TPF-I SWG Report - Exoplanet Exploration Program - NASA

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A PPENDIX B Table B-3. Design Team Mass Allocations Mass Collector Combiner Payload (each) 550 kg* 461 kg Spacecraft (each) 605 kg 684 kg Reserve (each) 276 kg 268 kg Total (each) 1431 kg 1413 kg Launch mass 5724 kg 1413 kg *Collector payload includes a 391-kg primary mirror with an aerial density of 30 kg/m 2 Table B-4. <strong>TPF</strong>-I Combiner Spacecraft Design Summary Parameter Design Team Allocation Architecture Modular, process-driven, fully redundant Attitude control 3-axis, zero-net-momentum Attitude determination Star trackers, inertial reference unit Attitude control actuators 4 reaction wheels, 16 RCS thrusters Formation acquisition sensors S-band and sensors Propulsion / RCS Ion thrusters, Isp = 2500–3500 s Delta-V capability 750 m/s Solar array type / size Rigid panel, 9.0 m 2 Solar cell type Array power at end of life (EOL) Battery type / Capacity Thermal shield Telecommunications Data rates up/down Inter-spacecraft telecommunications Cascade multi-junction, 28% efficiency at beginning of life(BOL) 1455 W (45° off-point) Li-ion, 72.7 A-h 5-layer, deployable sunshade X-band up / Ka and X-band down 2 kpbs / 1 Mbps (Ka-band) 16 kbps (X-band) UHF full-duplex, 2.0 Mbps 172
F L I G H T S YSTEM C ONFIGURATION Table B-5. <strong>TPF</strong>-I Collector Spacecraft Design Summary Parameter Design Team Allocation Architecture Modular, process-driven, fully redundant Attitude control 3-axis, zero-net-momentum Attitude determination Star trackers, inertial reference unit Attitude control actuators 4 reaction wheels, 16 RCS thrusters Formation acquisition sensors S-band and sensors Propulsion / RCS Ion thrusters, Isp = 2500–3500 s Delta-V capability 750 m/s Solar array type / size Rigid panel, 5.4 m 2 Solar cell type Cascade multi-junction, 28% efficiency (BOL) Array power (EOL) 862 W (45° off-point) Battery type / Capacity Li-ion, 19.8 A-h Thermal shield 5-layer, deployable sunshade Telecommunications X-band up/down (contingency mode) Data rates up/down 2 kbps / 16 kbps Inter-spacecraft telecommunications UHF full-duplex, 2.0 Mbps 173
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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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C HAPTER 5 Heavy launch vehicle. Th
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C HAPTER 5 5.3.2 Combiner Spacecraf
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C HAPTER 5 5.3.5 Beam Transfer betw
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C HAPTER 5 Figure 5-8. Control sche
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C HAPTER 5 Figure 5-9. First sectio
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C HAPTER 5 Figure 5-9 shows the fir
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C HAPTER 5 5.4.4 Shear Metrology Sh
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C HAPTER 5 Figure 5-15. TPF-I Fligh
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C HAPTER 5 secondary mirror along t
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C HAPTER 5 a) c) b) d) IWA = 43 mas
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C HAPTER 5 planets found. Figure 5-
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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 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: F L I G H T S YSTEM C ONFIGURATION
Page 190 and 191: A PPENDIX C 2. Identical FACS fligh
Page 192 and 193: A PPENDIX C 2. Recall that the coef
Page 194 and 195: A PPENDIX C Once the formation has
Page 196 and 197: A PPENDIX C Figure C-3. Example of
Page 198 and 199: A PPENDIX C Figure C-4. FAST Flight
Page 200 and 201: A PPENDIX C The “true” time of
Page 202 and 203: A PPENDIX C References Cohen, S., a
Page 204 and 205: A PPENDIX D DC DCB DM DM DOCS DOD D
Page 206 and 207: A PPENDIX D NaCl NAR NASA NASTRAN N
Page 208 and 209: A PPENDIX E Appendix E TPF-I Review
Page 210 and 211: A PPENDIX F Alice Quillen, Universi
Page 212: A PPENDIX F Figure 3-1 - Original f
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TPF-I SWG Report - Exoplanet Exploration Program - NASA

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