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s P6 P5 3.3.5.1 Habitation module AOCS P4 P3 Figure 3-46: Vehicle configuration EV Airlock A 1 Configuration Length (m) Total length (m) Station MEV 10 10 P1 THM 19 29 P2 ERC 0 29 P2 TEI 15 44 P3 MOI 0 44 P3 TMI 3 rd 15 59 P4 TMI 2 nd 15 74 P5 TMI 1 st 15 89 P6 Table 3-33: Vehicle Dimensions P2 Habitation Module A core ACS shall be installed in the Habitation Module extremities, at locations P1 and P2. EV Airlock A 1 Habitation Module Figure 3-47: Habitation module ACS Configuration Length Total mass Total length comp CoG Inertia total (m) (tonnes) (m) (m) kg*m^2/1000 MEV 10 46 10 5.0 THM 19 65 29 13.5 ERC 0 15 29 15.3 22 874 Table 3-34: Habitation module dimensions P1 HMM Assessment Study Report: CDF-20(A) February 2004 page 190 of 422
s HMM Assessment Study Report: CDF-20(A) February 2004 page 191 of 422 The functions the ACS has to accomplish are: • Attitude control while cruising to Earth • Earth retargeting • Rate dumping after TEI motor separation: 0.5 degrees/s dumped in 30 sec (maximum attitude error within 15 degrees) The most stringent requirement is the last one. To fulfil that a control authority of 6700 Nm is needed. If the thrusters are dislocated in the two stations P1 and P2, the following torque arms shall be realized (with respect to the centre of mass): b1 = 13.7 m, b2 = 5.3 m Thrust needed = 6700/13.7+5.3 = 360 N This can be realized by either ATV ACS thrusters of 220 N each or Ariane-5 SCA thrusters, qualified for 350 N but easily adaptable also to 550 N. So clusters of two thrusters could be used (or three thrusters, one redundant). This study will assume a cluster of two ATV thrusters, giving a control authority of 440 N. To save propellant, while cruising, the attitude control shall be performed by using Control Moment Gyros (CMG) instead of thrusters. A set of CMG of the class of those used on the ISS is preliminarily baselined. The set of 4 CMG is about 230 kg. However, the suitability of these devices have to be verified against the disturbances induced by the crew, which have not been estimated yet. 3.3.5.2 AOCS for MEV+THM+ERC+TEI+MOI Due to the integrated configuration for the TEI and MOI modules, a single ACS shall be designed, sized to comply with the worst case of the two mission phases. In this configuration three control points shall be actives: P1, P2 and P3, as shown in Figure 3-48. P3 EV Airlock A 1 P2 Habitation Module P1 Figure 3-48: TEI and MOI configuration
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s HMM Assessment Study Report: CDF-
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s STUDY TEAM HMM Assessment Study R
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s T A B L E O F C O N T E N T S HMM
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s L I S T O F F I G U R E S HMM Ass
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s L I S T O F T A B L E S HMM Asses
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s 1 INTRODUCTION 1.1 Background HMM
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s 2 GENERAL ARCHITECTURE 2.1 Study
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s 2.2.4.2 Accelerations HMM Assessm
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s 2.2.4.4 Temperature and relative
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s Figure 2-10: Trajectory Overview
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s 2.4.3.5 TEI and planetary protect
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s Mars Excursion Vehicle Transfer H
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s 2.7.5.1 Mission elements dry mass
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s 2.7.5.8 MEV release The MEV is re
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s Total mission time (days) 1200 10
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s stack 9 Propellant mass of the ne
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s The core supporting structure has
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s 2.7.7.1.3 Mars excursion module S
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s 2.7.7.1.4 Earth return capsule HM
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s Mission Phase Description Event s
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s Mission Phase Description Event s
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s 2.7.10 Mission performance Table
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s Days on Martian surface 450 400 3
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s Maximum manoeuvre duration 6 mont
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s % of loss from baseline 20 18 16
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s 2.7.15 Sensitivity analysis HMM A
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s 2.7.15.4 Influence of the mass of
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s Parameters used: • No Shuttle
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s 2.8.3.3 Launch 3- Front node Figu
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s 2.10.1.4 Communications HMM Asses
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s 2.10.2.2.2 LEO assembly HMM Asses
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s Basic RF link Four 70-m Ka-band s
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s 3 TRANSFER VEHICLE 3.1 Systems…
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s Operational Requirements It shall
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s Trans Mars Injection Module Mars
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s Figure 3-2: Parallel configuratio
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s Figure 3-6: Global dimensions com
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s Front Node 3.2.3.1.3 EVA systems
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s Trans Mars Injection (three stage
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Page 149 and 150: s Figure 3-24: Baseline design back
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Page 153 and 154: s Module part 3............= 0 m 3
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Page 187 and 188: s 3.3.4.3.3 Power conditioning and
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Page 193 and 194: s Configuration Length (m) Total ma
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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
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s 3.4.4 Mechanisms HMM Assessment S
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s 4 MARS EXCURSION VEHICLE 4.1 Syst
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s Figure 4-2: Option 2: Vertical co
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s 4.3 Surface habitation module Fig
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s Figure 4-11: Section through the
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s 4.3.1.5 Baseline design HMM Asses
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s 4.3.1.5.3 Top level Figure 4-20:
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s 4.3.2.3 Baseline design HMM Asses
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s Schedule in hours for the most ac
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s 4.3.3.6 Waste production HMM Asse
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s Figure 4-26: Total pressure vs. O
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s ECLS system mass: Figure 4-27: Ma
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s Figure 4-28: Mars albedo (L), ars
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s sun flux (W/m2) 450 400 350 300 2
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s Insulation structure (external) F
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s cryocooler heat lift [W] cryocool
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s • a duty cycle value (duration
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s Figure 4-48: MAV Power Inputs HMM
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s 4.3.5.4.2 Power storage HMM Asses
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s Figure 4-52: Regenerative Fuel Ce
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s Figure 4-54: Solar irradiance on
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s 450.00 400.00 350.00 300.00 250.0
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s 4.3.6.1 Budgets HMM Assessment St
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s Surface Surface Container MAV Con
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s 4.3.9.3 Baseline design 4.3.9.3.1
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s Bio-Lock Masses: Core Samples No.
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s Figure 4-72: Entry Velocity (L) a
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s 2 3.9 233 923.1 347 923 12.3 352
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s Figure 4-85: Communications MEV/M
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s 4.4.5.3.2 GNC equipment HMM Asses
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s 4.4.5.4 Control laws generation H
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s Finally, the Figure 4-97 shown th
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s velocity (m/sec) altitude (km) 50
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s 4.5 Mars Ascent Vehicle 4.5.1 Tra
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s Term Value Unit Radius of equator
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s 4.5.2.1 Requirements and design d
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s Inclination (deg) 47.5 47 46.5 46
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s 4.5.3 Structures HMM Assessment S
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s 4.5.5 Thermal HMM Assessment Stud
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s 4.5.5.3 Baseline thermal design H
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s Crew Ingress/Egress Hatch: HMM As
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s Element 3: Mars Ascent Vehicle HM
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s 4.5.7.5 Budgets Characteristic Va
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s PER DAY PER MISSION DRINKING WATE
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s 5 OVERALL CONCLUSIONS HMM Assessm
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s 6 APPENDIX A - MARTIAN SURFACE NU
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s Figure 6-1: Example of buried rea
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s 7 APPENDIX B - REFERENCES [RD1] C
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s [RD26] IES2, Phase A0: Final Repo
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s [RD85] Mars Transportation Enviro
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s 8 APPENDIX C - ACRONYMS AAA Avion
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s MLI Multi-Layer Insulation MMH Mo
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