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

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Figure 11-20. Pointing angle difference between primary and redundant readouts . . . . . . . . . . . . . . . . . . . . . . . . . 328Figure 11-21. The color variation of IM Peg. The sum of the detector current of one of the axisis also shown to indicate how star brightness varies. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 328Figure 11-22. The scaled summed current for each of the four pairs of detectors. . . . . . . . . . . . . . . . . . . . . . . . . . . . 329Figure 11-23. Comparison of four pairs of scaled summed current with each otherand with R band of ground measurement. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 329Figure 11-24. Scaled summed current compared with the values of channel XB.The ratios have been normalized for easy comparison. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 330Figure 11-25. Comparison of estimated photocurrent based on Science slopes andon least square fit slope derived from TRE snapshots . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 331Figure 11-26. Temperature variation of telescope top plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 332Figure 11-27. Temperature variation of Window 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 332Figure 11-28. Temperature variation of Window 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 332Figure 11-29. Temperature variation of Window 4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 332Figure 12-1. Integrated probe and dewar. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 335Figure 12-2. Temperature spiking at probe station 200 (primary cryogenic probe/dewar interface). . . . . . . . . 337Figure 12-3. Helium flow rate predicted by dewar model based on both the measuredshell temperatures and predicted temperatures. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 340Figure 12-4. Main tank temperature in response to fourth heat pulse measurement with lineartrendlines before and after heat pulse. Temperature increase is taken to be the difference in thetwo trendline values at the middle of the pulse. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 342Figure 12-5. Plot of the remaining mass of liquid helium as a function of HPM measurement date with lineartrendline. The fact that the trendline does not project backwards to the original quantity of liquidhelium (taken to be 337 kg) is indicative of a scale factor error. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 343Figure 12-6. Flow meter and ATC flow rates as a function of UTC date starting at launch. Data encompass periodsof flow control (constant segments in the ATC data) as well as pressure control. . . . . . . . . . . . . . . . 344Figure 12-7. Mass remaining estimated from integrated flow meter and ATC flow rates. Trendline fits areextrapolated to zero mass. Since depletion did not occur in early July, it is clear that the dewar flowmeter results under-predicted lifetime. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 344Figure 12-8. Flow meter data reduced by 10% and plotted with ATC flow rate and flow rate predicted by thedewar thermal model. Thermal model is based on measured shell temperatures rather thanpredicted shell temperatures. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 345Figure 12-9. HPM data analyzed under three different assumptions together with extrapolated linear trendlines.348Figure 13-1. Locations of Forward and Aft ECU boxes on the GP-B spacecraft . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 353Figure 13-2. ECU-operated heaters in the dewar & probe . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 354Figure 13-3. ECU-operated temperature sensors in the dewar & Probe . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 354Figure 13-4. ECU-operated heaters and temperature sensors in the Probe and Probe windows . . . . . . . . . . . . 355Figure 13-5. General locations of ECU-controlled subsystems on the spacecraft . . . . . . . . . . . . . . . . . . . . . . . . . . . 355Figure 13-6. A six-inch Vatterfly leakage exhaust valve at the top of the dewar . . . . . . . . . . . . . . . . . . . . . . . . . . . . 356Figure 13-7. The Gas Management System (GMA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 356Figure 13-8. UV lamps and the gyro electrostatic discharge system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 357Figure 13-9. The GP-B Proton Monitor box . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 357Figure 13-10. Performance during Low Temperature Bakeout . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 359Figure 13-11. ECU performance during IOC flux reduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 360Figure 13-12. ECU heater activity following launch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 361Figure 13-13. ECU heater activity during first month of IOC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 361Figure 13-14. ECU heater activity during the 2nd month of IOC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 362Figure 13-15. ECU heater activity from mid June - mid July, 2004 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 363Figure 13-16. ECU heater activity during gyro spinup and other critical IOC procedures . . . . . . . . . . . . . . . . . . . . . 363Figure 13-17. ECU heater activity during the last month of IOC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 364xx March 2007
Figure 13-18. ECU heater activity during the first half of the Science Phase . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 365Figure 13-19. ECU heater activity during the Science Phase, from January-May 2005 . . . . . . . . . . . . . . . . . . . . . . . . 366Figure 13-20. Typical Month of Proton Monitor Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 369Figure 13-21. Proton Monitor data in South Atlantic Anomaly . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 370Figure 13-22. Twice Orbital Component . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 370Figure 13-23. FFT of data from the horizontal detector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 371Figure 13-24. Histogram of Proton Events . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 371Figure 13-25. Proton Monitor Data from November 2004 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 372Figure 13-26. Zoomed out view of Figure 13-25 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 372Figure 13-27. Increased Proton Flux during the November 2004 solar activity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 373Figure 13-28. Correlation between Vertical PM Detector and Science Telescope (PXA) . . . . . . . . . . . . . . . . . . . . . . 373Figure 13-29. Correlation between Horizontal PM Detector and Science Telescope (PXA) . . . . . . . . . . . . . . . . . . . 374Figure 13-30. Correlation between Vertical PM Detector and Science Telescope (PYA). . . . . . . . . . . . . . . . . . . . . . . 375Figure 13-31. GP-B payload magnetometer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 376Figure 13-32. Measurement axes of the payload magnetometers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 377Figure 13-33. Mounting locations of the payload magnetometers. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 377Figure 13-34. Location of GPS equipment on GP-B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 379Figure 13-35. GPS Antennae Field of View . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 380Figure 13-36. Rolling Rig . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 381Figure 13-37. Master Antenna Switching . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 382Figure 13-38. Histogram of PPS Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 383Figure 13-39. Time difference between transmission and reception of GPS data packet. . . . . . . . . . . . . . . . . . . . . 384Figure 13-40. Residuals of Least Square fitting algorithm with 2nd order model. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 385Figure 13-41. Coverage Curves for GPS simulator, rolling rig, and flight data. At GP-B's roll rate, the simulatedcoverage is 86%, while flight rate is better than 95% . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 386Figure 13-42. Coverage rates during an increase in vehicle roll rate. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 387Figure 13-43. Percent Lock and data points used before and after the switch to the B-sidereceiver on March 4, 2005, day 64. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 389Figure 13-44. A Top View of the GMA Pallet with the Thermal Blanket Frame Attached . . . . . . . . . . . . . . . . . . . . . . 391Figure 13-45. A Bottom View of the GMA Showing the Supply Tanks and Outlet Valves . . . . . . . . . . . . . . . . . . . . . 392Figure 13-46. GMA vent manifold and service GSE used to minimize cryogenic contamination and ensureregulator lock-up for launch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 393Figure 13-47. Service valve assembly (fill and drain valves) used to service the GMA to reduce the risk of cryogeniccontamination during ground support . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 393Figure 13-48. The GMA configuration on a vented honeycomb pallet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 394Figure 13-49. Schematic diagram of the GMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 394Figure 13-50. Helium gas consumption for 10 hz and full spin-up of gyro #4 during IOC . . . . . . . . . . . . . . . . . . . . . 395Figure 13-51. Pressure Transducer GP-1 Snap-Shot of Actual Gas Consumed by the GMA . . . . . . . . . . . . . . . . . . . 395Figure 14-1. A drawing of the spacecraft communicating with ground tracking stations . . . . . . . . . . . . . . . . . . . 399Figure 14-2. A typical solid state recorder (SSR) manufactured by SEAKR Engineering . . . . . . . . . . . . . . . . . . . . . . 400Figure 14-3. A NASA TDRSS Satellite . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 401Figure 14-4. NASA ground stations at Svalbard, Norway (upper left), Poker Flats, Alaska (lower left),and Wallops Island, Virginia (right) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 402Figure 14-5. The GP-B building and Mission Operations Center (MOC) at Stanford University . . . . . . . . . . . . . . . 403Figure 14-6. ITF readout showing a discrepancy between the actual value (left) of memory location in thespacecraft's computer vs the correct value (right) stored in the ITF simulator. . . . . . . . . . . . . . . . . . 405Figure 14-7. Two members of the GP-B Mission Operations team discuss an MBE that triggered a B-Side (CCCBcomputer) reboot on March 18, 2005 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 405Figure 14-8. Uploading commands to the spacecraft from the MOC, following a B-side computer reboot. . . 406Gravity Probe B — Post Flight Analysis • Final Report March 2007 xxi
Page 1 and 2: Post Flight Analysis — Final Repo
Page 3 and 4: Signatures & ApprovalsPrepared byPu
Page 5 and 6: Table of ContentsPreface . . . . .
Page 8 and 9: 6.8 Sources and References . . . .
Page 10 and 11: 11 Telescope Readout Subsystem (TRE
Page 12 and 13: 14 Data Collection, Processing & An
Page 14 and 15: xiv March 2007 Table of Contents
Page 16 and 17: Figure 3-4. The GP-B dewar—one of
Page 18 and 19: Figure 8-5. The Seasons of GP-B . .
Page 22 and 23: Figure 14-9. In the Anomaly Room, t
Page 24 and 25: xxiv March 2007
Page 26 and 27: Table 13-3. GP-B payload magnetomet
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Page 30 and 31: 2 March 2007 Chapter 1 — Executiv
Page 32 and 33: facility, it was necessary to recas
Page 34 and 35: spacetime around with them as they
Page 36 and 37: After years of work and the inventi
Page 38 and 39: axis of a gyroscope rotor changes i
Page 40 and 41: Figure 1-8. Clockwise, from top lef
Page 42 and 43: “management experiment.” This w
Page 44 and 45: Attitude-Control Gyroscopes. Two pa
Page 46 and 47: Any significant deviation from “g
Page 48 and 49: established, ranging from Level 1 (
Page 50 and 51: 1.14 The Broader Legacy of GP-BAt l
Page 52 and 53: 24 March 2007 Chapter 2 — Overvie
Page 54 and 55: Figure 2-1. GP-B Historical Time Li
Page 56 and 57: Applied Physics Laboratory, of the
Page 58 and 59: William Fairbank once remarked: “
Page 60 and 61: In Einstein’s view, space and tim
Page 62 and 63: y a mere 1.1 inches. You can see th
Page 64 and 65: Figure 2-10. Schematic diagram of t
Page 66 and 67: Figure 2-12. Final assembly of the
Page 68 and 69: 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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Figure 12-3. Helium flow rate predi
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helium at 1.8 K. It does not appear
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Figure 12-6. Flow meter and ATC flo
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were generally within a day or so o
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shields) and subsequent instability
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350 March 2007 Chapter 12 — Cryog
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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
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13.1.3.7 Payload MagnetometersThe E
Page 388 and 389:
Figure 13-11. ECU performance durin
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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
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Figure 13-21. Proton Monitor data i
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In November, 2004 there was a large
Page 402 and 403:
Figure 13-28 shows a correlation th
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13.3.1 About the MagnetometersFigur
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13.3.2 Other Applications for Paylo
Page 408 and 409:
Figure 13-35. GPS Antennae Field of
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Figure 13-37. Master Antenna Switch
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Figure 13-39. Time difference betwe
Page 414 and 415:
13.4.6 On-Orbit ResultsThe GPS comp
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and velocity values erroneously cal
Page 418 and 419:
E. G. Lightsey, C. E. Cohen, B. W.
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Figure 13-45. A Bottom View of the
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Figure 13-48. The GMA configuration
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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
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14.1.6 Telescope Dither—Correlati
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14.1.6.3 The Telescope Dither Patte
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amplifications. Thus, in addition t
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14.2.2 Independent Data Analysis Te
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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
Page 468 and 469:
440 March 2007 Chapter 15 — Preli
Page 470 and 471:
442 March 2007 Chapter 16 — Lesso
Page 472 and 473:
16.1.1.3 Flight science downlink da
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Description of the GP-B experience:
Page 476 and 477:
Lessons:1. Perform all tests with a
Page 478 and 479:
Page 480 and 481:
Figure 16-1. Six interacting transl
Page 482 and 483:
16.1.3.2 Training and certification
Page 484 and 485:
Page 486 and 487:
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
Page 492 and 493:
Apogee altitude659.1 km (409.6 mile
Page 494 and 495:
466 March 2007 Chapter B — Spacec
Page 496 and 497:
Gravity Probe B — Post Flight Ana
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470 March 2007 Appendix C — Weekl
Page 500 and 501:
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
Page 512 and 513:
C.4 Science Mission Phase: 8/27/04
Page 514 and 515:
• GP-B also has an independent da
Page 516 and 517:
free suspension parameters to de-tu
Page 518 and 519:
We have received inquiries about a
Page 520 and 521:
One of the effects of geomagnetic s
Page 522 and 523:
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
Page 528 and 529:
8 APRIL 2005—GRAVITY PROBE B MISS
Page 530 and 531:
On Tuesday afternoon (19-April), GP
Page 532 and 533:
Norway or through the NASA space ne
Page 534 and 535:
Dewar Temperature: 1.82 kelvin, hol
Page 536 and 537:
visitors on a tour of the GP-B faci
Page 538 and 539:
test, we are planning on running fi
Page 540 and 541:
contractor at the Goddard Space Fli
Page 542 and 543:
On Wednesday, we visited the star H
Page 544 and 545:
Gyro Suspension System (GSS): All 4
Page 546 and 547:
The helium in the dewar has now sur
Page 548 and 549:
the all the spacecraft status data.
Page 550 and 551:
522 March 2007 Appendix D — Summa
Page 552 and 553:
Figure D-2 below shows the distribu
Page 554 and 555:
DateSeveritySubtypeTitle Descriptio
Page 556 and 557:
DateSeverity24 26-Apr-04 Obs F Nois
Page 558 and 559:
DateSeverity40 11-May-04 Obs T Dwel
Page 560 and 561:
Page 562 and 563:
DateSeverity68 16-Jun-04 Medium Dec
Page 564 and 565:
DateSeverity84 13-Jul-04 Obs F Slig
Page 566 and 567:
Page 568 and 569:
DateSeverity116 26-Sep-04 Obs F SG3
Page 570 and 571:
DateSeverity132 20-Dec-04 Obs F Unc
Page 572 and 573:
DateSeverity149 5-Mar-05 Obs T Few
Page 574 and 575:
DateSeverity169 04-Jun-05 Obs F MBE
Page 576 and 577:
DateSeverity191 04-Oct-05 Obs A GSS
Page 578 and 579:
550 March 2007 Appendix E — Fligh
Page 580 and 581:
ReqIDLevel 1CSCDMP DataMgmtProcessi
Page 582 and 583:
ReqIDLevel 1CSCLevel2 CSC Level 3 C
Page 584 and 585:
Page 586 and 587:
Page 588 and 589:
ReqIDLevel 1CSCSRM Solid StateRecor
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Page 592 and 593:
Page 594 and 595:
ReqIDLevel 1CSCSRP SafemodeResponse
Page 596 and 597:
ReqIDLevel 1CSCGUP GSS Processing g
Page 598 and 599:
570 March 2007 Appendix F — Acron
Page 600 and 601:
AcronymDefinitionAcronymDefinitionB
Page 602 and 603:
AcronymDefinitionAcronymDefinitionD
Page 604 and 605:
AcronymDefinitionAcronymDefinitionF
Page 606 and 607:
AcronymDefinitionIRUInertial Refere
Page 608 and 609:
AcronymDefinitionAcronymDefinitionM
Page 610 and 611:
AcronymPMPMAPMCPMEPMETPMSPMSUPNPoPO
Page 612 and 613:
AcronymSCMOSCMTSCNSCPASCPMSCRSCSASC
Page 614 and 615:
AcronymDefinitionAcronymDefinitionT
Page 616:
588 March 2007 Appendix F — Acron
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