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s 3.2.3.1.2 Back and front nodes Figure 3-7: Main cylinder (dimensions in mm) HMM Assessment Study Report: CDF-20(A) February 2004 page 134 of 422 These nodes are the interfaces between the main parts: PM, THM, ERC, EVA Airlock and MEV. Two solar arrays are connected to the left- and right-hand side of both nodes. The power batteries are accommodated inside the nodes, but if they leak they will not bring danger to the astronauts. The main cylinder is positioned between both nodes. The PM, the ERC and the airlock are attached to the back node (see Figure 3-8). The MEV and the cupola are attached to the front node (see Figure 3-9). The cupola allows the crew to have a 2.5D view outside and monitor Extra Vehicular Activities. Also all the communication antennas and equipment is attached to the front node. There is a spare docking point at the front node. The diameter of each node is 3.5 m and the length is 5.2 m. PM Adapter EarthReturnCapsule Airlock Figure 3-8: Back Node Back Node
s Front Node 3.2.3.1.3 EVA systems Figure 3-9: Front Node HMM Assessment Study Report: CDF-20(A) February 2004 page 135 of 422 The astronauts’ ability to move around and conduct useful tasks outside the pressurised volume is a required capability. A conceptual airlock configuration was designed taking the ISS airlock as example. The part directly connected to the back node is a facility for EVA suit maintenance and consumables servicing. 3.2.3.1.4 Earth return capsule The design of the ERC is not included in the current study. The ERC shown in Figure 3-9 is just an artistic impression of an ERC design. 3.2.3.2 Propulsion module Cupola Mars Excursion Vehicle Figure 3-10 shows the complete Propulsion Module. A modular system has been proposed for the PM. Separate propulsion systems, which are jettisoned after its usage, are designed for the three main propulsive manoeuvres: • Trans Mars Injection (TMI) • Mars Orbit Insertion (MOI) • Trans Earth Injection (TEI) A central cylinder of 5 m diameter acts as the backbone (Figure 3-11) of the PM. All the stacks are attached to this support structure (a stack is an autonomous propulsion system with an engine and propellant tanks). The large diameter of the backbone is driven by the need to have sufficient space between four stacks in one plane.
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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 87 and 88: s 2.7.15 Sensitivity analysis HMM A
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Page 91 and 92: s HMM Assessment Study Report: CDF-
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 131 and 132: s Figure 3-2: Parallel configuratio
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Page 149 and 150: s Figure 3-24: Baseline design back
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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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