ESA Document - Emits - ESA

More documents

Recommendations

Info

s 4.4.8 Propulsion HMM Assessment Study Report: CDF-20(A) February 2004 page 362 of 422 4.4.8.1 Requirements and design drivers According to mission analysis the total DV required for the deorbiting manoeuvre is estimated to be 98 m/s. Thrust required for this manoeuvre is assumed of 20 kN. This value has been selected by similarity on the basis of the thrust to mass ratio of the Soyuz module. 4.4.8.2 Assumptions and trade-offs Module dry mass is estimated 45 tonnes Only Storable bi-propellant are considered. 4.4.8.3 Baseline design Four YUZHNOYE RD 869 pump-fed thruster have been chosen as propulsion system for this module. The thruster is under development for 4 th stage of the European VEGA Launcher. The propulsion system presents the following characteristics. 4.4.8.4 Budgets Characteristic Value Number of thruster 4 Thrust 5 kN (pump- fed) Isp 325 sec exit diameter 325 mm length 600 mm thruster mass 34 kg propellant UDMH/NTO O/F ratio 2.1 number of tanks 2+2 Tanks material Ti max MEOP 7 bar Mass of UDMH tank 3 kg (each) Mass of NTO tank 2.5 kg (each) Table 4-46: De-orbit propulsion system summary Propellant mass 1463 kg Propulsion Dry mass (including margins) 253 kg This mass includes an estimation of thrusters mass, the tanks, and a roughly estimation of feedlines, valves and regulators, propulsion thermal control, avionics, actuators and does not consider the structure of the propulsion system, power and communication.
s 4.5 Mars Ascent Vehicle 4.5.1 Trajectories HMM Assessment Study Report: CDF-20(A) February 2004 page 363 of 422 4.5.1.1 Requirements and design drivers The objective is to obtain an ascent trajectory which minimises the lift off mass, by means of selecting the proper propellant masses in each stage, firing time in each stage, pitch and yaw profile. 4.5.1.2 Baseline trajectory 4.5.1.2.1 Input data Initial conditions The optimal trajectory depends on both the altitude and latitude of the launch pad. The landing site drives the latitude of the launch site, and it was agreed to be 20 degrees North as reference. The reference altitude was assumed to be 0 Km, to be conservative. The longitude was assumed to be equal to 0, since it has no influence in the trajectory computation. Final conditions The final conditions are those corresponding to a circular orbit of 500 km altitude and 32 degrees of inclination. Mass budget Table 4-47 shows the mass budget used for the baseline trajectory. During the optimisation process the mass of the tanks was considered as a variable, being equal to 3% of the propellant mass. Dry Mass (except Tanks) 1st Stage 2nd Stage Tanks Total Dry Mass Prop Dry Mass (except Tanks) Tanks Total Dry Mass Prop Lift Off Mass 700 388 1088 12922 5100 81 5181 2705 21896 Table 4-47: Mass budget in Kg Propulsion system Table 4-48 shows the performance data of the propulsion system and the final propulsion configuration. Type of engine Number of engines Thrust (N) Isp(s) Nozzle Diameter (mm) 1st Stage Aestus (advance) 4 33000 330 1070 2nd Stage RD 869 4 5000 325 375 Drag coefficients and reference area Table 4-48: Propulsion system
Page 1 and 2:
s HMM Assessment Study Report: CDF-
Page 3 and 4:
s STUDY TEAM HMM Assessment Study R
Page 5 and 6:
s T A B L E O F C O N T E N T S HMM
Page 7 and 8:
Page 9 and 10:
s L I S T O F F I G U R E S HMM Ass
Page 11 and 12:
Page 13 and 14:
Page 15 and 16:
s L I S T O F T A B L E S HMM Asses
Page 17 and 18:
Page 19 and 20:
s 1 INTRODUCTION 1.1 Background HMM
Page 21 and 22:
s 2 GENERAL ARCHITECTURE 2.1 Study
Page 23 and 24:
Page 25 and 26:
s 2.2.4.2 Accelerations HMM Assessm
Page 27 and 28:
s 2.2.4.4 Temperature and relative
Page 29 and 30:
Page 31 and 32:
Page 33 and 34:
s Figure 2-10: Trajectory Overview
Page 35 and 36:
s 2.4.3.5 TEI and planetary protect
Page 37 and 38:
Page 39 and 40:
Page 41 and 42:
Page 43 and 44:
Page 45 and 46:
s Mars Excursion Vehicle Transfer H
Page 47 and 48:
s 2.7.5.1 Mission elements dry mass
Page 49 and 50:
s 2.7.5.8 MEV release The MEV is re
Page 51 and 52:
s Total mission time (days) 1200 10
Page 53 and 54:
Page 55 and 56:
Page 57 and 58:
s stack 9 Propellant mass of the ne
Page 59 and 60:
Page 61 and 62:
Page 63 and 64:
Page 65 and 66:
s The core supporting structure has
Page 67 and 68:
s 2.7.7.1.3 Mars excursion module S
Page 69 and 70:
s 2.7.7.1.4 Earth return capsule HM
Page 71 and 72:
s Mission Phase Description Event s
Page 73 and 74:
s Mission Phase Description Event s
Page 75 and 76:
s 2.7.10 Mission performance Table
Page 77 and 78:
s Days on Martian surface 450 400 3
Page 79 and 80:
Page 81 and 82:
Page 83 and 84:
s Maximum manoeuvre duration 6 mont
Page 85 and 86:
s % of loss from baseline 20 18 16
Page 87 and 88:
s 2.7.15 Sensitivity analysis HMM A
Page 89 and 90:
s 2.7.15.4 Influence of the mass of
Page 91 and 92:
Page 93 and 94:
s Parameters used: • No Shuttle
Page 95 and 96:
s 2.8.3.3 Launch 3- Front node Figu
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:
s 2.10.1.4 Communications HMM Asses
Page 111 and 112:
Page 113 and 114:
s 2.10.2.2.2 LEO assembly HMM Asses
Page 115 and 116:
Page 117 and 118:
s Basic RF link Four 70-m Ka-band s
Page 119 and 120:
Page 121 and 122:
Page 123 and 124:
Page 125 and 126:
s 3 TRANSFER VEHICLE 3.1 Systems…
Page 127 and 128:
s Operational Requirements It shall
Page 129 and 130:
s Trans Mars Injection Module Mars
Page 131 and 132:
s Figure 3-2: Parallel configuratio
Page 133 and 134:
s Figure 3-6: Global dimensions com
Page 135 and 136:
s Front Node 3.2.3.1.3 EVA systems
Page 137 and 138:
s Trans Mars Injection (three stage
Page 139 and 140:
s Figure 3-16: Recommendations for
Page 141 and 142:
s Factors to be considered Impacts
Page 143 and 144:
Page 145 and 146:
Page 147 and 148:
Page 149 and 150:
s Figure 3-24: Baseline design back
Page 151 and 152:
s Figure 3-26: Baseline design priv
Page 153 and 154:
s Module part 3............= 0 m 3
Page 155 and 156:
s 3.3.2.1 Requirements and design d
Page 157 and 158:
Page 159 and 160:
Page 161 and 162:
Page 163 and 164:
Page 165 and 166:
Page 167 and 168:
s 3.3.3.1 Requirements and design d
Page 169 and 170:
Page 171 and 172:
Page 173 and 174:
Page 175 and 176:
Page 177 and 178:
s flux [W/m2] 250 200 150 100 50 0
Page 179 and 180:
s Figure 3-38: Power required to ma
Page 181 and 182:
Page 183 and 184:
Page 185 and 186:
s 3.3.4.3 Assumptions and trade-off
Page 187 and 188:
s 3.3.4.3.3 Power conditioning and
Page 189 and 190:
s 3.3.5 AOCS HMM Assessment Study R
Page 191 and 192:
Page 193 and 194:
s Configuration Length (m) Total ma
Page 195 and 196:
s 3.3.5.5 ACS for TMI 1 st HMM Asse
Page 197 and 198:
Page 199 and 200:
Page 201 and 202:
Page 203 and 204:
Page 205 and 206:
s 3.3.6.2 Baseline design HMM Asses
Page 207 and 208:
Page 209 and 210:
s 5 Reduce 2dB pointing precision t
Page 211 and 212:
s 70-m antenna 70-m antenna 3.3.7.5
Page 213 and 214:
s Angular separation SEM > 10º SEM
Page 215 and 216:
s Figure 3-63: Communications MEV/M
Page 217 and 218:
Page 219 and 220:
Page 221 and 222:
Page 223 and 224:
Page 225 and 226:
s Element 1: Transfer Habitation Mo
Page 227 and 228:
Page 229 and 230:
s Radiation Shielding Shielding Req
Page 231 and 232:
Page 233 and 234:
s The propulsion system and its cha
Page 235 and 236:
Page 237 and 238:
s Item Nr. Mass [kg] Margin [%] Mas
Page 239 and 240:
Page 241 and 242:
Page 243 and 244:
Page 245 and 246:
Page 247 and 248:
s 3.4.4 Mechanisms HMM Assessment S
Page 249 and 250:
s 4 MARS EXCURSION VEHICLE 4.1 Syst
Page 251 and 252:
Page 253 and 254:
s Figure 4-2: Option 2: Vertical co
Page 255 and 256:
Page 257 and 258:
s 4.3 Surface habitation module Fig
Page 259 and 260:
s Figure 4-11: Section through the
Page 261 and 262:
Page 263 and 264:
Page 265 and 266:
Page 267 and 268:
s 4.3.1.5.3 Top level Figure 4-20:
Page 269 and 270:
Page 271 and 272:
s Schedule in hours for the most ac
Page 273 and 274:
s 4.3.3.6 Waste production HMM Asse
Page 275 and 276:
s Figure 4-26: Total pressure vs. O
Page 277 and 278:
s ECLS system mass: Figure 4-27: Ma
Page 279 and 280:
Page 281 and 282:
s Figure 4-28: Mars albedo (L), ars
Page 283 and 284:
Page 285 and 286:
s sun flux (W/m2) 450 400 350 300 2
Page 287 and 288:
Page 289 and 290:
s Insulation structure (external) F
Page 291 and 292:
s cryocooler heat lift [W] cryocool
Page 293 and 294:
Page 295 and 296:
Page 297 and 298:
s • a duty cycle value (duration
Page 299 and 300:
s Figure 4-48: MAV Power Inputs HMM
Page 301 and 302:
Page 303 and 304:
s 4.3.5.4.2 Power storage HMM Asses
Page 305 and 306:
s Figure 4-52: Regenerative Fuel Ce
Page 307 and 308:
s Figure 4-54: Solar irradiance on
Page 309 and 310:
s 450.00 400.00 350.00 300.00 250.0
Page 311 and 312: s 4.3.6.1 Budgets HMM Assessment St
Page 313 and 314: s HMM Assessment Study Report: CDF-
Page 323 and 324: s Surface Surface Container MAV Con
Page 327 and 328: s 4.3.9.3 Baseline design 4.3.9.3.1
Page 329 and 330: s Bio-Lock Masses: Core Samples No.
Page 335 and 336: s Figure 4-72: Entry Velocity (L) a
Page 343 and 344: s 2 3.9 233 923.1 347 923 12.3 352
Page 345 and 346: s Figure 4-85: Communications MEV/M
Page 349 and 350: s 4.4.5.3.2 GNC equipment HMM Asses
Page 351 and 352: s 4.4.5.4 Control laws generation H
Page 355 and 356: s Finally, the Figure 4-97 shown th
Page 361: s velocity (m/sec) altitude (km) 50
Page 365 and 366: s Term Value Unit Radius of equator
Page 367 and 368: s 4.5.2.1 Requirements and design d
Page 373 and 374: s Inclination (deg) 47.5 47 46.5 46
Page 379 and 380: s 4.5.3 Structures HMM Assessment S
Page 383 and 384: s 4.5.5 Thermal HMM Assessment Stud
Page 385 and 386: s 4.5.5.3 Baseline thermal design H
Page 389 and 390: s Crew Ingress/Egress Hatch: HMM As
Page 391 and 392: s Element 3: Mars Ascent Vehicle HM
Page 393 and 394: s 4.5.7.5 Budgets Characteristic Va
Page 395 and 396: s PER DAY PER MISSION DRINKING WATE
Page 401 and 402: s 5 OVERALL CONCLUSIONS HMM Assessm
Page 403 and 404: s 6 APPENDIX A - MARTIAN SURFACE NU
Page 407 and 408: s Figure 6-1: Example of buried rea
Page 411 and 412: s 7 APPENDIX B - REFERENCES [RD1] C
Page 413 and 414:
s [RD26] IES2, Phase A0: Final Repo
Page 415 and 416:
Page 417 and 418:
s [RD85] Mars Transportation Enviro
Page 419 and 420:
s 8 APPENDIX C - ACRONYMS AAA Avion
Page 421 and 422:
s MLI Multi-Layer Insulation MMH Mo
show all

ESA Document - Emits - ESA

Create successful ePaper yourself

Delete template?

Save as template?