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

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars 0.25 0.2 0.15 0.1 kg LH2, 0.138 m Dia. Tank 0.2 kg LH2, 0.176 m Dia. Tank 0.5 kg LH2, 0.24 m Dia. Tank 1.0 kg LH2, 0.30 m Dia. Tank 1.5 kg LH2, 0.34 m Dia. Tank 2.0 kg LH2, 0.38 m Dia. Tank 0.1 0.05 0 0 0.05 0.1 0.15 0.2 0.25 Insulation Thickness (m) Figure 3-157: Rate of Energy Loss Due to Boil-off of the Liquid Hydrogen Most cryocoolers in production have capacities that are much greater than that shown in Figure 3-157. The power consumption of these cryocoolers is also much greater than that provided by the proposed Entomopter mission. State-of-the-art cryocoolers require between 2.5 kW to 7.5 kW of power and provide cooling capacities of between 5 W and 18 W at 20°K. This is much more than needed for this application. To get an estimate of the cryocooler power required to meet the power demand shown in Figure 3-157, therefore, the output/power consumption of a number of state-of-the-art cryocoolers was linearly scaled to the range shown in Figure 3-157. This scaling was based on the performance average of all the cryocoolers examined. The resultant cryocooler power requirement is shown in Figure 3-158. These power levels (shown in Figure 3-158) are achievable and realistic for the proposed Entomopter mission and justify the use of liquid hydrogen as a means of storing hydrogen for this mission. 196 Phase II Final Report
Chapter 3.0 Vehicle Design 3.5 Fuel Storage and Production 120 100 80 0.1 kg LH2, 0.138 m Dia. Tank 0.2 kg LH2, 0.176 m Dia. Tank 0.5 kg LH2, 0.24 m Dia. Tank 1.0 kg LH2, 0.30 m Dia. Tank 1.5 kg LH2, 0.34 m Dia. Tank 2.0 kg LH2, 0.38 m Dia. Tank 60 40 20 0 0 0.05 0.1 0.15 0.2 0.25 Insulation Thickness (m) Figure 3-158: Cryocooler Power Requirement to Meet Boil-off Demand To determine the optimum insulation thickness for a tank that includes the cryocooler, an overall mass estimate of this system has to be made. This mass estimate includes the tank mass, insulation mass, cryocooler mass, and additional power system mass needed to operate the cryocooler. The results of this analysis are shown in Figure 3-159. This figure was generated utilizing a PV battery power system as the power source. The power required to run the cryocooler was based on the heat load shown in Figure 3-157. The mass of the power system was based on the PV/battery system described in the power source section. For all of the liquid hydrogen masses examined, an insulation thickness of 0.04 m was optimal for minimizing the system mass. 197
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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 4.0 Entomopter Flight Opera
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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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