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s HMM Assessment Study Report: CDF-20(A) February 2004 page 110 of 422 • housekeeping, commanding and software maintenance require up to two orders of magnitude more link capability • as for satellites one contact/day with feedback possibility is sufficient but also necessary • availability should exceed 99% for 8 hours/day contact • Essential link is required that guarantees communications in all conceivable contingency situations. Degradations with respect to the links above are acceptable. 2.10.1.4.5 Communications link concept (cruise and at Mars) Essential link (operating under all failure scenarios, near real time, near 24-hour/day): X-band 70 m ground stations, MGA on-board • Crew – ground communications: e-mail • Essential housekeeping data downlink • Essential commanding capability to support on-board autonomy Basic RF link (near real time, near 24-hour/day, maximum outage 24-hour TBC): Downlink Based on a scaled up Ka-band implementation (70 m ground station, 4 m on-board terminal) Uplink Based on Ka-band with major improvements in the uplink data rate (by a combination of coded uplink, ground station high power amplifier power improvements, reduced losses, and low on orbit antenna and system temperatures.) • Crew – ground communications: (basic) video, voice, internet and e-mail • Housekeeping data, basic science data and software image downlink • Commanding, master plan uplink and software update High-performance optical down link (near real time, 24-hour/day capability (12 to 18 hours/day duty cycle), best effort): • Crew – ground communications: state of the art video, voice, and e-mail • Housekeeping data, science data and software image downlink • High-performance communications are vulnerable (e.g. Ka-band and optical links). Redundancy on a lower performance level is required. Communications shall be organised hierarchically. In case of loss of the high performance link, essential data still have to reach the ground (either along another path or in the same path with increased signal to noise ratio). 2.10.1.4.6 Tracking • The infrastructure shall be able to track orbits with the following methods: • Doppler • Ranging • GPS or Galileo in Earth orbit
s HMM Assessment Study Report: CDF-20(A) February 2004 page 111 of 422 • Delta DOR • Same Beam Interferometry • Satellite to satellite Doppler and Ranging • The accuracy of the above methods shall be at least the state of the art projected for 2010 (deltaDOR: 5 nrad, Doppler and Ranging as BepiColombo Radioscience (0.6*10-15 Allan variance and 10 cm ranging ground station contribution) • Navigation on Martian surface implemented locally (i.e. not via ground) 2.10.2 Ground segment concept The HMM is unique in several aspects: • It has a number of technologically driving aspects, e.g. large elements rendezvous and docking, optical communications etc. These have to be prepared by studies and precursor missions. • Its large size requires a special build up phase to create the pool of people with the respective expertise. This expertise cannot be drawn from the limited number of people involved in conventional missions. • The staffing cannot easily be adapted to changing workloads, because there are no other missions that large to absorb such a large workforce. • Existing centre infrastructures cannot just be adapted. New centre facilities must be created. 2.10.2.1 Central versus distributed control centre concept The HMM flight operations can be subdivided into major tasks: • Launches • LEO assembly • Habitation module mission • Martian surface mission Each respective major task should be operated centrally. It is, however, conceivable, that there are different dedicated Control Centres for each major task. No clear preference is given at this stage to a central or distributed approach for the overall HMM. A control infrastructure of this size is not available and has to be built up. A central structure makes sense if it is reused for similar endeavours. On the other hand, smaller (but still large) control infrastructures for the individual major tasks may be easier to adapt if smaller missions are conducted before and thereafter. As far as the communications network is concerned there is clear preference for a centralized approach, i.e. there should be one centre in charge of network operations. Except for the launches, each major task is assumed to be organised hierarchically with a system entity on top supported by entities responsible for the subsystems. The subsystem teams and tools are shared between the major tasks as applicable.
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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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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
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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
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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 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
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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
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
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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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