TPF-C Technology Plan - Exoplanet Exploration Program - NASA

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Chapter 7 model of TPF-C and should include appropriate flexible dynamics of the spacecraft and instrument module. The vibration isolation testbed has achieved TRL 3. The testbed schedule is given in Table 7-14. Table 7-14. Vibration Isolation Testbed Schedule Planned Completion Date Planned Activities Performance Targets TRL Pre-Phase A (Q4 & September FY05) Design and analyze three types of isolation systems: passive, augmented passive, and active. Develop models for each isolation design to support analysis. Demonstrate via analyses that each isolation design meets the following payload pointing and stability requirements: rigid body pointing, structure deformation, and optics deformation. 2, 3 Pre-Phase A (Q2 & March FY06) Improve isolation designs, add higherfidelity models to analyses, and conduct detailed sensitivity analyses. Complete system-level trade studies sufficient to assess the relative merits of isolation point designs. Identify testbed requirements needed to mature the technology. Select isolation design that achieves dynamics stability requirements based on analytical results including uncertainty parameter factors and trade study results. 3 Phase A Fabricate selected isolation devices and supporting testbeds for isolation subsystem test. Perform isolation subsystem tests. Update performance predictions based on isolation test results. Pointing and stability requirements met with analyses anchored from isolation subsystem test. 4, 5 Phase B Perform integrated pointing and isolation tests. Experimentally demonstrate performance of pointing and isolation system 5, 6 124
Plan for Technology Development 7.5.5 Closed-loop Secondary Mirror Position Control Scope Our plan is to start the testbed operation using stabilized lasers of wavelength 1.06 μm, currently in operation on the testbed. The first step will be to demonstrate active positioning at the 0.1 nm level along the beam axis (1 DOF), by the middle of FY05. By the middle of FY06, the goal will be to show the required secondary mirror positioning along all 6 DOF, using the down-selected TPF stabilized laser system described above. In Phase A we envision operating an engineering prototype, of order ¼ scale, that will lead to the design of the full mission system. Finally, in Phase B a realistic mission design will be tested, including the use of a 3 m tower to support the hexapod. The closed-loop secondary mirror position control has achieved TRL 3. The schedule is given in Table 7-15. Table 7-15. Closed-loop Secondary Mirror Position Control Schedule Planned Completion Date Planned Activities Performance Targets TRL Pre-Phase A Q3 FY05 Q2 FY06 Phase A Demonstrate required length control along optical axis (1 DOF) Demonstrate required length control along transverse axes, and in tip and tilt (6 DOF) Incorporate TPF down-selected stabilized laser system in testbed Implement Closed-loop Secondary Mirror Position Control on ¼ scale engineering prototype. Δx ~ 10 -10 m over 8 hour timescale 3 Δy, Δz ~ 10 -10 over 8 hour timescale Δθ, Δφ ~ 10 -10 over 8 hour timescale TPF secondary mirror positioning requirements in 6 DOF 4 4 5 Phase B Test of realistic system including 3 m tower support of hexapod TPF secondary mirror positioning requirements in 6 DOF 6 125
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JPL Publication 05-8 Technology Pla
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TECHNOLOGY PLAN TERRESTRIAL PLANET
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Recent Highlights Technical progres
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Figure i-4. Deformable mirror deliv
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Table of Contents Approvals........
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7.5.2 Precision Hexapod............
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Chapter 1 Figure 1-1. Artist's impr
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Chapter 1 interferometry, continues
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Chapter 1 Back end coronagraph opti
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Chapter 1 Surrounding the whole tel
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Chapter 1 Pol. BS fold/steering Mic
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Chapter 1 1.6.5 Sunshield The teles
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Chapter 1 expected architecture dow
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Chapter 1 Table 1-3. TPF-C Technolo
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Chapter 1 3B: Demonstrate, using th
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Chapter 2 2 Error Budgets 2.1 Contr
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Chapter 2 Error Budget Validation G
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Chapter 2 Further, it is shown that
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Chapter 2 Table 2-1. Requirement on
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Chapter 3 3 Optics and Starlight Su
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Chapter 3 are in progress with cont
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Chapter 3 Figure 3-5. Coronagraph s
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Chapter 3 (though not light-weight
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Chapter 3 Table 3-3. ITT Metrology
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Chapter 3 observations. The time it
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Chapter 3 vacuum-compatible, low-po
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Chapter 3 blank size. Westerhoff et
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Chapter 3 configurations, performan
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Chapter 3 Figure 3-10: Plots showin
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Chapter 3 The wavefront quality of
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Chapter 3 Figure 3-13. Optical layo
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Chapter 3 algorithms have limitatio
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Chapter 3 simulated star source is
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Chapter 4 Figure 4-1. Overview of t
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Chapter 4 enclosures, and stable la
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Chapter 4 facilities from which dat
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Chapter 4 Figure 4-5. Microslip Tri
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Chapter 4 Figure 4-7. Calibration o
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Chapter 4 Figure 4-8. Comparison of
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Chapter 4 4.2 Subsystem and System
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Chapter 4 Figure 4-11. Schematic of
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Chapter 4 Figure 4-12. Fine guiding
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Page 94 and 95: Chapter 5 TPF-C is planning a suite
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Page 118 and 119: Chapter 7 Improvements to the DM ov
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Page 122 and 123: Chapter 7 7.4 Optics and Starlight
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Page 128 and 129: Chapter 7 7.4.6 Transmissive Optics
Page 130 and 131: Chapter 7 7.4.8 Scatterometer Scope
Page 132 and 133: Chapter 7 7.5 Structural, Thermal,
Page 134 and 135: Chapter 7 7.5.3 Precision Structura
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Page 144 and 145: Chapter 7 7.7.3 Advanced Concepts:
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Page 148 and 149: Appendices Appendix B: TPF-C Detail
Page 150 and 151: Appendices Appendix D: TPF-C Techno
Page 152 and 153: Appendices Appendix F: Acronym List
Page 154: Appendices RWA SAO SBIR SIM SM SMFA
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TPF-C Technology Plan - Exoplanet Exploration Program - NASA

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