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

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars Table 3-16 lists the potential bipropellant combinations and monopropellants that would be applicable. Also given is the Isp of each propellant. This can be used to gauge the energy contained within the propellant. The higher the Isp the greater the energy released during combustion. Table 3-16: Propellant Candidates based on Temperature and Operational State Requirements Propellant Oxidizer/Fuel Ratio Isp Combustion Temperature ( o C) Fuel: Monomethyl Hydrazine Oxidizer: Nitrogen Tetroxide 2.20 288 3,122 Fuel: Monomethyl Hydrazine Oxidizer: Chlorine Trifluoride 3.00 283 3,318 Fuel: Monomethyl Hydrazine Oxidizer: IRFNA 2.50 274 2,848 Fuel: UDMH Oxidizer: Nitrogen Tetroxide 2.70 286 3,162 Fuel: UDMH Oxidizer: Chlorine Trifluoride 2.85 278 3,306 Fuel: RP-1 Oxidizer: IRFNA 4.90 263 2,881 Monopropellant: Hydrogen Peroxide na 148 757 Monopropellant: Ethylene Oxide na 199 1,004 Monopropellant: Nitromethane na 245 2,192 Monopropellant: n-Propyl Nitrate na 209 1,077 Monopropellant: HPB na 200 ---- Monopropellant: HAN na --- ---- 3.5.2.2 Fuel Production A key Entomopter capability is our ability to refuel it while it is on the Mars surface. One potential method for achieving this is to produce the fuel from resources found within the Mars environment. A list of the elements and compounds is given in the environmental section for both the soil and atmosphere. From the listing of elements and compounds available, it can be seen that there is very little hydrogen available on Mars. The only compound containing hydrogen is the trace water vapor within the Mars atmosphere, and this constitutes only 0.03% of the atmosphere makeup. However all the propellants listed in Table 3-13 require hydrogen. Therefore it will need to be assumed that unless a water source is found on Mars, the hydrogen needed to produce the selected fuel will need to be brought from Earth. As of this writing, data from the Mars Odyssey spacecraft has indicated that there may be large quantities of subsurface water on 176 Phase II Final Report
Chapter 3.0 Vehicle Design 3.5 Fuel Storage and Production Mars [199]. However, insufficient information is available to determine if the potential water could be extracted and utilized by the Entomopter system for fuel production. Therefore, the fuel selection and analysis will be based on the need to provide hydrogen from Earth. As more information is obtained on the potential of utilizing the subsurface water on Mars, the results of this selection process may change. The remaining elements that make up the fuels listed in Table 3-16 are present on Mars with the exception of fluorine. The lack of fluorine, as well as the scarcity of chlorine, eliminates the following four propellants as potential candidates for fueling the Entomopter: Monomethyl hydrazine and chlorine trifluoride, monomethyl hydrazine and IRFNA, UDMH and chlorine trifluoride, RPI and IRFNA. Also HAN and the HPB monopropellants were eliminated due the complexity in their chemical makeup, which would be very difficult to manufacture. Because the remaining propellants all require hydrogen (which must be brought from Earth) the next step is to determine which of these propellants minimize this hydrogen requirement. Table 3-17 shows the percentage of hydrogen on a weight basis for the candidate fuels. Table 3-17: Percent of Hydrogen by Weight for the Various Candidate Propellants Fuel/Oxidizer Chemical Makeup Percent Hydrogen by Weight Monomethyl Hydrazine and Nitrogen Tetroxide (N2H6C)+2(N2O4) 2.61% UDMH and Nitrogen Tetroxide (N2H6C)+2.7(N2O4) 1.96% Hydrogen Peroxide (0.9H2O20.1H2O) 5.38% Ethylene Oxide (C2H4O) 9.09% NitroMethane (CH3NO2) 4.92% n-Propyl Nitrate (C3H7NO3) 6.66% Based on Table 3-17, the primary choice to minimize the need for hydrogen is the bipropellant UDMH with nitrogen tetroxide. However, a bipropellant system will increase the complexity of the overall mission. It will require two separate production plants, one for the fuel and one for the oxidizer, as well as separate storage and fueling ports. Unless engine performance becomes a significant issue, the primary choice for the propellant will be a monopropellant that significantly reduces the complexity of the production system. Overall, the propellant selection can be narrowed to four potential candidates, two bipropellants and two monopropellants: monomethyl hydrazine fuel and nitrogen tetroxide oxidizer, UDMH fuel and nitrogen tetroxide oxidizer, hydrogen peroxide and nitromethane. Ethylene oxide and n- propyl nitrate were eliminated as potential fuels due to the relatively higher percentage of hydrogen content. Of these remaining four fuels, hydrogen peroxide is the primary candidate for production on Mars. 177
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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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