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s HMM Assessment Study Report: CDF-20(A) February 2004 page 224 of 422 point and the feet at the outer radius. In this way, the required ‘g’ environment is experienced at the feet with a decreasing ’g’-gradient towards the head. Table 3-50 and Figure 3-68 show the required rotation speed for a given ‘g’-load at the feet and also the resulting rotational momentum Min. Spin up Max. Spin-up Momentum g-load RPM time (sec) torque [Nm] [Nm.s] 0.38 13.03715 7.5 179.9270925 1349.45319 1 21.14905 20 109.4551074 2189.10215 2 29.90927 40 77.39644869 3095.85795 3 36.63123 60 63.19393573 3791.63614 4 42.2981 80 54.72755371 4378.2043 Momentum [Nm.s] 5000 4000 3000 2000 1000 0 Table 3-50: Required rotation speed for a given g-load Rotation Momentum 0 1 2 3 4 5 g-load Figure 3-68: Rotation momentum The rotational momentum can be compensated by a counter rotating mass of about 305 kg at a radius of 1.8 m. This results in an estimated additional mass of 500 kg including the static assembly and structure. 3.3.8.3.4.1 Budgets The mechanism budgets are shown in Table 3-51 to Table 3-53, which represent the model outputs:
s Element 1: Transfer Habitation Module MASS [kg] DIMENSIONS [m] TEMPERATURE REQs [deg C] Unit Element 1 Unit Name Quantity Mass per Maturity Level Margin Total Mass Dim1 Dim2 Dim3 Operation Operation NOP NOP quantity incl. margin Length Width Height (max) (min) (max) (min) Click on button below to insert new unit excl. margin or D or d 1 Hatch Cover-Internal 2 35.0 To be developed 20 84.0 1.5 0.007 2 Hatch Cover Locking Mechanisms- Internal 2 200.0 To be developed 20 480.0 1.6 1.5 0.05 3 Docking Mechanism- IBDM 3 334.4 To be modified 10 1103.5 1.371 0.813 0.254 50.0 -50.0 100.0 -100.0 4 Electronic Box- IBDM 24 8.8 To be modified 10 232.3 0.40 0.25 0.25 50.0 -20.0 70.0 -50.0 5 Berthing Mechanism- Active 2 311.0 To be modified 10 684.2 2.0 1.8 0.190 6 Berthing Mechanism- Passive 2 177.0 To be modified 10 389.4 2.0 1.8 0.343 7 Electronic Box- Berthing 2 8.0 To be modified 10 17.6 0.4 0.25 0.25 8 Crew Centrifuge- SRC 1 450.0 To be developed 20 540.0 4.5 2.0 9 Crew Centrifuge Counter Rotation Mass 1 500.0 To be developed 20 600.0 3.6 0.5 10 Antenna Pointing Mechanism- APM Ka-band & La 2 9.4 To be developed 20 22.4 11 Electronic Box- APM Pointing, Ka-band and Laser 2 5.0 To be modified 10 11.0 13 Berthing Mechanism- Prop. Passive 1 143.0 To be modified 10 157.3 2.8 2.6 0.3 15 Hatch Door-Egress External 3 18.0 To be developed 20 64.8 0.90 0.010 16 Hatch Door Locking Mechanisms- Egress Externa 3 120.0 To be developed 20 432.0 0.95 0.80 0.050 17 Hatch Door Radiation Protection- Egress External 3 51.0 To be developed 20 183.6 0.80 0.036 18 Crew Exercise Machine- Flywheel Exercise Device 2 55.0 To be developed 20 132.0 2.75 0.60 1.500 19 Solar Array Deployment Mechanism- SDM 4 40.3 To be modified 10 177.3 69.0 -32.0 70.0 -46.0 20 Solar Array SDM/Panel Hinges 4 5.6 To be modified 10 24.6 110.0 -69.0 21 Solar Array Yoke Panel 4 4.4 To be modified 10 19.4 1.0 2.50 22 Solar array Root Hinge 4 5.5 To be modified 10 24.2 0.5 0.30 0.150 23 Solar Array Drive/Rotation Mechanism (SEPTA 31) 4 5.0 To be modified 10 21.8 70.0 -35.0 75.0 -40.0 24 Solar Array Stowed Latch(s) 4 4.0 To be developed 20 19.2 25 Solar Array Drive Electronics 4 5.2 To be modified 10 22.7 26 Antenna Pointing Mechanism- Aero Stationary Ant 1 1.0 To be modified 10 1.1 0.15 0.15 0.075 27 Electronic Box- APM Pointing, Aero Stationary An 1 0.5 To be modified 10 0.6 - Click on button below to insert new unit 0.0 To be developed 20 0.0 - - ELEMENT 1 SUBSYSTEM TOTAL 25 4756.3 14.5 5445.1 Table 3-51: TV Mechanisms Mass and Thermal Budgets Element 1: Transfer Habitation Module PPEAK AND POWER SPECIFICATION PER MODE PPEAK AND POWER SPECIFICATION PER MODE Unit Element 1 Unit Name Quantity Ppeak OEM OEM OEM TMIM TMIM TMIM TMM TMM TMM MOAM MOAM MOAM Click on button below to insert new unit Pon Pstby Dc Pon Pstby Dc Pon Pstby Dc Pon Pstby Dc 1 Hatch Cover-Internal 2 2 Hatch Cover Locking Mechanisms- Internal 2 3 Docking Mechanism- IBDM 3 1806.0 0.0 4.106 4 Electronic Box- IBDM 24 152.0 0.0 24.541 5 Berthing Mechanism- Active 2 575.0 25.0 16.216 6 Berthing Mechanism- Passive 2 7 Electronic Box- Berthing 2 25.0 0.0 16.216 8 Crew Centrifuge- SRC 1 300.0 0.0 100.0 300.0 0.0 25.0 9 Crew Centrifuge Counter Rotation Mass 1 10 Antenna Pointing Mechanism- APM Ka-band & La 2 14.0 0.0 100.0 14.0 0.0 100.0 14.0 0.0 100.0 14.0 0.0 100.0 11 Electronic Box- APM Pointing, Ka-band and Laser 2 10.0 0.0 100.0 10.0 0.0 100.0 10.0 0.0 100.0 10.0 0.0 100.0 13 Berthing Mechanism- Prop. Passive 1 15 Hatch Door-Egress External 3 16 Hatch Door Locking Mechanisms- Egress Externa 3 17 Hatch Door Radiation Protection- Egress External 3 18 Crew Exercise Machine- Flywheel Exercise Device 2 61.0 0.0 100.0 61.0 0.0 25.0 19 Solar Array Deployment Mechanism- SDM 4 60.0 0.0 8.649 60.0 0.0 0.5556 60.0 0.0 0.5556 20 Solar Array SDM/Panel Hinges 4 21 Solar Array Yoke Panel 4 22 Solar array Root Hinge 4 23 Solar Array Drive/Rotation Mechanism (SEPTA 31) 4 20.0 4.0 100.0 20.0 4.0 100.0 24 Solar Array Stowed Latch(s) 4 25 Solar Array Drive Electronics 4 5.0 2.0 100.0 5.0 2.0 100.0 26 Antenna Pointing Mechanism- Aero Stationary Ant 1 10.0 100.0 10.0 100.0 10.0 100.0 10.0 100.0 27 Electronic Box- APM Pointing, Aero Stationary An 1 - Click on button below to insert new unit ELEMENT 1 SUBSYSTEM TOTAL 25 0.0 3038.0 31.0 94.0 0.0 480.0 6.0 34.0 0.0 Unit Table 3-52: TV Mechanisms Mission Modes Power Budget Element 1 Unit Name OMM OMM OMM TEIM TEIM TEIM TEM TEM TEM SM SM SM Click on button below to insert new unit Pon Pstby Dc Pon Pstby Dc Pon Pstby Dc Pon Pstby Dc 1 Hatch Cover-Internal 2 Hatch Cover Locking Mechanisms- Internal 3 Docking Mechanism- IBDM 1806.0 0.0 3.088 784.0 0.0 0.0 784.0 0.0 0.0231 4 Electronic Box- IBDM 152.0 0.0 18.455 5 Berthing Mechanism- Active 6 Berthing Mechanism- Passive 7 Electronic Box- Berthing 8 Crew Centrifuge- SRC 300.0 0.0 100.0 300.0 0.0 25.0 9 Crew Centrifuge Counter Rotation Mass 10 Antenna Pointing Mechanism- APM Ka-band & La 14.0 0.0 100.0 14.0 0.0 100.0 14.0 0.0 100.0 11 Electronic Box- APM Pointing, Ka-band and Laser 10.0 0.0 100.0 10.0 0.0 100.0 10.0 0.0 100.0 13 Berthing Mechanism- Prop. Passive 15 Hatch Door-Egress External 16 Hatch Door Locking Mechanisms- Egress External 17 Hatch Door Radiation Protection- Egress External 18 Crew Exercise Machine- Flywheel Exercise Device 61.0 0.0 25.00 61.0 0.0 25.00 19 Solar Array Deployment Mechanism- SDM 60.0 0.0 6.504 60.0 0.0 0.5556 20 Solar Array SDM/Panel Hinges 21 Solar Array Yoke Panel 22 Solar array Root Hinge 23 Solar Array Drive/Rotation Mechanism (SEPTA 31) 20.0 4.0 100.0 20.0 4.0 100.0 24 Solar Array Stowed Latch(s) 25 Solar Array Drive Electronics 5.0 2.0 100.0 5.0 2.0 100.0 26 Antenna Pointing Mechanism- Aero Stationary Ant 10.0 100.0 10.0 100.0 10.0 100.0 27 Electronic Box- APM Pointing, Aero Stationary Ant. ELEMENT 1 SUBSYSTEM TOTAL 2438.0 6.0 818.0 0.0 1264.0 6.0 0.0 0.0 Table 3-53: TV Mechanisms Mission Modes Power Budget HMM Assessment Study Report: CDF-20(A) February 2004 page 225 of 422
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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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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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Page 177 and 178: s flux [W/m2] 250 200 150 100 50 0
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Page 233 and 234: s The propulsion system and its cha
Page 237 and 238: s Item Nr. Mass [kg] Margin [%] Mas
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Page 249 and 250: s 4 MARS EXCURSION VEHICLE 4.1 Syst
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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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