Phase II Final Report - NASA's Institute for Advanced Concepts

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars PV Array Battery Charge Controller Battery To Load Figure 3-171: PV Array/Battery System Layout 3.6.5 Thin-film Photovoltaics There have been thin-film PVs since the beginning of PV technology. Thin film arrays are lightweight and highly flexible. The efficiencies of thin film arrays (although not as great as those of other types of solar arrays) has been steadily increasing. The current state-of-the-art thin film solar cells are primarily designed for terrestrial use and have achieved an efficiency in small area cells in excess of 12% AM0. (Efficiency here is defined for Air Mass Zero conditions, that is, for the solar spectrum outside the Earth's atmosphere.) There are four basic areas of research in thin film cells currently being supported in the United States by NASA, DOD, and DOE (i.e., Sibased, CIS-based, CdTe, and thin Si). All of these programs are working to develop a large area thin-film cell on a lightweight flexible polymer substrate or metal foil. Research has achieved respectable efficiency on glass, as well as on stainless steel foil. Progress has also been made toward substrates of Kapton or Mylar, and work is being done on a polymer with high temperature (600 o C) capabilities. However, large area thin film cells have yet to achieve 10% AM0 efficiencies. 210 Phase II Final Report
Chapter 3.0 Vehicle Design 3.6 Power System 16 14 12 10 CdS/Cu2S CuInSe2 CuGaSe2 CuInS2 CdTe a-Si CASCADES 8 6 4 2 0 1976 1978 1980 1982 1984 1986 1988 1990 1992 1994 1996 Figure 3-172: Historical Progress of Thin-film Solar Cell Efficiency. Experimentally Achieved Efficiencies (Extrapolated to Air Mass Zero Spectrum, in Percent) [293] The Kapton or other polymer substrate is capable of serving a double duty as the substrate for the cells and skin for the wing. The thin films are quite flexible and can easily accommodate the curved shape and flapping motion of the wing. Thin film cells tend to have a high optical absorption constant; therefore, active material may be as thin as 1 to 2 µ, yielding inherently lightweight cells. A very conservative projection of thinfilm solar cell technology would be a 5% efficient thinfilm cell fabricated on a 25 µ thick Kapton substrate. This yields a PV blanket specific power of 1.7 kW/kg. An optimistic projection might be a 15% thin film cell on a 7 µ thick Kapton substrate, leading to a PV blanket specific power of 15 kW/kg. These numbers compare favorably to current state-of-the-art spacecraft solar blankets (e.g., 67 W/kg at the array level for the flight-tested SAFE array) and 130 W/kg at the array level for the experimental APSA array using thin silicon solar cells. Preliminary results also indicate thin film solar cells may be inherently radiation-tolerant and not require a glass cover for radiation protection. They are highly tolerant of small damage areas from debris impact and any tearing. 211
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Planetary Exploration Using Biomime
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Table of Contents Table of Contents
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List of Tables List of Tables Table
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List of Figures List of Figures Fig
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List of Figures Figure 3-54: Pressu
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List of Figures Figure 3-138: Stere
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List of Figures Figure 4-24: Averag
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List of Contributors List of Contri
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Executive Summary Executive Summary
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Chapter 1.0 Introduction Chapter 1.
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Chapter 1.0 Introduction Figure 1-2
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Chapter 1.0 Introduction 1.1 Histor
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Chapter 1.0 Introduction 1.2 Origin
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Chapter 1.0 Introduction 1.3 Missio
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1.3.3.1 Surface Imaging The Entomop
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Chapter 2.0 Entomopter Configuratio
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Chapter 3.0 Vehicle Design 3.1 Wing
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3. Density: 1.40E-2 kg/m 3 4. Press
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Chapter 3.0 Vehicle Design 3.4 Reci
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Chapter 3.0 Vehicle Design 3.4 Reci
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Chapter 5.0 Potential Payload Funct
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Chapter 6.0 Media Exposure 6.1 Intr
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Chapter 6.0 Media Exposure 6.3 Onli
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Chapter 6.0 Media Exposure 6.6 Spec
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Chapter 7.0 Conclusion Chapter 7.0
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Appendix A: Mars Atmosphere Data JP
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Appendix A: Mars Atmosphere Data Ge
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Appendix A: Mars Atmosphere Data Ge
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Appendix A: Mars Atmosphere Data Ma
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Appendix B: Sizing Results Appendix
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Appendix B: Sizing Results 30 Wing
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Appendix B: Sizing Results 16 Wing
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Appendix B: Sizing Results Length 0
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Appendix B: Sizing Results Lenght 0
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Appendix C: List of References Appe
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Appendix C: List of References 41.
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Phase II Final Report - NASA's Institute for Advanced Concepts

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