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s 3.3.9.4 Budgets The structural mass composition is show in Table 3-56: Item Nr. Mass [kg] Margin [%] Mass with Margin [kg] THM Skin 1 2921.99 5 3068.9 Nodes_Skin 2 834.58 5 876.31 EVA 1 254.84 5 267.58 Total Stiffening 1 2005.71 5 2105.99 THM_Debris Shielding 1 964.94 5 1013.19 Nodes_Debris Shielding 2 302.73 5 317.86 Fixtures_large 1 1000 5 1050 Tools_gloveboxes Racks 1 2146 20 2575.20 TOTAL 12468.39 3.4 Propulsion module 3.4.1 Propulsion 3.4.1.1 Trans Mars Injection (TMI) Table 3-56: THM Structural Mass budget HMM Assessment Study Report: CDF-20(A) February 2004 page 230 of 422 3.4.1.1.1 Requirements and design drivers This propulsive module performs the transfer from a Low Earth Orbit to Martian orbit by three impulsive burns The TMI is composed of several stacks that are injected in LEO by a heavy launcher (Energia) and have to be assembled in orbit. Each stack contains an autonomous propulsion system with engines, and relevant tanks fully loaded. The TMI is composed of three stages each composed of four stacks. The four stacks in a stage will be fired together to provide the thrust to mass ratio required to avoid gravitational losses. The inertia forces generated on the solar arrays will be high, so the arrays will have to be folded. 3.4.1.1.2 Assumptions and trade-offs The TMI module uses LH2-LOX propellant at cryogenic storage conditions. The low Isp of the storable propellants resulted in prohibitive mass penalty for the TMI. A model to estimate the dry mass of each stack has been made including thermal protection system of the tanks, resulting in an inert dry mass of 11.5 % (9.2 tonne) for each stack. 3.4.1.1.3 Baseline design
s HMM Assessment Study Report: CDF-20(A) February 2004 page 231 of 422 One VULCAIN 2 gas generator (open cycle) engine has been selected as propulsion system for each cryogenic stack. The thruster is being developed for the first stage of the Ariane-5 launcher. Isp has been scaled with respect to the nominal for deep vacuum operations. The propulsion system and its characteristics are shown in Table 3-57: Characteristic Value Number of thruster 1 for each stack Thrust 1300 kN (gas generator) Isp 450 s Exit diameter 2100 mm lLength 3500 mm Thruster mass 2035 kg Propellant LOX/LH2 O/F ratio 6.2 Number of tanks 1+1 Bulkhead for each stack Tanks material Al-Li Alloys Max MEOP LOX 6 bar Max MEOP LH2 2 bar Mass of LH2 tank 1238 kg Mass of LOX tank 902 kg Table 3-57: TMI Summary Figure 3-72: VULCAIN 2
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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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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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Page 185 and 186: s 3.3.4.3 Assumptions and trade-off
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 209 and 210: s 5 Reduce 2dB pointing precision t
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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Page 229: s Radiation Shielding Shielding Req
Page 233 and 234: s The propulsion system and its cha
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Page 247 and 248: s 3.4.4 Mechanisms HMM Assessment S
Page 249 and 250: s 4 MARS EXCURSION VEHICLE 4.1 Syst
Page 253 and 254: s Figure 4-2: Option 2: Vertical co
Page 257 and 258: s 4.3 Surface habitation module Fig
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Page 267 and 268: s 4.3.1.5.3 Top level Figure 4-20:
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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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