January 5, 2007 THEMIS Mission Readiness Review. January 5, 2007THEMIS Mission Readiness Review 2 Mission Overview Mission Science/EPO System Engineering

January 5, 2007

THEMIS Mission

Readiness Review

January 5, 2007 THEMIS Mission Readiness Review 2

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



Frank Snow - Mission 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

Agenda


Mission Overview

Frank Snow

Mission Manager


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.


Organization

Mission Manager Frank Snow, GSFC

Mission Manager Frank Snow, GSFC

Financial MgrK. Harps, UCBFinancial MgrK. Harps, UCB

Launch Vehicle G. Skrobott, KSC

Launch Vehicle G. Skrobott, KSC

Project Scientist D. Sibeck, GSFC

Project Scientist D. Sibeck, GSFC

THEMIS PI V. Angelopoulos, UCB

THEMIS PI V. Angelopoulos, UCB

Project Manager P. Harvey, UCB

Project Manager P. Harvey, UCB

Science Co-I’s Science Co-I’s EPO N. Craig, UCB

EPO N. Craig, UCB

SubcontractsJ. Keenan, UCBSubcontracts

J. Keenan, UCBScheduling

D. Meilhan, UCBScheduling

D. Meilhan, UCBQuality

AssuranceR. Jackson, UCB

Quality Assurance

R. Jackson, UCB

Mission Systems

E. Taylor, UCB

Mission Systems

E. Taylor, UCB

Mechanical/ Thermal Systems

P. Turin, UCBC. Smith, UCB

Mechanical/ Thermal Systems

P. Turin, UCBC. Smith, UCB

Mag Cleanliness

C. Russell, UCLA

Mag Cleanliness

C. Russell, UCLA

Probe/Probe CarrierManagement

UCB Oversight: D. KingSwales Mgr: M. Cully

Probe/Probe CarrierManagement

UCB Oversight: D. KingSwales Mgr: M. Cully

Instruments

P. Berg, UCB

Instruments

P. Berg, UCB

Operations

M. Bester, UCB

Operations

M. Bester, UCB

Software Systems

D. King, UCB

Software Systems

D. King, UCB

Mission I&T

J. McCauley, UCBR. Sterling, UCB

Mission I&T

J. McCauley, UCBR. Sterling, UCB


TIME HISTORY OF EVENTS AND MACROSCALE

INTERACTIONS DURING SUBSTORMS (THEMIS)

RESOLVING THE PHYSICS OF ONSET AND EVOLUTION OF SUBSTORMS

Principal InvestigatorVassilis Angelopoulos, UCB

EPO LeadNahide Craig, UCB

Project ManagerPeter Harvey, UCB

Industrial PartnerSWALES Aerospace

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


LaunchVehicle: Delta II, Eastern RangeApogee: 91845.2 km ± 9567 kmPerigee: 435 km ± 10 km Inclination: 16.0 deg ± 0.5 degDate: February 15, 2007

Space SegmentSpacecraft: 5 Spinning Probes with Fuel for Orbit & Attitude

AdjustInstruments: 3-Axis Electric Field, Magnetic Field

3-D Ion & Electron Particle DetectorsSpin Rate: 20 RPMOrbit Period(s): 1, 2 and 4 daysOrientation: Ecliptic Normal

Ground SegmentObservatories: 20 Northern with All Sky Imagers and

MagnetometersControl Facilities: Mission and Science Operations Centers

OperationsPhases: L&EO, Cruise, Ascent, Campaigns, De-orbitLifetime:2.3 years

Mission Summary


Instrument Configuration

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


Fuel Tank

ESA

EFI SPB

Thruster T1

EFI Axial Booms (2, Stowed)

BatteryBAU

Repress Tank

Miniature Sun Sensor

Transponder

Thruster T2

IDPU

Fuel Tank

Antenna

EFI SPB

EFI SPB

Thruster A1

Thruster A2

AEB

Gyros

Probe Configuration


Ground Based Observatories

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

GeographicLongitude 324°

Geographic Longitude 195°

GeomagneticNorth Pole

GeographicNorth Pole


Ground Observatory Status

Unit # Location StatusGB0#02 Athabasca Operating normallyGB0#03 Prince George Down for Repair (/1)GB0#04 Ekati Diamond Mine Operating normallyGB0#06 The Pas Operating normallyGB0#07 Whitehorse Operating normallyGB0#08 Inuvik RF Interference (/2)GB0#09 Rankin Inlet RF Interference (/2)GB0#10 Fort Smith Operating normallyGB0#11 McGrath Operating normallyGB0#12 Fort Yukon Operating normallyGB0#13 Univ. of Calgary To Be Installed at NainGB0#14 Goose Bay RF Interference (/2)GB0#15 Kapuskasing Operating normallyGB0#16 Pinawa Operating normallyGB0#17 Chibougamau Operating normallyGB0#18 Gakona Operating normallyGB0#19 Gillam Operating normallyGB0#20 Kiana Operating normallyGB0#21 Ft. Simpson Operating normallyGB0#22 Sanikiluaq Operating normally

Ground Based ObservatoriesUnit # Location StatusGB0#02 Athabasca Operating normallyGB0#03 Prince George Down for Repair (/1)GB0#04 Ekati Diamond Mine Operating normallyGB0#06 The Pas Operating normallyGB0#07 Whitehorse Operating normallyGB0#08 Inuvik RF Interference (/2)GB0#09 Rankin Inlet RF Interference (/2)GB0#10 Fort Smith Operating normallyGB0#11 McGrath Operating normallyGB0#12 Fort Yukon Operating normallyGB0#13 Univ. of Calgary To Be Installed at NainGB0#14 Goose Bay RF Interference (/2)GB0#15 Kapuskasing Operating normallyGB0#16 Pinawa Operating normallyGB0#17 Chibougamau Operating normallyGB0#18 Gakona Operating normallyGB0#19 Gillam Operating normallyGB0#20 Kiana Operating normallyGB0#21 Ft. Simpson Operating normallyGB0#22 Sanikiluaq Operating normally


/1: Supply Down/2: Radar RF Noise


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


Pictures from JPL

Environmental Testing

Probe Carrier Assembly during Vibration

Installation of Thermal Vacuum Shrouds

Probe on GSFC Spin Balance Miller Table

Two Probes Ready for TV Testing


Probe Rollover Fixture in JPL Clean room

Probes in Storage, Ready for Launch Operations

Pictures from JPL



THEMIS Probe Carrier Assembly (PCA) in Launch Configuration

Pictures from JPL



Ground Stations

Ground StationStation

DesignatorFigure of

MeritLocation Function

Berkeley, CA BGS 11-m 24.0 dB/K37.879° N 122.243° W

Primary TLM/CMD/TRK

Wallops Island, VA WGS 11-m 23.0 dB/K37.925° N75.476° W

Secondary TLM/CMD/TRK

Merritt Island, FL MILA 9-m 1/2 21.6 dB/K28.508° N80.693° W


Santiago, Chile AGO 9-m 21.6 dB/K33.151° S70.668° W


Hartebeesthoek, SA HBK 10-m 20.4 dB/K25.883° S27.708° E


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


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

ProbeTDRSS Support

Launch Maneuver Contingency

1 1 h 19 h 2

2 19 h 2

3 2 h 2

4 2 h 2

5 5 h 2

Subtotal 1 h 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: 91845 km– Orbit Inclination: 16 degrees– Spacecraft (SC) Mass (will not exceed)

» 829 kg (2832.94lb) 775.60 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 - 162 rpm

• Mission Unique– 3712 Bolted PAF– Sep System (at PAF/PC Interface)

• Non-Standard Services– Category 1 Analysis

» (1st 7925-10C 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 19.6 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


Depletion Burn:Removes Stage 2 fromvicinity of spacecraft,while lowering Stage 2 perigee altitude andorbit inclination

Flight Profile

Liftoff

MECOt = 263.3 secAlt = 69.0 nmiVI = 20,060 fps

Second Stage Ignitiont = 276.8 secAlt = 72.9 nmiVI = 20,068 fps

Fairing Jettisont = 281.0 secAlt = 74.1 nmiVI = 20,103 fps

SECO 1t = 593.5 secAlt = 101.9 nmiVI = 25,923 fps

ORBIT:100 x 304 nmi28.50 deg inclination

Second Stage Restartt = 3859.4 secAlt = 282.7 nmiVI = 24,662 fps



TECOt = 4091.6 secAlt = 305.2 nmiVI = 33,975 fps

Separate Probe At = 4380.1 secAlt = 658.6 nmiVI = 32,368 fps

Orbit:235 x 49,592 nmi16.00 deg inclination-40.00 deg arg of per

SRM Impact SRM Impact

SRM Jettison (6)t = 66.0 / 67.0 secAlt = 9.9 / 10.2 nmiVI = 3,231 / 3,269 fps

SRM Jettison (3)t = 131.5 secAlt = 31.3 nmiVI = 8,018 fps

Third Stage Ignitiont = 4005.1 secAlt = 281.0 nmiVI = 25,775 fps

Note: Values shown are for 15-28 Feb 2007 launch


Integration Flow

Probe Fueling Probe RCS Electr. Verif.

Weigh Wet Probes, Attach Pyro

PCA Funct.Spin Balance

PCA Comm Check @ Blockhouse

Install Pyro Signal SMDC/ Weigh PCA

Engr Walk-down/ Trans- port Preps

Move Probes to HPF

Weigh PCA

PCA Mate to 3rd Stage/ Clamp-band Instl

Transport to Pad

S/C Functional & RF Test

Launch Rehearsal

Power On & Stray Voltage

Install Fairing

Prop. Load Prep

2nd Stage Fueling, Ordnance

Launch Readiness Review

La

un

ch

Sh

ipp

ing

fr

om

JP

L 12/08/06

12/21/06

02/02/07

02/15/0702/14/07

ASTROTECH and Launch Pad Flow

12/11/06 12/12/06

01/08/07

01/15/07

01/13/0701/05/0712/22/06

12/13/06

02/03/07 02/05/07 02/12/07 02/13/07

PCA Functional

01/23/0701/22/07

12/23/06 01/02/07

Reserve

Christmas Shutdown

12/11/06to

12/18/06

12/19/06

12/15/06

12/11/06

THEMIS Launch

01/03/07

02/07/0702/06/07

12/15/0612/14/06 12/19/0612/15/06 12/20/0612/19/06

5 Probes plus EGSE, MGSE at ASO

Probe Carrier Unpack

Unpack, Setup EGSE

PC-VCO Electrical Test

Install Sep. Harness

Install SMDC Lines

F1 RCS MEOP, LPT, S/A Test

Install Bolt Cutters, Therm. Closeouts

F2-3 RCS MEOP, LPT, S/A Test


Weigh, Move to Stands

Pre-VosMRR (GSFC)

01/0301/05

LVRR (KSC) 01/12

Media Day 01/12

01/09/07 01/10/07 01/11/07 01/12/07

MRR (HQ) 01/23

01/24/07 01/25/07 01/26/07 01/27/07 01/29/07 01/30/07

LSRR (CCAFS) 02/01

01/3107 02/01/07

02/09/0702/08/07

LMCM (KSC) 02/13FRR (KSC) 02/12



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 590 - Assoc. Division Chief, Champion Team Chair

–Rick Schnurr 560 - Chief Electrical Systems Architect

–Tom McCarthy 500 - 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)

RESOLVING THE PHYSICS OF ONSET AND EVOLUTION OF SUBSTORMS

Principal InvestigatorVassilis Angelopoulos, UCB

EPO LeadNahide Craig, UCB

Project ManagerPeter Harvey, UCB

Industrial PartnerSWALES Aerospace

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


Auroral Eruptions and Substorms

Auroral eruptions…

AuroraAurora

…are a manifestation ofmagnetospheric substorms

MAGNETOSPHERESO

LAR

WIN

D

EQUATORIAL PLANE


Mission ElementsProbe 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 producesstorm-time “killer” MeV electrons?

Affect satellites and humans in space

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

ANIK telecommunicationsatellites lost for days to weeks

during space storm


Second bonus: What controls efficiencyof 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 withNASA’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 ObjectivesTHEMIS 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 (P/dz, P/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).

– YP1/2/3/4/5<±2RE; ZP3,4,5/NS<±2RE; ZP1,2/NS<±5RE

Actual conjunction times in 1st year

Science orbits P1 P2 P3 P4 P5Period (days) 4 2Apogee (RE) 30 19 12 12 12

Perigee (RE) 1.5 1.2

Inc @ midtail

Drift @ apg., @6:30UT

Knowledge @ apg.

Y<1RE/month

100 km

1

1.16

~7o ~9o

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, 2007Conjunctions are robust

Nominal deltaV marginfor 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 1

Dayside

Tail 2

Baseline Requirement

Minimum Requirement




SST

ESA

EFIa

EFIs

FGM

SCM

Tspin=3s

1 FGM: Low freq. B-field (0-64Hz)1 ESA: Thermal plasma2 SSTh (heads): Super-thermal plasma1 SCM: High freq. B-field (1Hz-4kHz)4 EFIs (spin plane) &2 EFIa (axials): Low&High freq. E-field

Instruments Required:Redundancy and Overlap

Instruments required for Primary Mission Objective (Substorms)

Measurement goals P1 P2 P3 P4 P5Tim

e History of E

vents

P3,4&5 monitor CDP1,2 bracket Rxtres<30s, Y<±2RE

FGM

1SSTh

2EFIs

FGM

ESA

2SSTh

2EFIs

FGM

ESA

1SSTh

FGM

ESA

1SSTh

FGM

ESA

1SSTh

Macroscale Interactions

Track rarefaction wave, inward flows, Poynting with B<1nT, V/V~10%

FGM

ESA

FGM

ESA

FGM

ESA

FGM

ESA

Radial/cross-sheet pressure, velocity and current gradients require P/P~ V/V ~ B/B ~10%, non-MHD

FGM

ESA

FGM

ESA

2EFIs

FGM

ESA

2EFIs

FGM

ESA

2EFIs

Cross-tail pairs measure FLRs, KH, ballooning on B, V, P @ 10s and fast modes on Bxyz and Exy @ 60 Hz

FGMESA SCM

FGMESA

SCM 4EFIs2EFIa

FGM

ESA

2EFIs

FGM

ESA

SCM 4EFIs2EFIa

SU

MM

AR

Y

Minimum mission (Red)

Baseline add-ons (green)

FGM

1SSTh

2EFIs

FGM

ESA

2SSTh

SCM2EFIs

FGM

ESA

1SSTh

SCM 4EFIs2EFIa

FGM

ESA

1SSTh

2EFIs

FGM

ESA

1SSTh

SCM 4EFIs2EFIa


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)


• 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)

… continued: Baseline L1 Requirements


Minimum L1 Requirements (from L1’s)

• 4.1.2.1 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.

• 4.1.2.2 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 CD site (~8-10 Re). …(same as baseline)

• 4.1.2.3 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)

• 4.1.2.4 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.

• 4.1.2.5 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

• Meetings• Yearly post-AGU meetings at UCB since 2003

• “Data analysis tools” meeting at UCB, Nov-15-2006

– 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 13-15 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:http://themis.ssl.berkeley.edu/beta

– 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:http://themis.ssl.berkeley.edu

– 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:http://sscweb.gsfc.nasa.gov/ Thanks to excellent support from SPDF!

– Orbit visualization via “tipsod”: a Java – based software


Web-based L2 overview plot distribution (4)

http://themis.ssl.berkeley.edu/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


• 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 Carson City NV

Bay Mills College

THEMIS EPO Program


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

Magnetometer Data at Schools


• 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 THEMISAudience: ~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

Education Activities Examples


Public Outreach Examples

SAWANO NEWS (WI), Feb-2006


Systems Engineering

Peter Harvey

Project Manager


Design• 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

Systems Agenda


LaunchVehicle: Delta II, Eastern RangeApogee: 91845.2 km ± 9567 kmPerigee: 435 km ± 10 km (500 km ± 7 km on or after

3/1/2007)Inclination: 16.0 deg ± 0.5 degDate: February 15, 2007

Space SegmentSpacecraft: 5 Spinning Probes with Fuel for Orbit & Attitude

AdjustInstruments: 3-Axis Electric Field, Magnetic Field

3-D Ion & Electron Particle DetectorsSpin Rate: 20 RPMOrbit Period(s): 1, 2 and 4 daysOrientation: Ecliptic Normal

Ground SegmentObservatories: 20 Northern with All Sky Imagers and

MagnetometersControl Facilities: Mission and Science Operations Centers

OperationsPhases: L&EO, Cruise, Ascent, Campaigns, De-orbitLifetime: 2.3 years

Mission Summary


Instrument Configuration

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


Fuel Tank

ESA

EFI SPB

Thruster T1

EFI Axial Booms (2, Stowed)

BatteryBAU

Repress Tank

Miniature Sun Sensor

Transponder

Thruster T2

IDPU

Fuel Tank

Antenna

EFI SPB

EFI SPB

Thruster A1

Thruster A2

AEB

Gyros

Probe Configuration


Standard Delta 10 ft. Fairing Static Envelope

3712 PAF

Probe Carrier Assembly (PCA = 5 Probes + Probe Carrier) on L/V

Probe Carrier Assembly (PCA = 5 Probes + Probe Carrier) on L/V

THEMIS Launch Configuration

THEMIS Launch Configuration

Probe Carrier Assembly (PCA) on Delta 3rd StageProbe Carrier Assembly (PCA) on Delta 3rd Stage

Launch ConfigurationDedicated launch

accommodated within standard Delta 7925-10 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

Star 48 3rd Stage


Mission Profile


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 Status


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 Waived


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)

Requirements Pending


Mission Profile Review for Feb 15, 2007 Launch• EFI Boom Deploy delayed ~ 9 months on Probes 1 & 5

– THEMIS Deployment Motors Life Test (21 mo @ 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

New Mission Profile


Mass Status

• < 2% mass deviation between Probes (requirement)• Dry Mass Margin: 4.5% (Worst case)

Power Status• Probe CBE: 38.7 W• Probe Capability: 40.60 W• Probe Margin: 8.8% (First 3-hour Eclipse Season)

4.9% (Second 3- hour Eclipse Season)

Resources

Mass(Kg) F1 F2 F3 F4 F5Measured 78.04 77.62 76.72 76.72 78.08NTE 81.80 81.80 81.80 81.80 81.80Margin 3.76 4.18 5.08 5.08 3.72% 4.6% 5.1% 6.2% 6.2% 4.5%


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: 120-150 failure free hours were accumulated on all components during Probe Level TVac. Components accumulated and average of 250 hours during Component Level TVac.

Operating Hours

0

50

100

150

200

250

300

350

400

450

500

Hours Failure Free

F1

F2

F3

F4

F5


PFR Statistics (All Spacecraft)

• Total : 237

• Closed : 237

• Open : 0

• Unverifiable Failures : 13

• Operational Work-Arounds : 10

Problem/Failure Reports


Unverifiable Failures

PFR # Problem Description Highest Probability AssessmentPFR 039 FGM Telem Errors Memory Configuration LOW: Temporary Data LossPFR 062 EFI V1 Signal Loss Sphere Grounded in Chassis LOW: Non-Flight ConfigurationPFR 070 IDPU Command Loss DMA Channel Issue LOW: Hardware ModifiedPFR 074 SST Chan 2 Data Loss FPGA Low Voltage. LOW: Hardware ModifiedPFR 108 EEPROM Load Error Writing too fast. LOW: Procedure ModifiedPFR 121 IDPU ETU Current over

specMis-measurement LOW: Minimal Current

PFR 130 BAU corrupting IDPU cmds IDPU DMA Channel Issue LOW: Hardware Modified


PFR 147 BAU reset Break-out configuration MED: Operational complexity

PFR 161 Receiver lock prior to vib JPL Local transmitter LOW: No commands receivedPFR 172 K1 Battery Relay flipped GSE initial turn-on LOW: Only affected monitorSAI 0215 BAU reset and cmd loss GSE Power supply too low LOW: Non-Flight Configuration

SAI 0340 Thruster stops out of range. ITOS timing error LOW: Non-Flight Configuration

PFR # Problem Description Highest Probability AssessmentPFR 039 FGM Telem Errors Memory Configuration LOW: Temporary Data LossPFR 062 EFI V1 Signal Loss Sphere Grounded in Chassis LOW: Non-Flight ConfigurationPFR 070 IDPU Command Loss DMA Channel Issue LOW: Hardware ModifiedPFR 074 SST Chan 2 Data Loss FPGA Low Voltage. LOW: Hardware ModifiedPFR 108 EEPROM Load Error Writing too fast. LOW: Procedure ModifiedPFR 121 IDPU ETU Current over

specMis-measurement LOW: Minimal Current



PFR 147 BAU reset Break-out configuration MED: Operational complexity

PFR 161 Receiver lock prior to vib JPL Local transmitter LOW: No commands receivedPFR 172 K1 Battery Relay flipped GSE initial turn-on LOW: Only affected monitorSAI 0215 BAU reset and cmd loss GSE Power supply too low LOW: Non-Flight Configuration

SAI 0340 Thruster stops out of range. ITOS timing error LOW: Non-Flight Configuration


Operational WorkArounds

PFR Probe System Problem Description Operational Work-around030 A-E IDPU PCB FPGA command lockout SAFE Before Actuation Retry075 A-E ESA ESA Surge Current Disable Current Trip in Turn On164 A-E ESA ESA Supply Noise when Off Turn On ESA 183 A EFI EFI V6 Selt-test Signal Loss Ignore EFI V6 Self Test205 A-E Thermal RCS Cold Spot w/ only secondary Turn On RCS Primary Heaters210 A-E BAU RCS Missing First Pulse Start Maneuvers w/ "Stop" cmd226 A Thermal Swapped Temperature Monitors Reverse mnemonics230 A-E BAU Inaccurate 20Hz thruster counter Use VC4 data for verification231 A-E BAU Inaccurate Command Timer Do not use command timer.0339 A-E BAU IRU Noisy Measurements Ignore first samples of ACS

PFR Probe System Problem Description Operational Work-around030 A-E IDPU PCB FPGA command lockout SAFE Before Actuation Retry075 A-E ESA ESA Surge Current Disable Current Trip in Turn On164 A-E ESA ESA Supply Noise when Off Turn On ESA 183 A EFI EFI V6 Selt-test Signal Loss Ignore EFI V6 Self Test205 A-E Thermal RCS Cold Spot w/ only secondary Turn On RCS Primary Heaters210 A-E BAU RCS Missing First Pulse Start Maneuvers w/ "Stop" cmd226 A Thermal Swapped Temperature Monitors Reverse mnemonics230 A-E BAU Inaccurate 20Hz thruster counter Use VC4 data for verification231 A-E BAU Inaccurate Command Timer Do not use command timer.0339 A-E BAU IRU Noisy Measurements Ignore first samples of ACS


Integration and Test

Peter Harvey

Project Manager


Integration Agenda

Recent Activities• 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

Thermal Vacuum

Acoustics

Spin Balance

EMC

VibrationMagnetics


Probe Processing

Bolt Cutter Installation

Performance Tests

Solar Array Illumination

Delivery to ASO


Probe Fueling Preps

FM2/FM3 Thermal Vacuum

Vibration

Thermal Vacuum

Acoustics Spin Balance

Storage

Dry Weigh & Pressurize Ready for Fuel


Carrier Processing

Vibration Acoustics Spin Balance

Storage

PC Unload

SSS Installation

Ready for Probes


Instrument Status

Instrument StatusFlight Hardware Ready

Flight Software Ready

Recent Activities

Performance Test

Remaining Items

ESC Verification

SST/ESA Covers

EFI Hats

Contamination Samples

Instruments F1 F2 F3 F4 F5IDPU Complete Complete Complete Complete CompleteFSW 4.02 4.02 4.02 4.02 4.02EFI Complete Complete Complete Complete CompleteESA Complete Complete Complete Complete CompleteSST Complete Complete Complete Complete CompleteFGM Complete Complete Complete Complete CompleteSCM Complete Complete Complete Complete CompleteMagBoom Complete Complete Complete Complete CompleteIntegration Complete Complete Complete Complete CompleteTest Complete Complete Complete Complete CompleteEMC CompleteTV Complete Complete Complete Complete CompleteMagnetics Complete Complete Complete Complete CompleteESA Recal Complete Complete Complete Complete Complete

Instruments F1 F2 F3 F4 F5IDPU Complete Complete Complete Complete CompleteFSW 4.02 4.02 4.02 4.02 4.02EFI Complete Complete Complete Complete CompleteESA Complete Complete Complete Complete CompleteSST Complete Complete Complete Complete CompleteFGM Complete Complete Complete Complete CompleteSCM Complete Complete Complete Complete CompleteMagBoom Complete Complete Complete Complete CompleteIntegration Complete Complete Complete Complete CompleteTest Complete Complete Complete Complete CompleteEMC CompleteTV Complete Complete Complete Complete CompleteMagnetics Complete Complete Complete Complete CompleteESA Recal Complete Complete Complete Complete CompleteIDPU FSW F1 F2 F3 F4 F5Image1 4.02 4.02 4.02 4.02 4.02Image2 4.02 4.02 4.02 4.02 4.02Image3 4.02 4.02 4.02 4.02 4.02Image4 4.02 4.02 4.02 4.02 4.02ETC 5.A 5.B 5.C 5.D 5.EF5.BEB B0-c B0-c B0-c B0-c B0-cF6.BEB B1-c B1-c B1-c B1-c B1-cF7.BEB B2-c B2-c B2-c B2-c B2-cF8.BEB B3-c B3-c B3-c B3-c B3-cF9.DFB D1 D1 D1 D1 D1FA.DAP 12 12 12 12 12

IDPU FSW F1 F2 F3 F4 F5Image1 4.02 4.02 4.02 4.02 4.02Image2 4.02 4.02 4.02 4.02 4.02Image3 4.02 4.02 4.02 4.02 4.02Image4 4.02 4.02 4.02 4.02 4.02ETC 5.A 5.B 5.C 5.D 5.EF5.BEB B0-c B0-c B0-c B0-c B0-cF6.BEB B1-c B1-c B1-c B1-c B1-cF7.BEB B2-c B2-c B2-c B2-c B2-cF8.BEB B3-c B3-c B3-c B3-c B3-cF9.DFB D1 D1 D1 D1 D1FA.DAP 12 12 12 12 12


Probe Status

Probe StatusHardware 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

Probe F1 F2 F3 F4 F5Structures Complete Complete Complete Complete CompleteSep Systems Complete Complete Complete Complete CompleteSolar Arrays Complete Complete Complete Complete CompleteBAU 103 101 105 104 102FSW Image 1 V3.19 V3.19 V3.19 V3.19 V3.19FSW Image 2 V3.19 V3.19 V3.19 V3.19 V3.19RTS Complete Complete Complete Complete CompleteRCS Complete Complete Complete Complete CompleteTransponder Complete Complete Complete Complete CompleteAntenna Complete Complete Complete Complete CompleteBattery Complete Complete Complete Complete CompleteHarness Complete Complete Complete Complete CompleteIRU Complete Complete Complete Complete CompleteAEB Complete Complete Complete Complete CompleteBus CPT Complete Complete Complete Complete CompleteCTV Test CompleteInstrument I&T Complete Complete Complete Complete CompleteProbe CPT Complete Complete Complete Complete CompleteEMC CompleteVibration Complete Complete Complete Complete CompleteTV Complete Complete Complete Complete CompleteMagnetics Complete Complete Complete Complete CompleteSpin Balance Complete Complete Complete Complete CompletePressurize Complete Complete Complete Complete CompleteFuel Empty Empty Empty Empty EmptySafing Plugs NonFlight NonFlight NonFlight NonFlight NonFlight


Integration Flow

Probe Fueling Probe RCS Electr. Verif.

Weigh Wet Probes, Attach Pyro

PCA Funct.Spin Balance

PCA Comm Check @ Blockhouse

Install Pyro Signal SMDC/ Weigh PCA

Engr Walk-down/ Trans- port Preps

Move Probes to HPF

Weigh PCA

PCA Mate to 3rd Stage/ Clamp-band Instl

Transport to Pad

S/C Functional & RF Test

Launch Rehearsal

Power On & Stray Voltage

Install Fairing

Prop. Load Prep

2nd Stage Fueling, Ordnance

Launch Readiness Review

La

un

ch

Sh

ipp

ing

fr

om

JP

L 12/08/06

12/21/06

02/02/07

02/15/0702/14/07

ASTROTECH and Launch Pad Flow

12/11/06 12/12/06

01/08/07

01/15/07

01/13/0701/05/0712/22/06

12/13/06

02/03/07 02/05/07 02/12/07 02/13/07

PCA Functional

01/23/0701/22/07

12/23/06 01/02/07

Reserve

Christmas Shutdown

12/11/06to

12/18/06

12/19/06

12/15/06

12/11/06

THEMIS Launch

01/03/07

02/07/0702/06/07

12/15/0612/14/06 12/19/0612/15/06 12/20/0612/19/06

5 Probes plus EGSE, MGSE at ASO

Probe Carrier Unpack

Unpack, Setup EGSE

PC-VCO Electrical Test

Install Sep. Harness

Install SMDC Lines

F1 RCS MEOP, LPT, S/A Test

Install Bolt Cutters, Therm. Closeouts



Weigh, Move to Stands

Pre-VosMRR (GSFC)

01/0301/05

LVRR (KSC) 01/12

Media Day 01/12

01/09/07 01/10/07 01/11/07 01/12/07

MRR (HQ) 01/23

01/24/07 01/25/07 01/26/07 01/27/07 01/29/07 01/30/07

LSRR (CCAFS) 02/01

01/3107 02/01/07

02/09/0702/08/07

LMCM (KSC) 02/13FRR (KSC) 02/12



RFAs

Issue SubmittedRCS Proof Tests Jan 17 2006BAU EEPROM Signal Plots Jun 23 2006Energy Balance in Deep Eclipse Jun 26 2006Launch Window Analysis Nov 09 2006

Issue SubmittedRCS Proof Tests Jan 17 2006BAU EEPROM Signal Plots Jun 23 2006Energy Balance in Deep Eclipse Jun 26 2006Launch Window Analysis Nov 09 2006

RFA StatusIncomplete: 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

Start Event Description1/5/2007 MRR Mission Readiness Review

1/12/2007 LVRR Launch Vehicle Readiness Review1/19/2007 SMSR Systems and Safety Mission Assurance1/23/2007 MRB Mission Readiness Review2/1/2007 LSRR Launch Site Readiness Review

2/12/2007 FRR Flight Readiness Review 2/13/2007 LRR Launch Readiness Review


Operations

Peter Harvey

Project Manager


Operations Agenda

Ground Systems Development• Ground System Diagram• Mission Operations Center• Ground Stations• RF Licencing• Security• Software• Procedures• Verification and Training• GSFC Support

Launch and Early OrbitContacts Ground Based Observations


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


Mission Operations Center

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


MOC Expansion


Ground Stations

Ground StationStation

DesignatorFigure of

MeritLocation Function

Berkeley, CA BGS 11-m 24.0 dB/K37.879° N 122.243° W

Primary TLM/CMD/TRK

Wallops Island, VA WGS 11-m 23.0 dB/K37.925° N75.476° W


Merritt Island, FL MILA 9-m 1/2 21.6 dB/K28.508° N80.693° W


Santiago, Chile AGO 9-m 21.6 dB/K33.151° S70.668° W


Hartebeesthoek, SA HBK 10-m 20.4 dB/K25.883° S27.708° E


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


NTIA License

NTIA License Status• Identical Frequency Pairs for All Probes Assigned by GSFC

Spectrum Management Office– Telemetry: 2282.5 MHz– Command: 221 / 240 × 2282.5 = 2101.802083 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

– 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

Solaris Version 2003.01 Operational in FDC

GMAN GSFC Finite Maneuver Targeting and Reconstruction

Solaris Version 1994.03PC Operational in FDC

SatTrack BTS Pass Scheduling, Product Generation, Networking, 3-D Visualization, Ground Station Control

Solaris, Linux

Version 4.6.1 Operational in MOC, FDC and BGS

MSASS GSFC Attitude Determination Solaris, Windows XP

Version 2005.03 To Be Installed in MOC and FDC by L - 2 Months

CALIBATT GSFC Attitude Maneuver Calibration

Solaris, Windows XP

Version 2005.01 Operational in FDC


Software Status

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 Hammers 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 UCB Probe Bus and Instrument Trend Analysis

Solaris Operational in MOC

MOC Software CompleteCurrently Under Pre-Launch Software Freeze


Procedures

ID LEO PROCEDUREthm-fop-proc-001 THEMIS Probe Separation thm-fop-proc-002 THEMIS Probe Checkout Procedure (round-robin)thm-fop-proc-003 THEMIS Probe Latch Valves Open and Maneuver Checkoutthm-fop-proc-004 THEMIS Probe Sun-Normal Attitude Manueverthm-fop-proc-005 THEMIS Probe Maneuver Pass Procedurethm-fop-proc-006 THEMIS Pyro Valve Open Procedurethm-fop-proc-101 THEMIS IDPU Power-On and Check-out Procedurethm-fop-proc-102 THEMIS FGM Commissioning Procedurethm-fop-proc-103 THEMIS SCM/EFI Commissioning Procedurethm-fop-proc-104 THEMIS Mag Boom Deploy Procedurethm-fop-proc-105 THEMIS SST Commissioning Procedurethm-fop-proc-106 THEMIS ESA Commissioning Procedurethm-fop-proc-107 THEMIS ESA HV Ramp Up Procedurethm-fop-proc-108 THEMIS ESA Cover Open Procedurethm-fop-proc-109 THEMIS SPB Door Open Procedurethm-fop-proc-110 THEMIS SPB Motor Deploy Procedurethm-fop-proc-111 THEMIS AXB Deploy Procedurethm-fop-proc-112 THEMIS SDT Upload Procedurethm-fop-proc-113 THEMIS IDPU EEPROM/RAM Load Order Form

ID LEO PROCEDUREthm-fop-proc-001 THEMIS Probe Separation thm-fop-proc-002 THEMIS Probe Checkout Procedure (round-robin)thm-fop-proc-003 THEMIS Probe Latch Valves Open and Maneuver Checkoutthm-fop-proc-004 THEMIS Probe Sun-Normal Attitude Manueverthm-fop-proc-005 THEMIS Probe Maneuver Pass Procedurethm-fop-proc-006 THEMIS Pyro Valve Open Procedurethm-fop-proc-101 THEMIS IDPU Power-On and Check-out Procedurethm-fop-proc-102 THEMIS FGM Commissioning Procedurethm-fop-proc-103 THEMIS SCM/EFI Commissioning Procedurethm-fop-proc-104 THEMIS Mag Boom Deploy Procedurethm-fop-proc-105 THEMIS SST Commissioning Procedurethm-fop-proc-106 THEMIS ESA Commissioning Procedurethm-fop-proc-107 THEMIS ESA HV Ramp Up Procedurethm-fop-proc-108 THEMIS ESA Cover Open Procedurethm-fop-proc-109 THEMIS SPB Door Open Procedurethm-fop-proc-110 THEMIS SPB Motor Deploy Procedurethm-fop-proc-111 THEMIS AXB Deploy Procedurethm-fop-proc-112 THEMIS SDT Upload Procedurethm-fop-proc-113 THEMIS IDPU EEPROM/RAM Load Order Form

ID LEO CONTINGENCY PROCEDUREthm-cop-proc-001 THEMIS Cold Reset Recovery Procedurethm-cop-proc-002 THEMIS Load Shed Recovery Procedurethm-cop-proc-003 THEMIS Mag Boom Back-up Deploy Procedurethm-cop-proc-004 THEMIS AXB Back-up Deploy Procedurethm-cop-proc-005 THEMIS ESA Back-up Cover Open Procedurethm-cop-proc-006 THEMIS Latch Valve Anomaly Procedurethm-cop-proc-007 THEMIS Inadvertent Firing of Pyro Valve Contingency Procedurethm-cop-proc-008 THEMIS BAU FSW Image Uploadthm-cop-proc-009 THEMIS IDPU FSW Image Upload

ID LEO CONTINGENCY PROCEDUREthm-cop-proc-001 THEMIS Cold Reset Recovery Procedurethm-cop-proc-002 THEMIS Load Shed Recovery Procedurethm-cop-proc-003 THEMIS Mag Boom Back-up Deploy Procedurethm-cop-proc-004 THEMIS AXB Back-up Deploy Procedurethm-cop-proc-005 THEMIS ESA Back-up Cover Open Procedurethm-cop-proc-006 THEMIS Latch Valve Anomaly Procedurethm-cop-proc-007 THEMIS Inadvertent Firing of Pyro Valve Contingency Procedurethm-cop-proc-008 THEMIS BAU FSW Image Uploadthm-cop-proc-009 THEMIS IDPU FSW Image Upload

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• FDAB 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)

GSFC Support


LEO Operations

LEO Operations• State Vector Delivered to UCB via email @ 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 AcquisitionMultiple Ground Assets Have Good View Following LaunchProbe 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

Probe Bus / Simulator Name

Probe Bus ID

Instrument Suite ID

CCSDS V1 Command

SCID

CCSDS V1 Telemetry

SCID

NASA Support Identification

Code

Satellite Catalog

Number *

International Designator *

Constellation Identifier **

THEMISFlatSat West N/A N/A 0x150 0x150 N/A N/A N/A N/A

THEMIS A F1 FM1 0x153 0x153 0451 99001 2007-001A P1

THEMIS B F2 FM2 0x151 0x151 0452 99002 2007-001B P2

THEMIS C F3 FM3 0x155 0x155 0453 99003 2007-001C P3

THEMIS D F4 FM4 0x154 0x154 0454 99004 2007-001D P4

THEMIS E F5 FM5 0x152 0x152 0455 99005 2007-001E P5

THEMIS Spare N/A N/A 0x156 0x156 N/A N/A N/A N/A

THEMISFlatSat East N/A N/A 0x157 0x157 N/A N/A N/A N/A

* Assigned after Launch ** Assigned after Probe Placement Decision

LEO Probe Identification• Provides Unique Relationship between Various Probe Identifiers• Extensively Tested during Mission Integration


Contacts - Typical

Entire Ground Station View Periods at Nominal Low Data Rate of 4.096 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

ProbeBGS WGS AGO HBK

L&EO Science L&EO Science L&EO Science L&EO Science

1 150 750 60 50 30 20 20 20

2 150 750 60 90 30 20 20 30

3 150 750 60 20 30 20 20 20

4 150 750 60 20 30 20 20 20

5 150 750 60 150 30 60 20 40

Subtotal 750 3750 300 330 150 140 100 130

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

ProbeTDRSS Support

Launch Maneuver Contingency

1 1 h 19 h 2

2 19 h 2

3 2 h 2

4 2 h 2

5 5 h 2

Subtotal 1 h 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

GeographicLongitude 324°

Geographic Longitude 195°

GeomagneticNorth Pole

GeographicNorth Pole


Ground Observatory Status

Unit # Location StatusGB0#02 Athabasca Operating normallyGB0#03 Prince George Down for Repair (/1)GB0#04 Ekati Diamond Mine Operating normallyGB0#06 The Pas Operating normallyGB0#07 Whitehorse Operating normallyGB0#08 Inuvik RF Interference (/2)GB0#09 Rankin Inlet RF Interference (/2)GB0#10 Fort Smith Operating normallyGB0#11 McGrath Operating normallyGB0#12 Fort Yukon Operating normallyGB0#13 Univ. of Calgary To Be Installed at NainGB0#14 Goose Bay RF Interference (/2)GB0#15 Kapuskasing Operating normallyGB0#16 Pinawa Operating normallyGB0#17 Chibougamau Operating normallyGB0#18 Gakona Operating normallyGB0#19 Gillam Operating normallyGB0#20 Kiana Operating normallyGB0#21 Ft. Simpson Operating normallyGB0#22 Sanikiluaq Operating normally

Ground Based ObservatoriesUnit # Location StatusGB0#02 Athabasca Operating normallyGB0#03 Prince George Down for Repair (/1)GB0#04 Ekati Diamond Mine Operating normallyGB0#06 The Pas Operating normallyGB0#07 Whitehorse Operating normallyGB0#08 Inuvik RF Interference (/2)GB0#09 Rankin Inlet RF Interference (/2)GB0#10 Fort Smith Operating normallyGB0#11 McGrath Operating normallyGB0#12 Fort Yukon Operating normallyGB0#13 Univ. of Calgary To Be Installed at NainGB0#14 Goose Bay RF Interference (/2)GB0#15 Kapuskasing Operating normallyGB0#16 Pinawa Operating normallyGB0#17 Chibougamau Operating normallyGB0#18 Gakona Operating normallyGB0#19 Gillam Operating normallyGB0#20 Kiana Operating normallyGB0#21 Ft. Simpson Operating normallyGB0#22 Sanikiluaq Operating normally


/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 ChiefEngineer

James Wood

NASA Advisory Team

NASA AdvisoryManager

Joe Lackovich

NASA Launch ManagerChuck Dovale

Boeing Mission Director

Rich Murphy

NASA ENGINEERING Go / No-Go

ADVISORY

NASA Go / No-Go

MDC LVDC

MDC

MDC

Safety & Mission AssuranceRick Boutin

MDC

NASA SMAGo / No-Go

NASA ALM

NASA MIT

MissionIntegration Manager

Garrett Skrobot

MISSION INTEGRATIONGo / No-Go

Spacecraft Mission Director

Frank Snow

Go / No-Go

INFO

MDCMDC

SMDGo / No-Go

THEMIS Project Manager

Peter Harvey

Ground Operations Manager

Donald GatesMDC

Go / No-Go

MDC

NASA SMA Team

GSFC Safety & Mission Assurance

ManagerRon Perison MDC

Go / No-Go

Spacecraft Test ConductorDave Curtis

LVDC

Go / No-GoGSFC

Go / No-Go

Spacecraft I&T Manager

Rick SterlingASO

MissionOperations Manager

Manfred BesterMOC

Go / No-GoGo / No-Go

Go / No-Go


THEMIS Launch Decision Flow

LVDC-3

Astrotech(ASO)

UCB Mission Operations Center

(MOC)

Go/No-Go

LaunchDecision

MissileChief Engineer

(Boeing)

Vehicle Status

OperationsBuilding (OB)

Status

Mission Director Center (MDC)

MissionDirector(Boeing)

Status

RangeCoordinator

(Boeing)

StatusLaunchConductor(Boeing)

LaunchDirector(Boeing)

LaunchConcur

Range Operations

Control Center

• Range Safety Status

• Range Status

• Weather• Support Range Status (LV)

RangeControl Officer

LVDC

Launch VehicleSystems

Engineering(Boeing)

WINDS(Boeing)

NASA AdvisoryManager

(KSC)

Dir. of Eng.(Boeing)

Status

L/V Sys Status

Advisory

CMDRS NET

USAF45 SW/CCSpace Lift

Commander(SLCC)

NASAChief Engineer

(KSC)

Status

Go/No-Go

Go/No-Go

NASAMission

IntegrationMngr (KSC)

NASALaunchManager

(KSC)

Go/No-Go

StatusNASASpacecraft

Coordinator(KSC)

Go/No-Go

AF SiteDirector(1 SLS)

AF LaunchCrew

Commander(1 SLS)

Status

OperationsIntegrator(Boeing) Go/No-Go

MDC OpsDirector

(KSC)

SpacecraftTest

Conductor(UCB)

Go/No-Go

Go/No-Go

Status

Go/No-Go

Status

Spacecraft Mission Director(GSFC)

THEMISProject Manager

(UCB)

GSFCSafety & Mission Assurance Mngr

(GSFC)

NASASafety & Mission Assurance Mngr

(KSC)

Go/No-Go

Go/No-Go

SpacecraftI&T Manager

(UCB)

Go/No-Go

GroundOperations

Manager(GSFC)

GSFC Network Operations

Manager (GSFC)

GSFC

Go/No-Go

Go/No-Go

NASAEngineeringTeam (KSC)

Go/No-GoMission

Operations Manager

(UCB)

Go/No-Go


THEMIS Anomaly Resolution

Spacecraft Only

Anomaly

NASA Launch Manager's Net

LaunchVehicle / Integrated Anomaly

Boeing SLC-17 TeamNASA Engineering Team

Boeing HB Engineering Team

NLMNASA Launch Manager

Chuck Dovale

MDMission Director

Rich Murphy

MCEMissile Chief Engineer

Steve Huff

VSEVehicle Systems Engineer

Greg Radle

NASA CENASA Chief Engineer

James Wood

MissionManagement

Net

Anomaly Team

Anomaly NetOr

Boeing Mgmt Net

Anomaly NetOr

Boeing Mgmt Net

CLCDRLaunch Conductor

Bob Godin

DEDirector of Engineering

Dave Crosse

Integrated Anomaly Only

S/C Eng / Ops Team

Resource Protection

USAF CX-17 Engineering Team

LDLaunch DirectorMark Dowhan

MSEMission Systems Engineer

Stu Harris

ARCUSAF Anomaly Resolution Chief

Bryan Buckley

SMDSpacecraft Mission

DirectorFrank Snow

VIP SEATING AREA

-Network Drop for LaptopsXXXX

THEMIS Mission Director’s Center

BOEINGKRIS WALSHASST MISSION DIRECTOR

BOEINGRICH MURPHYMISSION DIRECTOR

ANALEX/KSCTRACY EVANSASST MISSION OPS DIR

NASA/KSCTUAN DOANMISSION OPS DIRECTOR

1ST SLSMAJ PAUL CAZIERDEPUTY AF SITE DIR

AEROSPACERANDY MOYERAIR FORCE ADVISOR

1ST SLSLT COL MYRON FORTSONAIR FORCE SITE DIR

NASA/KSC RICK BOUTINSAFETY & MSN ASSUR

NASA/KSCBERT GARRIDOSMA MISSION MGNT REP

NASA/HQWILLIS JENKINSPROGRAM EXECUTIVE

NASA/HQMIKE LUTHERSCIENCE MISSION DIR

BOEINGMARK WILKINSVICE PRES DELTA PROG

BOEINGDAVE CROSSEDIRECTOR OF ENGR

BOEING MIKE KENNARDOPERATIONS INTEGRATOR

BOEINGMIKE TAYLORFLIGHT OPS MANGER

NASA/HQBILL WROBELSPACE OPS MSN DIR

NASA/KSCJOE LACKOVICHNASA ADV MNGR

NASA/KSCSTEVE FRANCOISNASA ADVISOR

NASA/KSCOSCAR TOLEDONASA ADVISOR

26

25

28

27

6-4525

6-4526

6-4527

6-4528

MOD

AM

OD

6-4529

6-4530

30

29

SMA

MM

R

32

31

HQM

GCD

NAM

6-4531

6-4532

6-2242

KSA

KPM

6-4535

6-4536

6-4533

6-4534

36

34

33

35

KCD

NASA/KSC BILL PARSONSNASA ADVISOR

BOEINGSCOTT MESSERNLS PROGRAM MANAGER

21

43

65

AMD

MD

6-4501

6-4502

6-4503

6-4504

6-4505

6-4506

AFA

DA

FS

DA

FS

D

87

12

10

91

1

6-4507

6-4508

6-4509

6-4510

6-4511

6-4512

OI

DED

VPF

O

14

13

16

15

18

17

6-4513

6-4514

6-4515

6-4516

6-4517

6-4518

20

19

24

22

21

23

6-4519

6-4520

6-4521

6-4522

6-4523

6-4524

SMD

GS

MA

6-2241

6-2241

NASA/GSFCED WEILERGSFC CENTER DIRECTOR

NASA/GSFCFRANK SNOWS/C MISSION DIR

NASA/GSFCDONNIE GATESGROUND OPS MNGR

NASA/GSFCRON PERISONGSFC SAFETY & MISSION ASSURANCE

NASA/GSFCRICK OBENSCHEINFLT PROGRAMS DIR

UCBPETER HARVEYTHEMIS PROJ MNGR

UCBVASSILIS ANGELOPOULOSPRINCIPAL INVESTIGATOR

GO

MT

PMP

IF

PD

O N

ET

O N

ET

O N

ET

O N

ET

B N

ET

B N

ET

B N

ET

B N

ET

B N

ET

B N

ET

B N

ET

B N

ET

B N

ET

ANALEX TRACEY POSTLAUNCH OPS MNGR

NASA/KSCTBDNLM AWARD SEAT

FPO

NA

SA

M

IMA

LMN

LM

NASA/KSCAMANDA MITSKEVICHFLT PROJECTS OFFICE

NASA/KSCGARRETT SKROBOTNASA MSN INTEG MNGR

NASA/KSCCHUCK DOVALENASA LAUNCH MNGR

NASA/KSC OMAR BAEZASST LAUNCH MNGR

LOM

HQ

PX

HQ

SM

D

DPM

BOEINGTBD

BOEINGTBD



17

18

19

20

21

22

23

24

91

01

11

21

31

41

51

6 82

14

36

57

K-N

ET

THEMIS Mission Support LVDC-3

K-N

ET

Ron JacksonUCB

Linda WarnockJBOSC

Norm WhiteANALEX MGMT

Jan McMillenANALEX

Charlie FloydANALEX MGMT

Roy FisherANALEX

Tiffany NailNASA/KSC

Larry Ellis ANALEX MGMT

ReservedNASA KSC

6-45736-4574

6-45756-4576

6-45816-4582

6-45836-4584

6-45806-4579

6-45786-4577

K-N

ET

Steve Owens SAIC MGMT

-Network Drop for LaptopsXXXX

Joe BolekGSFC

Mike CulleySWALES

Paul TurinUCB

John ThurburGSFC

Jamey BurgetGSFC

Warren ChenSWALES

Dennis LeeGSFC

Jeremy McCauleyUCB

Greg DaltonUCB

Dave CurtisUCB STC

Stu HarrisUCB MSE

ReservedNASA KSC

ReservedNASA KSC

ReservedNASA KSC

O N

ET

O N

ET

O N

ET

O N

ET

O N

ET

O N

ET

O N

ET

O N

ET

O N

ET

O N

ET

O N

ET

O N

ET


• 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» Same as 24 hour recycle» If extended delay» Continue to Recharge Batteries – Remotely (Does Not Require Fairing

Access)

THEMIS Mission Recycle Requirements


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: 91845 km– Orbit Inclination: 16 degrees– Spacecraft (SC) Mass (will not exceed)

» 829 kg (2832.94lb) 775.60 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 - 162 rpm

• Mission Unique– 3712 Bolted PAF– Sep System (at PAF/PC Interface)

• Non-Standard Services– Category 1 Analysis

» (1st 7925-10C 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 19.6 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 2007 01-14 Mar 2007

• Spacecraft Mass Including Probe Carrier (lb) 1709.91 1709.91

• Second Stage Velocity Reserve at SECO 2 (fps) 1735 1970

• Second Stage Velocity Reserve Required 268 268

for PCS of 99.7% (fps)

• TAG Performance Allowance (fps) 75 75

• Velocity Reserve Margin (fps) 1392 1627


Depletion Burn:Removes Stage 2 fromvicinity of spacecraft,while lowering Stage 2 perigee altitude andorbit inclination

Flight Profile

Liftoff

MECOt = 263.3 secAlt = 69.0 nmiVI = 20,060 fps

Second Stage Ignitiont = 276.8 secAlt = 72.9 nmiVI = 20,068 fps

Fairing Jettisont = 281.0 secAlt = 74.1 nmiVI = 20,103 fps



Second Stage Restartt = 3859.4 secAlt = 282.7 nmiVI = 24,662 fps



TECOt = 4091.6 secAlt = 305.2 nmiVI = 33,975 fps

Separate Probe At = 4380.1 secAlt = 658.6 nmiVI = 32,368 fps

Orbit:235 x 49,592 nmi16.00 deg inclination-40.00 deg arg of per

SRM Impact SRM Impact

SRM Jettison (6)t = 66.0 / 67.0 secAlt = 9.9 / 10.2 nmiVI = 3,231 / 3,269 fps

SRM Jettison (3)t = 131.5 secAlt = 31.3 nmiVI = 8,018 fps

Third Stage Ignitiont = 4005.1 secAlt = 281.0 nmiVI = 25,775 fps

Note: Values shown are for 15-28 Feb 2007 launch


Orbit Trace – 15-28 Feb 2007

TEL4 = Eastern RangeANT = AntiguaCAIR = Cairns (Mobile Telemetry, MT)KWAJ = KwajaleinUCB = Berkeley Ground Station

Working with Big Crow to see if they can

overlap SC separation coverage


Telemetry Asset Plan/Acquisition

Asset Acquisition StatusTEL-4 - Eastern Range Station at KSC Complete

ANT - Eastern Range Station at Antigua Complete

Cair - Cairns (Big Crow) Complete

KWAJ - Kwajalein Complete


Accepted/Open Risks

ItemApproach

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 A V0037

Condition: Power and Control (P&C) Box capacitors have become loose in S/N 20070. Consequence: Undetected loose capacitors in other P&C Boxes.

Risk accepted by LSP 8/16/05, (Ref ERB-03-426; ERB 04-176)

3 A V0035

A photodiode failed within Redundant Inertial Flight Control Assembly (RIFCA) S/N 20093.

Risk accepted (Ref ERB 04-479). 6/8/06 ERB accepted S/N 20083 and all RIFCA after.

4 A 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 04-378; ERS-02-43; ERS-05-214 ERS-06-147).

S = Safety & Mission Assurance Designator

P = LSP Designator

5

4

3

2

1

1 2 3 4 5

L

I

KE

L

IH

O

OD

CONSEQUENCES

5

4

3

2

1

1 2 3 4 5

L

I

KE

L

IH

O

OD

CONSEQUENCES

2P

3S

4S6S

1S 2S

5S


Accepted/Open Risks (Cont.)

ItemApproach

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-02-085; ERB-01373KSC0; 01388KSC0; 02-245; 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 tankS = Safety & Mission Assurance Designator

P = LSP Designator

5

4

3

2

1

1 2 3 4 5

L

I

KE

L

IH

O

OD

CONSEQUENCES

5

4

3

2

1

1 2 3 4 5

L

I

KE

L

IH

O

OD

CONSEQUENCES

2P

3S

4S6S

1S 2S

5S


Readiness Reviews

Review Date Location

Pre Vehicle On Stand (PreVOS) 03 January HB

MRR* 05 January GSFC

• Launch Vehicle Readiness Review (LVRR) 12 January KSC

• Safety & Mission Success 19 January HQReview (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 andLaunch Site Status


Launch Site Schedule2006 2007

December January February

1/2/07

Name

12/21 2/2Upper Stage

PAF Mate Preps

PAF Mate to Motor

S/C Sep Connections

S/C Weigh Preps

Balance PAM

S/C Weigh

Preps for Motor Mate

Clampband Installation

Third Stage/Spacecraft Mate Preps

Third Stage Closeout

Transfer Third Stage to Astrotech

Spacecraft Mate

Spacecraft Finaling

Spacecraft Finaling (S/C Ops)

Engineering Walkdown

Third Stage and S/C Can-up & Transfer Preps

Third Stage and S/C Transport to Pad1/29 2/15Pad 17B

Preps of MST & Second Stage for S/C Erection

S/C Payload to Blockhouse Ringout

S/C Erection Preps

THEMIS S/C Erection

Spacecraft Functional Test

Spacecraft Launch Rehearsal

Flight Program Verification

Fairing Installation Preps

Fairing Installation

Fairing Elect Conn

Fairing Strongback Removal

S/C Systems Testing

FRR

Second Stage Prop Load

Mission Dress Rehearsal (MDR)

Spacecraft Testing

LRR

Preps for MST Move

Spacecraft Power/Clock Recycle

Post Launch SecuringLAUNCH

12/21 2/2

12/21

1/2

1/10

1/12

1/12

1/13

1/15

1/16

1/24

1/25

1/26

1/29

1/30

1/30

1/31

2/1

2/2

1/29 2/15

1/29

1/29

2/2

2/2

2/3

2/5

2/6

2/7

2/8

2/8

2/9

2/12

2/12

2/13

2/13

2/14

2/14

2/14

2/15

2/15

2/15



Eastern Range Operations Schedule

Jan/Feb/Mar 2007

X Range Configuration / Range Conflict \\ Additional Launch/Landing Attempt(s) HOLIDAY \ Configuration Hold

SUN MON TUE WED THU FRI SAT

4 5 6

15 16 17

18 19 22 23 24

25 26

3

7 109

20

1 228 3

313028

21

2

8

1211

1

HOLIDAY

JANUARY 29 FEBRUARY

27

Delta IITHEMIS

MARCH

13 14


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:– 608792-0J

» Lot used in units with LAT failure

– 60892-2B – 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 06-358 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.


• 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


• ERB 06-284-2 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 06-284-3 will be conducted to give

flightworthiness for FM13 in mid-January.

Second Stage Tank (Cont.)


Separation Sequencing System (SSS)

LV Firing Signal to the SSS (2 places)

• 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.


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.).



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



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% + CompleteAll GIDEPS have been assessed and impacts

understood, reviewing as issuedNone

Quality Assurance Surveillance Ongoing Launch site surveillance ongoing None

Reliability/Maintainability

FMEA/CIL CompleteAnalyses completed Swales, reviewed by GSFC

Code 302 and suppliersSee Systems Section

Reliability Assessment CompleteAnalyses completed by Swales, reviewed by GSFC

Code 302 and suppliersSee Systems Section

Limited Life Items Complete Tracked for observatory by GSFC Systems None

Safety

Safety Data Package Complete Controls in place and verification complete. None

Contingency Planning Complete Contingency plans in place None

Range Safety Complete MSPSP Approved None

NASA Safety Reporting System Complete Close calls are closed None

SMA Integrated Activities

Training Complete All certifications and training in place None

Lessons Learned Review Complete Will enter into LLIS after launch None

Risk Management Ongoing Risk discussed as open and residual See Systems Section

Waivers/Deviations/Exceptions Complete Class I and II waivers complete None


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

Orbital Debris• 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 AssuranceActivities

Evaluation Area Status Residual Risks

1.SAC Assessment at Swales Complete None

2. SAC Assessment at UCB Complete None

3.IV&V Assessment of Spacecraft Software

Complete None

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


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 PerisonGSFC 301-286-4649

Rick PfistererGSFC QE301-286-7866

Mark GoansGSFC

Judith ConnellyIV&V Facility304-367-8314

N/A N/A Brian Keegan

Spacecraft Ronald PerisonGSFC 301-286-4649

Mark GoansGSFC

Judith ConnellyIV&V Facility304-367-8314

N/A N/A Brian Keegan

Instruments Ronald PerisonGSFC 301-286-5817

Mark GoansGSFC

N/A Jeremiah TolbertRon Hallet

Brian Keegan


SMA Responsibility Matrix (2)

GSFC SMA Independent (Code 301)

IV&V Contractors Representative

In-Plant Representative

External Review

Parts Joseph OscheGSFC301-286-3306

Mark Goans N/A N/A N/A Brian Keegan

Materials Fred GrossGSFC301-286-8349


Safety Jamie BurgetGSFC301-286-7852


Reliability Nino IngenariGSFC301-286-6425


Software Cindy Taylor301-286-7763



GSFC Code 300“Watch List”

Item # Description Reply Status Comments

97-01 Optocouplers - SETs. Impact

The Amptek, HV601B (ESA instrument) and the Micro pack 66099-300 (LVPS and PCB instruments) are used. "THEMIS has screened devices … suitable ..."

99-01 Actel FPGAs: NA-046 ImpactStart-up rules are being followed. LASP and Orbital have consulted Actel."THEMIS is employing … recommendations

99-02 Vishay - Metal Foil Resistors. No impactThe Vishay, RNC90Z (MIL-PRF-55182/9), established reliability resistors are used.

99-03 SpecTran - Fiber Optic Cable. No impact Not used

99-04 Bell Labs - Up-screened diodes. No impact Not used

99-05 ATC Capacitors: NA-048. No impact Not used

00-01 Interpoint: MT2-P-00-01. No impact Not used

01-01 Advanced Analog: DC-DC converters. No impact Not used

02-01 ACS Polarity Verification. Impact “Swales has provided polarity verification plan."

03-01 Metropole: Diplexer anomaly. No impact Not used

04-01 Hitachi EEPROM: bit flips. Impact

The Maxwell EEPROM (5962-3826719Q7C, 28C011TRPFB-12) is used in the DCB instrument and has the Hitachi die. Reviewed and risk accepted.

04-02 cPCI Connector Qualification. No impact Not used

04-03 TRAK Microwave: Isolator. No impact Not used

05-01 Emcore: Solar Cell Welds. No impact Not used

05-02 Starsys: Qwknut. No impact Not used


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 Not used

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.

05-06Ball Aerospace – Conformal Coating No impact Not used

05-07Trompeter Electronics - Connector. No impact Not used

05-08 LoDs:DCMC Workmanship Certs. No impact Not used

05-09Conax Florida Corporation - Pyrovalves. No impact Not used

05-10 Actel RTAX FPGAs.No impact

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 …"

06-01RAD750 EEPROM Vibration Failure.

No impact Not used


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 & closedDetail on Two Programmatic Risks –(status closed )List of Artifacts AnalyzedBAU issues breakdown by FunctionIDPU issues breakdown by FunctionSeverity 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 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


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.

Summary of All Technical Issues of Memoranda (TIM) generated, resolved & closed

BAU IDPU System TotalRequirements 84 18 12 114

Design 7 50 N/A 57Code 58 0 N/A 58Test 125 6 N/A 131

Traceability 23 32 N/A 55

Total 297 106 415


Programmatic Project Risks

BAU Testing - Closed September 06IF 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

BAURequirements• 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 2.504 CPT• BAU FSW Test Plan v1.0

IDPURequirements• 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)

SystemRequirements• MRD Revs C, D, E, F, G, H

Below is a list of THEMIS artifacts which IV&V has reviewed.


All BAU TIMs by severity and function

1 2 3 4 5 Total Issue CountBoot 0 1 58 3 8 70

Bus Avionics Manager 0 0 3 0 0 3Checksumming 0 0 7 0 1 8

Command Processing 0 2 28 4 1 35Data Storage 0 0 30 0 0 30

General 0 1 27 5 1 34Health and Safety 0 0 4 1 0 5IRU Processing 0 0 0 0 0 0Limit Monitoring 0 0 1 1 0 2

Memory Management 0 1 13 4 0 18Stored Command Processing 0 0 26 0 0 26Sun Sychronous Processing 0 0 17 0 0 17

Telemetry Processing 0 0 33 3 1 37Thruster Firing 1 6 1 0 0 8

Time Code Processing 0 0 3 0 0 3Total Issue Count 1 11 252 21 12 297

All States Included and Parsed with Saved Query: BAU CFL MRR

Severity


All IDPU TIMs by severity & function

1 2 3 4 5 Total Issue CountAttitude Control 0 0 0 0 0 0

Background 0 0 2 0 0 2Burst Triggering 0 0 0 0 0 0

Commands 0 0 4 2 0 6Compression algorithms 0 0 2 1 0 3

EFI Deployment 0 1 4 0 1 6EFI FGM Fit Manager 0 0 4 0 0 4

EFI Manager 0 0 18 4 1 23ETC Manager 0 0 2 0 0 2

Executive 0 0 5 1 0 6Fast Floating Point 0 1 0 0 0 1

FGM Manager 0 0 2 0 0 2General 0 0 2 0 0 2

Housekeeping 0 0 4 1 0 5Input/Output 0 0 3 2 0 5

Loader 0 0 2 0 0 2Matrix Solver 0 0 1 0 0 1

Power Manager 0 0 8 0 0 8SCM Manager 0 0 4 0 0 4

Spin Fit Calculator 0 0 5 0 0 5SSR Manager 0 0 5 2 0 7

Telemetry 0 0 5 0 0 5Trigonometrics 0 0 0 0 0 0

Utilities 0 0 5 1 0 6Total Issue Count 0 2 88 14 2 106

All States Included and Parsed with Saved Query: IDPUCFL MRR

Severity


TIM Severity Definitions

*IEEE J-STD-016-1995 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.


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


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


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


THEMIS IIRT Reviews

Element Review Date

Mission

SRRJuly 8-9,

2003

PDRNov. 12-14,

2003

CDRJune 17,

2004

MORMarch 7-8,

2005

P2 PERMarch 16,

2006

P1,3,4,5 PERJune 23,

2006

FOROct. 4-5,

2006

PSR Oct. 26, 2006

Delta-PSR Dec. 5, 2006

Element Review Date

Payload

PDR @ MPDR

CDRJune 16,

2004

Test Summary

Dec. 9, 2004

F #1 PER May 2, 2005

F #1 PSRSept. 21,

2005

F #2,3 PERAug. 27,

2005

F #2,3 PSRNov. 10,

2004

F #4,5 PERNov. 10,

2005

F #4,5 PSR May 5, 2006

Element Review Date

Spacecraft

PDR Oct. 29-30, 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 May 31, 2006


THEMIS RFA Summary

0

10

20

30

40

50

60

Inst

. CD

RF1

PER

F1 P

SR

F2,3

PE

RF2

,3 P

SR

F4,5

PE

RS

/C P

DR

S/C

CD

RB

us 2

PSR

Bus

3 P

SRB

us 4

PSR

Bus

1 P

SRB

us 5

PSR

S

RR

PD

RC

DR

MO

RP

2 P

SRP

1,3,

4,5

PER

FOR

PSR

Del

ta-P

SR

RFAs Complete / Concurred (Total = 267)RFAs Complete / Not Concurred (Total = 2)


Key Project Management Practices

Legend: Green - To date, activities are fully compatible with good practice for similar successful projects. Yellow - To date, activities exhibit weakness that warrants change to control risk. Red - To date, activities are deficient and immediate corrective action is essential to minimize risk.

Key Management Practice SRR PDR CDR PER PSR

Organization & Communication

Systems Management

Safety

Risk Management

Mission Assurance

Integration TBD

Verification TBD

Operations

Engineering Peer Reviews TBD

Independent Reviews


THEMIS Residual Risk Rating

LIKELIHOOD

(0.1% <PT < 2%) (PS < 10-6)Very Low1

(2% < PT < 15%) (10-6 < PS < 10-3)Low2

(15% < PT < 25%) (10-3 < PS < 10-2)Moderate3

(25% < PT < 50%) (10-2 < PS < 10-1)High4

(PT > 50%) (PS > 10-1)Very High5

Technical SafetyLevel

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

CONSEQUENCE

LIK

EL

IHO

OD

F D,E

B,C*A

THEMIS RISK MATRIX

Note: Numerical techniques were not used to estimate likelihood probabilities.

= Technical Rating*


THEMIS Residual Risk Assessment

Item Risk Description Failure

LikelihoodFailure

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.



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.




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.




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.




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.




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 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.


Open IIRT Concerns

• None


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.


Public Affair Plan

Cynthia O’Carroll

GSFC Public Affairs Office


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.


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



• 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



• 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 - http://www.nasa.gov/themishttp://sprg.ssl.berkeley.edu/themishttp://ds9.ssl.berkeley.edu/themishttp://www.swales.com/company/themis_contract.html



• 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



• 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:• Moderator: George Diller, NASA KSC PAO• Craig Pollock, NASA HQ THEMIS Program Manager• David Sibeck, NASA THEMIS Project Scientist• Vassilis Angelopoulos, UC Berkeley THEMIS Principal Investigator



• 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



• Education

– NASA GSFC:• July 2006 - NASA Explorer Schools Orientation Workshop and

Distance Learning Network Workshop with presentations of Heliophysics science and solar classroom activities

• March 2007 - 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”



– 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.



• 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 (301-286-NEWS) and on the GSFC Web page. KSC will also update their Code-A-Phone beginning on L-3.


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: http://guestops.hq.nasa.gov– 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


Readiness Statement

Frank Snow

Mission Manager



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


Acronyms


M12. ACRONYMS LIST 3DP 3 Dimensional Plasma instrument on the WIND spacecraft A/D Analog-to-Digital Converter AA/OSS Associate Administrator for the Office of Space Sciences AC Alternatic Current ACE Advanced Composition Explorer ACS Attitude Control System ADC Analog to Digital Converter AEC-ABLE A company name AFRL Airforce Research Laboratories AGI Analytical Graphics Inc. AGO Automated Geophysical Observatory AGS Alaska Ground Station at Poker Flat AKM Apogee Kick Motor AKR Auroral Kilometric Radiation AMPTE US/European Mission consisting of 3 satellite: CCE, IRM and UKS AMSAT Amateur Radio Operator Satellite AO Announcement of Opportunity APER Argument of Perigee APID Application Process Identifier ASA Austrian Space Agency ASI All Sky Imager ASIC Application Specific Integrated Circuit ASCII American Standard Code for Information Interchange ATS Absolute Time Sequence AXB Axial Booms BAU Bus Avionics Unit

BEB Boom Electronics Board BGS Berkeley Ground Station (used for satellite tracking of FAST, HESSI, IMAGE and other spacecraft) BPSK Binary Phase Shift Keying BTE Bench Test Equipment BTS Bester Tracking Systems software C&DH Command & Data Handling C&T Command & Telemetry CAD Computer Aided Design CANOPUS A network of ground observatories (magnetometers, all sky cameras and meridional scanning photometers) in Canada Cassini European Spacecraft to Saturn CC Configuration Control CCAS Cape Canaveral Air Station CCD Charge-Coupled Device CCE A US / European Scientific Satellite CCI Cross Field Current Instability CCP Civil and Commercial Program CCSDS A signal encoding procedure outlined by NASA’s Consultative Committee for Space Data Systems CD Current Disruption CDAW Community Data Analysis Workshop A substorm event-based forum CDHS Command & Data Handling Subsystems CDI Command-Data Interface CDF Common Data Format CDROM A data archival medium

Acronyms List (Page 1 of 8)



CESR Centre d’Etude Spatiale des Rayonnements CEI Contract End Item CEO Chief-Executive Officer CETP Centre d’etude des Environnements Terrestres et Planetaires, Velizy, France CGM Canadian Geospace Monitoring CG Center of Gravity CGS Canadian Geospace System CHIPS Cosmic Hot Interstellar Plasma Spectrometer (A NASA UNEX mission). CITU Carrier Initiator and Telemetry Unit CLCW Command Link Control Word CLTU Command Link Transmission Unit CLUSTERA European / US Scientific Satellite that was destroyed at launch CLUSTERIIA repeat of CLUSTER CM Contracts Managers CMD Command CMS Command Management System CNES Centre National d’Etudes Spatiales CNR Carrier-to-noise Ratio COP Command Operation Procedure CPMN Circum Pacific Magnetometer Network CPT Comprehensive Performance Testing CPU Central Processing Unit CQ Calendar Quarter CRRES An Airforce Mission (Combined Release and Radiation Effects Satellite) with Scientific Instruments CSA Canadian Space Agency CSR Concept Study Report

CU Colorado University CY Calendar Year DAC Digital-to-Analog Converter DAS Debris Assessment Software DC Direct Current DC MUX Direct Current Multiplexer DET Direct Energy Transfer DFB Digital Fields Board in the Instrument Data Processing Unit (IDPU) DLR German Aerospace Center DMA Direct Memory Access DMI Danish Meterological Institute DOD Depth of Discharge DPMB Data Processor & Memory Board DPU Data Processing Unit DSN Deep Space Network (A NASA tracking antenna network) DSP Data Signal Processor Dst A Geomagnetic Activity Index E&B Electric and Magnetic (Fields) EDAC Error Detection and Correction circuit EECO Electronic Engineering Change Order EFI Electric Field Instrument EFW Electric Field andWave experiment on CLUSTER, and CLUSTERII EGSE Electrical Ground Support Equipment EM Engineering Models EMC/EMI Electromagnetic Cleanliness/Electromagnetic Interference EO-1 Earth-Observing Satellite-1, a NASA mission



HST Hubble Space TelescopeHV High VoltageI&T Integration and TestingIAT Independent Assessment TeamICD Interface Control DocumentsIDL Interactive Data Language (a data analysiscommercial program)IDPU Instrument Data Processing UnitIGRF International Geophysical ReferenceModelIIRV Improved Interrange VectorIMAGE Imager for Magnetopause-to AuroraGlobal Exploration (MIDEX Mission)IMPACT The In-situ Measurements of Particlesand CME Transients investigation onSTEREO. This is a consortium ofseven instruments: The Solar Wind/SW, Magnetometer/MAG, Solar EnergeticParticle package/SEP composedof 4 smaller instruments. The IMPACTdata processing unit accomodates these7 instruments and additionally thePlasma and Supra-Thermal Ions andComposition/PLASTIC investigationon STEREO.IMU Inertial Measurement Unit (a commercialgyroscope)IMF Interplanetary Magnetic FieldInterball A Russian scientific satelliteI/O Input/Output

EPO Education and Public OutreachEquator-S A German Scientific SatelliteESA Electrostatic AnalyzerESC Electrostatic CleanlinessESTEC European Space Research and TechnologyCenterETU Engineering and Testing UnitEUVE Extreme Ultra-Violet ExplorerFAST Fast Auroral SnapshoT Explorer, aSMEX missionFDAB Flight Dynamics Analysis BranchFDC Flight Dynamics CenterFDF Flight Dynamics FacilityFEM Finite Element ModelFFT Fast Fourier TransferFGM Fluxgate MagnetometerFGS Fluxgate SensorFLT Flight-ready componentsFMEA Failure modes, and effects analysesFOT Flight Operations TeamFOV Field of ViewFPGA Field Programmable Gate ArrayFreja Swedish SatelliteFSW Flight SoftwareFTE Flux Transfer EventsFTP File Transfer ProtocolFUSE Far UltraViolet Spectroscopic ExplorerFUV Far UltraViolet (experiment onIMAGE mission)FY Fiscal YearGalileo NASA Satellite to Jupiter

HST Hubble Space TelescopeHV High VoltageI&T Integration and TestingIAT Independent Assessment TeamICD Interface Control DocumentsIDL Interactive Data Language (a data analysiscommercial program)IDPU Instrument Data Processing UnitIGRF International Geophysical ReferenceModelIIRV Improved Interrange VectorIMAGE Imager for Magnetopause-to AuroraGlobal Exploration (MIDEX Mission)IMPACT The In-situ Measurements of Particlesand CME Transients investigation onSTEREO. This is a consortium ofseven instruments: The Solar Wind/SW, Magnetometer/MAG, Solar EnergeticParticle package/SEP composedof 4 smaller instruments. The IMPACTdata processing unit accomodates these7 instruments and additionally thePlasma and Supra-Thermal Ions andComposition/PLASTIC investigationon STEREO.IMU Inertial Measurement Unit (a commercialgyroscope)IMF Interplanetary Magnetic FieldInterball A Russian scientific satelliteI/O Input/Output

EPO Education and Public OutreachEquator-S A German Scientific SatelliteESA Electrostatic AnalyzerESC Electrostatic CleanlinessESTEC European Space Research and TechnologyCenterETU Engineering and Testing UnitEUVE Extreme Ultra-Violet ExplorerFAST Fast Auroral SnapshoT Explorer, aSMEX missionFDAB Flight Dynamics Analysis BranchFDC Flight Dynamics CenterFDF Flight Dynamics FacilityFEM Finite Element ModelFFT Fast Fourier TransferFGM Fluxgate MagnetometerFGS Fluxgate SensorFLT Flight-ready componentsFMEA Failure modes, and effects analysesFOT Flight Operations TeamFOV Field of ViewFPGA Field Programmable Gate ArrayFreja Swedish SatelliteFSW Flight SoftwareFTE Flux Transfer EventsFTP File Transfer ProtocolFUSE Far UltraViolet Spectroscopic ExplorerFUV Far UltraViolet (experiment onIMAGE mission)FY Fiscal YearGalileo NASA Satellite to Jupiter


Acronyms List (Page 4 of 8) IOC In Orbit Checkout IONet Internet Protocol Operational Network IPDR/ICDRInternal Preliminary and Critical Design Reviews IRM Spacecraft part of the AMPTE mission (also see AMPTE) IRT Independent Review Team ISDN Integrated Service Digital Network ISEE A NASA scientific satellite ISIS A US Polar Orbiting Satellite IT Information Technology ISTP International Solar-Terrestrial Program ISUAL Instrument built by UCB for a Taiwanese satellite ITAR International Traffic in Arms Regulations ITOS Integrated Test and Operation System IV&V Independent Verification and Validation IWF Institut für Weltraumforschung (Space Research Institute, Graz) IWS Integration Work Station JPL Jet Propulsion Laboratory KH Kelvin-Helmholtz KSC Kennedy Space Center L&EO Launch and Early Orbit LANL Los Alamos National Laboratory Landsat US Remote Sensing Satelllite LET Linear Energy Transfer (1 MeV cm2/g) LEO Low Earth Orbit LHS Lawrence Hall of Science LHCP Left Hand Circular Polarization

LME Lead Mechanical Engineer LOF Likelihood of Failure LPT Limited Performance Testing LV Launch Vehicle L/V also Launch Vehicle LVPS Low-Voltage Power Supply LWS Living With a Star program of NASA MACCS A Ground Magnetometer Network MAG MAGnetometers MagCon Magnetospheric Constellation a NASA mission under study, in the Solar Terrestrial Probes category MAM Mission Assurance Manager MCM-V Multi Chips Module Vertical MCP Micro-channel Plate MEASUREA ground magnetometer array along the Eastern United States MER Mars Exploration Rover MeV Mega (106) electron Volts MGS McMurdo Ground Station MHD Magnetohydrodynamics MIDEX Middle Explorer program of NASA MIR The Russian Space Station MI Magnetosphere-Ionosphere MLI Multi-layer Insulation MLT Magnetic Local Time MMS Magnetospheric Multiscale mission MO&DA Mission Operation and Data Analysis MOC Mission Operations Center MOM Mission Operations ManagerS MOSFET Metal-Oxide-Semiconductor Field- Effect Transistor



MOT Mission Operations Team MPS Mission Planning System MSASS Multimission Spin Axis Stabilized Spacecraft (MatLab-based GSFC code) MSE Mission Systems Engineer MSI&T Mission Integration and Testing (and Preparation for Operations as defined in this AO) N2H4 Monopropellant Hydrazine NASA National Aeronautics and Space Administration NENL Near-Earth Neutral Line model of substorms NIPR National Institute of Polar Research, Tokyo, Japan NLS NASA Launch Services NORAD North American Aerospace Defense Command NORSTARA Canadian program to instrument with filtered all sky imagers 6 ground stations NPD NASA Policy Directive NPG NASA Procedures and Guidelines NRC National Research Council NRE Non-Recurring Engineering NSES National Science Education Standards NSPAR Non-Standard Parts Approval Request NSSDC National Space Science Data Center NTIA National Telecommunications and Information Administration ODC Other Direct Changes OSS Office of Space Sciences

PA Product Assurance PAF Probe separation system PAIP Performance Assurance Implementation Plan PC Probe Carrier PCA Probe Carrier Assembly PESA-H PESA-High (an instrument on the WIND satellite) PFR Problem/Failure Reporting system Phobos A Russian Scientific Mission PI Principal Investigator Pi2 Pulsation irregular of type 2 PiB Pulsation irregular of type B PIL Parts Identification List PM Project Manager PM Phase Modulation PMC Program Management Council PMS Performance Measurement System POLAR A US Scientific Mission PPL Preferred Parts List PRA Probabilistic Risk Assessment PRIMAVERA Scheduling Software Package PROM Programmable Memory PSAT Predicted Site Acquisition Table PSR Program Status Reviews PTPNT Programmable Telemetry Processor for Windows NT QA Quality Assurance QUATRO QUantitative Assessment of Magnetospheric TRanspOrt RAID Redundant Array of Independent Disks



RAP Right Ascension of Perigee RAAN Right Ascension of the Ascending Node RE Mean Radius of Earth RHESSI Ramaty High Energy Solar Spectroscopic Imager RCS Reaction Control System RF Radio Frequency RFA Request for Action RFCS RF Comminations Subsystem RFQ Request for Quotations RHCP Right Hand Circular Polarization RID DSN station in MadRIT, Spain ROMAP A particle and field instrument on the European Rosetta Mission ROSETTA European Satellite RTS Relative Time Sequence Rx Reconnection site S3-3 An Airforce mission with scientific instruments to study the aurora SAC-C Brazilian satellite to be launched by NASA SACNAS Society for the Advancement of Chicanos and Native Americans in Science SAMBA A Ground Magnetometer Network SAMPEX Solar Anomalous and Magnetospheric Particle Explorer, A NASA Small Explorer mission SB Small Business SBUs Strategic Business Units SC Spacecraft

SCa Search Coil antennae SCpa Search Coil preamplifier unit SCAT Spacecraft Command and Telemetry SCAMA Switching, Conferencing and Monitoring Arrangement SCM Search Coil Magnetometer SCONCE A dispenser structure built for AFRL by Swales SDB Small Disadvantaged Business SDRAM Static/Dynamic Random Access Memory SDT Science Data Tool SEC Sun-Earth Connections SEGway Science Education Gateway, a UCBled education and public outreach program SEI-CMM Software Engineering Institute’s Capability Maturity Model. SEPT Solar Electron and Proton Telescope SERS Spacecraft Emergency Response System SEU Sudden Event Upset SMALL Sino-Magnetic Array at Low Latitudes (an NSF-funded effort) SMEX Small Explorer Program SMRB Swales Materials Review Board SN Space Network SOC Science Operations Center SOHO A US / European Scientific Satellite SOW Statement of Work SPB Spin-Plane Booms SPCB Swales Parts Control Board SPR Spare units SR&T Space Research and Technology program



of NASA SSD Space Sciences Division SSL Space Sciences Laboratory at UCB SSPA Solid State Power Amplifier SSS Swales Structure Systems SST Solid State Telescope SR System Reliability SRAM Static Random Access Memory SRO Systems Review Office STAFF A French experiment on the European satellite, CLUSTER STDN Spaceflight Tracking and Data Network STEM A production line of carbon epoxy tubular sensors STEREO A NASA Solar Terrestrial Probes mission to study the Sun from two spacecraft providing stereoscopic view of flares and coronal mass ejections ST5 A NASA technology demonstration mission STK Satellite Tool Kit STP Solar Terrestrial Probes STS/SHELS Shuttle Payload SWIFT US Mission TCP/IP Transmission Control Protocol/Internet Protocol TDRSS Tracking and Data Relay Satellite System, includes 6 spacecraft and ground centers for satellite communications TDRSS/MATDRSS Multiple Access mode THEMIS Time History of Events and Macroscale

Interactions during Substorms TIMED A NASA Scientific Satellite TLM Telemetry TRIANA NASA Mission to the L-1 Point TUBS Technical University, Braunschweig T/V Thermal Vacuum UA University of Alberta, Canada UC University of Calgary UCB University of California at Berkeley UCLA University of California at Los Angeles UC-LANLA Ground Magnetometer Network ULDB Ultra Long Duration Balloon ULF Ultra-low Frequency UNEX University Explorer UOSAT University of Surrey USAF US AirForce USN Universal Space Net, a commercial satellite tracking network. USN-AU Universal Space Network Australia USP University of Saint-Petersburg, Russia USGS U.S. Geological Survey UT Universal Time UTC Universal Coordinated TimeS UTDF Universal Tracking Data Format UV Ultra-Violet VSat Virtual Satellite VSAT A satellite internet connection Viking A Swedish Satellite VLSI Very Large Scale Integrated VME Virtual Memory Extension VRTX A Real Time Operating System commercial



program for microcontrollers WBS Work Breakdown Structure WGN Wallops Ground Network WGS Wallops Ground Station WGST White Sands Ground Terminal WIND An ISTP spacecraft to study the solar wind WOA Work Order Authorization WWW World-Wide Web