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s HMM Assessment Study Report: CDF-20(A) February 2004 page 228 of 422 3.3.9.3.3 Radiation shielding According to the duration and type of mission, the radiation dose limits that an astronaut can receive during the mission are different. These requirements are translated in terms of the ratio mass per area, kg/m 2 of the protection material. With the mass available on-board, it was analysed what was the protection provided, for the THM and for the storm shelter, and the necessary amount of mass to be added to fulfil the shielding requirements. The mass available on board that is able to provide shielding protection is shown in Table 3-54: Material Mass [kg] THM Skin + Stiffening 4382.9 Internal Equipment 28754 THM Debris Shielding 964.9 MLI 525.68 Water 1200 Total mass 43 944 Table 3-54: Mass Budget for radiation protection Shielding effectiveness depends largely upon the conductivity of the material. Materials with low Z are considered to be effective. For preliminary calculations the density ratio to convert from g/cm 2 to material shielding thickness was used, that is, 1 cm of H2O is generally equivalent to a 1 cm thick slab of water, or 4 mm of aluminium. The mass required for a certain shielding requirement is therefore independent of the type of material, only the thickness will be different from one material to the other. With the mass available on-board, two configurations for the shielding protection were analysed. The shielding effectiveness of each configuration, for nominal protection and for the storm- shelter is described in Table 3-55. Also on-board are the consumables, weighing 10 200 kg, which were not taken into account in these calculations because it is not yet known what percentage will be able to be used as shielding protection, after their usage. The mass necessary to add in the closures corresponds to 60.6% of the consumables. This value is assumed to be viable to be used as shielding material. Shielding to this area may be provided by the consumables and by propulsion modules on one side and on the other by the MEV. The necessary mass to be added in the skirt is smaller in case 1. Due to all the facts presented, case 1 was selected, and through this it's only necessary to add 2007kg of extra mass. It was decided to add extra mass in the form of water. Then instead of having two separated water tanks, the extra mass is located in the closures, and in the skirt the 2000 kg will be consumables. Figure 3-71 shows the selected configuration. Note that the shielding effectiveness of vehicle skin or equipment cases with metal walls of any reasonable thickness is limited by the apertures, joints and others discontinuities, rather than the metal itself.
s Radiation Shielding Shielding Requirements Habitation Module Storm-shelter 9 g/cm 2 25 g/cm 2 Mass available Internal Equipment (85%) MLI, Structural Skin, Debris Shielding 30341 kg Protection Provided Mass to add 9.5 g/cm 2 ----------- Case 1 Case 2 Skirt 15% - Internal Equipment 4500 kg Thickness: 0.42m Closures H2O – 1200 kg Thickness: 0.02m HMM Assessment Study Report: CDF-20(A) February 2004 page 229 of 422 H2O – 1200 kg Thickness: 0.03 m 15% - Internal Equipment 4500 kg Thickness: 0.3 m Skirt (10.58 g/cm 2 ) 20.05 g/cm 2 (2.96 g/cm 2 ) 12.43 g/cm 2 Closures (2.12 g/cm 2 ) 11.59 g/cm 2 (7.58 g/cm 2 ) 17.05 g/cm 2 Skirt 2007.2 kg 5094.4 kg Closures 7582.9 kg 4495.7 kg Total mass necessary: 9590.17 kg 9590.17 kg Table 3-55: Level of protection provided by the mass on-board Figure 3-71: Shielding configuration for the storm-shelter.
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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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Page 177 and 178: s flux [W/m2] 250 200 150 100 50 0
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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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s 4.4.5.3.2 GNC equipment HMM Asses
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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 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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