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

More documents

Recommendations

Info

Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars 3 2 Coefficient of Lift (CL) 1 0 0.000 0.020 0.040 0.060 0.080 0.100 0.120 0.140 0.160 0.180 -1 Case28 Case27 -2 -3 Time (t) in secs Figure 3-132: Variation of Lift Coefficient with Pitching Amplitude The results depict a similar trend for lift coefficient as that of flapping amplitude, except that in addition to influencing the thrust, it has a tremendous effect on the moment values. 3.3.3.11 Recommendations and Conclusion The results produced above are based on a simple analytical model defined to perform aeroelastic analysis. Although the results comport with the physics of the problem, the model is still not accurate enough to account for all the effects of flapping wing flight. To model the aerodynamics of Entomopter for true prediction of results in the lower Mars atmosphere, experimental results or more extensive CFD results must be calculated for all the cases defined in the designof-experiments array. Then, based on MANOVA analysis of the experimental results, the model can be refined to give better estimations. Also, the model used here can be rebased on vortex theory for propellers to accommodate the strong leading edge vortex effects. In addition to this modeling for the unblown wing, the main challenge will be to include the effects of circulation control into the analysis that can be modeled by addition of few more variables like: a. Temperature of blown gases b. Velocity of blown gases c. Blown area d. Direction of blown gases 150 Phase II Final Report
Chapter 3.0 Vehicle Design 3.3 Wing Aerodynamics This will further increase the number of cases required to be evaluated. The best option would be to perform CFD analyses for all these cases, and validating by experimental runs in the wind tunnel, to account for the unsteady effects of flapping wing flight. The experimental runs can be compensated for the Earth's environment and then based on Reynolds Number, the results could be extrapolated for the Mars Environment. Empirical results can be generated on a newly constructed flapping wing simulator in the GTRI wind tunnels (See Figure 3-133.). This hardware simulator, developed under a DARPA-funded project, is capable of operating with a full scale blown winglet of the exact planform used by the Mars Entomopter and at speeds comparable to those used in the CFD simulations. These wind tunnel tests are beyond the scope of work originally proposed under this NIAC Phase II effort, but will be conducted as follow-on work to advance and refine the CFD and analytical models developed here. Figure 3-133: GTRI Kinematically-correct Full-scale Wind Tunnel Wing Flapping Simulator 3.3.4 Active Flow Control (“Blowing” of the Wings) Even though positive net lift is obtained from both the CFD and analytical solutions, the force is not sufficient for flight in Mars’ lower atmosphere. Hence, active flow control technology will be used to augment the lift, and thrust along with reducing the drag of the Entomopter. The reciprocating chemical muscle-based propulsion of Entomopter provides exhaust that can be used as a supply of gas for circulation control. Blowing of the wing in a proper way is critical not only to the stability and control of the Entomopter, but in the Mars application, its ability to fly. Experiments on Earth in the wind tunnel have shown that blowing can achieve phenomenal results, with increases in lift by a factor of ten [83, 84]. Under the NIAC Phase II study, incorporation of the affects of blowing within the analytical formulation were not possible, though this has been identified as a follow-on effort. Similarly, the optimal computational description of the 151
Page 1 and 2:
Planetary Exploration Using Biomime
Page 3 and 4:
Table of Contents Table of Contents
Page 5 and 6:
List of Tables List of Tables Table
Page 7 and 8:
List of Figures List of Figures Fig
Page 9 and 10:
List of Figures Figure 3-54: Pressu
Page 11 and 12:
List of Figures Figure 3-138: Stere
Page 13 and 14:
List of Figures Figure 4-24: Averag
Page 15 and 16:
List of Contributors List of Contri
Page 17 and 18:
Executive Summary Executive Summary
Page 19 and 20:
Chapter 1.0 Introduction Chapter 1.
Page 21 and 22:
Chapter 1.0 Introduction Figure 1-2
Page 23 and 24:
Chapter 1.0 Introduction 1.1 Histor
Page 25 and 26:
Chapter 1.0 Introduction 1.2 Origin
Page 27 and 28:
Page 29 and 30:
Page 31 and 32:
Chapter 1.0 Introduction 1.3 Missio
Page 33 and 34:
Page 35 and 36:
1.3.3.1 Surface Imaging The Entomop
Page 37 and 38:
Page 39 and 40:
Page 41 and 42:
Page 43 and 44:
Chapter 2.0 Entomopter Configuratio
Page 45 and 46:
Page 47 and 48:
Page 49 and 50:
Page 51 and 52:
Page 53 and 54:
Page 55 and 56:
Page 57 and 58:
Page 59 and 60:
Chapter 3.0 Vehicle Design 3.1 Wing
Page 61 and 62:
Page 63 and 64:
Page 65 and 66:
Page 67 and 68:
Page 69 and 70:
Page 71 and 72:
Page 73 and 74:
Page 75 and 76:
Page 77 and 78:
Page 79 and 80:
Page 81 and 82:
Page 83 and 84:
Page 85 and 86:
Page 87 and 88:
Page 89 and 90:
Page 91 and 92:
Page 93 and 94:
Page 95 and 96:
Page 97 and 98:
Page 99 and 100:
Page 101 and 102:
Page 103 and 104:
Page 105 and 106:
Page 107 and 108:
Page 109 and 110:
Page 111 and 112:
Page 113 and 114:
Page 115 and 116:
Page 117 and 118: 3. Density: 1.40E-2 kg/m 3 4. Press
Page 119 and 120: Chapter 3.0 Vehicle Design 3.3 Wing
Page 167: Chapter 3.0 Vehicle Design 3.3 Wing
Page 173 and 174: Chapter 3.0 Vehicle Design 3.4 Reci
Page 187 and 188: Chapter 3.0 Vehicle Design 3.5 Fuel
Page 219 and 220:
Chapter 3.0 Vehicle Design 3.5 Fuel
Page 221 and 222:
Page 223 and 224:
Page 225 and 226:
Chapter 3.0 Vehicle Design 3.6 Powe
Page 227 and 228:
Page 229 and 230:
Page 231 and 232:
Page 233 and 234:
Page 235 and 236:
Page 237 and 238:
Page 239 and 240:
Page 241 and 242:
Page 243 and 244:
Chapter 4.0 Entomopter Flight Opera
Page 245 and 246:
Page 247 and 248:
Page 249 and 250:
Page 251 and 252:
Page 253 and 254:
Page 255 and 256:
Page 257 and 258:
Page 259 and 260:
Page 261 and 262:
Page 263 and 264:
Page 265 and 266:
Page 267 and 268:
Page 269 and 270:
Page 271 and 272:
Page 273 and 274:
Page 275 and 276:
Page 277 and 278:
Chapter 5.0 Potential Payload Funct
Page 279 and 280:
Page 281 and 282:
Page 283 and 284:
Page 285 and 286:
Chapter 6.0 Media Exposure 6.1 Intr
Page 287 and 288:
Chapter 6.0 Media Exposure 6.3 Onli
Page 289 and 290:
Chapter 6.0 Media Exposure 6.6 Spec
Page 291 and 292:
Chapter 7.0 Conclusion Chapter 7.0
Page 293 and 294:
Appendix A: Mars Atmosphere Data JP
Page 295 and 296:
Appendix A: Mars Atmosphere Data Ge
Page 297 and 298:
Appendix A: Mars Atmosphere Data Ge
Page 299 and 300:
Appendix A: Mars Atmosphere Data Ma
Page 301 and 302:
Page 303 and 304:
Page 305 and 306:
Page 307 and 308:
Appendix B: Sizing Results Appendix
Page 309 and 310:
Appendix B: Sizing Results 30 Wing
Page 311 and 312:
Appendix B: Sizing Results 16 Wing
Page 313 and 314:
Appendix B: Sizing Results Length 0
Page 315 and 316:
Page 317 and 318:
Page 319 and 320:
Appendix B: Sizing Results Lenght 0
Page 321 and 322:
Page 323 and 324:
Page 325 and 326:
Page 327 and 328:
Page 329 and 330:
Appendix C: List of References Appe
Page 331 and 332:
Appendix C: List of References 41.
Page 333 and 334:
Page 335 and 336:
Page 337 and 338:
Page 339 and 340:
Page 341 and 342:
Page 343 and 344:
show all

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

Create successful ePaper yourself

Delete template?

Save as template?