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

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars Figure 3-142: Coordinated Piston Extension Figure 3-143: Fourth-generation RCM Dual Opposing Piston Shaft and Spur Gear Shown in Place 162 Phase II Final Report
Chapter 3.0 Vehicle Design 3.4 Reciprocating Chemical Muscle Advantages of this version of the fourth generation RCM can be summarized as: 1. Vibrationless 2. Internal porting 3. Guaranteed extension synchronization 4. Idler Gear sees low force and has low inertia 5. Force applied along central axis with offset arms 6. Straight rack and idler gear teeth easier to machine 7. Piston shafts can't rotate (due to idler gear) In addition, by blocking one of the actuator pistons and removing the spur gear, the RCM can be made operate in a single ended mode. It can also be made to function in a “one-shot” mode. In addition the entire system has been manufactured of materials similar in coefficient of thermal expansion, in order to minimize seizures of close tolerance components. Special perfluoro organic and diamond like coatings will be used for high wear areas and gasketing material in a production version. 3.4.3 Sizing of the Entomopter-based Aerial Mars Surveyor Many of the problems associated with the miniaturization of the terrestrial RCM actuator are relaxed when considering the scaled up Mars version. Further, the reciprocation rate required of the Mars RCM actuator will be less than half that required for the terrestrial version, so although the inertias of the larger component masses will be greater, the forces will be mitigated due to the smaller accelerations of those masses. The sizing of the Entomopter for aerial Mars survey is driven by the constraints of the Mars environment and choices made regarding the RCM, fuel type, wing parameters, and the baseline mission. Variables to be considered in a first order sizing analysis include the following: RCM Actuator: • Single Cylinder Volume (liter) • Piston Diameter (cm) • Piston Area (typ) (square cm) • Single Cylinder Throw (cm) • Cylinder Pressure (N/m2) • Temperature of Fuel Decomposition (°K) • Reciprocation Frequency (Hz) • Fuel Expansion Ratio (liquid-to-gas) • Moles of Gas required per cycle (n=PV/RT) • Liquid Fuel Expended per flap (both cylinders) (liters) • Liquid Fuel Capacity per min of flight (liters/min) • Liquid Fuel Weight consumed per minute of flight (kg) • Linear Force of both Cylinders at full pressure (N) • Linear-to-Rotational Cam-Follower Ratio • Combined Rotational Force available (at wing root) (N) 163
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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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