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

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars which is determined and controlled by a fuel metering valve, is directed to the RCM actuator. The surface area of the actuator piston and its range and speed of throw, coupled with the pressure of the gas generated in the reaction chamber, ultimately determine the horsepower or wattage of the RCM system. The design point offered in Table 3-2 represents a realistic operating configuration for Entomopter on Mars. Here, a flapping frequency of 6 Hz over 75° will evolve 883W of power to nominally allow 14m/s flight in the lower atmosphere when using 1.2 m wings. In addition, this affords a useful lifting capacity of 1.5kg. Using the 883W power output as a goal (about 1 HP), an RCM can be designed with the following physical parameters: • 5.08 cm (2 in) Piston Diameter • 5.08 cm (2 in) Piston Throw • 3.5 kg/cm2 (50 psi) working pressure (maintained constant by the fuel metering through the reaction chamber) Working in units of pounds and inches, this results in a piston force of 157 lbs/sec at 6 Hz, or 0.29 HP. Since the fourth generation RCM actuator uses a split piston that is double-acting, the surface area is actually twice that of the single 2 inch face. This results in a power output of 852W. Variations due to friction losses and loading are easily accommodated by adjusting the working pressure. 50 psi is a low value relative to the thousands of pounds of pressure that can be evolved in a correctly designed RCM system. In fact, for the power output by the RCM actuator, its weight is quite modest. The RCM reaction chamber and actuator are the components that must withstand temperature and pressure extremes. These extremes will be dictated by the fuels used and the design pressure necessary to produce sufficient power for flight. Materials such as columbium coated titanium or Inconel steel are suitable candidates for the design of these components. Titanium alloys such as 6AL-V-2Sn exhibit 150,000 psi yield strength while Inconel-718X yields at 100,000 psi. The density of these materials is 0.164 lbs/in3 and 0.296 lbs/in3 respectively. Since RCM operation as defined above requires only 50 psi, the strength of a cylinder made from materials such as these is immense even with very thin walls. The addition of radial heat rejection fins adds significantly to the strength of the pressure vessels while not contributing greatly to the weight. In the final analysis, the thickness of the material will be dictated more by the desire for dimensional stability than pressure containment. For a split piston RCM actuator with a 2 inch diameter piston and 2 inch throw (per piston), the overall actuator size would be approximately 4 inches (10.16 cm) in length (excluding actuation shafts), and 2 inches in diameter plus the cylinder wall thickness and cooling fin diameter. Because the Mars atmosphere lack density, larger cooling fins will be desirable, perhaps on the order of 2 inches (5.08 cm) in radial length. To the 4 inch length of the actuator, one must add the length of the plena at each end to accommodate ejectors as shown in Figure 2-1, and the gas bearings with cam-follower wing cuffs to define the total length of the fuselage. 166 Phase II Final Report
Chapter 3.0 Vehicle Design 3.4 Reciprocating Chemical Muscle For the Mars Entomopter, the RCM actuator will have a volume of approximately 50.3 in3 (824 cm3), which is slightly larger than the volume of two cola cans. Figure 3-145 is a one-to-one representation of the RCM actuator when printed. Figure 3-145: Mars Entomopter RCM Actuator (Side View, Actual Size) The cooling fins will be designed to maximize mixing in the thin Mars atmosphere to create the maximum temperature differential and to prevent hot spots. Applied to the surface of these fins may be surface area-increasing treatments as well as heat-scavenging thermoelectric generator elements. The fins themselves act as strengthening bands like the hoops on a wooden barrel while avoiding unnecessary cylinder wall thickness and weight. As shown in Figure 3-146, the RCM actuator is mounted adjacent to its fuel tank that also contains the reaction chamber. Notional holes are shown in the cooling fins represent a mechanism to enhance mixing while reducing flat plate drag in forward flight. 167
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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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