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s Figure 3-60: Communications links after MEV landing. Normal and contingency cases Figure 3-61: Communications links before MAV take off Figure 3-62: Communications during solar superior conjunction HMM Assessment Study Report: CDF-20(A) February 2004 page 214 of 422
s Figure 3-63: Communications MEV/MAV-TV during take off – rendezvous and undocking-landing HMM Assessment Study Report: CDF-20(A) February 2004 page 215 of 422 3.3.7.5.5 TV contingency communications When laser downlink cannot be used, for example during the superior solar conjunction or during a contingency, Ka-band 3 m antenna will be used instead. Once in Martian orbit, the relay satellite could be used as well using the TV 40 cm X-band antenna, and would provide higher data rate than the 3m TV antenna with the G/S due to its 4 m antenna. The problem is that there is no continuous visibility, so it will be possible to use it during approximately 65% of the time. In case of a contingency with loss of attitude, in which it is not possible to use any HGA, a communications link has been designed by using two MGAs with an intelligent steering mechanism that will be pointing one of the antennas to the Earth. See Figure 3-59 for a summary of communications with the G/S during contingency. 3.3.7.5.6 Budgets 3.3.7.5.6.1 TV Antenna summary In total, three booms are necessary for telescope, Ka-band antenna and X-band antenna.
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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 167 and 168: s 3.3.3.1 Requirements and design d
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Page 179 and 180: s Figure 3-38: Power required to ma
Page 185 and 186: s 3.3.4.3 Assumptions and trade-off
Page 187 and 188: s 3.3.4.3.3 Power conditioning and
Page 189 and 190: s 3.3.5 AOCS HMM Assessment Study R
Page 193 and 194: s Configuration Length (m) Total ma
Page 195 and 196: s 3.3.5.5 ACS for TMI 1 st HMM Asse
Page 205 and 206: s 3.3.6.2 Baseline design HMM Asses
Page 209 and 210: s 5 Reduce 2dB pointing precision t
Page 211 and 212: s 70-m antenna 70-m antenna 3.3.7.5
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Page 225 and 226: s Element 1: Transfer Habitation Mo
Page 229 and 230: s Radiation Shielding Shielding Req
Page 233 and 234: s The propulsion system and its cha
Page 237 and 238: s Item Nr. Mass [kg] Margin [%] Mas
Page 247 and 248: s 3.4.4 Mechanisms HMM Assessment S
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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s 4.3.1.5.3 Top level Figure 4-20:
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s 4.3.2.3 Baseline design HMM Asses
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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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