ESA Document - Emits - ESA

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s 15 30 100 600 TransHab ISTC IOV Figure 2-1: Required pressurised volume as a function of the mission duration (historical data) HMM Assessment Study Report: CDF-20(A) February 2004 page 24 of 422 Based on historical data, the required pressurised volume for the THM was determined to be 75 m 3 /person. Out of this 25 m 3 /person was determined to be equipment-free space. In the case of the SHM, a gravity of 1/3 g will be affecting the astronauts, therefore the requirement changes to free surface. A survey has been carried out to assess the required surface: Surface (m2) 20 15 10 5 0 0.93 Fallout shelter 2.32 Multiple Occupancy cell Surface per occupant 3.33 Tent 6.66 6.69 Trailer/Mobile Home Naval Preventive Medicine 8 Lunar base 9 Accomodation law 17.33 Accomodation law (3 persons) Figure 2-2: Surface available in the different earth systems Naval Medicine Standards: 6.69 m 2 per occupant or 20 m 2 for a crew of 3 For a crew of three people at least 20 m 2 are required with a minimum altitude of 2.5 metres. This makes a volume of 50 m 3 , plus 25 m 3 for storage and 4 m 3 for the airlock. Total pressurised volume for the SHM is 79 m 3 . 75 60 20 9 5 (Apollo)
s 2.2.4.2 Accelerations HMM Assessment Study Report: CDF-20(A) February 2004 page 25 of 422 The requirements for maximum g-loads vary depending on the body axes considered (see Figure 2-3 for body axes). Crew seats are oriented so that the g-loads during the critical phases (i.e. launch and landing. etc) are along the +Gx direction, direction in which higher loads can be sustained. The maximum allowable loads along that axis are shown in Figure 2-4. Acceleration, g 7.00 6.00 5.00 4.00 3.00 2.00 1.00 0.00 Figure 2-3: Body axes directions Maximum g-loads allowable in the +Gx axis Mission Phases Earth Departure Mars Arrival Mars Departure Earth Arrival Figure 2-4: Maximum allowable g-loads in the +Gx direction Maximum allowable g-loads at Mars arrival, Mars departure and Earth return are lower to account for crew deconditioning after experiencing microgravity for several months. Due to the lack of data for very long durations during microgravity, after a certain threshold time the maximum g-loads have been assumed as constant (optimistic approach). The requirements for sustained g-loads are not only a function of the direction but also depend on the time of exposure. As shown in Figure 2-5, long-duration g-load limits depend linearly on the time of exposure. The +Gx axis direction has the highest allowable loads and –Gz the one with the lowest. Figure 2-5 data do not consider microgravity exposure.
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
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Page 27 and 28: s 2.2.4.4 Temperature and relative
Page 33 and 34: s Figure 2-10: Trajectory Overview
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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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s 2.7.10 Mission performance Table
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s Days on Martian surface 450 400 3
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s HMM Assessment Study Report: CDF-
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s Maximum manoeuvre duration 6 mont
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s % of loss from baseline 20 18 16
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s 2.7.15 Sensitivity analysis HMM A
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s 2.7.15.4 Influence of the mass of
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s Parameters used: • No Shuttle
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s 2.8.3.3 Launch 3- Front node Figu
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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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