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s Equipment Number Mass per of units unit (kg) ALS Airlock Air Save Pump Package 2.00 70.30 ALS CONVENTIONAL OVEN 1.00 50.00 ALS COOKING/EATING SUPPLY 1.00 5.00 ALS METOX CO2 removal (canister) 6.00 14.52 ALS METOX CO2 removal (regenerator) 2.00 47.63 ALS VACUUM 2.00 30.00 GENERIC ACCUMULATOR URINE STORAGE TANK (57L) 1.00 30.84 GENERIC CLOTHING 10kg 3.00 10.00 GENERIC INORGANIC STORAGE(200kg) 1.00 67.00 GENERIC LiOH incl. Activated Carbon (1kg) 30.00 1.00 GENERIC OPERATIONAL SUPPLIES (20kg) 3.00 20.00 GENERIC ORGANIC STORAGE(200kg) 1.00 80.00 GENERIC PERSONAL STOWAGE SPACE (50kg) 1.00 50.00 GENERIC TOOLS EQUIPMENT (20kg) 1.00 20.00 ISS AAA - avionics air assembly 2.00 12.40 ISS ACCUMULATOR POTABLE STORAGE WATER TANK (57L) 15.00 30.84 ISS ACCUMULATOR WASTE WATER TANK (46L) 1.00 67.59 ISS ACCUMULATOR WASTE WATER TANK (46L) 6.00 67.59 ISS CCAA 2.00 112.00 ISS commode/urinal 2.00 50.00 ISS condensate storage 1.00 21.20 ISS EMU (Shuttle) 4.00 135.00 ISS HEPA - BACTERIAL FILTER 3.00 5.20 ISS IMV - intermodule ventilation fan assembly 2.00 4.76 ISS IMV - intermodule ventilation valve 2.00 5.10 ISS NITROGEN STORAGE TANK 1.00 109.00 ISS OXYGEN TANK PRESSURISATION SYSTEM 1.00 102.00 ISS PFE - portable fire extinguisher 2.00 15.10 ISS Sample Delivery System 1.00 2.70 ISS smoke detector 2.00 1.50 ISS TCCS - trace contaminant control system 1.00 78.20 ISS trash compactor 1.00 27.00 Manual Pressure Equalization Valve (MPEV) 1.00 1.20 microwave oven 1.00 70.00 personal hygiene kit 3.00 1.80 Portable Breathing Aparatus 3.00 1.20 Pressure Control Assembly (PCA) 1.00 78.20 RESTRAINTS AND MOBILITY AIDS (100kg) 0.00 100.00 SLEEP PROVISIONS 0.00 9.00 SOYUZ FOOD SUPPLY CONTAINER 1.00 5.00 X-38 HI PRESSURE G02 REGULATOR 1.00 1.40 X-38 HI PRESSURE GN2 REGULATOR 1.00 1.40 X-38 LOW PRESSURE G02 REGULATOR 1.00 1.40 X-38 LOW PRESSURE GN2 REGULATOR 1.00 1.76 Table 4-8 Detailed unit breakdown for the anticipated life support system HMM Assessment Study Report: CDF-20(A) February 2004 page 278 of 422
s HMM Assessment Study Report: CDF-20(A) February 2004 page 279 of 422 The life support system should not be considered exhaustive. It is merely a list of major components, which give an indication of what LSS mass has to be anticipated. Between the power engineering domain and the life support domain it was agreed on using the cryogenic oxygen tanks for oxygen resupply to the crew and to collect all product water of the fuel cells in the storage tanks of the life support system. Note that that the list includes hardware based on life support and a fraction of crew accommodation needs. Additional fractions are found in the Human Factors engineering domain. 4.3.3.11 Budgets 4.3.4 Thermal Characteristic Value Ppeak (kW) 10.3 Pnight (kW) 1.7 Pday (kW) 1.6 Volume (m 3 ) 7.9 Mass (kg) 3208 Table 4-9: Life support power budget The SHM thermal control shall be designed to perform optimally during the stay on Mars. The question whether the same performance is expected during the transfer to Mars remains open. Not necessarily a permanent habitable module (economy of a radiation shield), its functions can be hold in a dormant mode, reactivated when a crew enters the module (storable zone for example). The advantage of this is a higher tolerance on the thermal control and a lower associated budget. 4.3.4.1 Requirements and design drivers The main requirements are the following • The external thermal control shall be effective in vacuum and in the Martian pressurised environment. • The TCS functions are to maintain air temperature and humidity in the HSNM zones within preset limits, and to thermally control the on-board systems. Therefore, TCS shall be designed to maintain: • the habitable zones in a certain comfort zone (temperature, humidity) but respecting also safety requirements (touch temperature, condensation avoidance). Standard figures are a medium temperature between 18 and 27C and a relative humidity from 25 to 70%. • a uniform environment for a crew up to 3 members. • elements and/or dedicated zones within temperature requirements (electronics, propellants, valves, …). To optimise the thermal budget, a certain rationalization of space and grouping of elements shall be carried out. Ideally, all equipments are within a single dedicated enclosure. • the interfaces of the others modules (ascent vehicle) within temperature requirements
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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 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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Page 233 and 234: s The propulsion system and its cha
Page 237 and 238: s Item Nr. Mass [kg] Margin [%] Mas
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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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