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s 3.2 Configuration 3.2.1 Requirements and design drivers HMM Assessment Study Report: CDF-20(A) February 2004 page 130 of 422 • The Transfer Vehicle (TV) is composed of the Transfer Habitation Module (THM) and the Propulsion Module (PM). The PM consists of three stages: Transfer Mars Injection stage (TMI), Mars Orbit Insertion stage (MOI) and Transfer Earth Injection stage (TEI). • All main components of the TV shall fit inside the fairing of the Energia launcher, a cylinder with a diameter of 6 m and a length of 35 m. • Interfaces between assembly elements shall be kept to a minimum to simplify the assembly. • THM shall be as independent as possible from the PM. • THM shall provide an interface with the Earth Return Capsule (ERC) and Mars Excursion Vehicle (MEV) allowing crew to move from one to the other. • Required pressurised volume of the THM should be 450 m 3 . • THM shall provide an airlock for Extra Vehicular Activities. • Each propulsion module shall be safely discardable after its usage. 3.2.2 Assumptions and trade-offs For the configuration of the THM, three options were considered: • One-module configuration (Figure 3-1). • Parallel configuration (Figure 3-2). • Cross configuration (Figure 3-3). Figure 3-1: One-module configuration
s Figure 3-2: Parallel configuration Figure 3-3: Cross configuration The one-module configuration (option 1) was chosen in the trade-off shown in Table 3-5: HMM Assessment Study Report: CDF-20(A) February 2004 page 131 of 422 Option 1 Option 2 Option 3 Habitable volume + + + Redundancy, isolation of depressurised part + + + Passable I/F with MEV, ERC and Airlock + + + Connection to Propulsion Module + + + Structural simplicity + - - Minimum number of interfaces (mass, leakage risk) + - - Mass radiation and debris shielding + - - Minimum number of launches + - - Privacy crew - + + Internal layout simplicity - + + Table 3-5: One model configuration (option 1)
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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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Page 93 and 94: s Parameters used: • No Shuttle
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Page 125 and 126: s 3 TRANSFER VEHICLE 3.1 Systems…
Page 127 and 128: s Operational Requirements It shall
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Page 153 and 154: s Module part 3............= 0 m 3
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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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