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

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars Figure 3-168: Typical Communication Power Profile for One Mission Segment 3.6.2 Science Instruments The science instrument power requirements will depend on what types of equipment are being used and their duration of use. Also, the ability to store and transmit the data collected will affect the rate of use and therefore power consumption of the science instruments. It is assumed that, while on the ground, soil collection and sampling will require more power than the in-flight instrumentation such as imaging. The energy consumption by the science instruments through one mission cycle would be 1.8 W-h. Figure 3-169: Typical Science Instrument Power Profile for One Mission Segment 208 Phase II Final Report
Chapter 3.0 Vehicle Design 3.6 Power System 3.6.3 Internal Systems The internal systems consist of any onboard computer as well as other internal systems used for vehicle operation. These systems would include health monitoring, avionics, and flight control. Energy consumption by the internal systems through one mission cycle would be 1.0 W-h. Figure 3-170: Typical Internal Systems Power Profile for One Mission Segment 3.6.4 Photovoltaic/Battery The photovoltaic (PV) system consists of a flexible thin film array mounted on the wings of the Entomopter with a rechargeable battery and battery-charge controller. The array supplies power directly to the loads and recharging the battery. The battery-charge controller monitors the rate and state of charge of the battery. The battery is used to supply power when either the array is inoperable (such as during the night period) or when the load requirements cannot be met by the array alone. A diagram of the system is shown in Figure 3-171. The sizing of each of the components depends on the load requirements as well as the available power from the solar array. Some candidate solar arrays and their characteristics are listed in Table 3-23 [293]. The type of PV array best suited for this application is the thin film array. Thin film arrays are very lightweight and flexible. They can be easily molded to the Entomopter's wing and should not affect the aerodynamic performance of the vehicle. Depending on the characteristics of the solar array chosen, it may be possible to use the array as the covering on the wing. This would reduce the structure mass of the vehicle, thereby reducing the impact of the PV array on the system. Thin film PV arrays are also very robust in their construction and present the greatest potential to withstand the acceleration/deceleration loads of the rapidly flapping wing. Because of these characteristics, only thin film PV arrays were considered for this application. Figure 3-172 shows the advancement in performance of thin film solar cells over the last 25 years. 209
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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 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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