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s HMM Assessment Study Report: CDF-20(A) February 2004 page 308 of 422 Nevertheless, mass, volume and efficiency of this subsystem is computed and taken into account in the design with an interpolation based on existing space PCDUs. 4.3.5.5.4 Budgets and trade-offs The list of the selected architecture is Figure 4-56 shows the possible power options for architecture for surface operations: Figure 4-56: List of power architecture options for surface operations The comparison between the architectures are presented for: • The total mass (Figure 4-57) • The total deployed solar array area required (Figure 4-58) • The volume of the power subsystem prior to the landing (Figure 4-59). 8000.000 7000.000 6000.000 5000.000 kg 4000.000 3000.000 2000.000 1000.000 0.000 Option1: Fuel Option2: Fuel Cells for 37 days Cells for 37 days w ith Liquid H2 + w ith gazeous LOX forms Option3: Solar Panels + Li-Ion Batteries Mass Computation Option4: Solar Cells Blanket + Li-Ion Batteries Option5: Solar Panels + Fuel Cells gazeous form Option6: Solar Cells Blanket + Fuel Cells gazeous form PV PCDU Storage Option7: Solar Panels + Fuel Cells Liquid Figure 4-57: Mass comparison for the eight architecture options c Option 8: Solar Cells Blanket + Fuel Cells Liquid
s 450.00 400.00 350.00 300.00 250.00 200.00 150.00 100.00 50.00 0.00 Option1: Fuel Cells for 37 days w ith Liquid H2 + LOX Option2: Fuel Cells for 37 days w ith gazeous forms Option3: Solar Panels + Li-Ion Batteries SA Area (m2) Option4: Solar Cells Blanket + Li-Ion Batteries Option5: Solar Panels + Fuel Cells gazeous form Option6: Solar Cells Blanket + Fuel Cells gazeous form Option7: Solar Panels + Fuel Cells Liquid Option 8: Solar Cells Blanket + Fuel Cells Liquid Figure 4-58: Area comparison of deployed solar arrays for the eight architecture options 9000.00 8000.00 7000.00 6000.00 5000.00 4000.00 3000.00 2000.00 1000.00 0.00 Option1: Fuel Option2: Fuel Cells for 37 days Cells for 37 days w ith Liquid H2 + w ith gazeous LOX forms Option3: Solar Panels + Li-Ion Batteries Option4: Solar Cells Blanket + Li-Ion Batteries Option5: Solar Panels + Fuel Cells gazeous form Option6: Solar Cells Blanket + Fuel Cells gazeous form Option7: Solar Panels + Fuel Cells Liquid Option 8: Solar Cells Blanket + Fuel Cells Liquid HMM Assessment Study Report: CDF-20(A) February 2004 page 309 of 422 Volume (l) with SA stowed PV PCDU Storage Figure 4-59: Comparison of required volume for the eight architecture options Options 1 and 2 would produce 1075 litres of water that can be used for life support purposes (drinking water included). In total, during the surface operations, 437 litres are necessary for the astronauts. Hence, for these two options, the fact that water is not stored anymore in the life support subsystem, 437 litres and 437 kg has to be deducted from the power subsystem mass and volume figures. Moreover, the production and consumption of the water is spread continuously for the duration of the mission. Therefore, the water storage tank does not need to be sized for the total duration of the stay on the surface. Option 1 (liquid storage) has as main disadvantage the cooling by the TV during all the cruise to Mars. Nevertheless, the increase of the required TV solar panels seems feasible.
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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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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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Page 275 and 276: s Figure 4-26: Total pressure vs. O
Page 277 and 278: s ECLS system mass: Figure 4-27: Ma
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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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