TPF-I SWG Report - Exoplanet Exploration Program - NASA

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C HAPTER 5 Figure 5-9. First section of beamcombiner spacecraft control system. The basic control scheme is laid out in the series of Figures 5-8 through 5-11. Some alignments will take place continuously, and others will take place occasionally; these have been differentiated using different gray shades for calibration-phase and observation-phase processes. Calibration-phase processes might take place once every few hours up to once every few days, depending on the stability of the systems involved. Observation-phase processes will have characteristic times of milliseconds up to minutes. 5.4.1 System Summary The system is briefly summarized here, and more detail is added in the following section. Referring to Figure 5-8, starlight enters the main beam train at the FOR mirror and starts its journey to the beamcombiner. A fine-guidance sensor behind the dichroic mirror controls the FOR mirror and maintains pointing on the star. A pointing light sensor and an alignment mirror allow the starlight and an alignment beam to be accurately co-aligned in the beamtrain. Also, a wavefront sensor allows sensing of any primary mirror aberrations which would be corrected by the DM. A metrology retroreflector reflects fullaperture metrology, co-aligned with the starlight, back to the beamcombiner spacecraft. An internalalignment mirror is included to facilitate any necessary post-launch adjustments, and then the science beam and alignment beam leave the telescope spacecraft via a pointing mirror. This pointing mirror is controlled from a shear sensor located on the next collector spacecraft, requiring a control loop running through the radio frequency (RF) link. Similarly, a pointing mirror on the second telescope is controlled by a shear sensor on the beamcombiner spacecraft (lower box on Figure 5-8). Thus, the science light, alignment, and metrology beams arrive at the beamcombiner spacecraft. 108
<strong>TPF</strong>-I F L I G H T B ASELINE D ESIGN Figure 5-10. Second section of beamcombiner spacecraft control system. Figure 5-11. Final section of beamcombiner spacecraft control system. 109
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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
Page 73 and 74: D ESIGN AND A R C H I T E C T U R E
Page 111: D ESIGN AND A R C H I T E C T U R E
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 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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F UTURE D EVELOPMENTS 7 Preparatory
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F UTURE D EVELOPMENTS • To comple
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F UTURE D EVELOPMENTS Table 7-1. Pr
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D ISCUSSION AND C ONCLUSION 8 Discu
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Appendices 167
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T E C H N O L O G Y A DVISORY C O M
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F L I G H T S YSTEM C ONFIGURATION
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F L I G H T S YSTEM C ONFIGURATION
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A PPENDIX C 2. Identical FACS fligh
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A PPENDIX C 2. Recall that the coef
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A PPENDIX C Once the formation has
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A PPENDIX C Figure C-3. Example of
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A PPENDIX C Figure C-4. FAST Flight
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A PPENDIX C The “true” time of
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A PPENDIX C References Cohen, S., a
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A PPENDIX D DC DCB DM DM DOCS DOD D
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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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TPF-I SWG Report - Exoplanet Exploration Program - NASA

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