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s • DCS treatment chamber • Safe area in case of contingency • Additional level of containment 4.3.3.8.4 Investigation of alternative inert gases HMM Assessment Study Report: CDF-20(A) February 2004 page 276 of 422 In the course of this study, alternative inert gases were investigated with the objective of minimising DCS risk and prebreathing time without compromising safety. Previous studies with rats demonstrated that the use of a mix of inert gases (nitrogen/argon, argon/helium, nitrogen/helium) does not represent any advantage over the use of one of the most advantageous inert gases such as helium. It was shown that the total pressure of gases except oxygen in the tissue is important and not the partial pressure of the individual gases except oxygen that are dissolved in the tissue. Neon has been suggested as the most advantageous inert gas for space flight applications; however, there have not been any reports of tests with neon as inert gas. Most likely reason for the absence of such data is the price of neon. 4.3.3.8.5 Contingency supply The use of an open-loop system reduces the need for an emergency supply. However, seven days have been taken in this study as the timeframe expected to prepare for ascent from the Martian surface and journey to the THM. Currently, the assumption is that the supply would be sufficient until the crew has been able to overcome the contingency situation or to return to the THM using MAV resources. 4.3.3.8.6 In-situ resource utilization (ISRU) ISRU has not been considered during this phase of the study. 4.3.3.9 Waste management strategy Waste has to be stabilized and stored on the surface. No recycling or return of the waste is envisaged to minimise down and up mass for the life support. Currently, the strategy is not compliant with the Planetary Protection rules and it is necessary to further study the waste handling strategy on the Martian surface. The only measure taken into account is to seal the SHM prior to the departure. 4.3.3.10 Baseline design The life support system is an open-loop life support system with limited regeneration. Water is provided by the fuel cells. Oxygen is stored with the oxygen needed for power generation in the fuel cells. All subsystems of the life support system are designed as open loop with replaceable consumables. The actual technical design of the subsystems has not been yet and needs further investigation.
s ECLS system mass: Figure 4-27: Mars SHM LSS design Consumables to be launched (kg) Oxygen 28.0 Nitrogen 91.0 Potable water 323.1 Hygiene water 114.0 Dry food 75.8 Packaging 27.4 Inorganic material excluding packaging 11.1 Total consumables to be launched 670.4 Waste production during mission (kg) Waste gases 37.4 Waste water 425.6 Solid organic waste 19.3 Solid inorganic waste excluding packaging 11.1 Packaging 27.4 Total waste produced 520.9 Rough estimate ECLSS mass (kg) Total ECLSS system mass 3208.0 Table 4-7: Mass estimates for a mission using current technology HMM Assessment Study Report: CDF-20(A) February 2004 page 277 of 422 The life support system has been estimated to have an approximate mass of 3 tonnes. The detailed unit breakdown is shown in Table 4-8:
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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 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 Figure 4-85: Communications MEV/M
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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 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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