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s P5 P4 P3 EV Airlock A 1 P2 Habitation Module Figure 3-50: TMI 2 nd configuration Configuration Length Total mass Total length Comp CoG Inertia total (m) (tonnes) (m) (m) kg*m^2/1000 MAV 10 46 10 5.0 HAB 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 TMI 2nd 15 332 74 48.7 370650 P1 HMM Assessment Study Report: CDF-20(A) February 2004 page 194 of 422 Table 3-37: TMI 2 nd dimensions ACS functions: • Attitude control while cruising to Mars • Manoeuvres • Rate dumping after TMI 1 st stage motors separation: 0.5 degrees/s dumped in 30 seconds (maximum attitude error 15 degrees) Maximum torque: 108 000 Nm Torque arms: b1 = 38.7 m, b2 = 19.7 m b3 = 4.7 m b4 = 10.3 m b5 = 25.3 m Considering 440 N thrust at b1 and b2, a torque contribution of 440*(38.7+19.7) = 25700 Nm is given by those ACS. Plus 1100 N by b3 = 5100 Nm for P3 Plus 1500 N by b4 = 15400 Nm for P4 A total control authority of 46 200 Nm is provided by higher stages ACS The additional thrusters to be located in P6 are: Thrust needed = 108000-46200/25.3 = 2500 N
s 3.3.5.5 ACS for TMI 1 st HMM Assessment Study Report: CDF-20(A) February 2004 page 195 of 422 In this configuration six control points shall be actives: P1, P2, P3, P4, P5 and P6, as shown in Figure 3-51. P6 P5 P4 Configuration Total mass (tonnes) P3 Figure 3-51: TMI 1 st configuration Total length (m) comp CoG (m) EV Airlock A 1 P2 Habitation Module Inertia total kg*m^2/1000 MAV 10 46 10 HAB 19 65 29 ERC 0 15 29 22874 TEI 15 160 44 63444 MOI 0 100 44 84414 TMI 3rd 15 249 59 172759 TMI 2 nd 15 332 74 370650 TMI 1 ST 15 332 89 679909 Table 3-38: TMI 1 st dimensions The ACS functions shall be: • Attitude control while cruising to Mars • Atmospheric disturbance rejection • Manoeuvres: a little re-orientation to get the optimal attitude for firing the TMI 1 st stage can be assumed. The last function is the dimensioning one. A re-orientation of 20 degrees in 4 minutes can be envisaged as dimensioning manoeuvre. This would mean a constant acceleration phase covering 10 degrees in 2 minutes and a constant deceleration phase. The acceleration needed is: 2*Dtheta/t^2 = 2*10*pi/120/120^2= 2.4e-5 rad/sec^2 The maximum torque needed is 17 000 Nm, which can be easily realized by using the higher stages ACS. As a result, in principle there would be no need for an ACS in the TMI 1 st stage. To give the control authority when the stage is not assembled on the main vehicle, most likely some ACS shall be envisaged as well. However the dimensioning is TBD. P1
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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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s Factors to be considered Impacts
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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
Page 155 and 156: s 3.3.2.1 Requirements and design d
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Page 185 and 186: s 3.3.4.3 Assumptions and trade-off
Page 187 and 188: s 3.3.4.3.3 Power conditioning and
Page 189 and 190: s 3.3.5 AOCS HMM Assessment Study R
Page 193: s Configuration Length (m) Total ma
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Page 211 and 212: s 70-m antenna 70-m antenna 3.3.7.5
Page 213 and 214: s Angular separation SEM > 10º SEM
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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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