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 same mass. The following system components will be evaluated for producing hydrogen peroxide fuel from the atmospheric gases and stored hydrogen: • Hydrogen storage system • Zirconia oxygen generator • Sorption compressor • Hydrogen peroxide reactor • Power source 3.5.3.1 Hydrogen Storage System Hydrogen is the only component of the potential fuels identified that cannot be obtained from the material found on Mars. Therefore, if fuel is to be produced utilizing the in situ resources available on Mars, hydrogen will need to be brought from Earth. The main issue with storing and using hydrogen is its very low density. At ambient conditions, 1 liter of hydrogen contains only 10.7 KJ of energy. Even in its liquid state, the volumetric energy density of hydrogen (8.4 MJ/liter) is less then half that of other fuels (natural gas 17.8 MJ/liter, gasoline 31.1 MJ/liter). Storing a sufficient amount of it for use requires a large volume. Therefore, to make it practical the storage method must increase the hydrogen density as much as possible. The first step in evaluating the fuel production system is to determine the best method for storing hydrogen. Conventional methods of storage are as a compressed gas or as a cryogenic liquid. Work is being done in these areas that would make them more applicable to a space mission by reducing storage tank weight (carbon composite tanks) or increasing the density of cryogenic hydrogen (gelled or slush hydrogen). In addition, new storage methods are being devised that may be capable of storing hydrogen without the need for high-pressure tanks or the need to manage a cryogenic liquid (carbon nanotubes, carbon fullerenes, and hydrides). Hydrogen can be stored as either a gas or liquid. However, the stored hydrogen is only one part of the fuel system. The hydrogen must be reacted with oxygen to form hydrogen peroxide, which is the fuel chosen for production on Mars. The layouts for each of these storage and production systems are given in Figures 3-160 and 3-161. Aside from the storage tank and its associated components, the description and analysis of the remaining components is common to both systems. 3.5.3.1.1 Gaseous Hydrogen Storage 3.5.3.1.1.1 Pressure Tank High pressure hydrogen storage is the most conventional type of hydrogen storage. As the storage pressure increases, the density of the hydrogen gas will also increase. This relationship is shown in Figure 3-147. This figure represents the change in density (ρ) of hydrogen gas at various temperatures and pressures. This figure is based on the ideal gas law with a compressibility 180 Phase II Final Report
Chapter 3.0 Vehicle Design 3.5 Fuel Storage and Production factor (Z) for the hydrogen gas. [22] Where P and T are the gas pressure and temperature respectively and R is the gas constant for hydrogen (4157 N m/kg °K) ρ = P / ZRT Equation 3-36 Z = 0.99704 + 6.4149E-9 P Equation 3-37 The tradeoff with utilizing high density/high pressure storage is the increase in tank mass necessary to withstand the higher pressures. The wall thickness of the tank will increase with the increasing hoop stress due to the higher gas pressure. The calculation of the tank mass for hydrogen gas stored under pressure is a fairly straightforward analysis. This analysis is outlined below. For this analysis it is assumed that hydrogen will follow the behavior of an ideal gas represented by the equation of state, P V H =nZRT Equation 3-38 where R is the gas constant for hydrogen and has a value of 4157.2 (N m/°K kg), P (Pa) is the pressure of the gas, V H (m 3 ) is the volume, and T (°K) is its temperature. Using the gas constant given above, Equation 3-42 can be restated as follows, where m H is the mass of hydrogen: V H = 4157.2 Zm H T / P Equation 3-39 181
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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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