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s HMM Assessment Study Report: CDF-20(A) February 2004 page 396 of 422 The produced waste is stored in waste storage canisters. The degree of stabilization has to be sufficient to guarantee 4.5.8.2.6 Waste management strategy Waste is stored in on-board containers. Stabilization is not a major issue due to the short duration before disposing of the MAV spacecraft. 4.5.8.3 Baseline design The design is based on the Soyuz-TM(A) life support system design. ECLS system mass: Figure 4-124: Mars MAV LSS design CONSUMABLES TO BE LAUNCHED (kg) OXYGEN 10.0 NITROGEN 0.0 POTABLE WATER 21.0 HYGIENE WATER 0.0 DRY FOOD 8.5 PACKAGING 4.0 INORGANIC MATERIAL ECXL. PACKAGING 2.0 TOTAL CONSUMABLES TO BE LAUNCHED WASTE PRODUCTION DURING MISSION (kg) 45.5 WASTE GASES 5.3 WASTE WATER 39.2 SOLID ORGANIC WASTE 0.9 SOLID INORGANIC WASTE excl. packaging 2.0 PACKAGING 4.0 TOTAL WASTE PRODUCED 51.4 ROUGH ESTIMATE ECLSS MASS (kg) TOTAL ECLSS SYSTEM MASS 549.0 Table 4-66: Mass Estimates for a Mission using Current Technology
s HMM Assessment Study Report: CDF-20(A) February 2004 page 397 of 422 The life support system has been estimated to have an approximate mass of 549 kg. The detailed mass budget is given in Table 4-67. Equipment Number of units Mass per units (kg) GENERIC PIPING 1/4"X1m 5.00 0.13 ISS PFE - portable fire extinguisher 1.00 15.10 ISS smoke detector 1.00 1.50 SOKHOL spacesuit 3.00 12.00 SOYUZ AIR PURIFICATION UNIT 4.00 10.00 SOYUZ ARGUS PRESSURE SENSOR 1.00 3.50 SOYUZ AUTOMATIC PRESSURE CONTROL UNIT 1.00 7.50 SOYUZ CHX 2.00 10.00 SOYUZ CONDENSATE STORAGE TANK 3.00 15.00 SOYUZ FAN 2.00 2.00 SOYUZ GAS ANALYZER 1.00 20.00 SOYUZ GASEOUS O2 STORAGE SYSTEM (12l) 1.00 10.00 SOYUZ GASEOUS O2 STORAGE SYSTEM (20l) 4.00 18.00 SOYUZ HAND PUMP 1.00 1.00 SOYUZ LIGHTING (20cm fluorecent) 2.00 1.00 SOYUZ LIGHTING (spot panel lighting) 13.00 0.20 SOYUZ O2 TANK PRESSURE SENSOR 2.00 2.00 SOYUZ O2 TANK WALL TEMPERATURE SENSOR 5.00 2.00 SOYUZ ONBOARD TANK 3.00 19.60 SOYUZ OXYGEN SUPPLY FITTINGS 17.00 4.00 SOYUZ personal hygiene kit 3.00 1.50 SOYUZ PORTABLE SURVIVAL KIT 1.00 15.00 SOYUZ PRESSURE ALARM SENSOR 1.00 0.72 SOYUZ PRESSURE EQUALIZATION VALVE 1.00 6.00 SOYUZ PURIFICATION CARTRIDGE (REGENERATOR) 1.00 10.00 SOYUZ RECEVING DEVICE 3.00 0.30 SOYUZ REFILLING VALVES 1.00 3.40 SOYUZ RELIEF VALVE 1.00 6.70 SOYUZ RESCUE AID AUTOMATIC UNIT 1.00 5.00 SOYUZ SAFETY UNIT 1.00 1.40 SOYUZ SOKHOL SUIT BLOWER ASSEMBLY 3.00 3.90 SOYUZ SOLID WASTE STORAGE CANISTER 1.00 10.00 SOYUZ SUIT FAN CIRCUIT BRAKER PANEL 1.00 1.00 SOYUZ TOILET 1.00 50.00 SOYUZ VALVE INHIBIT PANEL 1.00 1.00 Table 4-67: Detailed mass budget for the anticipated life support system The life support system may not be considered exhaustive. It is merely a list of major components, which give an indication of what LSS mass has to be anticipated. Note that the list includes hardware based on life support and crew accommodation needs. 4.5.8.4 Budgets ECLSS mass 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 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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s 2 3.9 233 923.1 347 923 12.3 352
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Page 403 and 404: s 6 APPENDIX A - MARTIAN SURFACE NU
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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
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