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s HMM Assessment Study Report: CDF-20(A) February 2004 page 90 of 422 • LEO is the preferred assembly orbit. An altitude of 400 km (similar to that of the ISS) has been selected. Figure 2-46 shows that the assembly activities potentially establish more than 50% of the total ‘life’ of (some of) the hardware for a given mission timeline. Thus the assembly sequence and the time spent assembling the composite becomes an important component of the mission timeline. Figure 2-46: Mission timeline • To estimate the composite in-orbit assembly time, the following parameters are critical: • Launcher type and frequency of launch • Element availability rate (on-ground production assumption) • EVA or Automated assembly • Cargo or ‘Manned launch’ or Resupply • Equipment Check-out Times • Launch failure assumptions The following assumptions have been made for the In-orbit assembly analysis: Cargo Launcher = Energia Launch Frequency o Min: every 3 months o Max: every month Assumptions Qualifying statement LEO Workbench/platforms present to support LEO operations & power requirements (LEO crew Habitat.) Equipment Check-out times o Habitation modules 3 months o Propulsion modules 1 month Minimise number of manned flights o Crew support using short term shuttle visits (Minimise the use of ‘flight systems’) Minimise Cryogenic Fuel Boil-off Minimal reconfiguration of vehicle in-orbit after initial capture & berthing or docking operations Time Launcher production infrastructure in place to be able to launch 1 per month Operational support o Up to eight teams working in parallel at ESOC- 1 for orbital vehicle, 1 each for launcher/mission in prep LEO workbench provides power, docking & resupply, AOCS and boost, autonomous Robotic Arm to support the composite and facilitate Capture & Berthing operations Table 2-32: Assumptions for assembly
s HMM Assessment Study Report: CDF-20(A) February 2004 page 91 of 422 The following are identified as open points whose influence is not considered within this analysis. • LEO Power Requirements • The service platforms are required to fully support the composite at all stages during the assembly operations. • TV Thermal Control in LEO • Specifically more important for the (Cryogenic-) propulsion stages. • TV susceptibility to ATOX- • Due to the LEO. Of more specific concern for the Solar Arrays. The Flight Arrays shall be launched as late as possible. • Crewed or Un-crewed LEO Operations • The baseline selected is for autonomous LEO operations in as far as possible. • Docking Constraints • Launch Failure Modes • On-orbit Cryogenic Stage Refuelling • Disposal/Handling of upper launch vehicle stages for each individual module. An Excel-based model has been developed to estimate the in-orbit assembly time based on a number of parameters. The following parameters are set per element: • Connecting two elements in orbit � 2 phases: 1) Docking I. Docking only. II. Capture & Berthing � Need robotic arm from service platform 2) Connection of cables (power, life support, etc) I. By Berthing/Docking II. External cabling � Need EVA/Robotics III. Internal cabling � Need Crew/Robotics • Assembly/Docking strategy – If EVA is required: Need either Shuttle launch each time or a manned assembly station • Boil-off Rate – The LH2 Boil-off Rate is assumed to be 70 kg per month on average • Production Assumptions – Availability rate of the elements • Operation Centre – What is the minimum time between one element is docked to the composite until the next element can be launched? • Other factors – LEOP and commissioning duration (+ GS) Within the model, the following is applicable: • Production & Testing of the elements is taken into account only as an availability rate (relative readiness).
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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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Page 45 and 46: s Mars Excursion Vehicle Transfer H
Page 47 and 48: s 2.7.5.1 Mission elements dry mass
Page 49 and 50: s 2.7.5.8 MEV release The MEV is re
Page 51 and 52: s Total mission time (days) 1200 10
Page 57 and 58: s stack 9 Propellant mass of the ne
Page 65 and 66: s The core supporting structure has
Page 67 and 68: s 2.7.7.1.3 Mars excursion module S
Page 69 and 70: s 2.7.7.1.4 Earth return capsule HM
Page 71 and 72: s Mission Phase Description Event s
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Page 75 and 76: s 2.7.10 Mission performance Table
Page 77 and 78: s Days on Martian surface 450 400 3
Page 83 and 84: s Maximum manoeuvre duration 6 mont
Page 85 and 86: s % of loss from baseline 20 18 16
Page 87 and 88: s 2.7.15 Sensitivity analysis HMM A
Page 89: s 2.7.15.4 Influence of the mass of
Page 93 and 94: s Parameters used: • No Shuttle
Page 95 and 96: s 2.8.3.3 Launch 3- Front node Figu
Page 109 and 110: s 2.10.1.4 Communications HMM Asses
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 and 128: s Operational Requirements It shall
Page 129 and 130: s Trans Mars Injection Module Mars
Page 131 and 132: s Figure 3-2: Parallel configuratio
Page 133 and 134: s Figure 3-6: Global dimensions com
Page 135 and 136: s Front Node 3.2.3.1.3 EVA systems
Page 137 and 138: s Trans Mars Injection (three stage
Page 139 and 140: 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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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 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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