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s Configuration Length (m) Total mass (tonnes) Total length (m) Comp CoG (m) Inertia total kg*m^2/1000 MEV 10 46 10 5.0 THM 19 65 29 13.5 ERC 0 15 29 15.3 22874 TEI 15 160 44 27.2 63444 MOI 0 100 44 31.5 84414 HMM Assessment Study Report: CDF-20(A) February 2004 page 192 of 422 Table 3-35: TEI and MOI dimensions The ACS functions shall be: • Attitude control while orbiting Mars • Manoeuvres • Rate dumping after MOI motor separation: 0.5 degrees/s dumped in 30 seconds (maximum attitude error 15 degrees) Again, the last one is the most demanding The maximum torque needed in this case is: 25 000 Nm If ACS is dislocated in the three points, the torque arms shall be: b1 = 21.5 m b2 = 2.5 m b3 = 12.5 m Considering 440N thrust at b1 and b2, a torque contribution of 440*(21.5+2.5) = 10500 Nm is given by the ACS of the habitation module. The additional thrusters to be located in b3 are: Thrust needed = 25000-10500/12.5 = 1160 N So a cluster of 2 Ariane-5 SCA thrusters (2x550=1100N) might be used here. 3.3.5.3 ACS for TMI 3 rd In this configuration four control points shall be actives: P1, P2, P3 and P4, as shown in Figure 3-49. P4 P3 EV Airlock A 1 P2 Habitation Module Figure 3-49: TMI 3 rd configuration P1
s Configuration Length (m) Total mass (tonnes) Total length (m) Comp CoG (m) Inertia total kg*m^2/1000 MEV 10 46 10 5.0 THM 19 65 29 13.5 ERC 0 15 29 15.3 22874 TEI 15 160 44 27.2 63444 MOI 0 100 44 31.5 84414 TMI 3rd 15 249 59 39.4 172759 HMM Assessment Study Report: CDF-20(A) February 2004 page 193 of 422 Table 3-36: TMI 3 rd dimensions The ACS functions shall be: • Attitude control while cruising to Mars • Manoeuvres • Rate dumping after TMI 2nd stage motors separation: 0.5 degrees/s dumped in 30 seconds (maximum attitude error 15 degrees) To cope with those functions, a maximum torque of 50 300 Nm is needed. The available torque arms should be: b1 = 29.4 m, b2 = 10.4 m b3 = 4.6 m b4 = 19.6 m The contribution from the other stages ACS have already been dimensioned: Considering 440 N thrust at b1, b2, a torque contribution of 440*(29.4+10.4) = 17500 Nm is given by those ACS. Plus 1100 N by b3 = 5000 N which is the contribution of P3, a total control authority of 22500 N is provided by the already designed ACS The additional thrust needed in b4 is: Thrust needed = 50300-22500/19.6 = 1500 N 3.3.5.4 ACS for TMI 2 nd In this configuration five control points shall be actives: P1, P2, P3, P4 and P5, as shown in Figure 3-50.
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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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Page 149 and 150: s Figure 3-24: Baseline design back
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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 Baseline design HMM Asses
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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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