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

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars For a cylinder: N UD = [0.60 + 0.387 R ad 1/6 / [1 + (0.559 /PR) 9/16 ] 8/27 ] 2 Equation 3-51 Where the Rayleigh number is given by the following equation in which g is the gravitational constant.: R ad = g β (T 8 – T s ) D 3 / (ν α) Equation 3-52 By assuming an ideal gas, the volumetric thermal expansion coefficient (β) is equal to the inverse of the gas temperature in °K (β = 1/ T 8 ). The gas diffusivity and viscosity can be represented by the following data-curve fits for CO 2 . α = -1.2959E-6 + 8.5377E-9 T 8 + 1.0846E-10 T 2 8 Equation 3-53 Equation 3-54 ν = 4.1273E-9 + 4.4095E-9 T 8 + 7.8266E-11 T 8 2 Equation 3-55 Once the insulation outer surface temperature is known, the boil-off rate (M) in kg/s of the liquid hydrogen can be calculated. This is done through an energy balance between the heat flow through the insulation and the energy taken to boil the liquid hydrogen. The energy to boil the liquid is based on the latent heat of vaporization of liquid hydrogen (h fg = 446592 J/kg): K A (T s – T LH2 ) /L = M h fg The above analysis produced an estimate of how long it takes to boil off 50% of the hydrogen and the tank total mass as a function of the insulation thickness. This is shown in Figures 3-153 and 3-154 for various amounts of stored liquid hydrogen. These results are based on using evacuated aluminum foil separated with fluffy glass mats as the insulation material. This insulation, although heavier the most of the others listed, has the lowest thermal conductivity and therefore was deemed the best choice. 192 Phase II Final Report
Chapter 3.0 Vehicle Design 3.5 Fuel Storage and Production 250 200 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 150 100 50 0 0 0.05 0.1 0.15 0.2 0.25 Insulation Thickness (m) Figure 3-153: Effect of Insulation Thickness on Overall Storage Tank Mass 30 25 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 20 15 10 5 0 0 0.05 0.1 0.15 0.2 0.25 Insulation Thickness (m) Figure 3-154: Effect of Insulation Thickness on Overall Tank Mass 193
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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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