THEMIS Mission Readiness Review

THEMIS Mission Readiness Review
January 5, 2007

Agenda Mission Overview Mission Science/EPO System Engineering Integration & Test Operations Launch Day Launch Vehicle Readiness Safety & Mission Assurance Software IV&V Integrated Independent Review Team Public Affair Plan Readiness Statement Frank Snow - Mission Manager Vassilis Angelopoulos - PI Peter Harvey - Project Manager Garrett Skrobot Mission Integration Manager Ronald Pierson - Explorer SAM Judith Connelly - THEMIS IV&V Mark Goans - IIRT Chair Cynthia O’Carroll - GSFC PAO Frank Snow – Mission Manager January 5, 2007 THEMIS Mission Readiness Review

Mission Overview Frank Snow Mission Manager January 5, 2007 THEMIS Mission Readiness Review

Purpose To show the CMC all elements, both ground and flight, are ready to proceed to launch. CMC concur with the residual risks for the THEMIS project. January 5, 2007 THEMIS Mission Readiness Review

Mechanical/ Thermal Systems
Organization Mission Manager Frank Snow, GSFC Project Scientist D. Sibeck, GSFC Launch Vehicle G. Skrobott, KSC THEMIS PI V. Angelopoulos, UCB EPO N. Craig, UCB Project Manager P. Harvey, UCB Science Co-I’s Financial Mgr K. Harps, UCB Subcontracts J. Keenan, UCB Scheduling D. Meilhan, UCB Quality Assurance R. Jackson, UCB Mechanical/ Thermal Systems P. Turin, UCB C. Smith, UCB Mission Systems E. Taylor, UCB Probe/Probe Carrier Management UCB Oversight: D. King Swales Mgr: M. Cully Instruments P. Berg, UCB Operations M. Bester, UCB Software Systems D. King, UCB Mag Cleanliness C. Russell, UCLA Mission I&T J. McCauley, UCB R. Sterling, UCB January 5, 2007 THEMIS Mission Readiness Review

TIME HISTORY OF EVENTS AND MACROSCALE INTERACTIONS DURING SUBSTORMS (THEMIS) SCIENCE GOALS: Primary: “How do substorms operate?” One of the oldest and most important questions in Geophysics A turning point in our understanding of the dynamic magnetosphere First bonus science: “What accelerates storm-time ‘killer’ electrons?” A significant contribution to space weather science Second bonus science: “What controls efficiency of solar wind – magnetosphere coupling?” Provides global context of Solar Wind – Magnetosphere interaction RESOLVING THE PHYSICS OF ONSET AND EVOLUTION OF SUBSTORMS Principal Investigator Vassilis Angelopoulos, UCB EPO Lead Nahide Craig, UCB Project Manager Peter Harvey, UCB Industrial Partner SWALES Aerospace January 5, 2007 THEMIS Mission Readiness Review

Mission Summary Launch Vehicle: Delta II, Eastern Range Apogee: km ± 9567 km Perigee: 435 km ± 10 km Inclination: 16.0 deg ± 0.5 deg Date: February 15, 2007 Space Segment Spacecraft: 5 Spinning Probes with Fuel for Orbit & Attitude Adjust Instruments: 3-Axis Electric Field, Magnetic Field 3-D Ion & Electron Particle Detectors Spin Rate: 20 RPM Orbit Period(s): 1, 2 and 4 days Orientation: Ecliptic Normal Ground Segment Observatories: 20 Northern with All Sky Imagers and Magnetometers Control Facilities: Mission and Science Operations Centers Operations Phases: L&EO, Cruise, Ascent, Campaigns, De-orbit Lifetime: 2.3 years January 5, 2007 THEMIS Mission Readiness Review

Instrument Configuration
IDPU: Instrument Data Processor Unit SPB : Spin Plane Booms (4x) AXB : Axial Booms (2x) SST : Solid State Telescope (2x) ESA : Electrostatic Analyzer FGM : Fluxgate Magnetometer SCM : Search Coil Magnetometer January 5, 2007 THEMIS Mission Readiness Review

Probe Configuration Fuel Tank ESA EFI SPB Thruster T1 EFI Axial Booms (2, Stowed) Battery BAU Repress Tank Miniature Sun Sensor Transponder Thruster T2 IDPU Antenna Thruster A1 Thruster A2 AEB Gyros January 5, 2007 THEMIS Mission Readiness Review

Ground Based Observatories
UCB has Delivered All 20 GBO (GMAG and ASI) units 19 Have Been Installed, 1 Needs Repair Automatic Data Collection and Archiving in Progress Remote Commanding and Diagnostics Working Expect to be Fully Functional at Winter 2008 Courtesy H.Frey, UCB Geographic Longitude 324° Longitude 195° Geomagnetic North Pole January 5, 2007 THEMIS Mission Readiness Review

Ground Observatory Status
/1: Supply Down /2: Radar RF Noise January 5, 2007 THEMIS Mission Readiness Review

Ground System Diagram Ground System Elements Ground Stations Ground Network Space Network Mission Operations Center Science Operations Center Flight Dynamics Center Including Mission Design Orbit & Attitude Determination Maneuver Planning Limit Detection and Notification Network Security January 5, 2007 THEMIS Mission Readiness Review

Pictures from JPL Environmental Testing
Probe Carrier Assembly during Vibration Probe on GSFC Spin Balance Miller Table Installation of Thermal Vacuum Shrouds Two Probes Ready for TV Testing

Probes in Storage, Ready for Launch Operations Probe Rollover Fixture in JPL Clean room

THEMIS Probe Carrier Assembly (PCA) in Launch Configuration

Secondary TLM/CMD/TRK
Ground Stations Mission Supported by 5 Ground Stations Ground Stations: BGS, WGS, MILA, AGO, HBK GN, SN and FDF Support Documented in PSLA All Stations Have Successfully Flowed Data with MOC Ground Station Station Designator Figure of Merit Location Function Berkeley, CA BGS 11-m 24.0 dB/K 37.879° N ° W Primary TLM/CMD/TRK Wallops Island, VA WGS 11-m 23.0 dB/K 37.925° N 75.476° W Secondary TLM/CMD/TRK Merritt Island, FL MILA 9-m 1/2 21.6 dB/K 28.508° N 80.693° W Santiago, Chile AGO 9-m 33.151° S 70.668° W Hartebeesthoek, SA HBK 10-m 20.4 dB/K 25.883° S 27.708° E

Contacts - TDRSS TDRSS Contact Summary Launch Support
Monitoring of Probe A Separation Maneuver Support Near Perigee for All Probes Apogee Change for Mission Orbit Placement Initiation of Reentry Contingency Support for All Probes Only Few TDRSS Contingency Support Hours Required Probe TDRSS Support Launch Maneuver Contingency 1 1 h 19 h 2 3 2 h 4 5 5 h Subtotal 47 h 10 h Total Support 58 h

Launch Vehicle Overview
Vehicle Configuration: Delta 7925–10C Launch Site: Eastern Range (ER), SLC-17B at Cape Canaveral Air Force Station (CCAFS) Mission Specifics: Perigee: 435 km, Apogee: km Orbit Inclination: 16 degrees Spacecraft (SC) Mass (will not exceed) 829 kg ( lb) kg actual STAR 48B Motor Nutation Control System Yo-Yo de-spin system Spin rates: During Third Stage operation - max  70 rpm S/C after spin-down and separation - 162 rpm Mission Unique 3712 Bolted PAF Sep System (at PAF/PC Interface) Non-Standard Services Category 1 Analysis (1st C ER) Five - 24” Doors Two 61 pin connectors Fairing Cleaning to VC 6 Separation System provided by THEMIS Spacecraft, contracted through Launch Services Program (LSP) NASA Launch Service (NLS) Contract

Mission Parameters Launch Period 15 February 07 – 14 March 07
Daily Launch Opportunities Single flight azimuth/SECO 1 trajectory 93 Deg Single Second Stage restart/Third Stage trajectories Window Duration min Launch period has been divided into two blocks of dates Opening 15 February to 28 February 23:08:00 UTC (Changes by 3:34 per day) 01 March to 14 March 21:57:00 UTC (Changes by 3:34 per day) Liftoff times are rounded to the nearest whole minute Mission Assurance Collision Avoidance (COLA) Measures will be accomplished Free Molecular Heating Rate at Fairing Separation < 0.1 BTU/ft2/sec Sun Angle Constraints: Centerline during coast 90 +/- 9 deg

Flight Profile Note: Values shown are for 15-28 Feb 2007 launch MECO
Liftoff MECO t = sec Alt = 69.0 nmi VI = 20,060 fps Second Stage Ignition t = sec Alt = 72.9 nmi VI = 20,068 fps Fairing Jettison t = sec Alt = 74.1 nmi VI = 20,103 fps SECO 1 t = sec Alt = nmi VI = 25,923 fps ORBIT: 100 x 304 nmi 28.50 deg inclination Second Stage Restart t = sec Alt = nmi VI = 24,662 fps SECO 2 t = sec Alt = nmi VI = 25,778 fps 280 x 825 nmi 26.58 deg inclination TECO t = sec Alt = nmi VI = 33,975 fps Separate Probe A t = sec Alt = nmi VI = 32,368 fps Orbit: 235 x 49,592 nmi 16.00 deg inclination deg arg of per SRM Impact SRM Jettison (6) t = 66.0 / 67.0 sec Alt = 9.9 / 10.2 nmi VI = 3,231 / 3,269 fps SRM Jettison (3) t = sec Alt = 31.3 nmi VI = 8,018 fps Third Stage Ignition t = sec Alt = nmi VI = 25,775 fps Note: Values shown are for Feb 2007 launch Depletion Burn: Removes Stage 2 from vicinity of spacecraft, while lowering Stage 2 perigee altitude and orbit inclination

ASTROTECH and Launch Pad Flow THEMIS Launch Integration Flow 12/08/06 Shipping from JPL to 12/11/06 12/11/06 12/12/06 12/13/06 12/14/06 12/15/06 12/15/06 12/19/06 12/19/06 12/20/06 12/21/06 5 Probes plus EGSE, MGSE at ASO Install Bolt Cutters, Therm. Closeouts F1 RCS MEOP, LPT, S/A Test F2-3 RCS MEOP, LPT, S/A Test F4-5 RCS MEOP, LPT, S/A Test Unpack, Setup EGSE Move Probes to HPF 12/11/06 Probe Carrier Unpack 12/15/06 PC-VCO Electrical Test 12/22/06 12/23/06 01/02/07 01/03/07 01/05/07 01/08/07 01/09/07 01/10/07 01/11/07 01/12/07 01/13/07 Weigh Wet Probes, Attach Pyro Weigh, Move to Stands Christmas Shutdown Probe RCS Electr. Verif. PCA Funct. Spin Balance 12/18/06 Probe Fueling Weigh PCA Install Sep. Harness Pre-Vos 01/03 LVRR (KSC) 01/12 MRR (GSFC) 01/05 Media Day 01/12 12/19/06 Install SMDC Lines 01/15/07 01/22/07 01/23/07 01/24/07 01/25/07 01/26/07 01/27/07 01/29/07 01/30/07 01/3107 02/01/07 02/02/07 PCA Comm Blockhouse Install Pyro Signal SMDC/ Weigh PCA PCA Mate to 3rd Stage/ Clamp-band Instl Engr Walk-down/ Trans- port Preps Reserve PCA Functional Transport to Pad MRR (HQ) 01/23 LSRR (CCAFS) 02/01 02/08/07 02/03/07 02/05/07 02/06/07 02/07/07 02/09/07 02/12/07 02/13/07 02/14/07 2nd Stage Fueling, Ordnance 02/15/07 S/C Functional & RF Test Launch Rehearsal Power On & Stray Voltage Install Fairing Prop. Load Prep Launch Readiness Review Launch FRR (KSC) 02/12 LMCM (KSC) 02/13 21 January 5, 2007 THEMIS Mission Readiness Review

Milestones/Reviews NASA funds THEMIS proposal/concept study March, 2003 Confirmation Review May 2004 Cost Credibility Review June 2005 Mission Readiness Review January 2007 27 IIRT Reviews Peer Reviews, Code 500 schedule reviews, Explorer Program Mission Analysis Reviews (before MOR and FOR), code 500 BAU Review team. Key Reviews Safety/Mission Assurance Review 1/19/07 Mission Readiness Board 1/23/07 Flight Readiness Review 2/12/07 Launch Readiness Review 2/14/07

Integrated Independent Review Team (IIRT) Members
Mark Goans GSFC [Systems Review Office] (Co-chair) Brian Keegan Independent (Co-chair) Bill Taylor Independent - Project Mgt., Systems Frank Martin Independent - Science, Instruments J. B. Joyce Independent - Operations Terry Ford Independent - GN & C Rick Schnurr GSFC - Electrical Systems Alan Posey GSFC - Mechanical Systems Lou Fantano GSFC- Thermal Scott Glubke GSFC - Propulsion Ed Gaddy GSFC - Power Ronnie Killough SWRI - Software

Explorer Program Champion Team
John Deily Assoc. Division Chief, Champion Team Chair Rick Schnurr Chief Electrical Systems Architect Tom McCarthy AETD Chief Engineer Ken Hinkle 540 Division Chief John Leon 556 Branch Head John Donohue 580 Assoc. Division Chief 24

Mission Science/EPO Vassilis Angelopoulos Principal Investigator
 Mission Science Overview and Investigation Strategy  Science Team Preparations and Readiness  Full and Minimum Science Criteria  EPO

TIME HISTORY OF EVENTS AND MACROSCALE INTERACTIONS DURING SUBSTORMS (THEMIS)
SCIENCE GOALS: Primary: “How do substorms operate?” One of the oldest and most important questions in Geophysics A turning point in our understanding of the dynamic magnetosphere First bonus science: “What accelerates storm-time ‘killer’ electrons?” A significant contribution to space weather science Second bonus science: “What controls efficiency of solar wind – magnetosphere coupling?” Provides global context of Solar Wind – Magnetosphere interaction RESOLVING THE PHYSICS OF ONSET AND EVOLUTION OF SUBSTORMS Principal Investigator Vassilis Angelopoulos, UCB EPO Lead Nahide Craig, UCB Project Manager Peter Harvey, UCB Industrial Partner SWALES Aerospace

MAGNETOSPHERE EQUATORIAL PLANE Auroral Eruptions and Substorms
…are a manifestation of magnetospheric substorms SOLAR WIND Aurora MAGNETOSPHERE EQUATORIAL PLANE

Mission Elements Probe conjunctions along Sun-Earth line recur once per 4 days over North America. Ground based observatories completely cover North American sector; can determine auroral breakup within 1-5s … … while THEMIS’s space-based probes determine onset of Current Disruption and Reconnection each within <10s. : Ground Based Observatory

First bonus: What produces storm-time “killer” MeV electrons?
Affect satellites and humans in space ANIK telecommunication satellites lost for days to weeks during space storm Source: Radially inward diffusion? Wave acceleration at radiation belt? THEMIS: Tracks radial motion of electrons Measures source and diffusion Frequent crossings Measures E, B waves locally

Second bonus: What controls efficiency of solar wind – magnetosphere coupling?
Important for solar wind energy transfer in Geospace Need to determine how: Localized pristine solar wind features… …interact with magnetosphere THEMIS: Alignments track evolution of solar wind Inner probes determine entry type/size

THEMIS is firmly aligned with NASA’s Vision for Space Exploration
…To Explore Earth-Sun System and understand effects on Earth and implications for human exploration [Strategic Roadmap #10 of Exploration Initiative] Radiation hazards pose a risk to spacecraft and humans in Earth orbit and en-route to Mars Radiation is caused by solar energetic particles and galactic cosmic rays, and radiation belts Nowhere else can the understanding of the underlying physics of particle acceleration more comprehensive, detailed and complete than at and around Earth’s vicinity. Exploration building blocks: Understand processes of particle acceleration at Earth and in solar wind Understand interactions between solar wind and planetary magnetospheres Understand how harmful particle populations develop and evolve Predict conditions and implications of radiation for human exploration THEMIS is a critical element of the ESS Exploration agenda: Addresses how fundamental particle acceleration processes operate First comprehensive, coordinated measurements of energy sources and sinks Tracks energetic particles from seed to target Probe conjunctions strategically designed to answer this question

Science Objectives THEMIS HAS FOCUSED MINIMUM (TO BASELINE) OBJECTIVES: Time History of Events… Auroral breakup (on the ground) Current Disruption [CD] (2 probes at ~10RE) Reconnection [Rx] (2 probes at ~20-30RE) … and Macroscale Interactions during >5 (>10) Substorms (Primary): Current Disruption and Reconnection coupling Outward motion (1600km/s) of rarefaction wave Inward motion of flows (1000km/s) and Poynting flux. Ionospheric coupling Cross-tail current reduction (P5u/P4) vs flows Field aligned current generation by flow vorticity, pressure gradients (dP/dz, dP/dx). Cross-scale coupling to local modes Field line resonances (10RE, 5 min) Ballooning modes, KH waves (1RE, 1min) Weibel instability, cross-field current instability, kinetic Alfven waves (0.1RE, 60Hz) Production of storm time MeV electrons (Secondary) Control of solar wind-magnetosphere coupling by the bow-shock, magnetosheath and magnetopause (Tertiary)

Probe Conjunction Requirements
BASELINE: >10 substorms per year for 2 tail seasons (188hrs / tail season) MINIMUM: >5 substorms in 1yr w/ 4 probes in 1 tail season (94hrs total). dYP1/2/3/4/5<±2RE; dZP3,4,5/NS<±2RE; dZP1,2/NS<±5RE Actual conjunction times in 1st year Prime Science: Feb 15+/- 1.5 mo: Between Winter Solstice and Equinox A compromise: Shadows vs Conjunctions Launch Delay (Oct 19 ’06 to Feb 15 ‘07) effects: Baseline science yield and quality are still nominal Adds an 8mo. coast phase ahead of 1st tail season Probes assigned positions early, placements after coast phase Avoids differential precession P2,3,4 deploy EFIs vs. P1,5 keep EFIs stowed for placements Compromise: ease of placement vs. early science

Probe Conjunctions Satisfied
Launch day analysis: Feb 15 to May 15, 2007 Conjunctions are robust Nominal deltaV margin for operations at launch: >25% for baseline mission >15% for replacement probe Conjunction Hours Expected: >25% margin above baseline >150% margin by 1st Tail Season Tail 2 Baseline Requirement Baseline Requirement Dayside Tail 1 Baseline Requirement Minimum Requirement

Instruments Required: Redundancy and Overlap
SST ESA EFIa EFIs FGM SCM Tspin=3s Instruments required for Primary Mission Objective (Substorms) Measurement goals P1 P2 P3 P4 P5 Time History of Events P3,4&5 monitor CD P1,2 bracket Rx tres<30s, dY<±2RE FGM 1SSTh 2EFIs ESA 2SSTh Macroscale Interactions Track rarefaction wave, inward flows, Poynting with dB<1nT, dV/V~10% Radial/cross-sheet pressure, velocity and current gradients require dP/P~ dV/V ~ dB/B ~10%, non-MHD Cross-tail pairs measure FLRs, KH, ballooning on B, V, 10s and fast modes on Bxyz and 60 Hz FGM ESA SCM FGM ESA SCM 4EFIs 2EFIa ESA 2EFIs SUMMARY Minimum mission (Red) Baseline add-ons (green) SCM 2EFIs 1 FGM: Low freq. B-field (0-64Hz) 1 ESA: Thermal plasma 2 SSTh (heads): Super-thermal plasma 1 SCM: High freq. B-field (1Hz-4kHz) 4 EFIs (spin plane) & 2 EFIa (axials): Low&High freq. E-field

Baseline L1 Requirements
S-1 Substorm Onset Time Determine substorm onset time and substorm meridian magnetic local time (MLT) using ground ASIs (one per MLT hr) and MAGs (two per MLT hr) with t_res<30s and dMLT<1 degree respectively, in an 8hr geographic local time sector including the US. (M-11, GB-1) S-2 Current Disruption (CD) Onset Time Determine CD onset time with t_res<30s, using two near-equatorial (within 2Re of magnetic equator) probes, near the anticipated current disruption site (~8-10 Re). CD onset is determined by remote sensing the expansion of the heated plasma via superthermal ion flux measurements at probes within +/-2Re of the measured substorm meridian and the anticipated altitude of the CD. (M-9, IN.SST-1, IN.SST-4, IN.FGM-1) S-3 Reconnection (Rx) Onset Time Determine Rx onset time with t_res<30s, using two near-equatorial (< 5Re from magnetic equator) probes, bracketing the anticipated Rx site (20-25Re). Rx onset is determined by measuring the time of arrival of superthermal ions and electrons from the Rx site, within dY=+/-2Re of the substorm meridian and within <10Re from the Rx altitude. ….. (M-9, IN.EFI-2, IN.ESA-1, IN.SST-2, IN.SST-3, IN.SST-4, IN.FGM-1) S-4 Simultaneous Observations Obtain simultaneous observations of: substorm onset and meridian (ground), CD onset and Rx onset for >10 substorms in the prime observation season (September-April). Given an average 3.75hr substorm recurrence in the target tail season, a 2Re width of the substorm meridian, a 1Re requirement on probe proximity to the substorm meridian (of width 2Re) and a 20Re width of the tail in which substorms can occur, this translates to a yield of 1 useful substorm event per 18.75hrs of probe alignments, i.e, a requirement of >188hrs of four-probe alignments within dY=+/-2Re. (M-1, M-12, IN.FGM-1)

… continued: Baseline L1 Requirements
S-5 Earthward Flows Track between probes the earthward ion flows from the Rx site and the tailward moving rarefaction wave in the magnetic field, and ion plasma pressure with sufficient precision to ascertain macroscale coupling between current disruption and reconnection site during >10 substorm onsets (>188hrs of four-probes aligned within dY of +-2Re). (IN.ESA-1, IN.SST-3, IN.FGM-1) S-6 Pressure Gradients Determine the radial and cross-current-sheet pressure gradients and ion flow vorticity/deceleration with probe measurement accuracy of 50km/s/Re, over typical inter-probe conjunctions in dR and dZ of 1Re, each during >10 onsets. (IN.EFI-1, IN.ESA-1, IN.ESA-2, IN.SST-3, IN.FGM-1) S-7 Cross-Current Sheet changes Determine the cross-current-sheet current change near the current disruption region (+/-2Re of meridian, +-2Re of measured current disruption region) at substorm onset from a pair of Z-separated probes using the planar current sheet approximation with relative (interprobe) resolution and inter-orbit (~12hrs) stability of 0.2nT. (IN.FGM-1, PB-42, PB-43, PB-44) S-8 non-MHD plasma Obtain measurements of the Magneto-Hydrodynamic (MHD) and non-MHD parts of the plasma flow through comparisons of ion flow from the ESA detector and ExB flow from the electric field instrument, at the probes near the current disruption region, with t_res<10s. (IN.EFI-1, IN.ESA-1, IN.SST-3, IN.FGM-1)

… continued: Baseline L1 Requirements
S-9 Cross-Tail Pairs Determine the presence, amplitude, and wavelength of field-line resonances, Kelvin-Helmholz waves and ballooning waves on cross-tail pairs (dY=0.5-10Re) with t_res<10s measurements of B, P and V for >10 substorm onsets. (IN.ESA-1, IN.SST-3) S-10 Cross-Field Current Instabilities Determine the presence of cross-field current instabilities (1-60Hz), whistlers and other high frequency modes (up to 600Hz) in 3D electric and magnetic field data on two individual probes near the current disruption region for >10 substorm events. (IN.EFI-3, IN.ESA-3, IN.SCM-1) S-11 Dayside Science Determine the source and acceleration mechanism of storm-time MeV electrons at the radiation belts by measuring the radial evolution of the electron phase space density over time-scales of 2-6 hrs. (IN.ESA-4, IN.SST-6) S-12 Dayside Science Determine the nature, extent and cause of magnetopause transient events via comparing simultaneous measurements of the dynamic pressure in the pristine solar wind and the foreshock with magnetic field perturbations near the magnetopause. (IN.ESA-4, IN.SST-6)

Minimum L1 Requirements (from L1’s)
Substorm Onset Time Determine substorm onset time and substorm meridian magnetic local time (MLT) using ground MAGs (at least one per MLT hr) with t_res<30s and dMLT<6 degrees respectively, in a 6hr geographic local time sector including the US. Current Disruption (CD) Onset Time Determine CD onset time with t_res<30s, using two near-equatorial (within 2Re of magnetic equator) probes, near the anticipated CD site (~8-10 Re). …(same as baseline) Reconnection (Rx) Onset Time Determine Rx onset time with t_res<30s, using two near-equatorial (<5Re of magnetic equator) probes, bracketing the anticipated Rx site (20-25Re). … (same as baseline) Simultaneous Observations Obtain simultaneous observations of: substorm onset and meridian (ground), CD onset and reconnection onset for >5 substorms in the prime observation season (September-April). Substorm statistics discussed in S-4 point to a requirement of >94hrs of four probe alignments. Earthward Flows Track between probes the earthward ion flows from the reconnection site and the tailward moving rarefaction wave in the magnetic field, and ion plasma pressure with sufficient precision precision to ascertain macroscale coupling between current disruption and reconnection site during >5 substorm onsets.

Science Team Composition
Added Strength w/ 5 new coIs: J. Bonnell (EFI) D. Larson (SST) J. P. McFadden (ESA) I. Mann (UoA GBO, RadBelt) I. Daglis (Athens, Ring Current) Established Partnerships with: Taiwan [Affiliate F. Cheng] Cluster [Affiliate S. Schwarz] SPDF [Affiliate R. McGuire] CCMC [Affiliate M. Hesse] Enlisted young bright stars: Chaston, Eastwood, Hull, Keiling (UCB), Strangeway, Schwarzl, Weygand (UCLA) Team is ready, awaiting launch!

Science Team Meetings and Products
Yearly post-AGU meetings at UCB since 2003 “Data analysis tools” meeting at UCB, Nov Exposed team to (and obtain feedback on) data analysis tools before they are finalized coast phase intra-calibration and unique science Weekly Science and Science Ops Center Development meetings Weekly International Instruments telecons (FGM, SCM, ASIs) Cape Canaveral Feb meeting announced (Team+Community) Call for Space Science Reviews instrument papers to be submitted Expect comprehensive volume by next summer, out well before for Tail 1: Analysis tools and methods First instrument results Web page development: Contracted analysis tools and data dissemination web-site Brainstorming team and Contractor interfaces established Skeleton and content material in place in beta site User interviews on-going to establish best look and feel.

Science Data Products Status
Level 0 Data : Raw files (*.pkt) one per APID (application identifier, straight from telemetry). Level 1 Data : Processed but uncalibrated data in CDF (Common Data Format) files (*.cdf) Software and calibration files will be distributed with the data. Level 2 Data: Calibrated data in CDF files – contain physical quantities.

Science Team Data Analysis Tools Status (1)
Analysis tools available now (IDL-based) at: Platform independent, works on Solaris, Linux, Win, MacOSx Auto file retrieval Easy to install and download files GUI available for IDL starters Contributions by any scientist Maintenance with SubVersioN Documentation includes: Users Guide Developers Guide Subversion Latest list of routines

Anyone can plot L1 data from THEMIS today: Data from I&T period, is auto-processed whenever software is updated Working on mirror sites Additional plots at SPDF: via CDAWweb

Orbit Visualization, conjunction searches and footpoints: Thanks to excellent support from SPDF! Orbit visualization via “tipsod”: a Java – based software

Web-based L2 overview plot distribution (4)
summary_plots/plot_display.php

Science Readiness Summary
Science Team In Place, Eagerly Awaiting Launch L0, L1 Automated Science Data Processing In Place L1 Data Analysis Tools Available for Team and Public L2 Data Production Routines Based on Past Missions, under construction (Expected before launch) Web-based Plots, Data and Tools Dissemination in Place Using I&T data for testing System in Place for Software Contributions L2 Data Readily Accessible by SPDF and Cluster ISTP compatible Self-documented and readable by QSAS

THEMIS EPO Program Carson City NV UCB
Started yearly teacher workshop site in Carson City, NV in collaboration with LHS Workshops held in June ’05 and June ‘06 Installed 13 magnetometers and involved teachers to test lesson plans Developed, tested & revised Magnetism on Earth teacher’s guide, used now in classrooms Real-time data on the web Archived data available on the web UCB Bay Mills College

Magnetometer Data at Schools
Overview Magnetometers in 13 schools in 10 states 14+ teachers involved Teachers leaving mirror lessons at next place Teacher turnaroud has multiplication effect Data on the web Mostly high school classes Students excited by wiggles and spectrograms Student research AGU presentations by students

Education Activities Examples
Background science lessons Exploring Magnetism and Magnetism on Earth teacher guides Space Science Weekly Problem Using data in the classroom Correlations of magnetism data with other space weather data Soda bottle Magnetometer comparison to research-grade school magnetometer Working with Teachers Maryland Science Center “Teacher’s Thursdays” featured: “Exploring Magnetis Storms and Space Weather with THEMIS” exposing Educator Groups to THEMIS Audience: ~30 present, 15 videoconferencing GEONS Workshops Local Schools when invited Leveraging Other activities THEMIS/GLOBE Workshops, Bay Mills, MI Mission Observatory, AK Michigan Science Teacher Association Workshops Connections with STEREO and RHESSI Connections with FAST

Public Outreach Examples
SAWANO NEWS (WI), Feb-2006

Systems Engineering Peter Harvey Project Manager

Systems Agenda Design Requirements Verification
Mission Description Instrument and Probe Configuration Launch and Mission Description Requirements Verification Summary, Waived and Pending Requirements New Mission Profile Review Resources Operating Hours Problem Failure Reports Statistics and Status Unverifiable Failures Operational WorkArounds

Mission Summary Launch Space Segment Ground Segment Operations
Vehicle: Delta II, Eastern Range Apogee: km ± 9567 km Perigee: 435 km ± 10 km (500 km ± 7 km on or after 3/1/2007) Inclination: 16.0 deg ± 0.5 deg Date: February 15, 2007 Space Segment Spacecraft: 5 Spinning Probes with Fuel for Orbit & Attitude Adjust Instruments: 3-Axis Electric Field, Magnetic Field 3-D Ion & Electron Particle Detectors Spin Rate: 20 RPM Orbit Period(s): 1, 2 and 4 days Orientation: Ecliptic Normal Ground Segment Observatories: 20 Northern with All Sky Imagers and Magnetometers Control Facilities: Mission and Science Operations Centers Operations Phases: L&EO, Cruise, Ascent, Campaigns, De-orbit Lifetime: 2.3 years

Instrument Configuration
IDPU: Instrument Data Processor Unit SPB : Spin Plane Booms (4x) AXB : Axial Booms (2x) SST : Solid State Telescope (2x) ESA : Electrostatic Analyzer FGM : Fluxgate Magnetometer SCM : Search Coil Magnetometer

Probe Configuration Antenna EFI Axial Booms (2, Stowed) ESA
Miniature Sun Sensor Fuel Tank IDPU EFI SPB Repress Tank Fuel Tank Transponder Thruster A2 Thruster T1 EFI SPB Thruster A1 BAU Battery Gyros EFI SPB Thruster T2 AEB

Launch Configuration Dedicated launch accommodated within standard Delta vehicle configuration and services 10’ Composite Fairing required to accommodate five Probes on the Probe Carrier in the “Wedding Cake” configuration PC stays attached to Delta 3rd stage after probe dispense Each probe dispense from the PCA is coordinated with but independent of the other probes No single probe anomaly precludes dispense of remaining probes Standard Delta 10 ft. Fairing Static Envelope Probe Carrier Assembly (PCA = 5 Probes + Probe Carrier) on L/V 3712 PAF Star 48 3rd Stage Probe Carrier Assembly (PCA) on Delta 3rd Stage THEMIS Launch Configuration

Mission Profile

Requirements Status Mission Requirements Documentation (MRD)
THM_SYS_001K_MRD.xls Mission Requirements Verification 476 Requirements total 467 Requirements verified 5 Requirements pending 4 Requirements waived

Requirements Waived Implementation Change
IN.ESA-08: ESA Dayside Energy Flux Attenuator Waived: Electronic Counting Was Fast Enough IN.DPU-09: Stored Housekeeping Telemetry Storage Waived: BAU saves all IDPU Engineering Data As Measured IN.EFI-11: EFI Noise Level < 1 x 10^-4 mV/m/sqrt(Hz). Waived: EFI measured noise level is 2 to 3 x 10^-4 mVm/sqrt(Hz). PC.Mech-1: Probe-to-Probe Static Clearance of 4 inches Waived: Current static clearance is 3.75 inches.

Requirements Pending Launch Site Verification
M-33 Electrostatic Cleanliness requirement verification pending ESC survey after all flight close-outs (Jan 9) M-45, M-47, PC-8 PCA Mass Properties (Mass, CG, and Principle Misalignment) requirement verification pending PCA Spin Balance Test and final weighing of PCA with fueled Probes. (Jan 12 and 13) Post-Launch Verification IN.ESA-13 ESA On-Orbit Calibration requires raw data to be collected prior to final coefficients to be delivered to the Science Operations Center. (March 2007)

New Mission Profile Mission Profile Review for Feb 15, 2007 Launch
EFI Boom Deploy delayed ~ 9 months on Probes 1 & 5 THEMIS Deployment Motors Life Test (21 50 C) CLUSTER lifetime tests also relevant and showed no issues RCS Re-pressurization delayed about 6 months No Issues with RCS Components Cassini waited several years to do the recharge. Ascent Maneuvers Delayed appx 6 months Increased IRU radiation qualification to 63 Krad (RDM of 2) Power considerations Improved launch orientation, side solar arrays in sun. No change in number or duration of eclipses Thermal environment No change

Resources Mass Status Power Status
< 2% mass deviation between Probes (requirement) Dry Mass Margin: 4.5% (Worst case) Power Status Probe CBE: 38.7 W Probe Capability: W Probe Margin: 8.8% (First 3-hour Eclipse Season) 4.9% (Second 3- hour Eclipse Season)

Operating Hours Integrated Probe Hours:
Components : Averaged 780 hours run time prior to integration. Failure Free Hours: Hours accumulated on core system after return of transponder and BAU during mission integration. Late Instrument Swaps (>100 hours gained on integrated system after all swaps): Spare SST on F1 swapped in prior to TVac in August Spare SCM on F1 swapped in early October EFI re-work on F1-F5 completed in November Thermal Vacuum Hours: failure free hours were accumulated on all components during Probe Level TVac. Components accumulated and average of 250 hours during Component Level TVac.

Problem/Failure Reports
PFR Statistics (All Spacecraft) Total : 237 Closed : 237 Open : 0 Unverifiable Failures : 13 Operational Work-Arounds : 10

Unverifiable Failures

Operational WorkArounds

Integration and Test Peter Harvey Project Manager

Integration Agenda Recent Activities Probe and Instrument Status
Environmental Tests Completed Delivery to Astrotech Probe Processing Fueling Preparations Carrier Processing Probe and Instrument Status Instrument Status and Remaining Items Probe Status and Remaining Items Integration Plan Review Process RFAs in Work Reviews Ahead

Environments Magnetics Vibration Acoustics EMC Thermal Vacuum
Spin Balance

Solar Array Illumination
Probe Processing Delivery to ASO Bolt Cutter Installation Performance Tests Solar Array Illumination

Probe Fueling Preps FM2/FM3 Thermal Vacuum Vibration Acoustics
Spin Balance Dry Weigh & Pressurize Ready for Fuel Thermal Vacuum FM2/FM3 Thermal Vacuum Storage

Carrier Processing PC Unload Vibration Acoustics Spin Balance
Ready for Probes Storage SSS Installation

Instrument Status Instrument Status Remaining Items
Flight Hardware Ready Flight Software Ready Recent Activities Performance Test Remaining Items ESC Verification SST/ESA Covers EFI Hats Contamination Samples

Probe Status Probe Status Hardware Complete Software Complete
Recent Activities at ASO Performance Tests Solar Array Illumination RCS Pressurization to 1.1*MEOP Dry Weigh Remaining Items Fueling Flight Plugs Integrate to PC Attach Sep System

ASTROTECH and Launch Pad Flow THEMIS Launch Integration Flow 12/08/06 Shipping from JPL to 12/11/06 12/11/06 12/12/06 12/13/06 12/14/06 12/15/06 12/15/06 12/19/06 12/19/06 12/20/06 12/21/06 5 Probes plus EGSE, MGSE at ASO Install Bolt Cutters, Therm. Closeouts F1 RCS MEOP, LPT, S/A Test F2-3 RCS MEOP, LPT, S/A Test F4-5 RCS MEOP, LPT, S/A Test Unpack, Setup EGSE Move Probes to HPF 12/11/06 Probe Carrier Unpack 12/15/06 PC-VCO Electrical Test 12/22/06 12/23/06 01/02/07 01/03/07 01/05/07 01/08/07 01/09/07 01/10/07 01/11/07 01/12/07 01/13/07 Weigh Wet Probes, Attach Pyro Weigh, Move to Stands Christmas Shutdown Probe RCS Electr. Verif. PCA Funct. Spin Balance 12/18/06 Probe Fueling Weigh PCA Install Sep. Harness Pre-Vos 01/03 LVRR (KSC) 01/12 MRR (GSFC) 01/05 Media Day 01/12 12/19/06 Install SMDC Lines 01/15/07 01/22/07 01/23/07 01/24/07 01/25/07 01/26/07 01/27/07 01/29/07 01/30/07 01/3107 02/01/07 02/02/07 PCA Comm Blockhouse Install Pyro Signal SMDC/ Weigh PCA PCA Mate to 3rd Stage/ Clamp-band Instl Engr Walk-down/ Trans- port Preps Reserve PCA Functional Transport to Pad MRR (HQ) 01/23 LSRR (CCAFS) 02/01 02/08/07 02/03/07 02/05/07 02/06/07 02/07/07 02/09/07 02/12/07 02/13/07 02/14/07 2nd Stage Fueling, Ordnance 02/15/07 S/C Functional & RF Test Launch Rehearsal Power On & Stray Voltage Install Fairing Prop. Load Prep Launch Readiness Review Launch FRR (KSC) 02/12 LMCM (KSC) 02/13 January 5, 2007 THEMIS Mission Readiness Review 76

RFAs RFA Status Final Four Closure Method Incomplete: 0 Complete: 308
Closed: 304 Total: 308 Final Four Closure Method RCS Proof Issue: Expected to Close with Risk Definition BAU EEPROM Plots Provided were Insufficient to the reviewer but it is no longer practical to obtain better plots. Energy Balance was Provided using Best Thermal Model at the time. Reviewer repeated request using new mission profile and correlated thermal model. This was delivered in December. Launch Window Analysis will be reviewed by GSFC by 1/15/07

Reviews Ahead

Operations Peter Harvey Project Manager

Operations Agenda Ground Systems Development Launch and Early Orbit
Ground System Diagram Mission Operations Center Ground Stations RF Licencing Security Software Procedures Verification and Training GSFC Support Launch and Early Orbit Contacts Ground Based Observations

Ground System Diagram Ground System Elements Including Ground Stations
Ground Network Space Network Mission Operations Center Science Operations Center Flight Dynamics Center Including Mission Design Orbit & Attitude Determination Maneuver Planning Limit Detection and Notification Network Security

Mission Operations Center
BGS Antenna, Equipment Racks and FOT Workstations at the Mission Operations Center

MOC Expansion

Secondary TLM/CMD/TRK
Ground Stations Mission Supported by 5 Ground Stations Ground Stations: BGS, WGS, MILA, AGO, HBK GN, SN and FDF Support Documented in PSLA All Stations Have Successfully Flowed Data with MOC Ground Station Station Designator Figure of Merit Location Function Berkeley, CA BGS 11-m 24.0 dB/K 37.879° N ° W Primary TLM/CMD/TRK Wallops Island, VA WGS 11-m 23.0 dB/K 37.925° N 75.476° W Secondary TLM/CMD/TRK Merritt Island, FL MILA 9-m 1/2 21.6 dB/K 28.508° N 80.693° W Santiago, Chile AGO 9-m 33.151° S 70.668° W Hartebeesthoek, SA HBK 10-m 20.4 dB/K 25.883° S 27.708° E

NTIA License NTIA License Status
Identical Frequency Pairs for All Probes Assigned by GSFC Spectrum Management Office Telemetry: MHz Command: 221 / 240 × = MHz DoD Approved Frequency Assignment Stage 4 License Approved Stage 2 Application Was Submitted to NTIA in June 2004 Reviewed by Space Frequency Coordination Group (SFCG) at Meeting in November 2004 Stage 2 License Was Approved in December 2004 Stage 4 License Was Approved in February 2006

IT Security Security Measures Physical Security Network Security
Facilities Locked and Protected by Alarm System Access Controlled by University of California Police Department Network Security Tight Access Rules on Firewalls Regular Password Changes Document Access Critical Documents and Databases Kept Confidential Personnel Screening and Background Checks Complete Establishment and Enforcement of Rules of Behavior

Software Status Tool Developer Function Platform Comments / Status MDT
UCB IDL Based THEMIS Mission Design Tool, Calls GTDS and GMAN for Orbit Propagation and Finite Maneuver Targeting Solaris Operational in MOC GTDS GSFC Orbit Propagation, Orbit Determination, Ephemeris Generation Version Operational in FDC GMAN Finite Maneuver Targeting and Reconstruction Version PC Operational in FDC SatTrack BTS Pass Scheduling, Product Generation, Networking, 3-D Visualization, Ground Station Control Solaris, Linux Version Operational in MOC, FDC and BGS MSASS Attitude Determination Solaris, Windows XP Version To Be Installed in MOC and FDC by L - 2 Months CALIBATT Attitude Maneuver Calibration Version Operational in FDC

Software Status MOC Software Complete
Tool Developer Function Platform Comments / Status ITOS Hammers Probe Command and Control, Telemetry Monitoring, Limit Checking Solaris, Linux Version 703p1-6 Operational in MOC, FlatSat and EGSE VirtualSat Dynamics Probe Simulation Windows XP Supplied with FlatSat West – Operational in FlatSat BMPS UCB ATS Load Generation Solaris Operational in MOC SERS MF Spacecraft Emergency Response System Windows NT Operational at MOC BTAPS Probe Bus and Instrument Trend Analysis MOC Software Complete Currently Under Pre-Launch Software Freeze

Procedures Procedure & Display Status
All 19 Flight Ops Procedures Ready All 9 Contingency Ops Procedures Ready All 178 Computer Procs Ready All Computer Displays Ready

Verification & Training
Verification and Training Program Operations Identified 238 Verification and Training Exercises Currently 90% Are Complete. Expecting 97% by Jan 15th All Launch Critical Exercises Completed This Week Fuel Record Keeping Closed Loop Maneuver Sims Launch Simulation in PCA Configuration Successful at JPL Launch Simulation is Planned Two More Times (ASO & PAD) Continuing Pass Simulations with Combined UCB/Swales Team Mission Dress Rehearsal at L-2 with MOC and GSFC/FDF

GSFC Support GSFC Support FDAB Support FDF Support SCP Support
MSASS Upgrade Including Kalman Filter and Usage Support GTDS Software Upgrade and Usage Support GMAN Support and Validation of Maneuver Scenarios CALIBATT Support for Attitude Maneuver Calibration FDF Support Assignment of BGS Transmit and Receiver Tracker IDs Verification of BGS Two-way Doppler Tracking Pre-launch Data Flows Orbit Determination Pre-Launch SImulations Orbit Determination Post-Launch Support SCP Support Network Operations Support Ground Network Support Space Network Support (TDRSS)

LEO Operations LEO Operations
State Vector Delivered to UCB via SECO-2 (65min) Monitoring of Probe Separation via TDRSS Top Probe Will Be Commanded to Transmit at T+70 mins Separation will occur at T+73 minutes All Probes Will Be Recording Engineering Data Separation Recorded by Each Probe Individually Engineering Data Dumped in Later Passes Probes Are Released at Good Sun Angle, Power Positive 43 degrees Side to Sun Probe A Released First Probes B−E Released Simultaneously 3 s Later All Probes Independent of Each Other

LEO Acquistion LEO Acquisition
Multiple Ground Assets Have Good View Following Launch Probe Attitude Around 1:30 MET is Poor for Telemetry Probes Contacted at 4Kbps for 5 Minutes each from 1:20 to 1:40

LEO Early Orbit Early Orbit Activities First Real Round-robin Contacts
Starting about T+2hr, Each Probe Will Be Contacted for 10 Mins Rest Period between Probe Contacts of 5 Mins Expected Battery SOC to Remain > 87% Initial Orbit and Attitude Determination Record and Process Two-way Doppler Data Perform Attitude Determination in Real-time Both UCB and GSFC FDF Function in Parallel Round-Robin Checkout of Key Systems on Each Probe Reaction Control System Readiness Attitude Sensors Functionality Perform Attitude Maneuver to Ecliptic Normal If Power Negative, Will Maneuver on First Orbit. Improves Power and Communications Coverage Systematic Instrument Power-up and Check-out Leads to Decision of Probe Orbit Placement in Appx 26 Days

LEO Orbit Placement Orbit Placement Decision
Decision Based on Probe Bus and Instrument Checkout Probe Bus RCS, ACS and Power System Unable to Check Probe Thermal System Entirely Instrument Check-out of FGM, SCM, SST and ESA Unable to Check EFI with AXB & SPB Booms Stowed PI Team Members Involved in Probe Placement Decision PI, PM, MSE, MOM, Swales Probe Bus Systems Lead, Instrument Scientists, GSFC Program Manager and GSFC Project Scientist Assignment of Constellation IDs According to Probe Placement Decision

LEO Probe Identification
Provides Unique Relationship between Various Probe Identifiers Extensively Tested during Mission Integration Probe Bus / Simulator Name Probe Bus ID Instrument Suite ID CCSDS V1 Command SCID Telemetry SCID NASA Support Identification Code Satellite Catalog Number * International Designator * Constellation Identifier ** THEMIS FlatSat West N/A 0x150 THEMIS A F1 FM1 0x153 0451 99001 A P1 THEMIS B F2 FM2 0x151 0452 99002 B P2 THEMIS C F3 FM3 0x155 0453 99003 C P3 THEMIS D F4 FM4 0x154 0454 99004 D P4 THEMIS E F5 FM5 0x152 0455 99005 E P5 THEMIS Spare 0x156 FlatSat East 0x157 * Assigned after Launch ** Assigned after Probe Placement Decision

Contacts - Typical Entire Ground Station View Periods at Nominal Low Data Rate of kbps

Contacts - Total Ground Station Contact Summary
Number of Passes Based on Detailed 2-Year Mission Design BGS 11-m (Primary) WGS 11-m, MILA 9-m, AGO 9-m and HBK 10-m (Secondary) Passes Included to Support Routine and Special Operations Daily BGS Contacts with All Probes for State-of-health Monitoring Maneuver Support, Instrument Commissioning, Doppler Tracking Probe BGS WGS AGO HBK L&EO Science 1 150 750 60 50 30 20 2 90 3 4 5 40 Subtotal 3750 300 330 140 100 130 Total Contacts 4500 630 290 230

Contacts - TDRSS TDRSS Contact Summary Launch Support
Monitoring of Probe A Separation Maneuver Support Near Perigee for All Probes Apogee Change for Mission Orbit Placement Initiation of Reentry Contingency Support for All Probes Only Few TDRSS Contingency Support Hours Required Probe TDRSS Support Launch Maneuver Contingency 1 1 h 19 h 2 3 2 h 4 5 5 h Subtotal 47 h 10 h Total Support 58 h

Ground Based Observatories
UCB has Delivered All 20 GBO (GMAG and ASI) units 19 Have Been Installed, 1 Needs Repair Automatic Data Collection and Archiving in Progress Remote Commanding and Diagnostics Working Expect to be Fully Functional at Winter 2008 Courtesy H.Frey, UCB Geographic Longitude 324° Longitude 195° Geomagnetic North Pole

Ground Observatory Status
/1: Supply Down /2: Radar RF Noise

Launch Day Frank Snow Mission Manager

THEMIS Launch Day Management Flow
GSFC Network Operations Manager Arnie Rausch NASA Eng Team NASA Chief Engineer James Wood NASA Advisory Team NASA Advisory Manager Joe Lackovich NASA Launch Manager Chuck Dovale Boeing Mission Director Rich Murphy NASA ENGINEERING Go / No-Go ADVISORY NASA MDC LVDC Safety & Mission Assurance Rick Boutin NASA SMA NASA ALM NASA MIT Mission Integration Manager Garrett Skrobot MISSION INTEGRATION Spacecraft Mission Director Frank Snow INFO SMD THEMIS Project Manager Peter Harvey Ground Donald Gates NASA SMA Team GSFC Safety & Mission Assurance Manager Ron Perison Spacecraft Test Conductor Dave Curtis GSFC Spacecraft I&T Manager Rick Sterling ASO Manfred Bester MOC

THEMIS Launch Decision Flow UCB Mission Operations Center (MOC)
THEMIS Launch Decision Flow UCB Mission Operations Center (MOC) NASA Mission Integration Mngr (KSC) Mission Director Center (MDC) GSFC Safety & Mission Assurance Mngr (GSFC) LVDC NASA Safety & Mission Assurance Mngr (KSC) Go/No-Go Go/No-Go Go/No-Go Status NASA Advisory Manager (KSC) Spacecraft Mission Director (GSFC) Go/No-Go NASA Chief Engineer (KSC) NASA Launch Manager (KSC) Advisory Go/No-Go Mission Operations Manager (UCB) Go/No-Go Go/No-Go Go/No-Go AF Site Go/No-Go Director Go/No-Go THEMIS Project Manager (UCB) MDC Ops Director (KSC) Go/No-Go (1 SLS) NASA Engineering Team (KSC) Go/No-Go CMDRS NET GSFC Mission Director (Boeing) Launch Concur Ground Operations Manager (GSFC) Operations Integrator (Boeing) Dir. of Eng. GSFC Network Operations Manager (GSFC) (Boeing) Status Go/No-Go Range Operations Control Center Launch Decision Go/No-Go Status L/V Sys Status Operations Building (OB) Launch Director (Boeing) Launch Vehicle Astrotech (ASO) USAF 45 SW/CC Space Lift Commander (SLCC) Systems Engineering (Boeing) Spacecraft I&T Manager (UCB) Vehicle Status Status WINDS Go/No-Go (Boeing) Missile Chief Engineer (Boeing) Launch Status Range Coordinator (Boeing) Status Conductor Range Control Officer LVDC-3 (Boeing) Go/No-Go Spacecraft Test Conductor (UCB) NASA AF Launch Crew Commander (1 SLS) • Range Safety Status Spacecraft Status Status • Range Status Coordinator Status • Weather (KSC) • Support Range Status (LV)

THEMIS Anomaly Resolution
NLM NASA Launch Manager Chuck Dovale MD Mission Director Rich Murphy Mission Management Net NASA Launch Manager's Net LD Launch Director Mark Dowhan CLCDR Launch Conductor Bob Godin Launch Vehicle / Integrated Anomaly Anomaly Net Or Boeing Mgmt Net Anomaly Team Spacecraft Only Anomaly NASA CE NASA Chief Engineer James Wood MCE Missile Chief Engineer Steve Huff NASA Engineering Team Boeing SLC-17 Team Anomaly Net Or Boeing Mgmt Net Resource Protection ARC USAF Anomaly Resolution Chief Bryan Buckley DE Director of Engineering Dave Crosse USAF CX-17 Engineering Team VSE Vehicle Systems Engineer Greg Radle SMD Spacecraft Mission Director Frank Snow Integrated Anomaly Only MSE Mission Systems Engineer Stu Harris Boeing HB Engineering Team S/C Eng / Ops Team

THEMIS Mission Director’s Center
NASA/KSC BERT GARRIDO SMA MISSION MGNT REP MMR NASA/HQ WILLIS JENKINS PROGRAM EXECUTIVE HQPX AEROSPACE RANDY MOYER AIR FORCE ADVISOR AFA 25 13 1 6-4525 6-4513 6-4501 NASA/KSC RICK BOUTIN SAFETY & MSN ASSUR 6-4526 NASA/GSFC RICK OBENSCHEIN FLT PROGRAMS DIR 6-4514 1ST SLS MAJ PAUL CAZIER DEPUTY AF SITE DIR 6-4502 26 SMA 14 FPD 2 DAFSD NASA/GSFC RON PERISON GSFC SAFETY & MISSION ASSURANCE GSMA UCB VASSILIS ANGELOPOULOS PRINCIPAL INVESTIGATOR PI 1ST SLS LT COL MYRON FORTSON AIR FORCE SITE DIR AFSD 27 15 O NET 3 6-4527 6-4515 6-4503 NASA/GSFC ED WEILER GSFC CENTER DIRECTOR 6-4528 UCB PETER HARVEY THEMIS PROJ MNGR 6-4516 BOEING KRIS WALSH ASST MISSION DIRECTOR 6-4504 28 GCD 16 O NET B NET TPM 4 AMD ANALEX/KSC TRACY EVANS ASST MISSION OPS DIR AMOD NASA/GSFC DONNIE GATES GROUND OPS MNGR 6-2241 GOM BOEING RICH MURPHY MISSION DIRECTOR MD 29 17 O NET 5 B NET 6-4529 6-4517 6-4505 NASA/KSC TUAN DOAN MISSION OPS DIRECTOR 6-4530 NASA/GSFC FRANK SNOW S/C MISSION DIR 6-4518 BOEING DAVE CROSSE DIRECTOR OF ENGR 6-4506 30 MOD 18 O NET 6-2241 SMD 6 B NET DE NASA/KSC JOE LACKOVICH NASA ADV MNGR NAM NASA/KSC CHUCK DOVALE NASA LAUNCH MNGR NLM BOEING MIKE KENNARD OPERATIONS INTEGRATOR OI B NET 31 19 7 6-4531 6-4519 6-4507 NASA/KSC STEVE FRANCOIS NASA ADVISOR 6-4532 NASA/KSC OMAR BAEZ ASST LAUNCH MNGR 6-4520 BOEING MIKE TAYLOR FLIGHT OPS MANGER 6-4508 32 KPM 20 ALM 8 B NET FO NASA/KSC BILL PARSONS NASA ADVISOR 6-2242 KCD NASA/KSC AMANDA MITSKEVICH FLT PROJECTS OFFICE FPO BOEING SCOTT MESSER NLS PROGRAM MANAGER DPM B NET 33 21 9 6-4533 6-4521 6-4509 NASA/KSC OSCAR TOLEDO NASA ADVISOR 6-4534 NASA/KSC GARRETT SKROBOT NASA MSN INTEG MNGR 6-4522 BOEING MARK WILKINS VICE PRES DELTA PROG 6-4510 B NET 34 KSA 22 NASA MIM 10 DVP NASA/HQ BILL WROBEL SPACE OPS MSN DIR HQM ANALEX TRACEY POST LAUNCH OPS MNGR LOM BOEING TBD B NET 35 23 11 6-4535 6-4523 6-4511 NASA/HQ MIKE LUTHER SCIENCE MISSION DIR 6-4536 NASA/KSC TBD NLM AWARD SEAT 6-4524 BOEING TBD 6-4512 36 HQSMD 24 12 B NET VIP SEATING AREA XXXX -Network Drop for Laptops January 5, 2007 THEMIS Mission Readiness Review 106

THEMIS Mission Support LVDC-3
Charlie Floyd ANALEX MGMT O NET O NET 17 Mike Culley SWALES 9 John Thurbur GSFC 1 6-4581 6-4580 6-4573 Norm White ANALEX MGMT Dave Curtis UCB STC 10 Dennis Lee GSFC 18 O NET 2 O NET Larry Ellis ANALEX MGMT Stu Harris UCB MSE O NET Warren Chen SWALES O NET 19 11 3 6-4582 6-4579 6-4574 Steve Owens SAIC MGMT Jeremy McCauley UCB Jamey Burget GSFC 20 12 4 O NET O NET Linda Warnock JBOSC K-NET O NET 21 Reserved NASA KSC 13 Joe Bolek GSFC 5 6-4583 6-4578 6-4575 Tiffany Nail NASA/KSC Reserved NASA KSC Paul Turin UCB 22 K-NET 14 6 O NET Jan McMillen ANALEX K-NET Reserved NASA KSC Greg Dalton UCB O NET 23 15 7 6-4584 6-4577 6-4576 Roy Fisher ANALEX Reserved NASA KSC 24 16 Ron Jackson UCB 8 O NET XXXX -Network Drop for Laptops

THEMIS Mission Recycle Requirements
THEMIS Spacecraft Recycle Requirements Same day recycle Spacecraft will remain on internal power 24 hour recycle Return to external power Recharge Batteries – Remotely (Does Not Require Fairing Access) 48 hour recycle Same as 24 hour recycle Multiple scrub limits If extended delay Continue to Recharge Batteries – Remotely (Does Not Require Fairing Access)

THEMIS Mandatory Launch Constraints

THEMIS Required Launch Constraints

Launch Vehicle Readiness
Garrett Skrobot Mission Integration Manager

Mission Overview

Launch Vehicle Overview
Vehicle Configuration: Delta 7925–10C Launch Site: Eastern Range (ER), SLC-17B at Cape Canaveral Air Force Station (CCAFS) Mission Specifics: Perigee: 435 km, Apogee: km Orbit Inclination: 16 degrees Spacecraft (SC) Mass (will not exceed) 829 kg ( lb) kg actual STAR 48B Motor Nutation Control System Yo-Yo de-spin system Spin rates: During Third Stage operation - max  70 rpm S/C after spin-down and separation - 162 rpm Mission Unique 3712 Bolted PAF Sep System (at PAF/PC Interface) Non-Standard Services Category 1 Analysis (1st C ER) Five - 24” Doors Two 61 pin connectors Fairing Cleaning to VC 6 Separation System provided by THEMIS Spacecraft, contracted through Launch Services Program (LSP) NASA Launch Service (NLS) Contract

Mission Parameters Launch Period 15 February 07 – 14 March 07
Daily Launch Opportunities Single flight azimuth/SECO 1 trajectory 93 Deg Single Second Stage restart/Third Stage trajectories Window Duration min Launch period has been divided into two blocks of dates Opening 15 February to 28 February 23:08:00 UTC (Changes by 3:34 per day) 01 March to 14 March 21:57:00 UTC (Changes by 3:34 per day) Liftoff times are rounded to the nearest whole minute Mission Assurance Collision Avoidance (COLA) Measures will be accomplished Free Molecular Heating Rate at Fairing Separation < 0.1 BTU/ft2/sec Sun Angle Constraints: Centerline during coast 90 +/- 9 deg

THEMIS PCS and Performance Margin
15-28 Feb Mar 2007 Spacecraft Mass Including Probe Carrier (lb) Second Stage Velocity Reserve at SECO 2 (fps) Second Stage Velocity Reserve Required for PCS of 99.7% (fps) TAG Performance Allowance (fps) 75 75 Velocity Reserve Margin (fps)

Flight Profile Note: Values shown are for 15-28 Feb 2007 launch MECO
Liftoff MECO t = sec Alt = 69.0 nmi VI = 20,060 fps Second Stage Ignition t = sec Alt = 72.9 nmi VI = 20,068 fps Fairing Jettison t = sec Alt = 74.1 nmi VI = 20,103 fps SECO 1 t = sec Alt = nmi VI = 25,923 fps ORBIT: 100 x 304 nmi 28.50 deg inclination Second Stage Restart t = sec Alt = nmi VI = 24,662 fps SECO 2 t = sec Alt = nmi VI = 25,778 fps 280 x 825 nmi 26.58 deg inclination TECO t = sec Alt = nmi VI = 33,975 fps Separate Probe A t = sec Alt = nmi VI = 32,368 fps Orbit: 235 x 49,592 nmi 16.00 deg inclination deg arg of per SRM Impact SRM Jettison (6) t = 66.0 / 67.0 sec Alt = 9.9 / 10.2 nmi VI = 3,231 / 3,269 fps SRM Jettison (3) t = sec Alt = 31.3 nmi VI = 8,018 fps Third Stage Ignition t = sec Alt = nmi VI = 25,775 fps Note: Values shown are for Feb 2007 launch Depletion Burn: Removes Stage 2 from vicinity of spacecraft, while lowering Stage 2 perigee altitude and orbit inclination

Orbit Trace – 15-28 Feb 2007 Working with Big Crow to see if they can
overlap SC separation coverage TEL4 = Eastern Range ANT = Antigua CAIR = Cairns (Mobile Telemetry, MT) KWAJ = Kwajalein UCB = Berkeley Ground Station

Telemetry Asset Plan/Acquisition
Acquisition Status TEL-4 - Eastern Range Station at KSC Complete ANT - Eastern Range Station at Antigua Cair - Cairns (Big Crow) KWAJ - Kwajalein

Accepted/Open Risks 6S 4S 2P 1S 2S 3S 5S Item Approach Risk ID Status
L I K E H O D CONSEQUENCES 2P 3S 4S 6S 1S 2S 5S Item Approach Risk ID Status Risk Description 1 A V0015 9 Flight critical engine section components are unqualified for the newly revised P95/50 MEFL MECO transient environment. Risk accepted by LSP 4/24/02, (Ref ERB 01377KSC0 and ERB 02-23) 2 V0037 Condition: Power and Control (P&C) Box capacitors have become loose in S/N Consequence: Undetected loose capacitors in other P&C Boxes. Risk accepted by LSP 8/16/05, (Ref ERB ; ERB ) 3 V0035 A photodiode failed within Redundant Inertial Flight Control Assembly (RIFCA) S/N Risk accepted (Ref ERB ). 6/8/06 ERB accepted S/N and all RIFCA after. 4 V0033 Condition: Cracks have occurred and been detected within Electronics Package (E-Package) Thick Film Assemblies (TFA's). Risk accepted by LSP 8/18/05 (Ref ERB ; ERS-02-43; ERS ERS ). S = Safety & Mission Assurance Designator P = LSP Designator

Accepted/Open Risks (Cont.)
5 4 3 2 1 L I K E H O D CONSEQUENCES 2P 3S 4S 6S 1S 2S 5S Item Approach Risk ID Status Risk Description 5 A V0034 Condition: Delaminations have occurred within the Graphite Epoxy Motor (GEM) nozzles' Exit Cone Liners (ECL) and Throat Support Insulators (TSI). Consequence: Detrimental hot gas flow, adverse heating and eventual failure of the nozzle. Risk accepted by LSP 8/10/05, (Ref ERB ; ERB-01373KSC0; 01388KSC0; ; 02-2). 6 M M0246 Condition: FM-14 2nd Stage tank assembly was found to have helium leakage from Oxidizer dome bracket at Decatur during fuel feedline leak checks. Membrane thinning due to aggressive sanding has concern as to whether there is acceptable membrane thickness in tank bracket locations. Consequence: Mission loss or hazard to personnel due to failure of the 2nd stage tank assembly. ERB to be held mid-Jan for Acceptance of Risks for THEMIS FM13 tank S = Safety & Mission Assurance Designator P = LSP Designator

Readiness Reviews Review Date Location
Pre Vehicle On Stand (PreVOS) 03 January HB MRR* January GSFC Launch Vehicle Readiness Review (LVRR) 12 January KSC Safety & Mission Success 19 January HQ Review (SMSR) Launch Site Readiness Review (LSRR) 01 February (est) KSC Flight Readiness Review (FRR) 12 February KSC Launch Mgmt. Coordination Meeting (LMCM)/ 13 February KSC Mission Dress Rehearsal (MDR) Launch Readiness Review (LRR) 14 February KSC * Normal sequence of reviews is to conduct the Launch Vehicle Readiness Review before the SC MRR. Any updates will be captured in the LVRR package.

Schedule, Range and Launch Site Status

Launch Site Schedule January 5, 2007 THEMIS Mission Readiness Review 123

Eastern Range Operations Schedule
Jan/Feb/Mar 2007 SUN MON TUE WED THU FRI SAT 28 29 30 31 FEBRUARY 1 2 3 JANUARY 4 5 6 7 8 9 10 11 12 13 14 15 16 17 Delta II THEMIS 18 19 20 21 22 23 24 HOLIDAY 25 26 27 28 MARCH 1 2 3 X Range Configuration / Range Conflict \\ Additional Launch/Landing Attempt(s) HOLIDAY \ Configuration Hold

THEMIS Documentation Status
Requirements Documentation Status All requirements documentation in place to support THEMIS processing (Launch Site Support Plan [LSSP], Program Requirements Document [PRD], Operation Requirements [OR]). Safety Documentation Status Missile System Pre-Launch Safety Package (MSPSP) – Approved. Hazardous procedure review and approval. 4 spacecraft standalone hazardous procedures for Pad operations. Launch Site Integration and Astrotech processing activities on track to support February 15, 2007 Launch Date.

Special Attention Items

Engineering Review Board (ERB) / Engineering Review Summary (ERS)
19 ERBs Remain Open, expected closure by January 31, 2007. 75 ERSs Remain Open, expected closure by February 7, 2007. All mission ERBs must be closed before the FRR. Mission ERSs can be open at the time of launch. Number of OPEN ERBs Number of OPEN ERSs Mission 1 13 Core/Fleet 18 62 TOTAL 19 75 Due to the sequence of the reviews, there are a large amount of ERBs and ERSs open at MRR. Many of these ERBs and ERSs will be closed shortly after the PreVOS and Launch Vehicle Readiness Review.

THEMIS Third Stage Confined TLX (CTLX)
Boeing notified LSP of a TLX LAT failure in a lot of new-design (generally referred to as "Gen-2") lines that occurred at UPCO, the TLX vendor. Investigation showed that the failure mechanism was the formation of a "powder plug" in the line that interrupted propagation of the ordnance impulse. Direct cause was identified by Boeing to be: Relatively insensitive explosive due to large explosive grain size Root cause was identified as: Inadequate manufacturing/processing equipment Ball milling process was inconsistent, permitted large grains to remain in milled powder Inadequate inspections after ball milling did not properly characterize grain size Two lots are now suspect for the direct and root causes: J Lot used in units with LAT failure B – lot used for THEMIS CTLX The 2B lot has successfully completed LAT with no failures If lot separation can be demonstrated, then the currently installed CTLX lines could be used for the THEMIS mission.

THEMIS Third Stage Confined TLX (CTLX) (Cont.)
LSP convened a joint ERB on December 20, 2006 to address flightworthiness impacts to the TLX and CTLX lots assigned to THEMIS. The TLX lines on the THEMIS vehicle were manufactured using a prior powder batch that was delivered with the desired grain size distribution and required no additional milling. Therefore, the TLX on the THEMIS vehicle is not suspect. Evaluation of the milling records and particle size distribution analysis data for each batch showed evidence that the milling procedure was not sufficiently specific to control the particle size distribution to the expected degree. The same data also convincingly showed that the batch used in the manufacture of the THEMIS CTLX lines was successfully milled to the desired size distribution, comparing very well with the prior batch of powder that required no milling. The milling records also provided sufficient data to recognize that the milling for 2B lot was set up differently than for 0J lot. All of 2B lot was milled in a consistent manner, all of 0J was milled in a consistent manner, but 2B lot was not milled like 0J lot . The ERB cleared the lines for THEMIS with no increased risk.

Second Stage Tank LSP was notified by Boeing that leaks were found at bracket weld of THEMIS’s second stage tank (FM14). Boeing reassigned tank FM11 to replace FM14 for the THEMIS Mission. During X-ray review, cracks were identified at the aft dome fuel feed line support bracket of FM11. Tank FM11 was de-assigned from THEMIS and Boeing reassigned the Orbview tank FM13. FM13 was inspected and evaluated at Decatur by the same NDE methods used for clearance of FM9 for STEREO. The dis-assembly of the FM14 tank was completed and re-assembly of the new THEMIS Second Stage (FM13) is completed and shipped to the Cape for processing.

Second Stage Tank (Cont.)
ERB was conducted November 02, 2006 to determine the flightworthiness of FM13 for THEMIS. The ERB assigned several action items that need to completed before acceptance of the tank could be given. The actions generated during the review are currently being worked and are expected to be closed by mid-January. A reconvene ERB will be conducted to give flightworthiness for FM13 in mid-January.

Separation Sequencing System (SSS)
Standard clampband boltcutters at the LV to SC interface replaced with 4 port manifolds on the probe carrier (2 places). Top Probe “A” separated first, then 3 sec later, 4 remaining Probes “B-E” are separated. GSFC provided SSS initiated by the DII upper stage event sequencing system (ESS). Manifolds incorporate output to ordnance initiated switches to confirm separation signal received at the LV to SC interface plane. LV Firing Signal to the SSS (2 places)

Additional Pyro Switches

Probe Separation Monitor System
Probe separation to be monitored by Launch Vehicle Third Stage Telemetry System, channel FM12. Launch Vehicle provides 28 VDC from Third Stage Telemetry control box to Probe Carrier. Separation breakwires used on each individual Probe. Voltage divider network produces 32 distinct output voltages (0-5 VDC) for all possible separation scenarios. Probe Carrier to Third Stage Telemetry System Side-by-Side test completed successfully at Kennedy Space Center (KSC) on December 14, 2006. All output voltages met tolerance specified in the procedure and the system met the Interface Control Document (ICD) requirement that output voltages differ by greater than 3%.

Summary NASA Launch Services Program is ready for continued THEMIS launch vehicle processing. NASA Launch Services Program will complete all required open work prior to approval for start of spacecraft mate activities (LSRR - February 1, 2007 est.).

Safety & Mission Assurance
Ronald Pierson Explorers Systems Assurance Manager

Mission Assurance Status
Safety documents are complete – supporting activities at Astrotech GSFC has at least 1 SMA person at Astrotech throughout for surveillance of launch activities Support of paperwork closure (PFRs, as-run procedures, Waivers, RFAs) is ongoing as work progresses As-built vs. as design parts and materials lists have been completed; no outstanding issues GIDEP Alerts are reviewed as issued (~95% closed) Safety and Mission Success Review (SMSR) is scheduled for 1/19/07 at HQ

System Safety Final MSPSP - Approved by NASA Explorers, KSC, and Range Safety. KSC approval memo granted permission to arrive at the launch site processing facility on 11/28/06. No expected liens against transport to the launch pad. Service Valve Waiver - RCS fill and drain valves are not 2-fault tolerant against inadvertent hydrazine leakage. Waiver processed to document non-compliance and additional controls implemented to protect personnel. Specifically, additional localized leak detection will be implemented after fueling. Waiver has been reviewed and approved by GSFC and KSC management. High Pressure Line Underproof - Small section of line on high pressure side of RCS not taken to correct proof pressure level. Additional testing was performed on 10 sample pieces using the same manufacturing and welding techniques to demonstrate strength margin. This section will not see flight levels until after RCS re-press on orbit. Noncompliance review conducted by GSFC Codes 300, 400, and 500 in Spring 2006 and controls were accepted. Underproof documented via a deviation and approved by 300, 400, and 500 on 12/7. Mechanical and Electrical GSE tested and approved Orbital Debris Analysis final report completed and submitted

Quality Assurance Mirror FOD P/FR - Concern that mirror piece potentially struck blanketed Probe 1 COPV tank during environmental testing. Visual Inspection of the blanket performed by UCB and GSFC QA; no scarring or damage found. Analysis performed by Explorers estimating worse case accelerations of mirror fragment during spin balance, loads not great enough to cause damage. GSFC Propulsion Branch briefed on results of inspection and analysis and confirmed an additional proof test at 1.5 MEOP would not be required. Tank taken to 1.1 MEOP for leak testing on 12/14 and is currently sitting at the flight pressure (1750 psi). P/FR closed. Probe capacitor replacement due to polarity error in PWA installation. All affected capacitors replaced in all 5 Probes. Probes are now finishing their additional free run time requirements (350 hous) after which the P/FR will be closed.

Ready to Support Launch
GSFC and UCB SMA team is fully staffed and well-coordinated, roles are fully understood SAM concurs with project risk assessment Project and Explorers is responsive to SMA concerns Safety and Mission Assurance is ready to support launch

Safety & Mission Assurance
BACKUP

Assurance/Technical Authority Activities
Status Summary Residual Risks Quality Assurance Software Complete Software assurance is complete None Hardware Problems/PRs Ongoing PFRs are being addressed as opened See Systems Section Alerts 98% + Complete All GIDEPS have been assessed and impacts understood, reviewing as issued Quality Assurance Surveillance Launch site surveillance ongoing Reliability/Maintainability FMEA/CIL Analyses completed Swales, reviewed by GSFC Code 302 and suppliers Reliability Assessment Analyses completed by Swales, reviewed by GSFC Code 302 and suppliers Limited Life Items Tracked for observatory by GSFC Systems Safety Safety Data Package Controls in place and verification complete. Contingency Planning Contingency plans in place Range Safety MSPSP Approved NASA Safety Reporting System Close calls are closed SMA Integrated Activities Training All certifications and training in place Lessons Learned Review Will enter into LLIS after launch Risk Management Risk discussed as open and residual Waivers/Deviations/Exceptions Class I and II waivers complete

GSFC Project Role per the THEMIS Surveillance Plan
THEMIS Project Surveillance Plan has been released and implemented Contract with UC Berkeley was executed for Phases B-E for the development of the THEMIS spacecrafts and instruments. Requirements and specifications contained in the contract, statement of work, and referenced documents establish the baseline. The contract is cost type with government Insight. Insight has included: MRB FRB Inspection PMPCB Weekly reporting to GSFC

GSFC Mission Assurance Role for Spacecraft
Spacecraft Development at Swales Product Assurance Implementation Plan via CDRL Government Source Inspection monitored by GSFC QA Software development monitored by GSFC Software Quality Assurance Roles and responsibilities: Clean room integration monitored by Swales QA team with GSFC surveillance at critical points Participation in Failure Review Boards at Probe s/c level,

GSFC Mission Assurance Role for Instruments
Instruments - University of California Berkeley Requirements levied via Product Assurance Implementation Plan Supplier Assurance Contract Assessment performed post CDR GSFC insight and in-plant Quality Assurance representative starting at Probe I&T Participation in Review Boards for parts, materials and anomalies Design reviews conducted by Independent Review Team

System Safety Hazards Controls are in place and verified for all hazards at ASO and Pad All hazards signed and residual risk accepted by program management Procedures for field operations Reviewed all mechanical procedures Reviewed all electrical and I&T procedures Reviewed all propellant loading procedures Status of safety documentation MSPSP approved by Range All Forms submitted and approved

Orbital Debris Assessment
Final Orbital Debris Assessment (ODA) submitted on 17 Feb 2006 to NASA HQ. THEMIS is non-compliant to Paragraph 4-2 for complete battery discharging. Waiver letter being developed. Delta II is non-compliant. This is a continuing issue. Recommend Approval of THEMIS for Orbital Debris with waivers for ODA as noted above.

Independent Assurance Activities
Evaluation Area Status Residual Risks 1. SAC Assessment at Swales Complete None 2. SAC Assessment at UCB 3. IV&V Assessment of Spacecraft Software THEMIS IIRT System Reviews conducted in accordance with Systems Review Plan. Board Members invited to participate in Peer Reviews.

Waivers No waivers to Level 1 Requirements

Description/Recommendation
New Lessons Learned Lesson Description/Recommendation Applicability 1. Review PWB silkscreen to engineering drawing to verify polarity specific parts orientation ID and Verify PWBs for polarity specific parts orientation All missions

SMA Responsibility Matrix
GSFC SMA Independent (GSFC Code 301) IV&V Contractor’s Representative In-Plant or Itinerant Representative External Review Overall Mission Assurance Ronald Perison GSFC Rick Pfisterer GSFC QE Mark Goans Judith Connelly IV&V Facility N/A Brian Keegan Spacecraft Instruments Jeremiah Tolbert Ron Hallet

SMA Responsibility Matrix (2)
GSFC SMA Independent (Code 301) IV&V Contractors Representative In-Plant Representative External Review Parts Joseph Osche GSFC Mark Goans N/A Brian Keegan Materials Fred Gross Safety Jamie Burget Reliability Nino Ingenari Software Cindy Taylor

GSFC Code 300 “Watch List” Item # Description Reply Status Comments
97-01 Optocouplers - SETs. Impact The Amptek, HV601B (ESA instrument) and the Micro pack (LVPS and PCB instruments) are used. "THEMIS has screened devices … suitable ..." 99-01 Actel FPGAs: NA-046 Start-up rules are being followed. LASP and Orbital have consulted Actel."THEMIS is employing … recommendations 99-02 Vishay - Metal Foil Resistors. No impact The Vishay, RNC90Z (MIL-PRF-55182/9), established reliability resistors are used. 99-03 SpecTran - Fiber Optic Cable. Not used 99-04 Bell Labs - Up-screened diodes. 99-05 ATC Capacitors: NA-048. 00-01 Interpoint: MT2-P 01-01 Advanced Analog: DC-DC converters. 02-01 ACS Polarity Verification. “Swales has provided polarity verification plan." 03-01 Metropole: Diplexer anomaly. 04-01 Hitachi EEPROM: bit flips. The Maxwell EEPROM ( Q7C, 28C011TRPFB-12) is used in the DCB instrument and has the Hitachi die. Reviewed and risk accepted. 04-02 cPCI Connector Qualification. 04-03 TRAK Microwave: Isolator. 05-01 Emcore: Solar Cell Welds. 05-02 Starsys: Qwknut.

GSFC Code 300 “Watch List” (2)
Item # Description Reply Status Comments 05-03 ARDE Overwrapped COPV No impact Not used 05-04 Goodrich Star Tracker No impact 05-05 Photography Impact "There are no contractual requirements for photography/video in the … THEMIS …. Contract". However Swales and Berkeley have been performiong photography as part of standard practice. 05-06 Ball Aerospace – Conformal Coating 05-07 Trompeter Electronics - Connector. 05-08 LoDs:DCMC Workmanship Certs. 05-09 Conax Florida Corporation - Pyrovalves. 05-10 Actel RTAX FPGAs. All contractors are applying power to these parts. It is the intent to acquire at least 1000 hours on each device prior to shipment. All time is being recorded. DPAs have been performed to each lot date code. 05-11 PK Selective - Unauthorized Paint. Yes, impact Approved per the PMPCB. "… the instruments have passed all outgassing requirements …" 06-01 RAD750 EEPROM Vibration Failure.

Software IV&V Judith Connelly THEMIS IV&V

Outline of Content Summary of IV&V tasks and recommendation
Summary of Project Accepts Risk (PAR) Issues Conclusion Backup Slides Backup Contents: Summary of All Issues generated, resolved & closed Detail on Two Programmatic Risks –(status closed ) List of Artifacts Analyzed BAU issues breakdown by Function IDPU issues breakdown by Function Severity Definitions

Summary of IV&V Tasks and Recommendation
The goal of IV&V work on THEMIS is to verify and validate that THEMIS FSW will support mission success. Towards that end IV&V performed analysis on Spacecraft Flight Software Bus Avionics Unit (BAU) and Instrument Data Processing Unit (IDPU) Software in the following areas: Requirements Analysis : To confirm that system and software requirements are complete, consistent, traceable and testable. Design Analysis: To verify software design models and algorithms provide implementation of associated requirements and handle off-nominal functionality. Code Analysis: To verify that code is free of implementation errors and that it fulfills the requirements. Test Program Analysis : To verify test artifacts cover all requirements levied on the software; to verify test results were expected; To confirm that testing demonstrated that the software performs reliably under realistic scenarios. Based on the results of these analyses, issue closures and the acceptance of risk by the Project of technical issues not resolved, IV&V has no significant concerns regarding the operational readiness of the THEMIS spacecraft FSW. IV&V has completed limited analyses of the Ground System, including analysis of the GSICD, Mission Ops and Flight Ops artifacts. No significant issues were found as a result of these analyses. IV&V recommends THEMIS for launch.

Project Accepts Risk (PAR) TIMs Summary
PAR TIMs (Technical Issue of Memoranda) state means that the Project recognizes that IV&V has some outstanding concerns with an issue and that the Project accepts risk, if any, associated with that issue. In accepting this risk the Project does not necessarily agree nor disagree with the issue itself. These TIMs have not been closed. The Project has demonstrated a workaround to the core issues identified in the TIMs. There are 13 PAR TIMs supporting the 3 impact statements below. IV&V concurs that there is a low likelihood of occurrence and that these are acceptable risks. Impact: Data Storage writes could be corrupted by a process interrupt, and THEMIS could be left in an incoherent state. THEMIS could fail to respond to time-critical events. Data quality may also be degraded. Specific area: Data Storage and Checksumming, Semaphore lock/unlock Impact: There is a potential for unexpected behavior of unused objects and functions. Emergent behavior is unknown for 1) inconsistently defined macros and 2) variables that are defined more than once. Untested return values could cause unexpected interrupts or failure of process execution. Specific area: Health & Safety, General, Boot Impact: Possible degradation of timing for probe stored command execution. Specific area: Stored Commands

IV&V recommends THEMIS for launch.
IV&V Conclusion Based on the results of these analyses, issue closures and the acceptance of risk by the Project of technical issues not resolved, IV&V has no significant concerns regarding the operational readiness of the THEMIS spacecraft FSW. IV&V has completed limited analyses of the Ground System, including analysis of the GSICD, Mission Ops and Flight Ops artifacts. No significant issues were found as a result of these analyses. IV&V recommends THEMIS for launch.

Backup Summary of All TIMs generated, resolved and closed
Detail on Two Programmatic Risks (closed ) List of Artifacts Analyzed BAU TIM breakdown by Function IDPU TIM breakdown by Function Severity Definitions

Summary of All Technical Issues of Memoranda (TIM) generated, resolved & closed
All TIMs are closed with the exception of Project Accepts Risks (PAR) TIMs as previously outlined. No formal TIMs were generated for the Ground System. Informal reports were delivered to the project with recommendations.

Programmatic Project Risks
BAU Testing - Closed September 06 IF the BAU test artifacts do not confirm traceability to all BAU FSW requirements THEN there is no confirmation that all BAU FSW requirements have been completely and adequately tested. Closure Comments: The dialogue with the project has resolved many testing TIMs. This dialogue will continue until testing artifacts have been shown to contain the required traceability. The original driver for the risk has been mitigated. Configuration Management - Closed June 06 IF the reallocated requirements identified in the Comments and ResChron sections of this Risk TIM are not adequately documented and controlled at the system level, THEN the receiving subsystem may not fully understand the intent and therefore may not properly implement the requirement. Closure Comments: “Through analysis of artifacts and discussion with the Project, IV&V has been able to verify that the Project does utilize their formal SCN process for requirements deletions and changes.

Artifacts Reviewed Below is a list of THEMIS artifacts which IV&V has reviewed. IDPU Requirements SRS Revs D, E, F Design THEMIS IDPU FSW Design document Code IDPU FSW Phase 1.04 IDPU FSW Phase 2.01 IDPU FSW Phase 3.03 IDPU FSW Phase 4 Test IDPU CPT Plan Ground GS artifacts analyzed: THM-SYS-013, THEMIS Mission Ops Plan, 10/3/06 THM-SYS-018, THEMIS Flight Ops Plan, 9/29/06 THM-SYS-117, THEMIS GS ICD, 10/3/06 Ground artifacts reviewed: THM-SYS-117, THEMIS GSICD, 11/20/06 Ground artifacts TO BE ANALYZED: THM-SYS-117, THEMIS GSICD, Final (Date TBD) System MRD Revs C, D, E, F, G, H BAU Requirements FSW SRS Revs 1.1, 2.0, 2.2, 3.0 Flight Software User’s Guide v1.0 Boot SRS Revs 1.0, 2.1, 2.2 Design BAU CDR Presentation (6/15/04) Code FSW Build 2 FSW Build 2.504 FSW Build 3.003 FSW Build 3.1 FSW Build 3.19 Boot Build 0 Boot 2.510 Test BAU FSW Build 2 BAU FSW Build 3.000/3.003/3.10 BAU FSW Build CPT BAU FSW Test Plan v1.0

All BAU TIMs by severity and function

All IDPU TIMs by severity & function

TIM Severity Definitions
*IEEE J-STD definitions are used. 1 a) Prevent the accomplishment of an essential capability b) Jeopardize safety, security, or other requirement designated critical. 2 a) Adversely affect the accomplishment of an essential capability and no work-around solution is known b) Adversely affect technical, cost or schedule risks to the project or life cycle support of the system, and no work-around solution is known 3 a) Adversely affect the accomplishment of an essential capability but a work-around solution is known b) Adversely affect technical, cost, or schedule risks to the project or life cycle support of the system, but a work-around solution is known 4 a) Result in user/operator inconvenience but does not affect a required operational or mission essential capability b) Result in inconvenience for development or maintenance personnel, but does not affect the accomplishment of these responsibilities 5 Any other affect

Integrated Independent Review Team
Mark Goans GSFC Systems Review Office Brian Keegan Independent Consultant

Integrated Independent Review Approach
Major technical and programmatic reviews were conducted per the “THEMIS Integrated Independent Review Plan”, dated July 29, 2004. Modifications from that plan were minor, being associated only with the S/N of the bus ship sequence from Swales and the conduct of a Delta-PSR telecon prior to shipment of the flight segment from JPL to KSC. A series of Engineering Peer Reviews were held by UCB Project Management preceding both Mission PDR and Mission CDR. Results were provided to and reviewed by the IIRT in conjunction with the Mission PDR & CDR Reviews. January 5, 2007 THEMIS Mission Readiness Review

Integrated Independent Review Team (IIRT) Members
Mark Goans GSFC [Systems Review Office] (Co-chair) Brian Keegan Independent (Co-chair) Bill Taylor Independent - Project Mgt., Systems Frank Martin Independent - Science, Instruments J. B. Joyce Independent - Operations Terry Ford Independent - GN & C Rick Schnurr GSFC - Electrical Systems Alan Posey GSFC - Mechanical Systems Lou Fantano GSFC- Thermal Scott Glubke GSFC - Propulsion Ed Gaddy GSFC - Power Ronnie Killough SWRI - Software January 5, 2007 THEMIS Mission Readiness Review

Mission Operations Review Team Members
-Mark Goans, GSFC [Systems Review Office] (Co-chair) -J.B. Joyce Independent (Co-chair) -Mary Foote CSC, IT Security -Steve Cooley GSFC, Flight Dynamics -Patrick Crouse GSFC, Space Science Mission Operations -John Jackson GSFC, Space-Ground Interface -John Donohue GSFC, Command and Control -Rob Messerly Titan, Mission Readiness Testing -Madeline Butler GSFC, Engineering -Bob Wiegand GSFC/Flight Dynamics Systems -Stan Scott GSFC/Science Data Processing -Glen Miller HTSI, Flight Operations -Emil Kirwan HTSI, Reliability Engineering January 5, 2007 THEMIS Mission Readiness Review

Flight Operations Review Team Members
-Mark Goans, GSFC [Systems Review Office] (Co-chair) -J.B. Joyce Independent (Co-chair) -Madeline Butler GSFC - Engineering -Paul Garza GSFC - Space/Ground Interface -Pat Johnson GSFC - Flight Dynamics Systems -Emil Kirwan HTSI - Reliability Engineering -Ben Lui GSFC - Command and Control -Maureen Madden GSFC - Space Science Mission Ops -Conrad Schiff GSFC - Flight Dynamics -Stan Scott GSFC - Science Data Processing January 5, 2007 THEMIS Mission Readiness Review

THEMIS IIRT Reviews Element Review Date Payload PDR @ MPDR CDR June 16, 2004 Test Summary Dec. 9, 2004 F #1 PER May 2, 2005 F #1 PSR Sept. 21, 2005 F #2,3 PER Aug. 27, 2005 F #2,3 PSR Nov. 10, 2004 F #4,5 PER Nov. 10, 2005 F #4,5 PSR May 5, 2006 Element Review Date Spacecraft PDR Oct , 2003 CDR June 14-15, 2004 Test Summary April 5, 2005 Bus #2 PSR Nov. 17, 2005 Bus #3 PSR March 23, 2006 Bus #4 PSR May 4, 2006 Bus #1 PSR May 31, 2006 Bus #5 PSR June 12, 2006 Carrier PSR Element Review Date Mission SRR July 8-9, 2003 PDR Nov , 2003 CDR June 17, 2004 MOR March 7-8, 2005 P2 PER March 16, 2006 P1,3,4,5 PER June 23, 2006 FOR Oct. 4-5, 2006 PSR Oct. 26, 2006 Delta-PSR Dec. 5, 2006 January 5, 2007 THEMIS Mission Readiness Review

THEMIS RFA Summary January 5, 2007 THEMIS Mission Readiness Review

Key Project Management Practices
Key Management Practice SRR PDR CDR PER PSR Organization & Communication Systems Management Safety Risk Management Mission Assurance Integration TBD Verification Operations Engineering Peer Reviews Independent Reviews January 5, 2007 THEMIS Mission Readiness Review

THEMIS Residual Risk Rating
Note: Numerical techniques were not used to estimate likelihood probabilities. LIKELIHOOD (0.1% <PT < 2%) (PS < 10-6) Very Low 1 (2% < PT < 15%) (10-6 < PS < 10-3) Low 2 (15% < PT < 25%) (10-3 < PS < 10-2) Moderate 3 (25% < PT < 50%) (10-2 < PS < 10-1) High 4 (PT > 50%) (PS > 10-1) Very High 5 Technical Safety Level THEMIS RISK MATRIX LIKELIHOOD B,C* F D,E A CONSEQUENCE = Technical Rating * CONSEQUENCE 1 2 3 4 5 Level No impact to full mission success criteria Minor impact to full mission success criteria Moderate impact to full mission success criteria. Minimum mission success criteria is achievable with margin Major impact to full mission success criteria. Minimum mission success criteria is achievable Minimum mission success criteria is not achievable TECHNICAL Negligible or No impact. Could cause the need for only minor first aid treatment . May cause minor injury or occupational illness or minor property damage. May cause severe injury or occupational illness or major property damage May cause death or permanently disabling injury or destruction of property. SAFETY January 5, 2007 THEMIS Mission Readiness Review

THEMIS Residual Risk Assessment
Item Risk Description Failure Likelihood Failure Consequence A For all probes, a segment of both the high and low pressure portions of the Hydrazine Propulsion System were not proof tested to 1.5 MEOP. 1 4 Rationale: Likelihood - All hardware components were proof tested to appropriate pressures. Only segments of the line welds were not properly tested. Separate testing of 10 sample welds burst at > 9 times the required THEMIS proof pressure. GSFC TA and safety as well as KSC safety has accepted the alternate approach. Consequence - Loss of the RCS would cause loss of the associated probe. Full mission science can be accomplished with four probes. January 5, 2007 THEMIS Mission Readiness Review

Item Description Likelihood Consequence B Set-point of thermostats in RCS secondary heaters is closer than desired to freezing temperature of hydrazine propellant. 2 1 Rationale: Likelihood - RCS design has fully redundant thermostat and heater circuitry. Primary RCS thermostat set points are above any threshold of hydrazine freezing concerns. Set point of secondary RCS thermostats is marginal. If primary RCS heaters fail, control of eclipse duration becomes required method of RCS temperature control. Consequence - Long duration eclipses do not occur until 2nd year of operations. Baseline mission plan accomplishes full mission objectives in first year. January 5, 2007 THEMIS Mission Readiness Review

Item Description Likelihood Consequence C THEMIS uses four HLX6228TBR devices per BAU Data Processing Module (DPM) all of which use ramp time in the suspect range identified in the recent GIDEP Alert. 2 1 (Technical) Rationale: Likelihood - The DPM is powered up only once prior to launch and remains powered throughout launch and during all mission phases. There is no credible failure which power cycles the SRAM on orbit. There have been no SRAM errors during the hundreds of power-cycles of the flight hardware/software testing performed to date on the five flight probes and two engineering units. Part testing by the manufacturer has shown behavior of affected devices (~ 3%) to be consistent over time. Screening recommended by Alert to 2x application ramp time was not possible however because devices had been already installed. Consequence - Technical consequence to achieving mission objectives is negligible given that launch will not have occurred upon discovery of the problem. A power recycle of the affected probe could be attempted. In the worst case, potentially significant cost and schedule implications could result. January 5, 2007 THEMIS Mission Readiness Review

Item Description Likelihood Consequence D Potential failure of AMPTEK A121 devices in ESA instrument cannot be ruled out given failure of device in same lot due to shorting effects of silver dendrite growth. 1 2 Rationale: Likelihood - GSFC recommended RGA, DPA, and life testing of residual devices from same lot has been completed with positive results. Consequence - Failure of limited numbers of devices on orbit could be tolerated with minimum mission impact through reorienting attitude at which science measurements are made. January 5, 2007 THEMIS Mission Readiness Review

Item Description Likelihood Consequence E Solar Panel Qualification Panels were not subjected to a test of their output at maximum operating temperature. 1 2 Rationale: Likelihood - Array design of THEMIS is similar to C/NOFS except that THEMIS uses "strain relief" cell interconnects. (Note that cell interconnects were an element of the C/NOFS failure.) While the THEMIS qualification panel was not operated at its highest predicted operating temperature subsequent to thermal cycling exposure, the panel did have current passed through it during the test, which would have likely caught the most serious issues of open welds. All THEMIS flight panels were subjected to "Hot LAPS" testing after thermal vacuum exposure and were thus shown to be good at max operating temperature. A post-failure mechanical analysis of the array configuration by Aerospace modeled the C/NOFS failure. The same analysis of the THEMIS configuration showed positive margin. Consequence - A single failure would result in 1/16 power loss which could be accommodated via duty cycling of instruments without significant effect on accomplishing mission science. January 5, 2007 THEMIS Mission Readiness Review

Item Description Likelihood Consequence F 100+ hour run time on EFI instrument since replacement of "reversed" capacitors has not occurred in T-V and is not likely to reach the 350 hour GSFC "rule" on failure-free operation. 1 Rationale: Likelihood - While not a formal requirement on THEMIS, the UCB approach complied with GSFC run time and failure free guidance except after replacement of reversed capacitors in the EFI Instruments. Single T-V cycle, 1 axis vibe, and > 100 hours of ambient operation has been successfully accomplished after rework. (Current planning will likely achieve ~200 hours.) Consequence - Single "open" capacitor failure has essentially no impact because of redundant measurements on opposite sides of spinning spacecraft. Single "short" failure causes loss of measurement in one axis, thereby degrading timing resolution. January 5, 2007 THEMIS Mission Readiness Review

Open IIRT Concerns None January 5, 2007 THEMIS Mission Readiness Review

IIRT Conclusions All THEMIS residual risks are low and are acceptable. IIRT review of all unverified failures uncovered no residual risks of note. Flight predicted temperatures for all planned nominal and contingency cases are satisfactory. Satisfactory concurrence with response to remaining RFAs is foreseen based upon completion of discussions currently underway. THEMIS is ready to proceed with final launch preparations. Upon satisfactory completion of processing and closure of remaining RFAs, THEMIS is ready for launch. January 5, 2007 THEMIS Mission Readiness Review

Public Affair Plan Cynthia O’Carroll GSFC Public Affairs Office
January 5, 2007 THEMIS Mission Readiness Review

Public Affairs Office (PAO) Responsibilities
Goddard Space Flight Center (GSFC) - leads, plans and coordinates public affairs and outreach activities with NASA Headquarters and our partner organizations; prepares and distributes all media materials, including news releases, the mission press kit, the mission Web site and other mission specific products; organizes press briefings; coordinates Guest Operations. Mission Partners - lead: Space Sciences Laboratory at the University of California at Berkeley (UC Berkeley); International space agencies from Germany, Canada, France and Austria; and NASA JPL. Kennedy Space Center (KSC) - lead for photo/video documentation of spacecraft processing and launch vehicle buildup; coordinates the spacecraft press opportunity at Astrotech; coordinates the L-1 Press Briefing to be held at the KSC Press Site; arranges NASA TV support and live coverage of the briefings and the launch; and provides launch commentary. Swales Aerospace - built spacecraft bus and probe carrier; participates in PAO activities and supports Guest Ops. United Launch Alliance (ULA) - provides Delta II Launch Vehicle; participates in PAO activities and supports Guest Ops. January 5, 2007 THEMIS Mission Readiness Review

PAO Responsibilities Press Kit THEMIS Fact Sheet THEMIS Lithograph Information on the instruments, the spacecraft bus, the probe carrier and the LV Other mission related products and images Press Kit will be available on the NASA Web site and in hardcopy January 5, 2007 THEMIS Mission Readiness Review

PAO Responsibilities News Releases: Spacecraft Arrival - NASA HQ, KSC, GSFC, and UC Berkeley issued release on 12/11 Weekly Status Reports - KSC; THEMIS and Delta II processing General News Release - NASA HQ, GSFC and UC Berkeley; general info about the THEMIS mission before the L-30 Press Briefing Note-to-Editors - NASA HQ, KSC and GSFC; logistics for the Press Opportunity at Astrotech Pre-launch/Mission Science Briefing Release - KSC; logistics and info about NASA TV coverage for the L-1 Press Briefing Post-launch Status Reports - GSFC and UC Berkeley; issue a status report after the successful launch Science Results News Releases - NASA HQ, GSFC and UC Berkeley; coordinate the timing and content of science results news releases with partners as necessary January 5, 2007 THEMIS Mission Readiness Review

PAO Responsibilities NASA Television and Web Coverage: THEMIS Promo - GSFC TV has produced a brief animated video of the THEMIS launch and deployment with music. Video File - GSFC TV has produced a video file that will be broadcast live on NASA TV for the L-30 and the L-1 Press Briefings and on the day of the launch. The video file contains B-roll of spacecraft at Swales, UC Berkeley, JPL and KSC. It also contains science and spacecraft animation and interviews. Pre-launch Support - KSC will arrange TV support and coverage the L-1 Press Briefings at the KSC Press Site to be carried live on NASA TV. Launch Coverage - KSC will arrange live launch day coverage as well as the launch commentary. The launch will also be available on the NASA Web site. THEMIS Web Sites - January 5, 2007 THEMIS Mission Readiness Review

PAO Responsibilities L-30 Press Briefing: Will be held by telecon and supported by the the mission Web site; NASA TV will air the THEMIS video file on the same day. Participants: Moderator: George Diller, NASA KSC PAO Craig Pollock, NASA HQ THEMIS Program Manager Frank Snow, NASA GSFC THEMIS Mission Manager Vassilis Angelopoulos, UC Berkeley THEMIS Principal Investigator Peter Harvey, UC Berkeley THEMIS Project Manager January 5, 2007 THEMIS Mission Readiness Review

PAO Responsibilities L-1 Briefings: Will be held on L-1 after the Launch Readiness Review at the KSC Press Site; will air on NASA TV with THEMIS video file. Pre-launch Briefing: Moderator: George Diller, NASA KSC PAO Richard R. Fisher, NASA HQ Director of Heliophysics Division Frank Snow, NASA GSFC THEMIS Mission Manager Peter Harvey, UC Berkeley THEMIS Project Manager Chuck Dovale, NASA KSC Launch Director ULA, Director of NASA Programs U.S. Air Force Delta II Launch Weather Officer, 45th Weather Squadron Mission Science Briefing: Craig Pollock, NASA HQ THEMIS Program Manager David Sibeck, NASA THEMIS Project Scientist Vassilis Angelopoulos, UC Berkeley THEMIS Principal Investigator January 5, 2007 THEMIS Mission Readiness Review

PAO Responsibilities Outreach Activities: Completed: Spring 2006 AGU: Science Writers Workshop highlighting THEMIS science November 2006: Media Training was provided to the PM, the PI and the PS as the primary spokespersons for the mission. September 2006 SpaceLink for Educators at the Maryland Science Center: GSFC’s Dr. Sten Odenwald, a THEMIS E/PO Formal Education Partner, discussed the THEMIS Mission science and provided activities for teachers and tips on how to share them with students. Planned: April 2007: Dave Sibeck to present THEMIS at “About Goddard” seminar Develop a feature presentation with SVS on Heliophysics for “Science on a Sphere” Space Chats at the GSFC Visitor Center GSFC View, Dateline, Intranet, poster boards Partner with public libraries for a Heliophysics speaker and special display of related materials Events/presentations at Maryland Science Center, Howard B. Owens Science Center and other community venues January 5, 2007 THEMIS Mission Readiness Review

PAO Responsibilities Education NASA GSFC: July NASA Explorer Schools Orientation Workshop and Distance Learning Network Workshop with presentations of Heliophysics science and solar classroom activities March Heliophysics Teacher Workshop for Stereo, THEMIS and AIM: science and classroom application activities using 3 new guides: “Exploring Magnetism”, “Exploring Magnetism in the Solar Wind” and “Exploring Magnetism in Solar Flares” Sun-Earth Day 2007/IHY - GSFC Visitor Center for local schools; theme is “Living in the Atmosphere of the Sun” January 5, 2007 THEMIS Mission Readiness Review

PAO Responsibilities UC Berkeley: Geomagnetic Event Observation Network by Students (GEONS) in which 10 magnetometers are placed in (or associated with) 13 schools across the country; receive data from the mission; teaches about Earth’s magnetic field and its changes that are related to auroral substorm activity Professional development for teachers, with a focus on the Tribal Colleges Planning to launch of a new Lawrence Hall of Science Great Explorations in Math and Science (GEMS) site in Nevada Creation and dissemination of a Space Telescope Science Institute ViewSpace show on auroras and THEMIS The THEMIS E/PO partnerships, methods, activities, and visibility are monitored and evaluated by Cornerstone Evaluation Associates (CEA); yearly formative evaluation reports are receieved and action taken as necessary Publications: “Exploring Magnetism,” “Exploring Magnetism on Earth,” “The Northern Lights” Development and maintenance of a THEMIS E/PO Web site. January 5, 2007 THEMIS Mission Readiness Review

PAO Responsibilities Post-Launch Events and Services: Contingency Press Briefing - If a launch contingency should occur, a briefing will be targeted for 2 hours after the contingency or as soon as significant information is available. Representatives from NASA, UC Berkeley, Swales and ULA will attend. GSFC Code-A-Phone and Web Page - Information regarding the THEMIS launch will be placed on the GSFC Code-A-Phone ( NEWS) and on the GSFC Web page. KSC will also update their Code-A-Phone beginning on L-3. January 5, 2007 THEMIS Mission Readiness Review

Guest Operations Guest Operations: NASA HQ in collaboration with GSFC, KSC, UC Berkeley, Swales and ULA Invitations mailed 4-6 weeks prior to launch Guests are encouraged to visit the Guest Operations Web site to RSVP and learn about updates to the schedule: Guest Operations typically include: Guest Check-in at the KSC Visitor Complex, beginning at L-1 Guest Briefing held on L-1 Transportation from Visitor Complex to launch viewing site Guests monitor launch schedule via NASA toll-free phone hotline Reception driven by contractor partners January 5, 2007 THEMIS Mission Readiness Review

Readiness Statement Frank Snow Mission Manager January 5, 2007 THEMIS Mission Readiness Review 196

Summary Summary Readiness to Proceed
Probes and Probe Carrier are Ready Plans and Procedures for Launch are Ready Mission Ops Center is Ready Ground Network Testing will be completed before 1/19/07 Ops Procedures & Personnel are Ready Ground Based Observatories are Ready Launch Vehicle – NASA LSP is ready for continued launch vehicle processing Key Reviews Safety/Mission Assurance Review 1/19/07 Mission Readiness Board 1/23/07 Flight Readiness Review 2/12/07 Launch Readiness Review 2/14/07

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Acronyms List (Page 1 of 8) January 5, 2007 THEMIS Mission Readiness Review

THEMIS Mission Readiness Review

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THEMIS Mission Readiness Review

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