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

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars considered. The main restriction is that the fuel needs to be a monopropellant. This requirement is based on reducing the complexity of the engine and fuel storage/feed system on the Entomopter. Minimizing wing loading on the Entomopter is critical, so a fuel system with only one tank and associated piping is highly beneficial. 3.5.2 Propellant Selection The design of the Entomopter requires the generation and expansion of gas for the vehicle to operate. This gas can be generated either by combustion, a catalytic reaction, or sublimation of a material. The gas is necessary to drive the reciprocating piston that drives the wing motion. However, it is also needed for various other aspects of the vehicle’s design, including ultrasonic emissions for altimetry and obstacle avoidance, air bearings supply, and lift-augmentation blowing. Because gas generation is an integral part of the operation of the vehicle, the power source must be a fuel-based system. Fuel selection will be based on the following criteria: 1. Ability of the fuel to meet the environmental conditions of the mission, 2. Ability of the fuel to provide the required amount of gas for the operation of the Entomopter, 3. and ability to make fuel on the Mars surface out of the indigenous materials present in the atmosphere and soil. The ideal fuel will be a liquid monopropellant. A monopropellant is desirable because it reduces the complexity of storage and delivery systems for the fuel. Liquid form minimizes the storage volume and provides for easier containment. The operational constraints on the fuel require it to be capable of being stored for extended periods of time (up to 2 years) with little or no degradation, and to be capable of withstanding the deep space environment during transit as well as the environment on the surface of Mars. The main environmental issue during transit and on the Mars surface is the temperature. Assuming that there is no active thermal control or heating available, the fuel must be capable of withstanding temperatures down to -40° C for extended periods of time. If the fuel can remain liquid at these temperatures, this greatly simplifies the propellant delivery system as well as eliminates the need for power- and weight-consuming heaters. This also reduces the overall risk of the mission by eliminating a failure source occurring from improperly thawed fuel or a failed heater. An overall list of potential fuels (and fuel oxidizer combinations) is listed in Table 3-10 [119, 45]. The ability to meet the requirements listed above will be evaluated, and each will be ranked regarding their applicability for the mission. 170 Phase II Final Report
Chapter 3.0 Vehicle Design 3.5 Fuel Storage and Production Table 3-10: Fuels and Their Phase-change Temperatures Fuel Boiling Point ( o C) Freezing Point ( o C) Potential Oxidizers Density (gm/cm 3 at 20 o C) Hydrogen (H2) -253 -259 Oxygen, Fluorine 0.071(at - 253°C) Ammonia (NH3) -33.4 -77.7 Hydrazine (N2H4) 113.4 1.5 Monomethyl Hydrazine (N2H6C) 89.2 -52.5 Unsymmetrical Dimethyl Hydrazine (N2H8C2) 63.8 -57.2 RP-1 (C11.74H21.83) 185 -40 Oxygen, Fluorine, Nitrogen Tetroxide, Chlorine Trifluoride 0.611 Oxygen, Fluorine, Nitrogen Tetroxide, Chlorine Trifluoride 1.008 Nitrogen Tetroxide, Chlorine Trifluoride, Inhibited Red Fuming Nitric Acid 0.874 Oxygen, Fluorine, Nitrogen Tetroxide, Chlorine Trifluoride 0.792 Oxygen, Inhibited Red Fuming Nitric Acid 0.801 Methane (CH4) -161 -183.9 Oxygen, Fluorine Propane (C3H8) -42.2 -187.1 Oxygen, Fluorine Diborane (B2H6) -92.6 -164.8 Difluoride 0.415 (at - 164°C) 0.585(at - 44°C) 0.435(at - 92.6°C) Table 3-11: Oxidizers and Their Phase-change Temperatures Oxidizer Boiling Point ( o C) Freezing Point ( o C) Density (gm/cm 3 ) Oxygen (O 2 ) -183 -218.8 1.143 Fluorine (F 2 ) -188.1 -219.6 1.505 Nitrogen Tetroxide (MON3) (N 2 O 4 ) 21.2 -11.2 1.45 Chlorine Trifluoride (CLF 3 ) 11.8 -76.6 1.825 Inhibited Red Fuming Nitric Acid (IRFNA) (0.835HNO 3 0.140NO 2 0.020H 2 O0.005HF) ~ 60 ~ -62.2 1.56 Oxygen Difluoride (OF 2 ) -145 -223.9 1.521 Nitrogen Tetroxide (MON25) (N 2 O 4 ) -9 -54 1.45 171
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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 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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