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

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28 JANUARY 2005—GRAVITY PROBE B MISSIONUPDATEMission Elapsed Time: 283 days (40 weeks/9.25 months)Current Orbit #: 4,178 as of 4:00 PM PSTSpacecraft General Health: GoodRoll Rate: Normal at 0.7742 rpm (77.5 seconds per revolution)Dewar Temperature: 1.82 Kelvin, holding steadyCommand & Data Handling (CDH): Multi-bit errors (MBE): 0, Singlebiterrors (SBE): 8.5 (daily avg.)Last Thursday morning (20 January 2005), GP-B entered Safemode 2A(gyro hold), due to the loss of the guide star. Analysis of this safemodeindicated that the telescope detectors were saturated by a large solarflare (X-7 class) that occurred Wednesday night.The solar flare had fluxes spiking several orders of magnitude abovenominal in the > 100MeV proton energy range. Less than a day later(16:27 PST), GP-B successfully re-locked onto the guide star and theAttitude and Translation Control (ATC) system returned to itsnominal configuration. During this event, the attitude error of thespacecraft and telescope remained within 800 arcseconds of the guidestar. A preliminary assessment suggests that this event had minimalimpact on the GP-B data or experiment.One issue currently being investigated is the spacecraft’s protonmonitor, which had been yielding spurious values before last week’ssolar storm. The proton monitor was power cycled this Tuesday night(25 January). After reboot, it provided two hours of meaningless datafollowed by zeros. The proton monitor team is examining the data foradditional clues, and a review of this issue will be forthcoming.4 FEBRUARY 2005—GRAVITY PROBE B MISSIONUPDATEMission Elapsed Time: 290 days (41 weeks/9.5 months)Science Data Collection: 161 days (23 weeks/5.25 months)Current Orbit #: 4,281 as of 4:00 PM PSTSpacecraft General Health: GoodRoll Rate: Normal at 0.7742 rpm (77.5 seconds per revolution)Dewar Temperature: 1.82 kelvin, holding steadyCommand & Data Handling (CDH): Multi-bit errors (MBE): 1 (See MDSummary below), Single-bit errors (SBE): See MD Summary below)Last weekend, on both Saturday and Sunday, the spacecraft’s maincomputer (CCCA) erroneously displayed a dramatic increase insingle-bit errors (SBE). We observed similar SBE increases in July 2004and one other time since then. In both previous cases, the SBE countquickly returned to normal, and we were unable to determine the rootcause of the erroneous increase. SBEs are self-correcting, so noparticular action is required, but we are monitoring this situation.Also, this past Tuesday, a new multi-bit error (MBE) was discovered ina memory location of the CCCA computer. A command wassubsequently sent to reload this memory location, clearing the MBE.The health of the spacecraft’s Proton Monitor is still underinvestigation. Telemetry indicates that it is powered on, but the dataappears to be corrupt. Note that the science mission is NOT affectedby the loss of the Proton Monitor. The Proton Monitor Engineeringunit is continuing to investigate this failure.We have been notified that the sun spot which caused the GP-Bscience telescope to lose track of the guide star two weeks ago, will becoming around to the front side of the sun on 5 February 2005.Geomagnetic activity around the Earth tends to increase after theappearance of sun spots. Thus, we have added extra telemetry passesand increased sensitivity to this issue during the next two weeks.11 FEBRUARY 2005—GRAVITY PROBE B MISSIONUPDATELast week’s intense solar storm has died down, and solar protonactivity, as reported by the National Oceanic & AtmosphericAdministration’s (NOAA) Space Environment Center (SEC), hasreturned to normal levels. (The left solar photo and graph are from lastweek; the solar photo and graph on the right are from today.)Likewise, the GP-B spacecraft has returned to normal functioning,with the ATC system locking normally on the guide star each orbitand the telescope detectors returning normal values. GP-B was not theonly satellite affected by last week’s solar storm; other satellites faredworse from the ordeal. In fact, given that last week’s solar storm wasthe worst one since October, 2003, the GP-B spacecraft performedremarkably well, with a very swift recovery and no significant impactto the experiment.Mission Elapsed Time: 297 days (42 weeks/9.75 months)Science Data Collection: 168 days (24 weeks/5.5 months)Current Orbit #: 4,384 as of 4:00 PM PSTSpacecraft General Health: GoodRoll Rate: Normal at 0.7742 rpm (77.5 seconds per revolution)Dewar Temperature: 1.82 Kelvin, holding steadyCommand & Data Handling (CDH): Multi-bit errors (MBE): 0, Singlebiterrors (SBE): 1,731 (daily average)This past week was a quiet one for GP-B, with very few activitiesscheduled. The solar flares that caused us to lose the guide star threeweeks ago came around to the front of the Sun, facing towards Earth,again this past week. We took extra precautions and scheduled extratelemetry passes to deal with possible effects of these solar flares on thespacecraft. However, this time, the solar flares produced no substantialgeomagnetic activity around the Earth. This may be a sign that the Sunhas moved into a quieter part of the solar cycle.496 March 2007 Appendix C — Weekly Chronicle of the GP-B Mission
18 FEBRUARY 2005—GRAVITY PROBE B MISSIONUPDATEMission Elapsed Time: 304 days (43 weeks/10.0 months)Science Data Collection: 175 days (25 weeks/5.75 months)Current Orbit #: 4,486 as of 2:00 PM PSTSpacecraft General Health: GoodRoll Rate: Normal at 0.7742 rpm (77.5 seconds per revolution)Dewar Temperature: 1.82 Kelvin, holding steadyCommand & Data Handling (CDH): Multi-bit errors (MBE): 0, Singlebiterrors (SBE): 4,704 (daily average)This past week was again a relatively quiet one for GP-B. Solar flareactivity is low, and solar radiation levels are normal. Guide starcapture times (time required to re-lock the telescope onto the guidestar as the spacecraft emerges from behind the Earth each orbit) areaveraging approximately one minute, which is excellent. Thebrightness table was updated for two of the stars that are monitored bythe spacecraft’s star trackers, and this significantly improved the startracker’s performance. Brightness tables for other stars in the startracker catalog will be updated next week.To determine how much helium is currently left in the dewar, the GP-B dewar team is in the process of performing another heat pulse meteroperation. The heat pulse test works in the following way: The amountof heat that it takes to warm an object by a specified amount dependson the type of material, its temperature, and its mass. Thus, if the“specific heat” (the amount of heat needed to warm a kilogram ofmaterial by one degree Kelvin) is known, it is a simple matter tomeasure the mass by applying a known amount of heat (usually withan electric heater) and measuring the resultant temperature rise.Star Sensor Magnitude Update was run Thursday to adjust thecataloged magnitude of star 173. As of Tuesday, updates of observedmagnitude of stars 50 and 173 were successful. Other stars’magnitudes may be updated.Two separate communications issues at Poker Flat, AK (2hr40m) andWallops Ground Station (2hr50m) caused brief outages of data. All thedata was recovered from Alaska; Wallops data was unrecoverable.Since the start of the mission, the GP-B team has successfully collected99.0% of the data (requirement is 90%).4 MARCH 2005—GRAVITY PROBE B MISSIONUPDATEMission Elapsed Time: 318 days (45 weeks/10.5 months)Science Data Collection: 189 days (27 weeks/6.25 months)Current Orbit #: 4,694 as of 2:00 PM PSTSpacecraft General Health: GoodRoll Rate: Normal at 0.7742 rpm (77.5 seconds per revolution)Dewar Temperature: 1.82 Kelvin, holding steadyCommand & Data Handling (CDH): Multi-bit errors (MBE): 0, Singlebiterrors (SBE): 8,198 (daily average)In the case of the GP-B dewar, the situation is simplified by the factthat heat distributes itself virtually instantaneously throughoutsuperfluid helium. The amount of heat used in the test must be largeenough to cause a measurable temperature change (approximately 10millikelvin) but not so large as to appreciably shorten the missionlifetime.The dewar team expects to complete their analysis of the heat pulsedata next week, and we will report the results in next week’s update.Our current expectation is that the science phase of the mission willconclude towards the end of June, and the results of the heat pulsemeter operation will help us determine whether or not the currentmission time line is correct.25 FEBRUARY 2005—GRAVITY PROBE B MISSIONUPDATEMission Elapsed Time: 311 days (44 weeks/10.25 months)Science Data Collection: 182 days (26 weeks/6.0 months)Current Orbit #: 4,589 as of 2:00 PM PSTSpacecraft General Health: GoodRoll Rate: Normal at 0.7742 rpm (77.5 seconds per revolution)Dewar Temperature: 1.82 kelvin, holding steadyCommand & Data Handling (CDH): Multi-bit errors (MBE): 0, Singlebiterrors (SBE): 9,937 (daily average)Three activities occupied our attention this past week:The Heat Pulse Meter Operation (HPMO), used to determine heliumin the dewar, occurred as scheduled on Wednesday night, 16-February. Preliminary analysis has been concluded and a sub-systemlevel review is in progress.Guide star capture times have improved to the one-minute range aftergyro biases were updated on all three axes. This is a typical adjustmentof the positioning gyroscopes on the satellite (which are different thanthe science gyros) that is required due to the influence of the Sun asGP-B orbits the Earth. These adjustments allow the satellite to morequickly re-focus, or “capture”, the guide star as it emerges from theEarth's eclipse on each orbit.11 MARCH 2005—GRAVITY PROBE B MISSIONUPDATEMission Elapsed Time: 325 days (46 weeks/10.75 months)Science Data Collection: 196 days (28 weeks/6.50 months)Current Orbit #: 4,767 as of 2:00 PM PSTSpacecraft General Health: GoodRoll Rate: Normal at 0.7742 rpm (77.5 seconds per revolution)Dewar Temperature: 1.83 kelvin, decreasing slowlyCommand & Data Handling (CDH): Now using B-side (backup)computer & guidance systemsMulti-bit errors (MBE): 0, Single-bit errors (SBE): 7 (daily average)The switch-over to the backup systems occurred automatically at 7:17am PST last Friday morning, 4 March 2005, due to two or more multibiterrors (MBE’s) in the flight computer, occurring within a 0.2second interval. The MBEs were caused by radiation hits in the southGravity Probe B — Post Flight Analysis • Final Report March 2007 497
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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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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
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Figure 13-2. ECU-operated heaters i
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13.1.3.1 Vatterfly Valve Operations
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13.1.3.7 Payload MagnetometersThe E
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Figure 13-11. ECU performance durin
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As we entered the second month of o
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During the last month of IOC, prepa
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Figure 13-19. ECU heater activity d
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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
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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
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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
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13.4.6 On-Orbit ResultsThe GPS comp
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and velocity values erroneously cal
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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
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398 March 2007 Chapter 14 — Data
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a relatively slow data rate, so we
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Figure 14-4. NASA ground stations a
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electronic components to recover fr
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By a process of elimination, the GP
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A special room in the GP-B Mission
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Starting on 3 December 1725, Bradle
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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
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424 March 2007 Chapter 15 — Preli
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Figure 15-2. A diagram of the GP-B
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15.4 The Two Surprises and Their Im
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Near Zeroes.) The exception that we
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Figure 15-8. A slide from the GP-B
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Figure 15-9. A poster on the effect
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electrostatic patches, located at o
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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
Page 474 and 475: Description of the GP-B experience:
Page 476 and 477: Lessons:1. Perform all tests with a
Page 480 and 481: Figure 16-1. Six interacting transl
Page 482 and 483: 16.1.3.2 Training and certification
Page 486 and 487: Below is an edited summary of six a
Page 488 and 489: 460 March 2007 Chapter 16 — Lesso
Page 490 and 491: 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
Page 498 and 499: 470 March 2007 Appendix C — Weekl
Page 500 and 501: 16 April 2004—Vehicle is Prepared
Page 502 and 503: The electrical power system is full
Page 504 and 505: 4 JUNE 2004—MISSION UPDATE: DAY 4
Page 506 and 507: SQUIDs to detect their rotation spe
Page 508 and 509: 17 JULY 2004—MISSION UPDATE: DAY
Page 510 and 511: 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
Page 526 and 527: 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 562 and 563: DateSeverity68 16-Jun-04 Medium Dec
Page 564 and 565: DateSeverity84 13-Jul-04 Obs F Slig
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
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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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Page 592 and 593:
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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
Page 602 and 603:
AcronymDefinitionAcronymDefinitionD
Page 604 and 605:
AcronymDefinitionAcronymDefinitionF
Page 606 and 607:
AcronymDefinitionIRUInertial Refere
Page 608 and 609:
AcronymDefinitionAcronymDefinitionM
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AcronymPMPMAPMCPMEPMETPMSPMSUPNPoPO
Page 612 and 613:
AcronymSCMOSCMTSCNSCPASCPMSCRSCSASC
Page 614 and 615:
AcronymDefinitionAcronymDefinitionT
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588 March 2007 Appendix F — Acron
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GP-B Post-Flight AnalysisÃ¢Â€Â”Final Report - Gravity Probe B - Stanford ...

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