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 3-12: Monopropellants and Their Phase-change Temperatures Monopropellant Boiling Point ( o C) Freezing Point ( o C) Density (gm/cm 3 ) Combustion Temperature ( o C) Specific Impulse (Isp) Hydrogen Peroxide (0.9H 2 O 2 0.1H 2 O) 141.1 -11.5 1.39 757 148 Ethylene Oxide (C 2 H 4 O) 10.6 -112.8 0.87 1004 199 Nitromethane (CH 3 NO 2 ) 101.2 -29 1.14 2193 245 n-Propyl Nitrate (C 3 H 7 NO 3 ) 110.5 -101.1 1.057 1078 210 Hydrazine (N 2 H 4 ) 113.4 1.5 1.008 633 199 Hydrazine Propellant Blend (HPB) HPB-1808 (18% HN, 8% water) 100 -20 na 230 61% Hydroxylammonium Nitrate (NH 3 OH)NO 3 (HAN) 14% Glycine (H 2 NCH 2 CO OH) 100 -35 na 190 Table 3-13: Characteristics of Fuel Candidates Hydrogen Ammonia Hydrazine Fuel Monomethyl Hydrazine Unsymmetrical dimethyl-hydrazine (UDMH) Characteristics Hydrogen is a stable, noncorrosive, nontoxic material. However, in order to be usable for this mission it must be kept in a liquid state. This requires cryogenic storage which would significantly increase the complexity of the mission. Ammonia is a stable compound that can be stored in Teflon, 18-8 stainless steel, aluminum or polyethylene. It is mildly toxic but can be fatal in concentrated exposure. The main issue with its use for this mission is that it is in the gaseous state under mission conditions. Although its most common use is as a monopropellant, hydrazine can also be used as a bipropellant. It has the same general properties as the monopropellant version; however, its performance is significantly improved when utilized in combination with an oxidizer. Monomethyl hydrazine is fairly stable at lower temperatures; however, it becomes unstable above 260°C (500°F). It can be stored in 18-8 stainless steel, aluminum, or Teflon. It is toxic. Its liquid temperature range is well within the requirements for the mission environment. Unsymmetrical dimethyl-hydrazine is stable at low temperatures but becomes violently unstable at temperatures above 260°C (500°F). It can be stored in most materials including mild steel, 18-8 stainless steel, aluminum, Teflon, and polyethylene. It has a lower level of toxicity then hydrazine but more then that of ammonia. Its liquidstate temperature range is well within that of the mission requirements. 172 Phase II Final Report
Chapter 3.0 Vehicle Design 3.5 Fuel Storage and Production Table 3-13: Characteristics of Fuel Candidates (Continued) Fuel Characteristics RP-1 Methane Propane Diborane RP-1 is a stable fuel developed for space applications. It is stable up to 370°C (700°F) and is compatible with all common metals, as well as meoprene, asbestos, fluorocarbons and epoxies. Its toxicity is comparable to that of kerosene. The liquid temperature range for RP-1 is within the operating range for the mission. However, the freezing point is at the estimated low temperature for the mission. To insure that RP-1 doesn't freeze during the mission, some active thermal control would probably be required. Methane is stable and compatible with all common metals as well as neoprene, asbestos, fluorocarbon, and epoxies. It is essentially nontoxic. The main issue with it is its low boiling point. This would require it to be used as a gas or stored cryogenically. Due to the small volume of the proposed Entomopter, storing the fuel as a gas would significantly limit the flight duration. Also using it as a cryogenic liquid would greatly increase the mission complexity. Propane essentially has the same properties as methane. It is stable and compatible with all common metals, as well as neoprene, asbestos, fluorocarbons, and epoxies. The issues with its use are the same as those of methane. Diborane is a gas at room temperatures and will slowly decompose. At higher temperatures it decomposes rapidly. It is compatible with most metals and some organic materials. It has moderate toxicity. The issues with using diborane are significant. It would need to be stored as a cryogenic liquid in order to provide for sufficient mission duration as well as minimize the decomposition rate. Because of these issues it would not be suitable for the proposed Entomopter mission. Table 3-14: Characteristics of Oxidizer Candidates Oxygen Fluorine Oxidizer Characteristics Oxygen is highly reactive and nontoxic. It is noncorrosive and is very stable in storage. The main issue with its use is that it would be in the gaseous form under the mission conditions. This will significantly limit the volume of oxygen which can be stored. Liquid oxygen can be used; however, this brings up significant issues regarding the storage and manufacture of a cryogenic liquid. Fluorine is highly reactive with almost any material. It can be stored in 18-8 stainless steel or copper but monel is preferred. It is very important that all materials that come into contact with fluorine are thoroughly cleaned so that there are no contaminating particles for the fluorine to react with. There are no nonmetallic materials which are completely unreactive with fluorine. It is also highly toxic and corrosive to body tissue. Like oxygen, it is a gas at mission temperatures. Therefore, it would need to be stored cryogenically in order to be used in the mission. 173
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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 3.6 Powe
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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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