ESA Document - Emits - ESA
ESA Document - Emits - ESA ESA Document - Emits - ESA
s 4.5.3.4 Budget Figure 4-114: MAV Propulsion Module Item Nr. Mass [kg] Margin [%] Mass with Margin [kg] MAV Skin 1 219.53 20 263.43 MAV Stiffeners 1 109.76 20 131.72 1 st stage plate 1 24.12 20 28.95 1 st stage lateral support 1 70.68 20 84.81 MAV Rings 4 61.29 20 73.55 2 nd stage plate 1 24.12 20 28.95 2 nd stage lateral support 1 25.44 20 30.53 TOTAL 862.59 4.5.4 Power 4.5.4.1 Inputs and assumptions Table 4-56: SHM Structures mass budget HMM Assessment Study Report: CDF-20(A) February 2004 page 380 of 422 4.5.4.1.1 Architecture The mission of the MAV is to: • Launch from the Martian surface to a parking orbit around Mars (max duration 90 minutes) • Stay a few days on this orbit (Orbit: 118 min, max eclipse: 41 min) • Perform the rendezvous with the TV (max duration 30 min) Reviewing the power that needs to be supplied during all these modes, a non-regenerative power system would be too heavy, either with fuel cells or primary batteries. Therefore, solar cells are required in the design to decrease significantly the power storage module.
s HMM Assessment Study Report: CDF-20(A) February 2004 page 381 of 422 As regards the parking orbit, the attitude of the satellite is not constrained at all (use of a patch antenna, no payload pointing requirement…). Consequently, solar panels can be body-mounted and always assumed sun-pointed during this phase. This solution is selected because it offers: • the lightest system • the most reliable system (no deployment or SADM mechanisms) On top of the spacecraft, a flat area of 17.5 m² is available and will be used for mounting the cells (Figure 4-115). Solar Cells Location 4.5.4.1.2 Power storage Figure 4-115: MAV solar cells location The use of a secondary battery is the best-qualified and efficient way of storing the required energy. Currently, Li-Ion cells offer the best performances (around 94% of energy round efficiency, a specific energy of 100Wh/kg). As for the Habitation Module, a specific energy of 150Wh/kg is expected to be reached in 2015 and will be considered in this study. When these batteries will be in use (from the launch from the Martian surface until the rendezvous with the TV), the batteries will not have an important cycling effect degradation but are already between 2 to 5 years old (depending on the LEO assembly time). Hence, a maximum depth of discharge of 60% that should cover also the failure cases is selected. 4.5.4.1.3 Power generation In this architecture, AsGa MJ cells are body-mounted on the top ring of the MEV because they offer the best conversion efficiency.
- Page 329 and 330: s Bio-Lock Masses: Core Samples No.
- Page 331 and 332: s HMM Assessment Study Report: CDF-
- Page 333 and 334: s HMM Assessment Study Report: CDF-
- Page 335 and 336: s Figure 4-72: Entry Velocity (L) a
- Page 337 and 338: s HMM Assessment Study Report: CDF-
- Page 339 and 340: s HMM Assessment Study Report: CDF-
- Page 341 and 342: s HMM Assessment Study Report: CDF-
- 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 347 and 348: s HMM Assessment Study Report: CDF-
- 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 353 and 354: s HMM Assessment Study Report: CDF-
- Page 355 and 356: s Finally, the Figure 4-97 shown th
- Page 357 and 358: s HMM Assessment Study Report: CDF-
- Page 359 and 360: s HMM Assessment Study Report: CDF-
- Page 361 and 362: s velocity (m/sec) altitude (km) 50
- Page 363 and 364: s 4.5 Mars Ascent Vehicle 4.5.1 Tra
- 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 369 and 370: s HMM Assessment Study Report: CDF-
- Page 371 and 372: s HMM Assessment Study Report: CDF-
- Page 373 and 374: s Inclination (deg) 47.5 47 46.5 46
- Page 375 and 376: s HMM Assessment Study Report: CDF-
- Page 377 and 378: s HMM Assessment Study Report: CDF-
- Page 379: 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 387 and 388: s HMM Assessment Study Report: CDF-
- 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 397 and 398: s HMM Assessment Study Report: CDF-
- Page 399 and 400: s HMM Assessment Study Report: CDF-
- Page 401 and 402: s 5 OVERALL CONCLUSIONS HMM Assessm
- Page 403 and 404: s 6 APPENDIX A - MARTIAN SURFACE NU
- Page 405 and 406: s HMM Assessment Study Report: CDF-
- Page 407 and 408: s Figure 6-1: Example of buried rea
- Page 409 and 410: s HMM Assessment Study Report: CDF-
- 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: s HMM Assessment Study Report: CDF-
- 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
s<br />
4.5.3.4 Budget<br />
Figure 4-114: MAV Propulsion Module<br />
Item Nr. Mass [kg] Margin [%] Mass with Margin [kg]<br />
MAV Skin 1 219.53 20 263.43<br />
MAV Stiffeners 1 109.76 20 131.72<br />
1 st stage plate 1 24.12 20 28.95<br />
1 st stage lateral support 1 70.68 20 84.81<br />
MAV Rings 4 61.29 20 73.55<br />
2 nd stage plate 1 24.12 20 28.95<br />
2 nd stage lateral support 1 25.44 20 30.53<br />
TOTAL 862.59<br />
4.5.4 Power<br />
4.5.4.1 Inputs and assumptions<br />
Table 4-56: SHM Structures mass budget<br />
HMM<br />
Assessment Study<br />
Report: CDF-20(A)<br />
February 2004<br />
page 380 of 422<br />
4.5.4.1.1 Architecture<br />
The mission of the MAV is to:<br />
• Launch from the Martian surface to a parking orbit around Mars (max duration 90<br />
minutes)<br />
• Stay a few days on this orbit (Orbit: 118 min, max eclipse: 41 min)<br />
• Perform the rendezvous with the TV (max duration 30 min)<br />
Reviewing the power that needs to be supplied during all these modes, a non-regenerative power<br />
system would be too heavy, either with fuel cells or primary batteries.<br />
Therefore, solar cells are required in the design to decrease significantly the power storage<br />
module.