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s HMM Assessment Study Report: CDF-20(A) February 2004 page 304 of 422 Figure 4-51: Primary FC with Air+H2 as reactants There are five types of fuel cells: • Phosphoric Acid Fuel Cell (PAFC): phosphoric acid is used as an electrolyte. It needs to operate around 200°C and the cathode performance is inefficient. • Proton Exchange Membrane Fuel Cell (PEMFC): The mechanism is the same as PAFC. They differ in that PEMFCs operate at relatively low temperatures (about 100°C). They have high power density and can vary their output quickly to meet shifts in power demand • Molten Carbonate Fuel Cell (MCFC): An alkali metal carbonate (Li, Na, K) is used as the electrolyte. It needs to operate at about 600°C. • Solid Oxide Fuel Cell (SOFC): solid, nonporous metal oxide electrolytes are used. The cell operates at about 800-1000°C with an efficiency that can reach 60%. • Alkaline Fuel Cell (AFC): AFC uses alkaline potassium hydroxide as the electrolyte. These cells can achieve power generating efficiencies of up to 70%. PEMFC and SOFC have the best maturity and European strength and fit the best with the Martian surface requirement. Due to the relatively low efficiency of fuel cells, the thermal dissipation will be important and can be used for thermal regulation of fuel cells themselves but also for the rest of the spacecraft. Using H2/O2 fuel cells has an important added value: water is the product of the reaction and can be used for the life support. Hence, the trade-off of the power system on the Martian surface should also include the water for the life support. 4.3.5.4.3.2 Regenerative fuel cells Some fuel cells called “regenerative FC” can also be used in a reverse way: when power is supplied, an electrolysis process take place and the fuels are produced.
s Figure 4-52: Regenerative Fuel Cell with O2/CO/H2 as reactants HMM Assessment Study Report: CDF-20(A) February 2004 page 305 of 422 Fuel cell technology becomes extremely interesting on the Martian surface, as soon as the fuels can be found there. Unfortunately, until now, except the ice located in some spots close to the poles, the only interesting element is the CO2. Some processes are studied to reduce the CO2 to CO and then O2 ([RD70]), but therefore, power is first needed. Such a process should be really interesting for a permanent mars base but not for a mission of only 37 days. [RD68] and [RD69] present the use of a regenerative-SOFC on the Martian surface using that concept of oxygen extraction from the mars atmosphere. With that concept, the fuel cells could provide: • power for the electrical equipments • heat for the thermal system • fuel for the take-off from Mars • oxygen and water for the life support Figure 4-53: R-SOFC potential system on Mars
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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 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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