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s 7. Capture into Mars orbit 8. Final orbit acquisition 14. Trans Earth injection 13. Rendezvous and docking 12. Ascent 10. Undocking, entry, descent and landing 9. Orbital operations 6. Earth- - Mars cruise 11. Surface operations 15. Mars-Earth cruise 4. Crew training 5. Trans Mars injection 3. Crew transfer 16. Earth orbit acquisition 17. Undocking, entry descent and landing Figure 2-37: Mission phases The mass evolution of the composite is shown in Table 2-25: Phases Initial Mass (tonnes) Final Mass (tonnes) 2. Check out HMM Assessment Study Report: CDF-20(A) February 2004 page 74 of 422 1. Launch and LEO operations Comments 1. Launch and LEO operations 0 1355 All the modules are launched and assembled in LEO 2. Check-out 1355 1355 All the systems are checked before departure 3. Crew transfer 1355 1355 4. Crew training phase 1355 1355 5. Trans-Mars Injection 1355 485 Three stages, discarded after its use, T/m from 3.8 to 9.8 Cruise correction manoeuvres 6. Earth-Mars cruise 485 470 performed, waste discarded before MOI manoeuvre 7. Capture into Martian orbit 470 310 Stacks discarded after their use, thrust over mass from 2.6 to 3.8 8. Final orbit acquisition 310 204 Stage discarded after its use, thrust over mass from 4 to 5.6 9. Orbital operations 204 157 MEV discarded, waste discarded prior to TEI 10. Undocking, entry descent and landing 204 157 MEV detached from TV 11. Surface operations 45 23 Exploration, SHM discarded prior to ascent 12. Ascent 23 6 Propellant burnt, first stage discarded 13. Rendezvous and docking 6 157 157 MAV capsule discarded after its use 14. Trans-Earth Injection 157 74 Stage discarded after its use, thrust over mass from 4 to 7.7 15. Mars-Earth cruise 74 72 Cruise correction performed manoeuvres 16. Earth orbit acquisition 72 11.2 TV discarded 17. Undocking, descent and landing 11.2 11.2 Table 2-25: Mass evolution
s 2.7.10 Mission performance Table 2-26 shows a summary of the mission case: Characteristics Value Crew Total number of crew six Number of crew landed three Masses THM mass (tonnes) 66.7 (wet) 56.5 (dry) MEV mass (tonnes) 46.5 ERC mass (tonnes) 11.2 Consumables (tonnes) 10.2 Propellant (tonnes) 1083 Propulsion systems (tonnes) 130 Supporting structures (tonnes) 19.7 Total mass at Earth departure (tonnes) 1357 Sampled collected (kg) Trajectories 65 Earth departure 8 April 2033 Mars arrival 11 November 2033 Mars departure 28 April 2035 Earth arrival 27 November 2035 Duration of stay on the surface (days) 30 TMI ∆V (m/s) 3639 MOI ∆V (m/s) 2484 TEI (m/s) 2245 Earth atmospheric entry velocity (m/s) Launches 11505 Total number of launches 28 Total mass launched (tonnes) 1541 Assembly time (years) 4.6 Table 2-26: Mission case summary HMM Assessment Study Report: CDF-20(A) February 2004 page 75 of 422 The total mission duration since the launch of the first element is 7.2 years, of which only 2.6 correspond to the trip to Mars and back. From the 1541 tonnes that will be launched, only 1355 will depart to Mars, the rest being supporting structures, workbenches and tools for the assembly, and propellant boiled off. 89% of the mission mass corresponds to propulsion systems. 2.7.11 Surface opportunities The mission architecture takes into account the periods of time during which it is possible to carry out an excursion to the Martian surface. A surface opportunity is considered to be any period of 40 days that does not coincide with:
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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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Page 25 and 26: s 2.2.4.2 Accelerations HMM Assessm
Page 27 and 28: s 2.2.4.4 Temperature and relative
Page 33 and 34: s Figure 2-10: Trajectory Overview
Page 35 and 36: s 2.4.3.5 TEI and planetary protect
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 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
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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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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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