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

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Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars to address this subject. Similarly an analytical solution to blown flapping wing flight does not exist and new formulations for the aerodynamics of the flapping wing have been developed during this NIAC study as a first step toward addressing this deficiency. In both the CFD and analytical formulations, certain physical properties have yet to be implemented. For example, the analytical formulation correctly characterizes the aerodynamics of the flapping wing and is in agreement with the CFD results, but it has yet to implement those modules that account for the circulation due to the LEV and the effects of blowing. On the other hand, while CFD has been able to show that the effects of a correctly configured and blown flap significantly increase lift, the parameters of the point solution chosen did not yield the optimum levels of performance encountered experimentally in the wind tunnel for other blown wings. The analytical formulation for the flapping wing aerodynamics is designed to be a tool that can allow rapid permutations of these parameters to define the bounds of the design space and also to identify optima within that space. The CFD codes developed can then validate the analytical findings, however the ultimate validation will be future wind tunnel tests that are designed to test the Entomopter wing with the predicted optimal parameter set under Mars atmospheric conditions. This NIAC study has been able to develop the basic tools that will ultimately lead to these validating wind tunnel tests. The Entomopter’s Reciprocating Chemical Muscle was also sized for the Mars flight vehicle. Although torsional resonance is designed into the Entomopter’s wing flapping mechanism, this has not been modeled as part of the power calculations used in the design of the propulsion system. Therefore the payload capacity and endurance estimates for a Mars Entomopter with a 1.2 m wing span are conservative. Having addressed the flight regime and sizing of the Mars Entomopter, the issues of navigation and communication were considered. In particular the issues of Entomopter location and selfawareness amid unbriefed Mars terrain features were addressed. Two approaches were taken, the first of which was “rover-centric” with the philosophy that to reduce Entomopter weight and increased endurance, as much communications and navigation capability as possible should be contained in the Entomopter’s refueling rover. The second approach involved a more traditional design in which various sensor systems would be carried by the Entomopter to allow greater self-sufficiency albeit at the cost of greater gross weight and power consumption. Various science payload packages have been identified as well as Entomopter-enabled missions. Dual use of communications and navigation equipment was explored in support of the science missions so as to reduce the weight of redundant electronics. Based on the research conducted during this NIAC Phase II study, a design space has been identified in which Mars Entomopter flight is practical. The added capability offered by an Entomopter-based Mars surveyor is significant and will increase the amount of useful science that can be conducted during a Mars mission. The results of this NIAC study indicate that no other Mars surveying vehicle concept is comparable to that of the Entomopter when the combination of mission endurance and surveillance information resolution is considered. 274 Phase II Final Report
Appendix A: Mars Atmosphere Data JPL Reference Mars Atmosphere for -20° Latitude Appendix A: Mars Atmosphere Data JPL Reference Mars Atmosphere for -20° Latitude Mars Atmosphere Model coxZ 0.7 Lat = -20 Z,deg 41.9298101 H, km T, K P, Pa p, g/m3 µ, Pa*s v, m2/s 1/v 9.8750 205 273.6 6.968 1.04E-05 0.00150 667 9.6250 206 280.2 7.100 1.05E-05 0.00148 677 9.3750 207 286.8 7.234 1.05E-05 0.00146 687 9.1250 208 293.6 7.369 1.06E-05 0.00144 696 8.8750 209 300.6 7.507 1.06E-05 0.00142 706 8.6250 209 307.6 7.683 1.06E-05 0.00138 723 8.3750 210 314.8 7.826 1.07E-05 0.00136 733 8.1250 211 322.2 7.970 1.07E-05 0.00135 743 7.8750 212 329.7 8.117 1.08E-05 0.00133 753 7.6250 213 337.3 8.266 1.08E-05 0.00131 764 7.3750 214 345.0 8.416 1.09E-05 0.00129 774 7.1250 215 352.9 8.569 1.09E-05 0.00127 785 6.8750 216 361.0 8.724 1.10E-05 0.00126 795 6.6250 217 369.2 8.880 1.10E-05 0.00124 806 6.3750 218 377.5 9.039 1.11E-05 0.00122 817 6.1250 218 386.0 9.243 1.11E-05 0.00120 835 5.8750 219 394.7 9.407 1.11E-05 0.00118 847 5.6250 220 403.5 9.574 1.12E-05 0.00117 858 5.3750 221 412.5 9.743 1.12E-05 0.00115 869 5.1250 222 421.6 9.914 1.13E-05 0.00114 881 4.8750 223 430.9 10.087 1.13E-05 0.00112 892 4.6250 224 440.4 10.262 1.14E-05 0.00111 904 4.3750 224 450.0 10.487 1.14E-05 0.00108 924 4.1250 225 459.9 10.669 1.14E-05 0.00107 936 A-1
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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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Phase II Final Report - NASA's Institute for Advanced Concepts

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