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s 4.3.5.3 Mars environment description Figure 4-49: Power inputs at MEV level HMM Assessment Study Report: CDF-20(A) February 2004 page 300 of 422 On Mars, there are specific degradation factors affecting solar energy technology performances (typically solar cells): • Presence of direct but also diffuse light from the atmosphere and suspended dust particles (‘diffusion’) • Scattering of the sunlight spectrum towards the red end, due to suspended dust particles (‘scattering’) • Dust deposition effects on solar array surfaces (‘dust deposition’) Note that diffusion, scattering and dust deposition effects are not constant but vary depending on seasonal and geographical conditions, as well as on the occurrence of large dust storms. In summary, solar cell efficiencies can be broadly affected by the Martian climate changes, and to an extent that can only partially be quantified for the time being. Other important environmental factors are: • Potentially lower operational temperatures than orbital conditions • High-speed winds, but with much lower force than in similar circumstances on Earth, due to the lower ambient pressure (average value is 6.4 mbar compared with Earth average 1013 mbar) • The presence of oxidizing soil characteristics (and potential corrosion of PVAs). For more information on the issues presented above can be found in [RD83] through [RD85]. The source of information for the Sun irradiance at Mars ground level is the Martian Climate database ([RD83]), which provides accurate information relating to the Mars latitude/longitude
s HMM Assessment Study Report: CDF-20(A) February 2004 page 301 of 422 and the Solar longitude Ls (indicating the Mars seasons: if Ls = 0 represents the spring equinox, then Ls=90 is the summer solstice, Ls=180 the fall equinox and Ls=270 the winter solstice). The selected database option is the Mars Global Surveyor Dust Scenario – January 2001, ‘a best guess’ representing the moderately dusty planet as observed by Mars Global Surveyvor (MGS) without the dust storms. This scenario is recommended for those who seek one annual scenario to represent the Martian mean climate, which is a reference for a moderate opacity of the atmosphere. Figure 4-50: Example of Data (Solar Flux) from the Mars Climate Database 4.3.5.4 Trade-off between technologies for the SHM Several processes to store or to generate energy on the Martian surface may be interesting. A specific chapter deals with the fuel cells since they can be used as power storage, as a power generation device or even more as part of the life support. 4.3.5.4.1 Power generation 4.3.5.4.1.1 Beamed power systems With this concept, the energy is sent by microwaves or lasers from an orbiter to the SHM. The main advantage is a light power collecting system. The disadvantages are: • requirement for a huge antenna on an orbiter • orbiter should have an orbit providing the maximum visibility of the SHM • technology is not proven in space • the Martian dust may significantly affect the performances • risk of depointment of the beam towards the crew This power generation option was therefor rejected. For information, a sizing has been estimated in [RD62].
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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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Page 277 and 278: s ECLS system mass: Figure 4-27: Ma
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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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