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s • The candidate TCS architecture shall be also capable of: • performing effectively under Martian gravity HMM Assessment Study Report: CDF-20(A) February 2004 page 280 of 422 • guaranteeing adequate flexibility and reliability of the system until the end of the stay on Mars • guaranteeing the performance of the system for any spacecraft attitude during transfer and for any orientation after landing, this for all thermal loads derived from the mission requirements • optimising the heat management system in term of efficiency versus penalties to the system (mass, energy consumption) • Safety shall be guaranteed by adequate provision of thermal hardware for the whole mission (necessary autonomy of the crew) • TCS shall be fully verifiable/testable on ground 4.3.4.2 Assumptions 4.3.4.2.1 Transfer phase thermal environment The same environment as for the transfer vehicle applies for the Mars Excursion vehicle including the Habitation Module. A conservative approach is to consider envelopes through worst-case scenarios: Solar flux [W/m 2 ] Planet albedo Planet IR [W/m 2 ] Hot case (Earth LEO, WS, 1 AU) 1423 0.33 241 Hot case (Mars orbit, perihelion, 1.38 AU) 2 717 0.29 (subsolar) 470 (subsolar) to 30 Cold case (Mars orbit, aphelion, 1.66 AU) 3 493 0.29 (subsolar) 315 (subsolar) to 30 Table 4-10: Thermal cases definition Note that with respect to Mars arrival and departure dates, the vehicle passes aphelion and perihelion and that hot and cold cases around Mars depend to a certain extent on the orbit of the spacecraft (and thermal characteristics of the underneath regions). The worst cold case is sought with long eclipse duration: 500 km circular orbit and a coplanar Sun (beta 0) give a 13.6-minute eclipse out of a 40.2-minute orbit. 4.3.4.2.2 Martian thermal environment Environmental thermal loads depend on the landing site and on the relative position of Mars with regards to the Sun. A mapping of Martian thermal characteristics is shown in Figure 4-28 to show the disparity of the induced environment. A higher albedo drives a lower temperature, while a low thermal inertia accelerates the variation of temperature.
s Figure 4-28: Mars albedo (L), ars thermal inertia(R) HMM Assessment Study Report: CDF-20(A) February 2004 page 281 of 422 As a preliminary approach, no particular constraints are taken regarding the landing site and the landed time, except to avoid the dust-storm period (Ls 200 to 300). A conservative approach is therefore considered based on worst-case scenarios. The following figures indicate the seasonal variation of the thermal environment and the related constraints regarding the thermal design. Hot cases are conditioned to peak intensity (at noon time) and duration of the day. The first occurs at the perihelion (Ls = 250) and the second at the solstice (Ls = 270 for the southern latitudes, Ls = 90 for the northern latitudes). In the contrast, the worst cold cases are found either with long duration night at the solstice (Ls = 90 for the southern latitudes, Ls = 270 for the northern latitudes) or when Mars is at its aphelion (Ls = 70). martian day duration [hr] 24 21 18 15 12 9 6 3 0 0 45 90 135 180 225 270 315 360 heliocentric longitude Ls [deg.] 0N 15N 30N 45N 60N 75N 90N solar flux [W/m2] 750 700 650 600 550 500 450 400 0 45 90 135 180 225 270 315 360 heliocentric longitude Ls [deg.] Figure 4-29: Martian day duration versus latitude and Ls (L), Solar flux versus Ls (R)
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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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Page 233 and 234: s The propulsion system and its cha
Page 237 and 238: s Item Nr. Mass [kg] Margin [%] Mas
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Page 249 and 250: s 4 MARS EXCURSION VEHICLE 4.1 Syst
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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 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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