TPF-I SWG Report - Exoplanet Exploration Program - NASA

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C HAPTER 4 The full set of metrics and scores for each combination of option and discriminator is listed in Lay et al. (2005). The final scores are tabulated in Table 4-3, with the breakdown into performance and cost/risk. The X-Array scored the highest, followed by the Linear Dual Chopped Bracewell. Table 4-4 gives a breakdown of the key discriminators, ie. those responsible for most of the differentials in the final scores. 4.10 Structurally Connected Interferometer Prior to 2004, the <strong>TPF</strong>-I project developed designs for both a formation-flying interferometer (FFI) and a structurally connected interferometer (SCI) architecture. In the following we briefly describe the SCI design and summarize a 2006 reassessment of its planet-finding performance. 4.10.1 Baseline design The SCI architecture created by the <strong>TPF</strong>-I Design Team has four 3.2-m diameter collectors, spaced along a 36-m linear structure as depicted in Fig. 4-24. The light from the collectors can be phased as a Dual Chopped Bracewell Nuller in two different ways. Configuration A has longer nulling baselines and therefore a small inner working angle, but the short imaging baselines result in poor angular resolution. a) b) c) Figure 4-25. (a) SCI with deployed thermal shade. (b) SCI with thermal shade removed. (c) End view to illustrate the ±45 degree solar shading limit. 92
D ESIGN AND A R C H I T E C T U R E T RADE S TUDIES Configuration B has almost twice the angular resolution, but it has three times the inner working angle. Different views of the SCI design are shown in Fig. 4-25. The combiner optics are located at the center of the structure, as is the spacecraft bus. The 36-m length is constrained by the volume available in the shroud of the Delta IV Heavy launch vehicle (Fig. 4-26). The structure is folded at three hinge points. Further deployments are necessary for the thermal shades and secondary mirror supports. 4.10.2 Performance Assessment With a maximum baseline of 36 m, the SCI has lower planet-finding capability compared to an FFI. The planet-finding process has three stages: (1) Detection of candidate planets, (2) Orbit determination, and (3) Spectroscopic characterization. Orbit determination and spectroscopy require greater angular resolution than the initial detection, and it is therefore these stages that most constrain the SCI performance. Three criteria were applied to determine those stars for which an Earth-like planet could be detected and characterized: (a) Inner Working Angle (IWA) — at least 50% of the planet’s orbit must lie outside the IWA, averaged over all inclinations, (b) Angular resolution — the planet should be unconfused with other planets at least 50% of the time, and (c) Spectroscopy time — no more than 100 days of integration time is allowed to achieve an SNR of 5 relative to the continuum over 9.5–10 μm (for detection of ozone). The angular resolution criterion was evaluated by calculating the fraction of time that a planet in an Earth-like orbit would be confused (i.e., not resolved as a separate entity) with either a Venus or Mars analog. 2b 2a 1b 1a 2 3a 3b 3 Outer Collector Inner Collector Deployment of each arm occurs in 3 steps: 1) Rotation of folded arm assembly about s/c y-axis 2) Rotation of short segment into final position 3) Rotation of outer segment into final position 1 2 3 1 Figure 4-26. Stowed configuration for launch on a Delta-IV Heavy and schematic of on-orbit deployment sequence. 93
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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
Page 56 and 57: C HAPTER 3 clouds or an OB associat
Page 58 and 59: C HAPTER 3 Figure 3-3. Three possib
Page 60 and 61: C HAPTER 3 the circumstellar disk,
Page 62 and 63: C HAPTER 3 Figure 3-6. (Left panel)
Page 64 and 65: C HAPTER 3 Continuum interferometry
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Page 68 and 69: C HAPTER 3 3.3 Conclusions Darwin/T
Page 70 and 71: 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
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Page 124 and 125: C HAPTER 5 Figure 5-9 shows the fir
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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
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Page 138 and 139: C HAPTER 5 5.8.4 Angular Resolution
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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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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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