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s HMM Assessment Study Report: CDF-20(A) February 2004 page 124 of 422
s 3 TRANSFER VEHICLE 3.1 Systems…… HMM Assessment Study Report: CDF-20(A) February 2004 page 125 of 422 The Transfer Vehicle is the vehicle that hosts the crew for most of the mission. It acts as transfer vehicle both in the outward and the inward cruise and must provide an adequate habitat for the astronauts as well as the propulsion means required. The transfer vehicle is composed of the Transfer Habitation Module (THM), where the astronauts will live, and the Propulsion Module (PM), that will provide the propulsion system for the main propulsive manoeuvres. 3.1.1 System requirements At the beginning of the study the following requirements were established: Study Objectives Study a minimal achievable first mission with capability of extending to more advanced subsequent missions Architecture design for all elements and phases of the mission System and S/S conceptual design for key elements and phases Assembly, operations and logistics assessment Safety and Technical risk assessment System Requirements Land a crew of humans on Mars by 2030 and return them safely Deliver 6 crew members Mars 6 Land 3 astronauts on Mars 3 Bring back to Earth at least 100 kg of Martian samples Astronauts shall perform exploration on Mars surface Maximise the reusability of the mission elements / design 100 100 kg Crew non survival shall be lower than 1 in 200 Mission constraints 0.01 0.01 Operational date 2040 2025 2030 Launcher Energia Reference First Mission Requirements Departure date 2033 Trip time E-M 207 days Time around Mars 553 days Low altitude circular orbit around Mars 500 km Time on Mars surface 30 days Trip time M-E 206 days Minimum ∆V for TMI 3639 3639 m/s Minimum ∆V for MOI 2490 2490 m/s Minimum ∆V for TMI Direct entry at Earth arrival 2254 2254 m/s Max Min Ideal Units
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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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Page 75 and 76: s 2.7.10 Mission performance Table
Page 77 and 78: s Days on Martian surface 450 400 3
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Page 85 and 86: s % of loss from baseline 20 18 16
Page 87 and 88: s 2.7.15 Sensitivity analysis HMM A
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Page 93 and 94: s Parameters used: • No Shuttle
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Page 113 and 114: s 2.10.2.2.2 LEO assembly HMM Asses
Page 117 and 118: s Basic RF link Four 70-m Ka-band s
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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
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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
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Page 153 and 154: s Module part 3............= 0 m 3
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s flux [W/m2] 250 200 150 100 50 0
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s Figure 3-38: Power required to ma
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s 3.3.4.3 Assumptions and trade-off
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s 3.3.4.3.3 Power conditioning and
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s 3.3.5 AOCS HMM Assessment Study R
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s Configuration Length (m) Total ma
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s 3.3.5.5 ACS for TMI 1 st HMM Asse
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s 3.3.6.2 Baseline design HMM Asses
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s 5 Reduce 2dB pointing precision t
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s 70-m antenna 70-m antenna 3.3.7.5
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s Angular separation SEM > 10º SEM
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s Figure 3-63: Communications MEV/M
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s Element 1: Transfer Habitation Mo
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s Radiation Shielding Shielding Req
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s The propulsion system and its cha
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s Item Nr. Mass [kg] Margin [%] Mas
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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 4.3.1.5.3 Top level Figure 4-20:
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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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