GP-B Post-Flight AnalysisÃ¢Â€Â”Final Report - Gravity Probe B - Stanford ...

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E. G. Lightsey, C. E. Cohen, B. W. Parkinson, Development of a GPS Receiver for Reliable Real-Time AttitudeDetermination in Space, Proceedings of 7th International Technical Meeting of the Satellite Division of theInstitute of Navigation, 1994, p. 1677-1684.13.5 Gas Management Assembly (GMA)The GMA performed nominally during both the IOC and science (data collection) phases of the mission. Alltasks were completed on schedule and without any errors.All sub-systems of the GMA, including pressure and temperature were “green” throughout the mission, withthe exception of a few hours during the second week after launch, when the spacecraft sustained a proton strike,causing a switch-over from the main “A-side” computer and systems to the backup “B-side” systems. Duringgyro spin-up procedures, the GMA performed “as expected” with respect to spin-up manifold pressure vs. timeplots.No anomalies and only two observations were attributed to the GMA during the mission. The two observationswere for silicone diode temperature spikes that did not affect the thermal control of the GMA and an increasedpressure down stream of the pressure regulators due to gas leakage through the GMA latch valves. This wasexpected based on ground testing.13.5.1 GMA Development and Operational ConceptThe GMA was a late delivery sub-assembly that was fabricated, environmentally tested, and delivered toStanford in 13 months. At Stanford, the GMA was functionally verified by spinning up a low temperature (4ºKelvin) gyroscope. It was mated to the space vehicle at Lockheed Martin in Sunnyvale, California just prior tothe space vehicle thermal vacuum testing. The GMA passed functional testing for both pre and post thermalvacuum testing.The GMA has three main operating parts:• Two high-pressure storage vessels filled with 10.4 liters of helium at 2000psia.• Two redundant gas manifolds that lead to each gyro inlet, a probe inlet, and a vent path to space. Eachgas manifold has two redundant pressure regulators, two flow controllers (725 sccm and 2 sccm), 15latch valves, and 7 pressure transducers.• Two heater strips to heat the GMA pallet to 20ºC ±8ºC during valve operations.Ultra-pure (99.9999%) helium gas is streamed from the Gas Management Assembly (GMA), mounted in a bayon the spacecraft frame, through tubing that enters the “top hat” (the thermal interface at the top of the Probe)and travels down to the gyro housings in the Science Instrument Assembly (SIA) at the bottom of the Probe. Asthe helium gas descends into the Probe, which is at a temperature of approximately 1.8 Kelvin, the gas coolsdown from 273 Kelvin to around 12 Kelvin.The GMA was used to perform the “flux reduction” and all phases of gyroscope spin-ups - 0Hz, 5Hz, 10Hz, andthe final “Full” spin. Flux reduction was performed through an inlet into the Probe with a helium gas flow at 2sccm while the Probe leakage valve was open.The GMA consists of the components shown in Table 13-9 below. Note the redundancy some of thecomponents.390 March 2007 Chapter 13 — Other Payload Subsystems Analyses
Table 13-9. Summary of Components for the Gas Management AssemblyComponent Qty Redundancy CommentsRegulators 4 2 Pairs 2 regulators in seriesLatch Valves 30 15 Gyro outlet branches included 2 of 4 valves that were in anopen state for electrical redundancyFlow Control Orifices 5 2 10 SCCM flow control for flux reduction was in place toreduced the risk of over pressurizing the ProbeFilters 4 0 Filters were primarily for filling the GMA with He gasFill and Drain Valves 4 0 Used to fill GMA w/He gas and servicing the regulators (lockup).Pressure Sensors 14 0 Pressure sensors were primarily used to evaluate the status ofa latch valve (open or closed)Gas Bottles (5.2 literseach)2 0 Gas bottles were in parallel and not isolated from each other(total gas - 2000psia / 99.9999% helium)Figure 13-44. A Top View of the GMA Pallet with the Thermal Blanket Frame AttachedGravity Probe B — Post Flight Analysis • Final Report March 2007 391
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Post Flight Analysis — Final Repo
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Signatures & ApprovalsPrepared byPu
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Table of ContentsPreface . . . . .
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6.8 Sources and References . . . .
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11 Telescope Readout Subsystem (TRE
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14 Data Collection, Processing & An
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xiv March 2007 Table of Contents
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Figure 3-4. The GP-B dewar—one of
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Figure 8-5. The Seasons of GP-B . .
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Figure 11-20. Pointing angle differ
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Figure 14-9. In the Anomaly Room, t
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xxiv March 2007
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Table 13-3. GP-B payload magnetomet
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xxviiiMarch 2007
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2 March 2007 Chapter 1 — Executiv
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facility, it was necessary to recas
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spacetime around with them as they
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After years of work and the inventi
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axis of a gyroscope rotor changes i
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Figure 1-8. Clockwise, from top lef
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“management experiment.” This w
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Attitude-Control Gyroscopes. Two pa
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Any significant deviation from “g
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established, ranging from Level 1 (
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1.14 The Broader Legacy of GP-BAt l
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24 March 2007 Chapter 2 — Overvie
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Figure 2-1. GP-B Historical Time Li
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Applied Physics Laboratory, of the
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William Fairbank once remarked: “
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In Einstein’s view, space and tim
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y a mere 1.1 inches. You can see th
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Figure 2-10. Schematic diagram of t
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Figure 2-12. Final assembly of the
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Sun Shield. The sun shield is a lon
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2.1.8 The Broader Legacy of GP-BWhe
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2.3 Spacecraft SeparationThe Solar
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Flight Anomalies.) Furthermore, a d
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Table 2-2. Weekly summary of IOC ac
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2.4.3.2 Guide Star AcquisitionAbout
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A second mass trim operation had be
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On Friday, 2 July 2004, the spin ra
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Low temperature bakeout was first p
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2.5.1.3 Lockheed Martin Team Phase-
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Monthly Highlights of the GP-B Scie
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2.6.1 Overview of the Calibration P
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Weekly Highlights of the GP-B Final
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66 March 2007 Chapter 3 — Accompl
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It was in this pristine, near-zero
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Each quartz rotor is coated with a
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Figure 3-3. Functional diagram of a
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Based on data from the on-board tel
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Ideally, the telescope should have
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Figure 3-9. Schematic diagram of st
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used. The star trackers are essenti
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Result: By using the porous plug, w
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Solution: Create a tetrahedral lapp
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Constraint 2: The exhaust tube must
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Result: The on-orbit gyroscope spin
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spacecraft's subsystems for the dur
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Constraint 3: Keep the spacecraft p
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Technology Category Specific Implem
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96 March 2007 Chapter 4 — GP-B On
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Any significant deviation from “g
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packages, one for each Ping load an
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In addition to these software packa
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Table 4-6. Features & benefits of W
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This software added considerable ef
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It is said that “an experiment is
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Table 4-10. Significant Events/Sour
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Figure 4-5. Pictorial depiction of
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Figure 4-7. Eta-Average Error Assoc
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4.4.4.2 OD Using SLR DataFigure 4-9
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4.4.5 ConclusionsFigure 4-11. Compa
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Overall, the storage issues did not
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Table 4-11. ITF equipment listEQUIP
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124 March 2007 Chapter 5 — Managi
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5.2 Overview of GP-B Anomalies in O
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Figure 5-1. Anomaly Review Team Org
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5.3.3.1 Anomaly Investigation and R
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5.3.5 Anomaly Identification and Re
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5.4.3 Risk Management ApproachThe r
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Table 5-1. Summary of Open GP-B ris
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138 March 2007 Chapter 5 — Managi
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140 March 2007 Chapter 6 — The GP
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3. Payload Integration, Testing and
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Figure 6-1. Clockwise from top left
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MSFC conducted an in-house Phase A
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It is important to note that from t
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6.3.1 Incremental PrototypingThe pe
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alignment, and act as an accelerome
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Figure 6-9. The Lockheed Martin GP-
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Furthermore, a fourth electronic sy
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positive thermal connections betwee
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astrophysics/cosmology. Many of the
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Figure 6-10. MSFC Program Managers/
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As described in Chapter 2, the flig
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6.7 Some Observations on the Manage
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168 March 2007 Chapter 6 — The GP
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170 March 2007 Chapter 7 — Attitu
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7.1.2 Vehicle ATC ModesThere are es
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The output of the pressure transduc
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Figure 7-3. Science Telescope Compo
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Figure 7-5. Pitch and Yaw Pointing
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Figure 7-7. Magnitude of the roll r
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Changing the method by which the gy
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7.3.3 Drag-Free Control SystemFigur
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7.3.3.1 DFS - PerformanceThe GP-B d
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Figure 7-15. Mass flow effects of a
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7.5.2 Successful recovery from mult
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If the vehicle control system were
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accomplish this, the ARPs are mount
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7.5.6.1 South Atlantic AnomalyProto
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Figure 7-23. Effects on telescope p
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200 March 2007 Chapter 7 — Attitu
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202 March 2007 Chapter 8 — Other
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Figure 8-2. Block Diagram of CDH co
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8.1.1.4 WATCH DOG TIMERFigure 8-4.
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of eclipses each day (approximately
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Figure 8-8. GSS1 Temperature Trends
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Figure 8-10. Forward Dewar Vacuum S
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The Gravity Probe B spacecraft has
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Figure 8-13. Forward -X Thruster Te
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gaFigure 8-15. Aft -X Thruster Temp
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Because there are only two SQUID br
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Because the specifications for SRE
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8.3.2 Critical Mission RequirementT
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Figure 8-19 is a plot of the power
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Battery Performance Summary:Figure
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Figure 8-23. Solar Array Temperatur
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8.3.10 ConclusionThe electrical pow
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8.4.1 TDRSS OperationsFigure 8-28.
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Figure 8-30. Xpndr-A STDN (green),
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Figure 8-32. Plot of TDRS AGC vs Te
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The FSW also met its subsystem leve
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Appendix E, Flight Software Applica
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Table 8-4. SCRs Addressed in On-orb
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The software and macro changes resu
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Figure 8-38 below is an excerpt fro
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Figure 8-40. A-side CCCA Single Bit
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Figure 8-43. A-side CCCA Single Bit
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When single MBEs did not result in
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256 March 2007 Chapter 9 — Gyro S
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9.1 GSS Hardware DescriptionFigure
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significantly reduces and thus pres
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9.1.11 Clock synchronizationThe aft
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Figure 9-8. Block diagram of the LQ
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direction (transverse to the space
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9.2.2.2 Spin-up SuspensionDuring sp
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Figure 9-16. Predicted and measured
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Figure 9-18. The GSS passes rotor c
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Figure 9-20. Representative drag-fr
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Table 9-1. GSS Science Mission Mode
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Table 9-3. GSW application source l
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The Design and Testing of the Gravi
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282 March 2007 Chapter 10 — SQUID
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ate uncertainty). Although we have
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All of the GP-B electronics have be
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10.3 Pre-Launch Ground-Based TestsW
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Figure 10-6. AC Magnetic Shielding
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Figure 10-8. Temperature Error of S
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Figure 10-10. Quiescent SQUID Noise
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Analog control loops on the electro
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The science support applications ru
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Table 10-7. SSW application source
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308 March 2007 Chapter 11 — Teles
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Figure 11-1. Block diagram of TRE a
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Additionally, the warm electronics
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Figure 11-3. CLL switch states duri
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Table 11-3. Dates and UTC times whe
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Figure 11-7. Low Gamma Angle Data S
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s N+w i= sign+w i++−+−w i−w i
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expression, which otherwise on a po
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Figure 11-14. Y axis, B side RMS po
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Figure 11-17. X axis, B side curren
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Figure 11-20. Pointing angle differ
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Figure 11-24. Scaled summed current
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Figure 11-26 through Figure 11-29 s
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334 March 2007 Chapter 12 — Cryog
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12.2 Temperature / pressure control
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control the space vehicle without t
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Page 380 and 381: 352 March 2007 Chapter 13 — Other
Page 382 and 383: Figure 13-2. ECU-operated heaters i
Page 384 and 385: 13.1.3.1 Vatterfly Valve Operations
Page 386 and 387: 13.1.3.7 Payload MagnetometersThe E
Page 388 and 389: Figure 13-11. ECU performance durin
Page 390 and 391: As we entered the second month of o
Page 392 and 393: During the last month of IOC, prepa
Page 394 and 395: Figure 13-19. ECU heater activity d
Page 396 and 397: Table 13-1. Proton monitor channel
Page 398 and 399: Figure 13-21. Proton Monitor data i
Page 400 and 401: In November, 2004 there was a large
Page 402 and 403: Figure 13-28 shows a correlation th
Page 404 and 405: 13.3.1 About the MagnetometersFigur
Page 406 and 407: 13.3.2 Other Applications for Paylo
Page 408 and 409: Figure 13-35. GPS Antennae Field of
Page 410 and 411: Figure 13-37. Master Antenna Switch
Page 412 and 413: Figure 13-39. Time difference betwe
Page 414 and 415: 13.4.6 On-Orbit ResultsThe GPS comp
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Page 420 and 421: Figure 13-45. A Bottom View of the
Page 422 and 423: Figure 13-48. The GMA configuration
Page 424 and 425: Table 13-10. Summary for Helium Gas
Page 426 and 427: 398 March 2007 Chapter 14 — Data
Page 428 and 429: a relatively slow data rate, so we
Page 430 and 431: Figure 14-4. NASA ground stations a
Page 432 and 433: electronic components to recover fr
Page 434 and 435: By a process of elimination, the GP
Page 436 and 437: A special room in the GP-B Mission
Page 438 and 439: Starting on 3 December 1725, Bradle
Page 440 and 441: seemed that aberration of starlight
Page 442 and 443: 14.1.6 Telescope Dither—Correlati
Page 444 and 445: 14.1.6.3 The Telescope Dither Patte
Page 446 and 447: amplifications. Thus, in addition t
Page 448 and 449: 14.2.2 Independent Data Analysis Te
Page 450 and 451: monthly time scales. Though only sh
Page 452 and 453: 424 March 2007 Chapter 15 — Preli
Page 454 and 455: Figure 15-2. A diagram of the GP-B
Page 456 and 457: 15.4 The Two Surprises and Their Im
Page 458 and 459: Near Zeroes.) The exception that we
Page 460 and 461: Figure 15-8. A slide from the GP-B
Page 462 and 463: Figure 15-9. A poster on the effect
Page 464 and 465: electrostatic patches, located at o
Page 466 and 467: Last summer (2006), Mac Keiser devi
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440 March 2007 Chapter 15 — Preli
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442 March 2007 Chapter 16 — Lesso
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16.1.1.3 Flight science downlink da
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Description of the GP-B experience:
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Lessons:1. Perform all tests with a
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Figure 16-1. Six interacting transl
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16.1.3.2 Training and certification
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Below is an edited summary of six a
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460 March 2007 Chapter 16 — Lesso
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462 March 2007 Appendix A — Gravi
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Apogee altitude659.1 km (409.6 mile
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466 March 2007 Chapter B — Spacec
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Gravity Probe B — Post Flight Ana
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470 March 2007 Appendix C — Weekl
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16 April 2004—Vehicle is Prepared
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The electrical power system is full
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4 JUNE 2004—MISSION UPDATE: DAY 4
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SQUIDs to detect their rotation spe
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17 JULY 2004—MISSION UPDATE: DAY
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indicate that we have reduced the t
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C.4 Science Mission Phase: 8/27/04
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• GP-B also has an independent da
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free suspension parameters to de-tu
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We have received inquiries about a
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One of the effects of geomagnetic s
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egan transmitting, one-by-one, stat
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28 JANUARY 2005—GRAVITY PROBE B M
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magnetic pole. This event triggered
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8 APRIL 2005—GRAVITY PROBE B MISS
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On Tuesday afternoon (19-April), GP
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Norway or through the NASA space ne
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Dewar Temperature: 1.82 kelvin, hol
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visitors on a tour of the GP-B faci
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test, we are planning on running fi
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contractor at the Goddard Space Fli
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On Wednesday, we visited the star H
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Gyro Suspension System (GSS): All 4
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The helium in the dewar has now sur
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the all the spacecraft status data.
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522 March 2007 Appendix D — Summa
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Figure D-2 below shows the distribu
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DateSeveritySubtypeTitle Descriptio
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DateSeverity24 26-Apr-04 Obs F Nois
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DateSeverity40 11-May-04 Obs T Dwel
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DateSeverity68 16-Jun-04 Medium Dec
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DateSeverity84 13-Jul-04 Obs F Slig
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DateSeverity116 26-Sep-04 Obs F SG3
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DateSeverity132 20-Dec-04 Obs F Unc
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DateSeverity149 5-Mar-05 Obs T Few
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DateSeverity169 04-Jun-05 Obs F MBE
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DateSeverity191 04-Oct-05 Obs A GSS
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550 March 2007 Appendix E — Fligh
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ReqIDLevel 1CSCDMP DataMgmtProcessi
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ReqIDLevel 1CSCLevel2 CSC Level 3 C
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ReqIDLevel 1CSCSRM Solid StateRecor
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ReqIDLevel 1CSCSRP SafemodeResponse
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ReqIDLevel 1CSCGUP GSS Processing g
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570 March 2007 Appendix F — Acron
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AcronymDefinitionAcronymDefinitionB
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AcronymDefinitionAcronymDefinitionD
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AcronymDefinitionAcronymDefinitionF
Page 606 and 607:
AcronymDefinitionIRUInertial Refere
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AcronymDefinitionAcronymDefinitionM
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AcronymPMPMAPMCPMEPMETPMSPMSUPNPoPO
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AcronymSCMOSCMTSCNSCPASCPMSCRSCSASC
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AcronymDefinitionAcronymDefinitionT
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588 March 2007 Appendix F — Acron
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