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s Supporting structure Value characteristic Overall mass (tonnes) 3.6 Diameter (m) 5 Length (m) 9 HMM Assessment Study Report: CDF-20(A) February 2004 page 66 of 422 Figure 2-33: MOI supporting structure characteristics Once used, the stacks of the first stage are jettisoned. Once the stacks of the second stage are used, they and the supporting structure are jettisoned. The used stacks of the first stage will be provided with a small propulsion system that will allow the required manoeuvres to avoid the collision with Mars (raise the pericentre). 2.7.7.1.2.3 TEI It provides the required ∆V for the trans Earth injection manoeuvre. It is composed of one single stage, composed of a 80-tonne stack and a supporting structure. Storable propulsion technology has been selected for this module. The design of the stack is identical to the one of the first stage of the MOI. Stack characteristics Value Overall mass (tonnes) 80 Propellant mass (tonnes) 76.3 Engine RD-0212 Thrust (kN) 612 Diameter (m) 5 Length (m) about 9.5 Figure 2-34: TEI stack characteristics The stack will be placed inside the supporting structure of the MOI, attached to a conical adapter to the THM.
s 2.7.7.1.3 Mars excursion module Supporting characteristics structure Value Overall mass (tonnes) 5.2 Initial diameter (m) about 2 Final diameter (m) about 2 Length (m) 5 Figure 2-35: TMI supporting structure characteristics HMM Assessment Study Report: CDF-20(A) February 2004 page 67 of 422 This mission element is the one that allows a crew of three astronauts to land on the surface of Mars and take off after 30 days to rendezvous and dock with the TV. It is composed of three main elements: • Descent Module, mainly composed of the deorbit propulsion system, inflatable heat shield, back cover and parachutes for the entry and descent. • Surface Habitation Module, a cylindrical module that will house the astronauts during their stage on the surface providing life-support systems and EVA equipment to perform the exploration. The landing systems (retrorockets and landing legs) are located in this module. It will also provide the interfaces with the MAV. • Mars Ascent Vehicle, the ascent vehicle in which the astronauts will return to orbit, mainly composed of a capsule (in which the astronauts will be placed also during the descent) and a propulsion module split into two stages. It will provide life support for 5 days. The MEV will be attached to one of the extremities of the TV, in a docking port on the longitudinal axis of the TV.
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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 15 and 16: s L I S T O F T A B L E S HMM Asses
Page 17 and 18: s HMM Assessment Study Report: CDF-
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
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Page 75 and 76: s 2.7.10 Mission performance Table
Page 77 and 78: s Days on Martian surface 450 400 3
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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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