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

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars tional fixed wing flight. Similar advantage can be extracted in the case of flapping wing flight. The optimum airfoil suggested for low Reynolds number flight should have maximum camber and minimum thickness. Some of the suggested airfoils are shown in Figure 3-109. The pressure distribution on an optimized airfoil as compared to a conventional airfoil is shown in Figure 3- 110. Conventional Optimum Figure 3-110: Pressure Distribution for an Optimized Airfoil vs. That of a Conventional Airfoil However, with regard to the requirements of the Mars environment, this optimal airfoil shape in a flapping mode would still not be able to sustain steady flight as the lift coefficient values required for Mars are much higher than those in the Earth's atmosphere. To achieve efficient and controllable Mars flight at slow speeds, it was decided that active flow control of the airfoils would be used along with flapping to increase the lift values. This will be discussed in more detail below. After taking into consideration the lift requirement, another important aspect is the minimum value of thrust required for forward flight. In fact, in flapping motion, the resultant force produced has two components: lift and thrust, which should as a minimum, equal the weight and drag respectively for a steady flight. Unlike the conventional fixed wing airplane, where thrust is provided by engines, the sole contributor of thrust is the flapping motion. Many researchers in the past have addressed the thrust produced as a result of flapping. Kevin D. Jones has provided some experimental data for thrust produced by flapping motion of a 15 cm micro air vehicle in Earth's atmosphere [133]. His experimental model used is shown below as Figure 3-111. The experimental results are not generic and are only true for the current point solution problem, but can be extrapolated in the close vicinity of design points for thrust predictions. The model is fully capable of generating sufficient thrust to overcome drag values and produce forward flight for flapping frequencies of more than 25 Hz. Although the experimental data is only available for lower flapping frequencies (less than 12 Hz), values predicted by panel methods and CFD analysis can be taken for the purpose of estimation. 118 Phase II Final Report
Chapter 3.0 Vehicle Design 3.3 Wing Aerodynamics Figure 3-111: Flapping Wing Micro Air Vehicle Test Model The equations of motion have been derived from the schematic given in Figure 3-112. Figure 3-112: Parameter Definitions for the Jones Model For the purpose of analysis, Dr. Jones has selected different combinations of airfoils, and then studied their combined effects. These studied combinations are given in Figure 3-113. 119
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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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Chapter 3.0 Vehicle Design 3.5 Fuel
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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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