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s Figure 3-65: Russian Docking System & International Berthing & Docking Mechanism HMM Assessment Study Report: CDF-20(A) February 2004 page 220 of 422 Russian Docking System has the following features: • Both half of the system are integrated in to the hatch doors • ‘Male’ half situated on approaching vehicle (MAV) • Receptacle situated on the TV • Internal Redundancy of systems • System level redundancy not complete-redundant receptacle can be provided, but no redundant probe can be mounted on MAV. International Berthing & Docking Mechanism (IBDM) has the following features: • Androgynous system- identical mechanism mounted to both vehicles • Full redundancy of system provided • Full Internal Mechanism redundancy • Treble redundancy for release/emergency release • Mechanism independent of hatch door • Hatch door diameter limited to ingress/egress suitability (diameter 813 mm) 3.3.8.2.4 Crew conditioning and exercise facilities The following assumptions have been applied: • A redundant crew exercise facility shall be provided including medical (cardio-vascular) monitoring • A Short Arm Centrifuge (SRC) shall be provided: • Due to the large rotational momentum, a counter rotation device shall be implemented. • The SRC shall have two astronaut positions • Urgent/Emergency stop
s HMM Assessment Study Report: CDF-20(A) February 2004 page 221 of 422 Improvements to the arrays are made as follows: • Increase of panel length to 6.33 m; Individual panel size 6.33 m x 1 m • 15 active panels per wing; wing requires 16 panels for deployment system to function correctly, panel no. 1 to be spacing panel only. • Inclusion of the retraction/re-stowage capability; function already available, but not qualified. • Inclusion of a re-latching and release capability in the stowed configuration. An analysis of the loading applied to the solar array as a result of the propulsive manoeuvres shows that the deployed wing is unable to withstand the loading (see Table 3-48) and therefore a re-stowage capability is required. Solar Array Wing Mass Deployment System (Kg) Panel/Cells (Kg) Total (Kg) 45.7 149.6 195.3 CoM position 8 m Allowable Shear 25 N (Derived from Bending allowable, not actual shear) Allowable Bending 185 Nm Mass. Vehicle (Kg) Thrust (N) Acceleration ( m / s) SA Force applied at CoG/Shear Load SA Bending Moment Margin of Safety Bending TMI. 1 st Start 1363000 5200000 3.81511372 745.0917095 5960.733676 -0.968963552 TMI. 1 st End 1084000 5200000 4.79704797 936.8634686 7494.907749 -0.975316574 TMI. 2 nd Start 1045000 5200000 4.976076555 971.8277512 7774.62201 -0.976204631 TMI. 2 nd End 766000 5200000 6.788511749 1325.796345 10606.37076 -0.982557653 TMI. 3 rd Start 728000 3900000 5.357142857 1046.25 8370 -0.977897252 TMI. 3 rd End 518000 3900000 7.528957529 1470.405405 11763.24324 -0.984273045 MOI. 1 st Start 474000 1530000 3.227848101 630.3987342 5043.189873 -0.963316868 MOI 1 st End 293000 1530000 5.221843003 1019.825939 8158.607509 -0.977324562 MOI. 2 nd Start 277000 612000 2.209386282 431.4931408 3451.945126 -0.946407028 MOI. 2 nd End 205000 612000 2.985365854 583.0419512 4664.33561 -0.960337331 TEI. Start 165000 612000 3.709090909 724.3854545 5795.083636 -0.968076388 TEI. End 82000 612000 7.463414634 1457.604878 11660.83902 -0.984134932 3.3.8.3.2 Communications system Table 3-48: Solar array wing loads A number of antenna pointing mechanisms exist. A schematic of a typical boom mounted deployment and pointing mechanism for the TV antennas. For a complete 180° hemispherical coverage, the axial and azimuth axes shall rotate through 180°. An analysis of the loading applied to the antenna boom as a result of the propulsive manoeuvres shows that the 3-metre deployed boom assemblies are highly loaded in bending (the analysis results are shown in Table 3-49). Three solutions are possible; 1 Rigidly mount the antenna and APM on a truss structure- no deployment, pre-installed during LEO assembly 2 Static or deployable boom with the deployment axis orientated along the load vector (large bending moment occurs across the hinge) 3 Deployable boom with a re-stowage and latching capability
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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 179 and 180: s Figure 3-38: Power required to ma
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 and 194: 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
Page 215 and 216: s Figure 3-63: Communications MEV/M
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Page 225 and 226: s Element 1: Transfer Habitation Mo
Page 229 and 230: s Radiation Shielding Shielding Req
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 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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