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s 4.5.8.1 Requirements and design drivers HMM Assessment Study Report: CDF-20(A) February 2004 page 394 of 422 The MEV complex consists of two main modules. The Surface Habitation Module (SHM) and the Mars Ascent Vehicle (MAV). The study required both modules to be equipped with life support systems, which are not interconnected. The MAV life support system is designed to provide life support to a crew of three for 5 days. The mission parameters and the size of the crew allow this study to use the Soyuz TM(A) design as a reference point. 4.5.8.2 Assumptions and trade-offs Metabolic Requirements of the Crew The metabolic needs of the crew have been calculated using the correlations given in <strong>ESA</strong> standard PSS-03-406 and crosschecked with relevant sources. The entire calculations have been based on the energy expenditure of the crew. The schedule for crew activity is shown in Figure 4-122. SCHEDULE IN HOURS FOR THE MOST ACTIVE DAY ACTIVITY ASTRONAUT 1 2 3 sleep 8 8 8 pre- and post sleep 5 5 5 leisure activities 0 0 0 personal hygiene 1 1 1 eating 2 2 2 exercise 0 0 0 station keeping 8 8 8 laboratory activities 0 0 0 Metabolic Cost of EVA EVA mission tasks 0 0 0 EMU donning/doffing 0 0 0 egress/ingress 0 0 0 pre-EVA setup & post EVA EMU care 0 0 0 TOTAL TIME (24hrs) 24 24 24 Figure 4-122: Crew Activity Schedule during Martian surface Stay Based on the energy expenditure, the metabolic needs and products by the crew have been estimated and are shown in Figure 4-123. PER DAY PER MISSION ENERGY CONSUMPTION (W*h) 8512.8 35753.8 ENERGY CONSUMPTION (J) 30646080 128713536 OXYGEN CONSUMPTION (m3) 1.5 6.4 OXYGEN CONSUMPTION (kg) 2.1827 9.1675 DRINKING WATER (m3) 0.0051 0.0214
s PER DAY PER MISSION DRINKING WATER (kg) 5.1 21.4 DRY FOOD (kg) 2.0 8.5 CARBON DIOXIDE PRODUCTION (m3) 1.3 5.3 metabolic water production (kg) 0.9 3.8 URINE PRODUCTION (kg) 4.6 19.3 FAECAL LIQUIDS (kg) 0.13 0.6 INSENSIBLE WATER (kg) 4.6 19.3 TOTAL SOLID WASTE PRODUCTION FAECES (kg) 0.2 0.9 HMM Assessment Study Report: CDF-20(A) February 2004 page 395 of 422 Figure 4-123: Metabolic needs and products of the crew The data presented in this figure suggest a mass of consumables of about 503kg. Taking into account that consumables need additional hardware for storage and use, as well as the need to treat and store the metabolic products, the use of an open loop system seems favourable. The data strongly suggests the use of open loop systems except a recovery system for condensate. Additional considerations 4.5.8.2.1 Hygiene water There is no hygiene water allowance during this phase of the mission. 4.5.8.2.2 Drinking water The drinking water allowance for the crew has been estimated to be 1.7 l/crew/d and was oriented on the drinking water allowance on-board a Soyuz TM(A) vehicle. 4.5.8.2.3 Cabin atmosphere The cabin atmosphere has been selected as follows: Total Cabin Pressure: 50.0 kPa Partial Pressure Oxygen: 25.0 kPa Partial Pressure Nitrogen: 25.0 kPa Partial Pressure Carbon Dioxide: TBD Preferably, the atmosphere would be free of any contaminants. However, as a minimum requirement, the spacecraft atmosphere shall adhere to the requirements given in <strong>ESA</strong> PSS-03- 401. Based on the experiences with long term pressurised spacecrafts there shall be more stringent limits on microbial contamination. Following limit has been proposed during this study: Total microflora count: 200CFU/m3 (CFU - colony forming units) 4.5.8.2.4 EVA considerations No EVAs are to be performed during this mission phase. 4.5.8.2.5 Waste production
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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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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 3.3.3.1 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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Page 373 and 374: s Inclination (deg) 47.5 47 46.5 46
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Page 411 and 412: s 7 APPENDIX B - REFERENCES [RD1] C
Page 413 and 414: s [RD26] IES2, Phase A0: Final Repo
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Page 419 and 420: s 8 APPENDIX C - ACRONYMS AAA Avion
Page 421 and 422: s MLI Multi-Layer Insulation MMH Mo
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