TPF-I SWG Report - Exoplanet Exploration Program - NASA

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C HAPTER 6 Table 6-4. Requirements of the Formation Control Testbed vs. Flight Requirements Parameter Flight Performance Formation Control Testbed Comments Number of spacecraft 5 3 Operational capability Standalone operations 5 yr 36 min Total floatation time Mission duration 5 yr 5+ yrs Observational duration ~20 hr ~15 min For an “observation on the fly” Availability Continuous 8 hrs/day Ground testbed facility Motion DOFs 6 5+1 FCT:+ articulated DOF Operating envelope 3D space 2D plane FCT: with limited out-of-plane Control 2 cm / 20 arcsec 5 cm / 60 arcmin Fault recovery Active and passive None Flight capability Sensor Inertial Gyro/accel Gyro/accel Celestial Star tracker Pseudo-star tracker Relative Coarse, Med., Fine Medium Actuator Thruster, RWA Thruster, RWA Control Architecture Distributed Distributed Control Algorithms Flight Flight Developed by FAST Dynamic DOFs 6 5 FCT: +1 articulated DOF Range of motion Angular-in-plane 2π 2π Angular-out-of-plane ± 45° ± 45° Linear-in-plane Linear-out-of-plane Maneuvers Limited by sensor range Limited by sensor range Limited by lab space Acquisition 3D space 2D space Array rotation in-plane Yes Yes Array re-sizing Yes Yes Array re-targeting Yes Yes Collision Avoidance 3D space 2D space ± 25 cm Emulate deadband during observations 142
T E C H N O L O G Y R OADMAP FOR TPF-I 6.3.2 Formation Algorithms and Simulation Testbed (FAST) Formation and Attitude Control System (FACS) lies at the heart of the formation-flying software. It is designed to provide three-axis inertial attitude and inter-s/c range and bearing control of each of the spacecraft in the TPF-I formation. Additionally, FACS provides the capability of initializing/reacquiring the formation through the acquisition of inter-s/c range/bearing knowledge, using the available on-board formation sensing capability. FACS ensures collision free operation of the formation throughout all nominal phases of the TPF-I mission. It is described in more detail in Appendix C. Here it is used for two software demonstrations that are described in the following pages. Two high-level scenarios have been demonstrated in FAST. The first consists of two spacecraft functioning as a distributed interferometer. The second is a two-robot simulation of the FCT. Figure 6-6. (top left) Spacecraft spring apart, arrest separation velocity, acquire relative sensor, and rotate formation to center Sun on panels; (top right) Beginning of second retarget: only relative position is controlled, the formation is drifting downwards; (bottom left) Approximately half-way through second retarget. Bowed trajectory is for collision avoidance; (bottom right) View after second retarget completed. 143
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JPL Publication 07-1 Terrestrial Pl
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Abstract Over the past two years, t
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Acknowledgements Twenty-two represe
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Table of Contents 1 Introduction...
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4.8.3 Post-Nulling Calibration.....
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6.4.5 Double Fourier Interferometry
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I NTRODUCTION 1 Introduction Over 2
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I NTRODUCTION et al. 2004), and res
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I NTRODUCTION Standard Interferomet
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I NTRODUCTION 1.4 References Angel,
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C HAPTER 2 0.7 to 1.5 AU scaled by
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C HAPTER 2 Table 2-2. Illustrative
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C HAPTER 2 Classical interferometry
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C HAPTER 2 trivial in the absence o
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C HAPTER 2 Figure 2-3. Simulated mi
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C HAPTER 2 would be in atmospheres
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C HAPTER 2 Figure 2-6. The mid-infr
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C HAPTER 2 Lines of constant stella
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C HAPTER 2 presence of zodiacal clo
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C HAPTER 2 S EZ 2π ∫ θ max ∫
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C HAPTER 2 Figure 2-11. Observation
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C HAPTER 2 Figure 2-12. Models of t
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C HAPTER 2 Beichman, C. A., Fridlun
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C HAPTER 2 2.7.4 Suitable Targets E
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C HAPTER 2 Reach, W. T., Franz, B.
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C HAPTER 3 3.1.1 Darwin/TPF-I Prope
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C HAPTER 3 clouds or an OB associat
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C HAPTER 3 Figure 3-3. Three possib
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C HAPTER 3 the circumstellar disk,
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C HAPTER 3 Figure 3-6. (Left panel)
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C HAPTER 3 Continuum interferometry
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C HAPTER 3 Figure 3-9: Simulated im
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C HAPTER 3 3.3 Conclusions Darwin/T
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C HAPTER 3 Nguyen, H. T., Kallivaya
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D ESIGN AND A R C H I T E C T U R E
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Page 105 and 106: D ESIGN AND A R C H I T E C T U R E
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Page 114 and 115: C HAPTER 5 Heavy launch vehicle. Th
Page 116 and 117: C HAPTER 5 5.3.2 Combiner Spacecraf
Page 118 and 119: C HAPTER 5 5.3.5 Beam Transfer betw
Page 120 and 121: C HAPTER 5 Figure 5-8. Control sche
Page 122 and 123: C HAPTER 5 Figure 5-9. First sectio
Page 124 and 125: C HAPTER 5 Figure 5-9 shows the fir
Page 126 and 127: C HAPTER 5 5.4.4 Shear Metrology Sh
Page 128 and 129: C HAPTER 5 Figure 5-15. TPF-I Fligh
Page 130 and 131: C HAPTER 5 secondary mirror along t
Page 132 and 133: C HAPTER 5 a) c) b) d) IWA = 43 mas
Page 134 and 135: C HAPTER 5 planets found. Figure 5-
Page 136 and 137: C HAPTER 5 30 25 5 M earth 3 M eart
Page 138 and 139: C HAPTER 5 5.8.4 Angular Resolution
Page 140 and 141: C HAPTER 5 Table 5-3. Angular Resol
Page 142 and 143: C HAPTER 5 The optimization works b
Page 145 and 146: T E C H N O L O G Y R OADMAP FOR TP
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Page 173 and 174: F UTURE D EVELOPMENTS 7 Preparatory
Page 175 and 176: F UTURE D EVELOPMENTS • To comple
Page 177 and 178: F UTURE D EVELOPMENTS Table 7-1. Pr
Page 179 and 180: D ISCUSSION AND C ONCLUSION 8 Discu
Page 181 and 182: Appendices 167
Page 183 and 184: T E C H N O L O G Y A DVISORY C O M
Page 185 and 186: F L I G H T S YSTEM C ONFIGURATION
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Page 192 and 193: A PPENDIX C 2. Recall that the coef
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Page 202 and 203: A PPENDIX C References Cohen, S., a
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A PPENDIX D NaCl NAR NASA NASTRAN N
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A PPENDIX E Appendix E TPF-I Review
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A PPENDIX F Alice Quillen, Universi
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A PPENDIX F Figure 3-1 - Original f
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