ESA Document - Emits - ESA

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s Factors to be considered Impacts Source dining Toilet far away from Noisiest item during sleep crew quarters periods Multiple volumes Provide compartiments in case of: Fire Contamination Loss of pressure FLEXIBILITY OF USE Crew autonomy Flexible design of workstations Access to control systems from more points in any module At least two, separate, isolatable pressurised volumes within the habitat core to allow egress from one volume to the other in contingency situations. Elimination of dedicated workstations with their displays and controls Portable computers More autonomous working Table 3-8: Architecture configuration HMM Assessment Study Report: CDF-20(A) February 2004 page 142 of 422 [RD92],p151 [RD96] [RD92],p151 For long duration stays, communication with “home” becomes one of the major issues. Diverse studies – space mission reports or studies of humans living in extreme environments on Earth – have shown that good and efficient communication within the interior configuration is crucial for mission success in long duration missions. Table 3-9 shows recommendations for communication: Factors to be considered Impacts Reference Training Mission very long Provision of: [RD92],p143 Psychological factor Virtual-reality-training Training for 0g and xg Training Software during Travel Two-way Link with home (family, Confidential and direct [RD92], p165 communication children, friends) and simultaneous Interview Video-conference, Valery messaging Polyakov Alternative (Modern communication through Times voice, auditive, tactile, Spezial, sensory ORF) Responsibility and Less ground support [RD92], p173 authority for crew through distance increasing Table 3-9: Recommendations (communication)
s HMM Assessment Study Report: CDF-20(A) February 2004 page 143 of 422 The texture and materiality of interior spaces are considered to be a stimulating factor for a crew’s health and productivity. Noise reduction must be addressed in the design for future space habitats so that noise levels become reduced to a level of comfort. Currently noise levels on ISS are as high as on a four-lane highway (about 60 dB or even more) Table 3-10 shows recommendations for lighting, colour and sounds (about 27a). Visual stimulation 3.3.1.2 Design drivers Factors to be considered Impacts Reference Psychological well-being Through sounds colour, lighting, [RD92], p145 Orientation Up and down perception Biorhythm Create day and night/winter [RD99] and summer Different atmosphere Sunny day, cloudy day, party [RD99] mood Noise reduction to a [RD92], p155 comfortable level especially in crew quarters Table 3-10: Architecture (light, colour and sound) Initial interior design drivers depend on the decision if the THM is a rigid cylindrical module, or an arrangement of spheres, or an inflatable, or a hybrid construction of inflatable and hard shell modules. The approach of the study was to organise and design a core rigid cylindrical module where all the needed hardware, parts and functional spaces needed for habitability of the required 450m 3 should be incorporated. Moreover, how should the module be organised regarding interior space and efficient use of volume mass efficiency, habitability, psychology, physiology and spatial architectural issues?
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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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s Mars Excursion Vehicle Transfer H
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s 2.7.5.1 Mission elements dry mass
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s 2.7.5.8 MEV release The MEV is re
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s Total mission time (days) 1200 10
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s stack 9 Propellant mass of the ne
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s The core supporting structure has
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s 2.7.7.1.3 Mars excursion module S
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s 2.7.7.1.4 Earth return capsule HM
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s Mission Phase Description Event s
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s Mission Phase Description Event s
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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 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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Page 93 and 94: s Parameters used: • No Shuttle
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Page 113 and 114: s 2.10.2.2.2 LEO assembly HMM Asses
Page 117 and 118: s Basic RF link Four 70-m Ka-band s
Page 125 and 126: s 3 TRANSFER VEHICLE 3.1 Systems…
Page 127 and 128: s Operational Requirements It shall
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Page 131 and 132: s Figure 3-2: Parallel configuratio
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Page 149 and 150: s Figure 3-24: Baseline design back
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Page 153 and 154: s Module part 3............= 0 m 3
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Page 177 and 178: s flux [W/m2] 250 200 150 100 50 0
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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 4.5.2.1 Requirements and design d
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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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