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s For more detailed information, see section 3.2.1 Transfer Habitation Module. 2.7.7.1.2 Propulsion module HMM Assessment Study Report: CDF-20(A) February 2004 page 64 of 422 The propulsion module is split into three submodules, one for each main propulsive manoeuvre, as shown in Figure 2-29. 2.7.7.1.2.1 TMI Figure 2-29: Propulsion module It provides the required ∆V for the trans Mars injection manoeuvre. It is composed of three serial stages, each of them split into four identical stacks and a supporting structure. Cryogenic propulsion technology has been selected for this module. Each stack has a wet mass of 80 tonne to fit into Energia, and it is equipped with a single engine and the corresponding oxygen and hydrogen tanks. Stack characteristic Value Overall (tonnes) mass 80 Propellant 70.7 Figure 2-30: TMI stack characteristics mass (tonnes) Engine Vulcain 2 Thrust (kN) 1300 Diameter (m) 5 Length (m) 13.6
s The core supporting structure has a cylindrical shape, as shown in Figure 2-31: Supporting structure characteristics Value Overall mass (tonnes) 5.2 Diameter (m) 5 Length (m) 16.8 Figure 2-31: TMI supporting structure characteristics HMM Assessment Study Report: CDF-20(A) February 2004 page 65 of 422 The four stacks and the associated supporting structure are discarded once the burn is performed. The used stage will be provided by a small propulsion system that will allow the required manoeuvres for a controlled entry in the case of the first and second stage, or put it into a trajectory the does not impact Mars or the TV in the case of the third stage. 2.7.7.1.2.2 MOI It provides the required ∆V for the Mars orbit injection and final orbit acquisition manoeuvres. It is composed of two stages, each of them split into two identical stacks, and a supporting structure. Storable propulsion technology has been selected for this module. The first stage (orbit insertion) is composed of two stacks of 80 tonnes, while in the case of the second stage (final orbit acquisition, it is composed of two stacks of 50 tonnes each. Stack characteristics Value Overall mass (tonnes) 80 Propellant mass (tonnes) 76.3 Diameter (m) 5 Length (m) about 9.5 Overall mass (tonnes) 50 Propellant mass (tonnes) 47.7 Diameter (m) 5 Length (m) about 8 Engine RD-0212 Thrust (kN) 612 Figure 2-32: MOI stack characteristics The four stacks are attached to a supporting structure with a cylindrical shape.
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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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Page 13 and 14: s HMM Assessment Study Report: CDF-
Page 15 and 16: s L I S T O F T A B L E S HMM Asses
Page 19 and 20: s 1 INTRODUCTION 1.1 Background HMM
Page 21 and 22: s 2 GENERAL ARCHITECTURE 2.1 Study
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 33 and 34: s Figure 2-10: Trajectory Overview
Page 35 and 36: s 2.4.3.5 TEI and planetary protect
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 57 and 58: s stack 9 Propellant mass of the ne
Page 63: s HMM Assessment Study Report: CDF-
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 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
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Page 93 and 94: s Parameters used: • No Shuttle
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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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s Figure 3-16: Recommendations for
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s Factors to be considered Impacts
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s Figure 3-24: Baseline design back
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s Figure 3-26: Baseline design priv
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s Module part 3............= 0 m 3
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s 3.3.2.1 Requirements and design d
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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 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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