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

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars 140 ρ=0.0000279 slug/cu ft, T=-20.4°F 130 120 110 100 90 80 V req'd , m/s 70 60 50 Pneumatic Flyer, W/S=0.73 lb/sq ft Conventional Wing, W/S=1.46 psf W/S=2.92 lb/sq ft 40 30 20 10 Conventional Wing, CL=1.0 C L =5.3 C L =1.5x C L =2x 0 0 1 2 3 4 5 6 7 8 9 10 11 12 C L req'd Figure 3-134: Flight Speed at Mars Surface vs. Required C L 3.4 Reciprocating Chemical Muscle The heart of the proposed Mars Entomopter is a reciprocating chemical muscle (RCM). Internally-funded efforts at the Georgia Tech Research Institute were conducted to develop a proof of principal RCM. The RCM is an anaerobic, ignitionless, catalytic device that can operate from a number of chemical fuel sources. While under funding from DARPA/DSO to show feasibility of an Entomopter-based MAR, the RCM was refined, reduced in size, and demonstrated to develop the power and speed necessary for flight. 154 Phase II Final Report
Chapter 3.0 Vehicle Design 3.4 Reciprocating Chemical Muscle The RCM is a regenerative device that converts chemical energy into motion through a direct noncombustive chemical reaction. Hence, the concept of a “muscle” as opposed to an engine. There is no combustion taking place nor is there an ignition system required. The RCM is not only capable of producing autonomic wing flapping as well as small amounts of electricity for control of MEMS devices and the “nervous system” of the Entomopter, but it creates enough gas to energize circulation-controlled airfoils. This means that simple autonomic (involuntary, uncontrolled) wing flapping of constant frequency and equal amplitude can result in directional control of the Entomopter by varying the coefficient of lift (CL) on each of the wings, thereby inducing a roll moment about the body of the Entomopter while in flight. Figure 3-135 shows 'milli-scaled' wing structures grown in the Institute's stereolithography and fused deposition modeling machines. Wings like these will not only act as smart structures to create a proper angles of attack under opposite aerodynamic loads during the up beat and down beat, but the hollow micro-channels in the ribs provide circulation control gas from the RCM to “blow” the wings for directional control in flight as well as lift when the wing is at negative angles of attack during the up beat. Figure 3-135: Wing Structures Grown in Georgia Tech’s Stereolithography and Fused Deposition Modeling Machines. The implementation of a RCM is motivated chiefly by the basic necessity for very high rate of energy release from compact energy sources. Electrically-driven systems suffer from the poor energy density of batteries, while electrical actuators are typically dense (heavy), or suffer from insufficient force and motion as in the case of electrostatic or piezoelectric propulsors. To increase motion, piezoelectric ceramics can be stacked, but this leads to greater weight, stiffness, and often higher required voltages. Rheological fluids can be slow to respond and will therefore be difficult to use with flapping wing implementations requiring beat frequencies of 20 to 50 Hz. Faster acting polymeric muscles have been demonstrated, but require high actuation voltages, dictating the need for power conversion circuits which add weight and loss to the already heavy onboard battery pack. Actuators of NITINOL wire are totally out of the question due to the significant current requirements and variable performance under environmental extremes. The RCM was originally conceived as an actuator for the flapping wing of a small insect-like terrestrial entomopter. (See Figure 3-136.) It had a reciprocation rate limited by inertia and fric- 155
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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 3.5 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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