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s Ka-Band Antenna Force applied at CoG/Shear Load (N) Ka-Band Bending Moment (Nm) Laser Antenna Force applied at CoG/Shear Load (N) Laser Bending Moment (Nm) Aero-Stationary Antenna Force applied at CoG/Shear Load (N) Aero-Stationary Antenna Bending Moment (Nm) TMI. 1 st Start 165.9574468 497.8723404 127.8063096 383.4189288 7.630227439 3.81511372 TMI. 1 st End 208.6715867 626.0147601 160.701107 482.103321 9.594095941 4.79704797 TMI. 2 nd Start 216.4593301 649.3779904 166.6985646 500.0956938 9.95215311 4.976076555 TMI. 2 nd End 295.3002611 885.9007833 227.4151436 682.2454308 13.5770235 6.788511749 TMI. 3 rd Start 233.0357143 699.1071429 179.4642857 538.3928571 10.71428571 5.357142857 TMI. 3 rd End 327.5096525 982.5289575 252.2200772 756.6602317 15.05791506 7.528957529 MOI. 1 st Start 140.4113924 421.2341772 108.1329114 324.3987342 6.455696203 3.227848101 MOI 1 st End 227.1501706 681.4505119 174.9317406 524.7952218 10.44368601 5.221843003 MOI. 2 nd Start 96.10830325 288.3249097 74.01444043 222.0433213 4.418772563 2.209386282 MOI. 2 nd End 129.8634146 389.5902439 100.0097561 300.0292683 5.970731707 2.985365854 TEI. Start 161.3454545 484.0363636 124.2545455 372.7636364 7.418181818 3.709090909 TEI. End 324.6585366 973.9756098 250.0243902 750.0731707 14.92682927 7.463414634 Table 3-49: Antenna loads HMM Assessment Study Report: CDF-20(A) February 2004 page 222 of 422 The second selection is the least helpful because this will likely lead to a large and massive hinge. Additionally, the required orientation of the hinge will lead to a difficult stowed configuration. The third solution will add the requirement for a deployment hinge. As an indication of size and mass, the Envisat DRS boom antenna deployment system had a mass of 28 kg for a 26 kg payload mass. An additional 10 kg is added for the restraint and release system. It should also be noted that this system was a spring-driven hinge. The presence of an additional hinge in the support structure and also the rather long boom required to support the payload will lead to a reduction in the pointing accuracy/stability of the system. Therefore, to minimise these effects and to optimise the support structure required mass, The first solution was chosen as is the preferred mounting option. Current APM systems are able to meet the pointing requirements for the laser-bench and aerostationary antenna. However, although an APM exists that can carry the Ka-band antenna mass, the pointing accuracy will require improvement. 3.3.8.3.3 Vehicle connections The IDBM shall be implemented for the TV/ERC and TV/DM Interface. The IDBM has the following mechanical characteristics: • Interface loads (at the sealing interface)- acting simultaneously while docked (Flightlimit) o Axial load (1200 lbf) 5338 N o Shear load (1000 lbf) 4448 N o Bending moment (80000 in*lbf) 9039 Nm o Torsion moment (70000 in*lbf) 7909 N*m • Internal Pressure (16 psi) 110316.1 Pa • Life 15 years, Functional Life 20 Berthing/un-berthing or Docking/undocking cycles It is likely that the loading across the I/F induced by the DM and ERC will exceed the allowable loads above. Therefore, for all phases of the mission prior to I/F separation and additional a
s HMM Assessment Study Report: CDF-20(A) February 2004 page 223 of 422 support (truss) structure will be required. This will be released prior to vehicle separation. Each individual IBDM is supported by eight electronic boxes. For all berthing I/Fs, the common berthing mechanism shall be implemented. The following I/F are affected: • Node-to-TV volume • Cupola-to-Node • Node-to-TEI backbone Figure 3-66: Active and passive common berthing mechanisms For release of individual propulsion stages, a clamp-band with ejection springs shall be the baseline. 3.3.8.3.4 Crew conditioning and exercise facilities A Flywheel Exercise Device (FWED), shall provide the general crew exercise facility. The FWED provides a crew monitoring function and also is collapsible for storage in a suitable container. Figure 3-67: Flywheel exercise device A short arm centrifuge of diameter 4.5 m shall be implemented. The device shall have two stations allowing the astronaut to lay on a bench with the head positioned close to the rotation
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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 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 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 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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