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s HMM Assessment Study Report: CDF-20(A) February 2004 page 88 of 422 In the case of zero level of closure all the consumables have to be brought from the beginning. The study considered only dry food. In terms of power requirements, only a small increase is observed in the system when a high level of recycling is used, although the power requirements for storage in this case are smaller. Dry food is considered somewhat inert and requires less power for storage than fresh food. Insitu food either needs to be processed or needs higher storage power (refrigerator, freezer). Therefore, the reduction is only 400W in this analysis as no extensive processing and fresh food storage were assumed. Open-loop life support systems for such a long duration mission with no resupply capabilities represents a prohibitive mass and volume for the system. The overall mass required is four times bigger. In terms of power requirements there is no great difference between the closed and the open loop systems. This mission therefore requires a high level of closure life support system.. 2.7.15.3 Influence of the mass of the ERC Mass to LEO (Tonnes) 1550 1500 1450 1400 1350 ERC influence 1300 8 10 12 14 16 18 20 ERC mass (Tonnes) Figure 2-44: Influence of the ERC mass The ERC mass has also a large influence on the initial mass for the same reason as the THM, although the mass of the ERC itself is lower and such is its effect compared with the one of the THM. The sudden increases shown in Figure 2-44 are due to the approach followed for the TMI propulsion module, which is composed of 12, 13 and 14 stacks respectively.
s 2.7.15.4 Influence of the mass of the MEV Mass to LEO (Tonnes) 1500 1400 1300 1200 1100 Influence of MEV 1000 20 25 30 35 40 45 50 55 60 MEV mass (Tonnes) HMM Assessment Study Report: CDF-20(A) February 2004 page 89 of 422 Figure 2-45: Influence of the MEV mass As shown in Figure 2-45, the influence of the MEV mass on overall mass is lower than that of the THM, as it is discarded during Martian orbit. 2.8 In orbit assembly 2.8.1 Assumptions and trade-offs Note that when considering the mission architecture: • A chemical mission results in a high mass into LEO and a configuration with several elements • The parameter to assess the feasibility of a mission architecture is the time-toassemble such elements in LEO (or the selected orbit) • A long assembly time would result in: o Aging of elements even before the mission starts (potentially, unacceptable aging). o Unacceptable boil-off losses for the case of cryogenic-propulsion. o Delay of the following mission within a chosen exploration strategy. Several orbits are candidates for the assembly operations: • LEO • Nuclear safe orbit • MEO • GEO • HEO Note that when choosing the orbit for the assembly operations: • All the elements have to be inserted into the assembly orbit and perform a rendezvous & berthing or docking with the already existing composite. • Human interaction may be required to complete any given addition to the composite. • Nuclear safe orbits will only be considered if nuclear devices are present in the composite, currently none are baselined. • Elliptical orbits are discarded due to the complexity of the RVD manoeuvre. • GEO and HEO are discarded due to the loss of performance of the launchers and the (potentially) more hostile environment.
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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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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
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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: s 2.7.15 Sensitivity analysis HMM A
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
Page 129 and 130: s Trans Mars Injection Module Mars
Page 131 and 132: s Figure 3-2: Parallel configuratio
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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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