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s 4.2.5 Mars ascent vehicle HMM Assessment Study Report: CDF-20(A) February 2004 page 256 of 422 In Figure 4-7 the complete MAV is shown. It is composed of a capsule (see Figure 4-8) and two propulsion stages. In Figure 4-9 the MEV is shown after the first propulsion stage is jettisoned. In Table 4-4 the pressurised volume of the capsule is presented. Figure 4-7: Mars ascent vehicle Figure 4-8: Capsule of the MAV with the conical interface to surface habitation module Length Internal Diameter Volume [mm] [mm] [m 3 ] Cylinder 1800 2700 10.3 Lower Closure 1000 3.5 Upper Closure 150 0.8 Total Pressurised Volume 14.6 Table 4-4: Dimensions and volume capsule
s 4.3 Surface habitation module Figure 4-9: Mars excursion vehicle; Capsule with its second stage HMM Assessment Study Report: CDF-20(A) February 2004 page 257 of 422 4.3.1 Internal configuration The development of the baseline design for the SHM included an investigation on the usage of inflatable technologies. Before the final baseline design, three main steps (including eight different designs and configurations) were developed followed by two detailed designs of different interior layouts for the three main zones: the private, the personal and the social zone. (See THM internal configuration for definitions 3.3.1) 4.3.1.1 Preparing the baseline design – investigations of SHM’s interior configuration The final diameter for the SHM is 3.60 m, derived from the limitations of the launch vehicle /diameter of 6.00 m) and the safety distance required between the plume of the MAV during take-off and the ground or the habitat. Where and how to place the life support system optimally still remains an open issue. Three options were considered: at the top level of the habitat, in the middle, and at the bottom. The option with the LSS at the top level was discarded, because the mass of the LSS would have been too high up, considering the fact that the MAV with the propulsion tanks already has a substantially high weight within the overall MEV configuration. Prior to a final conclusion, the following two options were developed: 4.3.1.2 Option 1 – LSS in the middle of the habitat SHM - cylinder: Height: 7.00 m Diameter: 3.60 m LSS: 10 m 3 in the middle of the habitat
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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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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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Page 205 and 206: s 3.3.6.2 Baseline design HMM Asses
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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
Page 225 and 226: s Element 1: Transfer Habitation Mo
Page 229 and 230: s Radiation Shielding Shielding Req
Page 233 and 234: s The propulsion system and its cha
Page 237 and 238: s Item Nr. Mass [kg] Margin [%] Mas
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Page 249 and 250: s 4 MARS EXCURSION VEHICLE 4.1 Syst
Page 253 and 254: s Figure 4-2: Option 2: Vertical co
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Page 277 and 278: s ECLS system mass: Figure 4-27: Ma
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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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