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s HMM Assessment Study Report: CDF-20(A) February 2004 page 44 of 422 proton events. It will also be necessary to provide a minimum of 9 g/cm 2 of shielding throughout the habitation module to ensure the yearly limit and career dose limits are not exceeded by the galactic cosmic ray radiation. The BFO career radiation limits vary with the age and sex of the astronaut. The lowest career radiation limit of 1 Sv is set for young females and will be exceeded during the mission. However, by selecting crew by age and sex, it should be possible to ensure a minimum crew dose limit that is above the 1.4 Sv dose to be accrued on the mission. Finally, the solar proton particle fluence calculation should be reviewed and the uncertainties from the high-energy solar proton fluence resolved. Additionally, the radiation transport dose calculation should be revisited with greater accuracy models. 2.7 Mission architecture 2.7.1 Mission case Many design options are possible for a human mission to Mars, but only a limited set has been considered according to the criteria defined for the case selection: • Capability to perform quantitative assessments in a reliable way (e.g. selected technologies known and relatively mature even if not the most mass effective) • Mass effectiveness sought in trajectory and architecture definition (e.g. type of trajectory, surface stay duration, number of vehicles, etc.) • Possibility to extend the results to more generic/advanced missions 2.7.2 Mission case basic architecture The main goal of the human mission to Mars is to land a crew of astronauts on the Martian surface and bring them back to Earth. The minimum elements required (are shown in Figure 2-17): • Propulsion system to perform the cruise to Mars and back, Propulsion Module (PM) • Habitation module to support the astronauts during the trip, Transfer Habitation Module (THM) • Descent/Ascent module to land onto Mars and get back to Mars orbit, Mars Excursion Module (MEV) • Entry capsule to allow astronauts to reenter the Earth’s atmosphere on return, Earth Reentry Capsule (ERC)
s Mars Excursion Vehicle Transfer Habitation Module Earth Re-entry Capsule Figure 2-17: Mission elements for a human mission to Mars HMM Assessment Study Report: CDF-20(A) February 2004 page 45 of 422 Propulsion Module If no extra infrastructure is available in LEO on return, an ERC is required to return the crew to Earth surface, either performing a direct entry from interplanetary trajectory or by parking the TV in LEO. In the case of an existing infrastructure, the TV could rendezvous and dock to it to allow the transfer of the astronauts. This last option has not been considered in the study. 2.7.3 Key parameters To perform the selection of the mission case, the following parameters have been analysed: • Overall mass into LEO • Overall mission duration • Assembly time • Time availability for Martian surface operations 2.7.4 Mission case architecture options A preliminary set of trade-offs and options was established at the beginning of the study. The trade space has been already reduced by taking into account all the technological and programmatic constraints, as well as the criteria defined for the mission case study. The main trade-offs and options studied are shown in Table 2-6.
Page 1 and 2: s HMM Assessment Study Report: CDF-
Page 3 and 4: s STUDY TEAM HMM Assessment Study R
Page 5 and 6: s T A B L E O F C O N T E N T S HMM
Page 9 and 10: s L I S T O F F I G U R E S HMM Ass
Page 15 and 16: s L I S T O F T A B L E S HMM Asses
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
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Page 47 and 48: s 2.7.5.1 Mission elements dry mass
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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
Page 67 and 68: s 2.7.7.1.3 Mars excursion module S
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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
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Page 93 and 94: s Parameters used: • No Shuttle
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s 2.8.3.3 Launch 3- Front node Figu
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s HMM Assessment Study Report: CDF-
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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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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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