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

More documents

Recommendations

Info

Planetary Exploration Using Biomimetics An Entomopter for Flight on Mars 0.4 0.35 0.3 13.8 Mpa (2000 psi) 34.5 Mpa (5000 psi) 68.9 Mpa (10,000 psi) 0.25 0.2 0.15 0.1 0.05 0 0 0.5 1 1.5 2 2.5 Hydrogen Mass Stored (kg) Figure 3-149: Tank Radius as a Function of Storage Pressure for Various Hydrogen Mass The material utilized in constructing the tank can be either a metal such as steel, titanium, aluminum or a composite. Since most composites are porous to hydrogen, a composite tank will require a liner to prevent the hydrogen from migrating through the tank wall. Liner materials are usually a type of polymer or a metal such as aluminum. Also, coatings are being investigated as a lightweight means of preventing hydrogen penetration through the tank. Composite tanks offer the best weight density of hydrogen. Tanks under development at Quantum Technologies have achieved up to 11.3% hydrogen by weight. However, a more realistic number for composite storage tanks in practical use is between 7.5% and 8.5% weight of hydrogen. In addition to the stress placed on the tank due to the pressure-loading additional issues will arise when using a high-pressure tank for space applications. These issues include radiation effects, thermal cycling, aging, creep, fatigue, and hydrogen embitterment. Depending on the tank material chosen, the design life and the operating pressure each of these factors would need to be investigated to determine their effects on a particular tank design. To maximize the storage volume for a given tank placement, the ideal configuration would be to construct a conformal tank. A conformal tank can hold up to 20% more hydrogen in a given envelope and pressure then a cylindrical or spherical tank. This presumes that a conformal tank 184 Phase II Final Report
Chapter 3.0 Vehicle Design 3.5 Fuel Storage and Production can use more than 80% of its envelope volume. This increase in usable storage compared to a conventional cylindrical tank is shown in Figure 3-150. 0.85 0.8 0.75 0.7 0.65 0.6 0.55 Cylindricl Tank Conformal Tank 0.5 0.45 0.4 1 1.5 2 2.5 3 3.5 4 4.5 5 Space Envelope Aspect Ratio Figure 3-150: Effect of Conformal Tanks on Available Space Utilization [91] The ability to construct a lightweight, high-pressure conformal tank is presently being investigated by Thiokol Propulsion under a Department of Energy contract. [91] 3.5.3.1.1.2 Metal Hydride Metal hydrides are metallic alloys that absorb hydrogen. These alloys can be used as a storage mechanism because of their ability to not only absorb hydrogen but also release it. The release of hydrogen is directly related to the temperature of the hydride. Typically, metal hydrides can hold hydrogen equal to approximately 1% to 2% of their weight. If active heating is supplied to remove the hydrogen this can increase to 5% to 7% of the hydride weight. If the temperature is held constant, the hydrogen is released at a constant pressure. The metal hydride tank can be used repeatedly to store and release hydrogen. The limiting factor on its ability to store hydrogen is the accumulation of impurities within the tank. These impurities fill the spaces that would normally store hydrogen, thereby reducing tank capacity. The key trade off to utilizing a metal hydride storage system is whether there is sufficient heatgeneration capability to extract the hydrogen from the hydride. The heat available to the hydride must also address the inefficiencies associated with the heat transfer device used to move the 185
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:
Page 121 and 122:
Page 123 and 124:
Page 125 and 126:
Page 127 and 128:
Page 129 and 130:
Page 131 and 132:
Page 133 and 134:
Page 135 and 136:
Page 137 and 138:
Page 139 and 140:
Page 141 and 142:
Page 143 and 144:
Page 145 and 146:
Page 147 and 148:
Page 149 and 150:
Page 151 and 152: 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 201: Chapter 3.0 Vehicle Design 3.5 Fuel
Page 225 and 226: Chapter 3.0 Vehicle Design 3.6 Powe
Page 243 and 244: Chapter 4.0 Entomopter Flight Opera
Page 253 and 254:
Chapter 4.0 Entomopter Flight Opera
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?