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s HMM Assessment Study Report: CDF-20(A) February 2004 page 296 of 422 Figure 4-45: MEV Modes The MEV power subsystem has to cope with three different types of mission requirements: • during the descent: power needs to be supplied in a short time with some peak power constraint (pyros…) • during the surface operations: important level of power needs to be supplied for a long duration with possibility to generate power • during the launch, the parking orbits and the rendezvous: power needs to be supplied for a few days with a possibility to store energy during the sunlight, to have enough energy available for the eclipses and non-Sun pointed phases. Since the power system designed for the surface operations is able to cope with high power level during periods of 14 hours, it can also cover the energy requirements for the descent phase. Therefore, it has been chosen in this study not to develop a specific power subsystem for the descent phase. Nevertheless, a dedicated DM power subsystem is not excluded given that its mass would be negligible compared to the total MEV mass. On the MAV’s side, the mass is an important mission driver. Consequently, the implementation of the huge power subsystem required for the surface operation inside the MAV has been rejected. However, such a design would be possible in some particular cases for example when using fuel cells by keeping the useless and empty reactant tanks outside of the MAV. The MEV power system is composed of: • one power system inside the SHM which is also used by the DM • one power system located in the MAV for supplying the power after the launch from Mars. These two subsystems are completely independent, except that the MAV power subsystem can be charged by the SHM power system to the launch. 4.3.5.2.2 Power requirements In this study, the power requirements have been computed unit per unit and mode per mode (DM: Figure 4-46, SHM: Figure 4-47, MAV: Figure 4-48). Each unit power profile is defined by three values: • a peak power • a standby power
s • a duty cycle value (duration of the peak power compared to the total duration) HMM Assessment Study Report: CDF-20(A) February 2004 page 297 of 422 For every mode, the peak and standby values have been added to obtain the values at system level. An equivalent duty cycle has also been computed to keep the same level of energy (See Figure 4-49). Figure 4-46: DM power inputs
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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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Page 249 and 250: s 4 MARS EXCURSION VEHICLE 4.1 Syst
Page 253 and 254: s Figure 4-2: Option 2: Vertical co
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Page 275 and 276: s Figure 4-26: Total pressure vs. O
Page 277 and 278: s ECLS system mass: Figure 4-27: Ma
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Page 299 and 300: s Figure 4-48: MAV Power Inputs HMM
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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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