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s HMM Assessment Study Report: CDF-20(A) February 2004 page 306 of 422 For this mission, the short stay on the surface is not sufficient for the fuel production. A trade-off has been performed in combination with the life support subsystem concluding that such a recycling design is not advantageous in term of mass. Primary and regenerative fuel cells are kept as candidates for this mission. Therefore, the fuel cell model is inspired from [RD5]. 4.3.5.4.4 Conclusions For the power subsystem of the Habitation Module, the topologies kept for the design are: • Use of a secondary Li-Ion improved battery with solar cells (either thin film or mounted on rigid panels). • Use of a regenerative fuel cell that can be daily recharged with solar cells (either thin film or mounted on rigid panels). • Use of a primary H 2 /O 2 fuel cells with tanks sized for providing the total energy required on the surface. The sizing of these several subsystems are hereafter performed and compared. 4.3.5.5 Surface habitation module power design 4.3.5.5.1 Inputs and assumptions 4.3.5.5.1.1 Solar cells The landing requirement area is all in the range between 20°N to 20°S. Figure 4-54 shows the daily solar energy on a horizontal surface of 1 m² depending on the latitude and the solar longitude of Mars. An absolute design that is fit for all landing dates would require as input an irradiance of 2000 Wh/m²/day. Since the size of the solar panels is critical and the window of landing for the crew is about one terrestrial year, it has been chosen to add the following power constraint: “Surface Operations are not possible when the irradiance is under 3500 Wh/m²/day”. This new operation requirement does not forbid any landing latitude. For every latitude in the range 20°N to 20°S, at least two time-opportunities are possible for a landing. The periods in which landing on the surface will not be possible are summarized in Figure 4-55. Dust accumulation and contingency surface operations duration have been taken into account.
s Figure 4-54: Solar irradiance on the Martian surface during one Martian year Figure 4-55: Periods for which landing cannot be performed based on solar-cell design HMM Assessment Study Report: CDF-20(A) February 2004 page 307 of 422 For the designs without solar cells, this operations limitation simply disappears. For example, the design based on primary fuel cells is not dependent the landing date nor the latitude of the landing site. 4.3.5.5.2 Fuel storage for FC Hydrogen and oxygen can be stored either in gaseous or in liquid form. For the gaseous forms, high-pressure storage is necessary to limit the volume, especially for the hydrogen that has a low density. Therefore, hydrogen is assumed to be stored at 700 bars. The storage in a liquid state without losses due to boil-off can only be performed by cooling the tanks to 20° K for H2 and 90° K for O2. Therefore, the corresponding power requested for this thermal regulation has permanently to be supplied by the TV until the separation of the MEV. On the Martian surface itself, with the tanks protected by the structure, the boil-off has been estimated only around 1% per month. Consequently, the cooling of the tanks doesn’t need to be continued during this phase. 4.3.5.5.3 PCDU At this stage of definition, the power conditioning and distribution has not been analysed in details. Indeed, this module is not as critical as the power generation and storage modules for all aspects: mass, volume, technology, cost.
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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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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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