ESA Document - Emits - ESA

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s • Safety, so a fail-safe design is mandatory • Has to provide interfaces with all the other elements, because it is the ‘backbone’ The PM main design drivers are: • ∆Vs required for the mission are of the order of 3 km/s for each manoeuvre • Large payloads, specially the THM which has to be sent to Mars and brought back • Launcher constraints in terms of mass and dimensions • Only cryogenic and storable technologies to be used • Boil-off rate • Usage of existing engines 3.1.3 Mass budget The mass budget for the THM is shown in Table 3-2: Transfer Habitation Module Mass (kg) Margin applied (%) Total Mass with Margin 66764 Total Dry Mass with Margin 56545 System Margin Applied 9424 20 Structure 12468 7.8 Thermal Control 3920 8.7 Mechanisms 5445 14.5 Communications 162 13.4 Data Handling 660 20 GNC 1800 0 Propulsion 0 0 Power 4483 20 Harness 2000 0 Lifesupport 15592 14.4 Consumables: 10219 Potable Water 1009 Hygiene Water 324 Dry Food 3831 Oxygen 394 Packaging 1392 Inorganic Material (excluding packaging) 3178 Nitrogen 91 Waste generated (from consumables) 5375 Payload 0 0 Astronauts 591 0 Total Propellant Mass 0 0 Table 3-2: Mass budget for the THM The mass budget for the propulsion modules is shown in Table 3-3: HMM Assessment Study Report: CDF-20(A) February 2004 page 128 of 422
s Trans Mars Injection Module Mars Orbit Insertion Module Trans Earth Injection Module Number of stages 3 2 1 Number of stacks 12 4 1 First stage 4 2 1 Second stage 4 2 Third stage 4 Number of supporting structure 3 1 1 Stack design Total mass with margin (kg) 80000 80000 80000 Total dry mass with margin (kg) 9214 3676 3676 Structure with margin (kg) 5702 2416 2416 Thermal control with margin (kg) 843 95 95 Mechanisms with margin (kg) 33 36 36 Propulsion with margin (kg) 2637 1130 1130 Total propellant mass (kg) 70786 76324 76324 Supporting structure design Total mass with margin (kg) 5178 3572 683 Structure with margin (kg) 3776 2533 523 Mechanisms with margin (kg) 540 443 46 System margin (%) 20 20 20 Table 3-3: Mass budget for the PM Therefore, the total mass to be launched into LEO is: HMM Assessment Study Report: CDF-20(A) February 2004 page 129 of 422 Element Mass per unit Number Total mass (tonnes) (tonnes) THM 66.7 1 66.7 TMI stacks 80 12 960 TMI supporting structure 5.2 3 15.6 MOI stacks first stage 80 2 160 MOI stacks second stage 50 2 100 MOI supporting structure 3.6 1 3.6 TEI stacks 80 1 80 TEI supporting structure 0.7 1 0.7 TOTAL 1386.6 Table 3-4: Total mass to be launched into LEO Note that the mass presented above is not the mass prior to the departure due to the losses due to the boil-off.
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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
Page 77 and 78: s Days on Martian surface 450 400 3
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Page 85 and 86: s % of loss from baseline 20 18 16
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Page 93 and 94: s Parameters used: • No Shuttle
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Page 113 and 114: s 2.10.2.2.2 LEO assembly HMM Asses
Page 117 and 118: s Basic RF link Four 70-m Ka-band s
Page 125 and 126: s 3 TRANSFER VEHICLE 3.1 Systems…
Page 127: s Operational Requirements It shall
Page 131 and 132: s Figure 3-2: Parallel configuratio
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Page 139 and 140: s Figure 3-16: Recommendations for
Page 141 and 142: s Factors to be considered Impacts
Page 149 and 150: s Figure 3-24: Baseline design back
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Page 153 and 154: s Module part 3............= 0 m 3
Page 155 and 156: s 3.3.2.1 Requirements and design d
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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 4.3 Surface habitation module Fig
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s Figure 4-11: Section through the
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s 4.3.1.5.3 Top level Figure 4-20:
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s Schedule in hours for the most ac
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s 4.3.3.6 Waste production HMM Asse
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s Figure 4-26: Total pressure vs. O
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s ECLS system mass: Figure 4-27: Ma
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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 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 4.5.2.1 Requirements and design d
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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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