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s Figure 2-36: Mars Excursion Vehicle The main characteristics and dimensions of the MEV are in Table 2-21. Characteristics Value Overall mass (tonnes) 46.5 Consumables mass (tonnes) 0.3 Propellant mass (tonnes) 20.5 Total pressurised volume (m 3 ) 80 Overall length (m) 12.1 Overall diameter (m) 6 Table 2-21: MEV properties HMM Assessment Study Report: CDF-20(A) February 2004 page 68 of 422
s 2.7.7.1.4 Earth return capsule HMM Assessment Study Report: CDF-20(A) February 2004 page 69 of 422 This mission element will house the whole crew for the entry descent and landing on Earth return. It has not been designed within this study. A reference mass of 11.2 tonnes has been taken into account for the analysis. The figure came from a scaling up of an Apollo capsule. 2.7.7.1.5 Additional mission elements For the mission, more infrastructure is also required: • Mars Stationary Satellite for data relay with the surface. • Workbenches for the assembly of the composite in LEO. 2.7.8 Launchers To be able to run the analyses, it has been decided to use existing launchers for the mission case, as information can be gathered about them, instead of defining a new “theoretical” launcher being able to launch hundreds of tonnes to LEO. 2.7.8.1 Energia The Russian launcher Energia has been selected as the main launcher for the mission. Although it is no longer in production, it was assumed that the effort to make it operational is smaller than the one to develop a launcher of such performances or even higher from scratch. The Energia launcher was designed in the 1970s and made only two flights at the end of the 1980s, one with an external cargo (1987) and a second one with the Russian shuttle, Buran (1988). It is a two-stage launcher, consisting of central core and booster, with a lateral configuration for the payload. No user manual for the launcher is available, but performances have been taken from international launchers guides. The performances and characteristics assumed are shown in Table 2-22: Characteristics Value Overall mass (tonnes) 2400 Payload mass (tonnes) 80 Success rate (%) 100 Status Out of production Fairing length (m) 35 Fairing diameter (m) 6 Table 2-22: Energia launcher The payload is inserted into a low orbit of 200 x 200 km from where it is pushed up to the final orbit by an RCS stage. This stage is assumed to have attitude control capabilities and will be used to perform the rendezvous and docking of the payload with the composite to proceed to the assembly. 2.7.8.2 Other launchers Smaller launchers may be also used for the assembly. The launchers used and their main characteristics are shown in Table 2-23:
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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
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
Page 65 and 66: s The core supporting structure has
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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
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
Page 89 and 90: s 2.7.15.4 Influence of the mass of
Page 93 and 94: s Parameters used: • No Shuttle
Page 95 and 96: s 2.8.3.3 Launch 3- Front node Figu
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Page 113 and 114: s 2.10.2.2.2 LEO assembly HMM Asses
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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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