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

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars The C rating is a gauge of the current producing capacity and discharge time of the battery. At 1C the 930 mAh battery would produce 930 mA for 1 hour. At C/5 it would produce 186 mA for 5 hours, and at 2C it would produce 1,860 mA for 0.5 hour. It should be noted that as the discharge time decreases, the overall capacity of the battery will also decrease. Based on the estimated power consumption of the various systems, shown in Figures 3-168 through 3-170, the maximum power consumption is 3.5 W, and the total energy consumption for a mission cycle is 3.1 W-h. An estimate of the required battery capacity is 100% of the total energy required for the mission. This battery capacity allows the battery to provide power to the systems when the array is offline (shadowed). This also provides a redundancy for supplying sufficient power in the event the array fails. This requires a battery with 3.1 W-h of capacity. Based on the battery data listed in Table 3-25, the battery mass would be 0.023 kg. The overall system mass estimate for the array/battery system is listed in Table 3-26. Table 3-26: PV/Battery System Mass Estimate System Component Mass (kg) Solar Array 0.014 Battery 0.023 Contingency (50% for wiring, electronics, etc.) 0.037 Total System Mass 0.0555 It should be noted that the system mass shown in Table 3-26 represents values based on state-ofthe-art components. With future advancements in these components, this may be significantly reduced. Also any variation in the assumptions used to generate these numbers will also greatly affect these results. 3.6.7 Thermoelectric Power Generation The basic principle behind a thermoelectric power generator is that if two different metals, semimetals, or semiconductors are joined at one end and separated along their length, a current will be produced in each metal strip as long as there is a temperature difference between each side of the junction. The configuration of a thermoelectric power generator is shown in Figure 3-181. The heat source provides a high-temperature source from which heat will flow through the converter. For the Entomopter application, heat can be generated either through the combustion of the propellant or from an isotope heat source. A heat sink must also be used to dissipate the excess heat and maintain the cold side of the thermoelectric generator at a temperature below that of the hot side. It is this temperature difference that produces the direct current electrical power. Thermoelectric generators can be made for power levels ranging anywhere from 10 -6 W to 10 2 W. Semiconductor material is by far the best choice for the construction of a thermoelectric generator. These materials can presently achieve efficiencies on the order of 5% to 10%. 220 Phase II Final Report
Chapter 3.0 Vehicle Design 3.6 Power System Figure 3-181: Operational Diagram of a Thermoelectric Generator For use on the Entomopter, the thermoelectric generator would need to be very lightweight and compact. A micro-thin film thermoelectric, under development through DARPA [197], would be the ideal candidate. State-of-the-art thin film thermoelectric devices, shown in Figure 3-182, have efficiencies in the 5% range. However, projections for future efficiencies are up to 20%. These thin film thermoelectric devices can be integrated onto the combustion chamber wall and use the excess heat produced during combustion to produce electricity. Experimental models are capable of generating 20W of power from a 1 cm 3 combustion engine. The specific mass of these devices is on the order of 4 W/gm. Figure 3-182: Photo of a Thin Film Thermoelectric Device [27] 221
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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 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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