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s 2.10 Ground segment and operations 2.10.1 Mission operations concept The ground operations shall be able to support the following operational tasks: • In-orbit assembly • Operation of Life Support System • Operation of subsystems • Support crew work • Support crew daily life • Interplanetary transfer • Mars orbit insertion • Landing on Mars • Ascent from Martian surface • Rendezvous and docking in Mars orbit • Insertion into Earth trajectory from Mars • Earth reentry 2.10.1.1 On-board autonomy The following autonomy concept is assumed: HMM Assessment Study Report: CDF-20(A) February 2004 page 106 of 422 • On-board autonomy (cruise and at Mars) • Short term for all situations • Medium term for nominal operations/situations by: - Crew to handle higher level decisions - On-board hierarchical operations concept with automatisms on lowest level • Earth Orbit Assembly Phase under real-time ground control. • Critical Phases Operations (cruise and at Mars) • Real time and lower level decisions by automatisms • Crew autonomy for decisions that do not allow for ground feedback • Ground control responsibility for high-level decisions as far as commensurable with ground feedback time • Mission Planning (long term) on ground • Monitoring on ground • Permanent Presence of basic ground control • Think Tank on ground on call to solve problem situations The above autonomy concept is based on the following rationale: On-board autonomy implications
s HMM Assessment Study Report: CDF-20(A) February 2004 page 107 of 422 Long feedback loops make ground real time control impossible. System is very complex, complete automation would be too risky and costly. High effort to make system operable for onboard crew Earth orbit assembly phase Near real-time ground control is feasible. Crew presence and involvement to be minimised. Assembly contains complex one of a kind steps. Higher level on-board autonomy is unfeasible and unnecessary. Critical phases operationsNominal operations to be preplanned because they contain highly complex operations steps. Failure scenarios to be worked out with on-board automatic, crew and on-ground decision distribution as appropriate considering the feedback loop times. Mission planning (long term) on ground Natural task for the ground is to set the long-term aims taking into account complex mission parameters. Uplink of medium-term master time line. Monitoring on ground Highly complex (prototype) system requires detailed monitoring. Think tank on ground to solve problem situations Full understanding of the system is feasible only through on-ground sources. Permanent presence of ground control • Time for build up of critical situations shall be minimised • Within reason smaller degradations shall be analysed to keep crew comfort at a high level, crew may also delegate lower level tasks to ground • Crew has to be given the feeling of being taken care of by ground Permanent Presence shall be provided on a best effort basis. Compared to the other items above it has a lower priority. On-board survivability autonomy for credible failures without ground support, at least: 1 week. Time is driven by unavoidable gaps in communications, activation times of full expert ground support, and time to draw up recovery procedures. (In contrast to unmanned satellites a safe mode with a deactivated satellite that buys time to solve the problem is not feasible for Human Mission to Mars. A basic functionality has to be always guaranteed.) • On-board degradations management autonomy for 1 week supported by: • Automatic redundancy management on lowest level • Design for graceful degradations • Crew interaction possibility on higher level to restore • Ground control first-level support to crew available round the clock • Ground control second-level support available on call 2.10.1.2 On-board operations The following factors have been considered: • Low-risk safe mode concept • Graceful degradation of subsystems/components
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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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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
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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
Page 87 and 88: s 2.7.15 Sensitivity analysis HMM A
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Page 93 and 94: s Parameters used: • No Shuttle
Page 95 and 96: s 2.8.3.3 Launch 3- Front node Figu
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Page 109 and 110: s 2.10.1.4 Communications HMM Asses
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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
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Page 135 and 136: s Front Node 3.2.3.1.3 EVA systems
Page 137 and 138: s Trans Mars Injection (three stage
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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
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s 3.3.3.1 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 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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