneuver GMAN Compatibility Orbit Maneuver A 1 and A 2 Continuous Firing Perigee or Apogee Change Preceded and Followed by Attitude Maneuver High Fuel Efficiency Arc Limited Near Perigee to Minimize Cosine Loss Apogee or Perigee Yes Orbit Maneuver A 1 and A 2 Continuous Firing Inclination Change with or without Arg Per Change Preceded and Followed by Attitude Maneuver High Fuel Efficiency Apogee Yes Orbit Maneuver A 1 and A 2 Continuous Firing Apogee or Perigee Yes Orbit Maneuver A 1 and A 2 Continuous Firing Alternating with T 1 and T 2 Pulsed Firing Apogee or Perigee Yes Attitude Maneuver A 1 and / or A 2 Pulsed Firing Any Yes Spin Up or Spin Down T 1 or T 2 Pulsed Firing Any Yes Combined In-plane and Out-of-plane Orbit Change Preceded and Followed by Attitude Maneuver High Fuel Efficiency Arc Limited Near Perigee to Minimize Cosine Loss In-plane and Out-of-plane Orbit Tweak in Mission Attitude Large Beta Angle Loss Sunlight on Sun Sensor Required Arc Limited Near Perigee to Minimize Cosine Loss Attitude Change to or from Mission or Maneuver Attitude High Efficiency Prior to Spin-plane Boom Deploy Low Efficiency after Spin-plane Boom Deploy Sunlight on Sun Sensor Required Spin Rate Adjustment Sunlight on Sun Sensor Required THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 25 June 1 -2, 2004

Maneuver Sequence Ground-Based Attitude Determination (MSSS / FGM) Precession Maneuver to Normal Attitude Upload: Thruster Enable Earth Upload: Thruster Enable Upload: Thruster Commands Upload: Thruster Enable THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 26 Precession Maneuver to Axial Thrust Attitude Monitoring (MSSS / IRU) June 1 -2, 2004

Mission Orbit Placement for P 1 • Accelerated Maneuver Sequence Modeled with GMAN – Apogee and Perigee Raises – Inclination Adjustment • Goals of Study – Determine Communications Coverage THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 27 June 1 -2, 2004

Communications Coverage THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 28 June 1 -2, 2004

Maneuver Details Spin-up and Spin-down Maneuvers • Spin Rate Limits: 2 - 25 rpm Timing of Pulse Maneuvers • Ensure Pulse Frequencies Do Not Coincide with Probes’ Fundamental Frequencies (Nutation, Spin-plane Booms, Axial Booms, Propellant Slosh) Flight Rules Related to Maneuver Operations • • • RCS Configuration Maintain Spin Rate Within Allowable Limits Select Pulse Timing to Avoid Exciting of Resonances THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 29 June 1 -2, 2004

Real-time Maneuver Support • Communications Requirements – Ground Station Contact – TDRSS Contact • Real-time Monitoring – – • Tank Pressure Thruster Temperatures Probe Attitude Vector Doppler Profile Compare Observed Against Predicted Performance – Real-time Trend Plots for Observed Minus Calculated Attitude and Doppler Residuals – Plotting Doppler Residuals Requires Real-time Data from Ground Stations – Plotting Attitude Angle Residuals Requires Data from Probe Telemetry Via ITOS THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 30 June 1 -2, 2004

Attitude Control Plan • • • Probe Release from Launch Vehicle, Nominally at 15 rpm Optional De-spin to 15 rpm, in Case of Off-nominal Release Attitude Maneuver to Place Spin Axis Perpendicular to Probe -to-sun Line at 15 rpm Deploy of Magnetometer Booms at 15 rpm Spin-up to 20 rpm Attitude and Orbit Maneuvers at 20 rpm Attitude Maneuver to Point Spin Axis Towards Ecliptic South pole at 20 rpm Spin-up to 25 rpm Prior to Spin-plane Boom Deploy at Variable Spin Rate 5 - 25 rpm Spin-up to 20 rpm After Last Spin-plane Boom Deploy Step Axial Boom Deploy at 20 rpm THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 31 June 1 -2, 2004

Instruments THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 32 June 1 -2, 2004

IDPU Power Modes • • Launch Configuration: Shut Down Mode FGM Operation: Requires at Least Low Power Mode IDPU Power Modes Mode IDPU & Instrument Status Power Consumption Shut Down Mode IDPU Off All Instruments Off 0. 0 W Safe Mode IDPU On All Instruments Off 7. 8 W Low Power Mode IDPU On FGM On All Other Instruments Off 8. 0 W Engineering Mode IDPU On Instrument States Vary Depending on Activity Science Mode IDPU On All Instruments On THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 33 N/A 11. 8 W June 1 -2, 2004

Instrument Commissioning 1. IDPU Turn-on As Soon As Probe Power System Is Stable and Temperature Within Operating Limits, Verification of Nominal Voltages and Currents, Command Communications and DCB Functionality 2. FGM Turn-on, Power Verification and Uplink of Parameter Load for 32 Hz Bx, By and Bz, Verification of Sensitivity Control on Each Axis, Select Sensitivity 3. EFI Turn-on, Power Verification and Configuration for 32 Hz E & B Sample Rates 4. SCM Turn-on, Power Verification and Activation of Calibration Sequence 5. Magnetometer Boom De-spin to <15 rpm and Deployment With FGM at 32 Hz Real-time Science TLM; Cross-calibration of Magnetometers While Probe Separations Are Still Small 6. SST Turn-on After Initial Outgassing Phase, Power Verification, High-voltage Ramp-up and Attenuator Functional Test 7. ESA Turn-on After Initial Outgassing Phase, Power Verification, Cover Release and High-voltage Ramp-up 8. EFI Spin Plane Boom Deployment − Procedure Controlled by IDPU 9. EFI Axial Boom Deployment − Procedure Controlled by IDPU THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 34 June 1 -2, 2004

EFI Deployment Details EFI Deployment Overview • Initial On-orbit Check-out – EFI SOH Determined Using Stowed DC and AC Functional Test Capability • Booms Deployed After Completion of Initial Orbit Placement – Attitude Maneuvers with Deployed Booms Too Expensive • Deployment Sequence – Spin-plane Boom Deployment – 5 to 6 Intermediate Deploy Lengths with Interleaved Spin-up – Axial Boom Deployment – 1 Step to Deploy Both Axial Booms • Primary Constraints for Deploy and Commissioning – Transmit Time Limited to 30 min – Required Transmitter Cool-down Period of 3. 5 h – Desire to Gather Science Data at Intermediate Deploy Lengths and in Different Plasma Regimes THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 35 June 1 -2, 2004

EFI Deployment Sequence Per Probe • Deploy SPB-X – Deploy Boom Section – Wait for Transmitter to Cool Down – Run Slow Sweep and Take Diagnostic Mode Data • Deploy SPB-Y – Deploy Boom Section – Wait for Transmitter to Cool Down – Run Slow Sweep and Take Diagnostic Mode Data • Spin Up to 20 rpm – Prepare for Next Deploy Cycle Slow Sweep • Large Parameter Space to Be Explored – 4 Braid, 3 Usher, 3 Guard and 32 Bias Settings – 1152 Steps, 1 Step / Spin – Sweep Duration Approximately 1 hour THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 36 June 1 -2, 2004

EFI Deployment Order • P 3 and P 4 Deploy First – 2 -day, 2 -orbit Cycle: – P 3 Deploying and P 4 Pausing – P 4 Deploying and P 3 Pausing – Full deploy and commissioning takes 14 days • P 1 and P 2 Deploy Next – P 2 on 2 -day (1 -orbit) Cycle – Deploy on Outbound, Quiescent on Inbound; 14 Days Total – P 1 on 4 -day (1 -orbit) Cycle – Deploy on Outbound, Quiescent on Inbound; 28 Days Total – P 1 Deploy Cycle May Be Accelerated – Depends on Experience Gained and Data Gathered During P 3 and P 4 Deploy and Commissioning • P 5 Deploys Last – 1 or 2 -day cycle – Full Deploy and Commissioning Takes 7 -14 Days THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 37 June 1 -2, 2004

EFI Science Operations EFI Normal Science Operations • EFI Instrument Mode – Slow Survey, Fast Survey, Particle Burst, Wave Burst and Diagnostic Mode – Set by ~30 Registers on BEB – Configurable Data Rates Via DFB Mode Commands – Typical Mode Specified with ~200 Commands – Valid Over a Typical One-month Period, Once Deploy and Commissioning Completed • Slow Sweeps and Diagnostic Data – Taken Several Times per Year – Upon First Entry into New Plasma Regime – After Long Shadows – Maintain Optimal Bias Settings – Monitor EFI State-of-health THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 38 June 1 -2, 2004

Flight Rules • Preliminary Collection for All Subsystems – – – – Power System Telecommunications Subsystem Reaction Control System Attitude Control System Flight Software Command & Data Handling Instruments • Detailed List Developed During I&T THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 39 June 1 -2, 2004

Power System Flight Rules Activity Flight Rule Potential Impact of Violation Subsystem power-on Subsystems must be powered on only when their temperatures are within the specified limits. Damage to flight hardware. Load shedding Bus voltage must be kept within specified operating limits. Load shedding will occur autonomously on-board when under-voltage condition is detected. Battery state-of-charge too low. THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 40 June 1 -2, 2004

Telecom Flight Rules Activity Flight Rule Potential Impact of Violation Transmitter operation Transmitter on-time limited to 30 min. For nominal science operations planning and analyses, transmitter on-time is limited to 30 min per day. Overheating of transmitter. Transmitter operation Minimum transmitter off-time of 3 hours between Overheating of transmitter on-times. Current thermal analyses show that transmitter needs to be off for 3 hours to cool down completely. Transmitter operation Minimum period of transmitter off-time prior to entry and after exit of long shadows. Exact times are driven by operational activities and overall power management. Battery state-of-charge too low. Transmitter operation Transmitter on-time during shadows limited to less than 30 min. Allowed transmitter-on times for a given shadow period are driven by overall power management. Battery state-of-charge too low. THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 41 June 1 -2, 2004

RCS Flight Rules Activity Flight Rule Potential Impact of Violation Thruster operation Catalyst bed heaters must be turned on 60 min before Damage to catalyst beds. thrusting to heat up, and turned off before thrusting. Thruster firing Thrusters must not be fired unless ESA HV is ramped Damage to ESA and/or SST. down and SST attenuators are closed. Thruster firing Maneuvers must not be performed in shadow. Tangential thruster firing Tangential thruster T 1 (spin-up thruster) must not be fired until SCM boom is deployed. Erroneous maneuver execution. Damage to SCM sensor by thruster plume. Pyro valve operation Pyro valve used to repressurize fuel tanks must not be Bursting of fuel tanks. opened until pressure in fuel tanks has dropped to Destruction of probe. 580 k. Pa. Latch valve operation Latch valves must be configured to allow for equal Gas migration into fuel lines due depletion of fuel tanks in case mass properties are off- to unequal depletion of fuel nominal. tanks. This situation may occur if the spin-plane booms do not deploy symmetrically. Load shedding Both RCS heater services must not be turned off simultaneously. Freezing of fuel and bursting of fuel lines. Thruster monitoring Limits for allowable thruster sum current must be set prior to thruster operation. Erroneous limit violations. THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 42 June 1 -2, 2004

RCS Flight Rules - Continued Activity Flight Rule Potential Impact of Violation FDC management Maximum angular rates measured by IRUs must be set according to planned attitude maneuver. Premature or late maneuver abortion. FDC management Maximum thruster on-time must be configured for expected duration of thruster operation. Premature maneuver termination. Pulsed thruster firing Pulsed operation of thrusters must not be performed at pulse rates at or near natural frequencies of nutation, spin-plane booms, axial booms and propellant slosh. Loss of dynamic stability. THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 43 June 1 -2, 2004

ACS Flight Rules Activity Spin rate control Flight Rule Spin rate must be maintained within 2 - 25 rpm. THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 44 Potential Impact of Violation Loss of dynamic stability. Damage to booms. June 1 -2, 2004

FSW / C&DH Flight Rules Activity Flight Rule Potential Impact of Violation RTS operation FDC algorithms and ATS loads must be set up such Erroneous command execution. that not more than two RTSs operate at the same time. FDC management Turn off Data Monitors when components are turned off. Erroneous limit violations. FDC management Disable Data Monitors that use delta time before setting the clock. Erroneous limit violations. FDC management Reset time before enabling Data Monitors that use delta time. Erroneous limit violations. Clock adjustments must not be performed during critical operations such as maneuvers. Erroneous maneuver execution. THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 45 June 1 -2, 2004

Instrument Flight Rules Activity Flight Rule Potential Impact of Violation IDPU power-on IDPU temperature must be within allowed operational Damage to IDPU electronics. limits prior to powering up. ESA HV power-on ESA HV must not be turned on until initial outgassing Damage to ESA. is completed. ESA HV ramp-down ESA HV must be ramped down prior to thruster operations. SST HV power-on SST HV must not be turned on until initial outgassing Damage to SST. completed. SST attenuator operation SST attenuators must be closed prior to thruster operations. Boom deployment Booms must be deployed only when their temperature Unsuccessful boom deploy. is within allowed range. Damage to boom deployment mechanism. Probe attitude may have to be adjusted to bring temperature into allowed range. Magnetometer boom deployment Magnetometer booms must be deployed at spin rates Damage to magnetometer from 2 to 15 rpm. booms. EFI radial boom deployment EFI radial booms must be deployed at spin rates from Unsuccessful boom deploy. 2 to 25 rpm. Damage to boom deployment mechanism. EFI axial boom deployment EFI axial booms must not be deployed unless spinplane booms are deployed to their nominal distance. THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 46 Contamination of ESA. Damage to SST. Loss of dynamic stability. June 1 -2, 2004

Instrument Flight Rules - Continued Activity EFI axial boom deployment Flight Rule EFI axial booms must be deployed at spin rates from 2 to 25 rpm. THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 47 Potential Impact of Violation Damage to axial booms. June 1 -2, 2004

Normal Science Operations Mission Planning • Pass Schedule and Command Load Generation Probe Command Control • • • Probe Health and Safety Monitoring Recovery of Science and Engineering Data Command Load Uplink Twice Per Week Probe Clock Adjustments Instrument Configuration and Data Trending Orbit and Attitude Determination • Routinely Performed Multiple Times per Week Maneuver Planning and Execution • • Orbits of P 1 and P 2 Adjusted Few Times Per Year to Optimize Conjunctions and Annually to Avoid Shadows Orbit of P 5 Adjusted for First Year Dayside and Second Year Tail and Dayside Seasons THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 48 June 1 -2, 2004

Weekly Operations Schedule Week Operations Schedule for the Constellation Mon Tue Wed Thu Fri Sat Sun 5 Pass Supports 5 Pass Supports FOT On Console FOT On Console Lights-out Operation Generation and Uplink of ATS Loads Pass Scheduling Uplink of Table Loads (If Required) Pass Scheduling Generation and Uplink of ATS Loads Telemetry Recovery Telemetry Recovery Data Trending Data Trending and Limit and Limit Checking Checking Tracking Data Pre-processing Attitude Validation Maneuver Calibration Tracking Data Pre-processing Attitude Validation Orbit Determination Attitude Determination Maneuver Planning Orbit Determination Attitude Determination Ephemeris and Ephemeris and Product Product Generation Generation Delivery of IIRVs and PSATs Delivery of IIRVs and PSATs THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 49 Delivery of IIRVs and PSATs June 1 -2, 2004

Probe Safing Operations • Power System – Automatic Load Shedding • Attitude Control System – Spinning Platform • Reaction Control System Shutdown – Various Fault Detection Mechanisms – Time-out for Thrusting – Rate Monitoring Via IRUs • Instrument Safing – HV Ramped Down and Attenuators Moved into FOV for Thruster Operations THEMIS FDMO CDR Peer Review − L&EO and Normal Operations 50 June 1 -2, 2004