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s Figure 3-18: Recommendations for volumes for different areas of the social zone © LIQUIFER HMM Assessment Study Report: CDF-20(A) February 2004 page 140 of 422 To complement the requirements and numbers shown previously a set of recommendations were considered from different sources. The general architecture is shown in Table 3-7: GENERAL Anthropometric design and layout Factors to be considered Impacts Reference Neutral body posture changes the geometry of the eye`s reference point Different muscular effort in zero-g and partial-g Socialization Support social cohesion Reduction of interpersonal tension Groups vs. Privacy of small groups Privacy Individual crew activities such as sleeping, reading, personal communications COMPONENTS Laundry Mass reduction of textiles Psychological issue Self-cleaning Radiation shielding Galactic Cosmic Rays (GCR) Different design for workstations, clothing and equipment in zero-g and partial-g Areas designed for group interaction (dining, wardroom, entertainment area, group work sites) Separation of private crew quarters from: • Public view • Sounds • Vibrations Water requirements Solar Particle Event (SPE) Storm shelter must be included in the architecture [RD92], p 147 [RD93] [RD93] [RD95]
s Factors to be considered Impacts Reference Windows Provide the ability to observe outside the habitat Exercise Fitness Micro-g Countermeasures Personal Hygiene Whole body cleansing in privacy Changing clothes Greenhouse Fresh food Take care of live system Table 3-7: General architecture Cupola: observation of exterior of module, EVA and robotic operations Windows in private crew quarters with automatic shutters HMM Assessment Study Report: CDF-20(A) February 2004 page 141 of 422 [RD96] cosmonaut rec. [RD97] Dedicated areas [RD96] Areas for personal hygiene [RD93] Dedicated areas [RD98] Table 3-9 shows factors that become especially relevant in studies dedicated to human long-term missions such as a human mission to Mars. Themes such as adjacency and separation derive from the spatial position of the functions in relation to each other inside the spacecraft. Table 3-8 shows the internal configuration: Factors to be considered ADJACENCY and SEPARATION Impacts Source Simultaneous crew Reduce the change of [RD92],p151 activities to be located accidental interference far enough apart Easy access to Easy repair and [RD96] potential trouble spots adjustments (leak points, motors, valves, controllers) Emergency routes at every stage of the habitat [RD92],p151 Protection from Communications and Physical separation of [RD96] electronic magnetic computation equipment power cables from interference may be interfered computer systems and data cables Layout of raceways Mechanical systems Sound, vibration and smell [RD96] (motors, pumps, LSS, waste management, toilets) far away from crew quarters control Separating waste Hygienic and aesthetic [RD96] management from food preparation and reasons
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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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Page 93 and 94: s Parameters used: • No Shuttle
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Page 125 and 126: s 3 TRANSFER VEHICLE 3.1 Systems…
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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
Page 179 and 180: s Figure 3-38: Power required to ma
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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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