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s Figure 4-62: Communication frequencies using a repeater and data rates from Figure 4-61 4.3.7.4 Budgets 4.3.7.5 Options Unit Number Unit massTotal massPower of units (kg) (kg) (W) UHF omni antenna 2 1.0 2 X-band dish antenna 2 2.5 5 UHF transceiver 2 1.0 2 2.0 X-band transponder 2 4.6 9.2 20.0 TWT 2 0.8 1.6 120.0 Global RFDU unit 2 1.2 2.4 Harness 3.3 Total: 25.5 142.0 Table 4-22: SHM communications budget Unit Unit size (mm) Total massPower (kg) (W) UHF radio 304.8 x 109.2 x 88.9 mm 2 Omni antenna 304.9 mm length Total: 3.95 2 Table 4-23: Communications budget for the EVA space suit. HMM Assessment Study Report: CDF-20(A) February 2004 page 316 of 422 The TV laser link could be used by the SHM to increase the data rate. The link to the TV would be done using the Mars relay satellite. 4.3.8 Mechanisms 4.3.8.1 Requirements and design drivers The HMM science requirements do not set any specific requirements applicable to the SHM mechanisms. As a result of the SHM’s configuration, the following necessary mechanisms and their requirements can be derived:
s HMM Assessment Study Report: CDF-20(A) February 2004 page 317 of 422 • Crew Egress Hatches: • External Hatches and Locking Mechanism at the SHM Separation I/F • Vehicle Stage Separation System: • Release & Separation of MAV • Crew Egress and EVA: • Egress Hatch (MAV/TV I/F) • EVA Suit Egress system • Communication System: • Antenna Pointing and Tracking Mechanism Surface to Aerostationary satellite communication antenna: � Antenna diameter: 1 m � Antenna mass: 4 kg estimated � Coverage: 180° hemispherical. � Pointing Accuracy: 2° • Sample Handling: • Bio-lock quarantine facility/enclosure • Landing System: • Locking Latches for the Landing Leg damping system due to loads on heat shield during reentry. • The COSPAR Planetary Protection rules apply for the in- and egress of the astronauts. The habitable volume of the SHM is assumed to be an extension of the Earth environment and therefore contamination is prohibited. 4.3.8.2 Assumptions and trade-offs No system-specific assumptions or trade-off have been performed for the SHM mechanisms. As regard sample handling, the quarantine enclosure forms part of the overall sample handling methodology described in the appropriate chapter 4.3.9. The in- and egress of the astronauts presents a significant problem for the contamination of the SHM habitable volume. With adequate attention to the design of the latching a sealing mechanism associated with the restraint of the EVA suit to the SHM outer wall and the EVA suit hatch, the contamination can be minimised. However, a small surface area still remains that will see both the external Martian environment and the SHM habitable volume. Current decontamination developments are exploring chemical at the molecular level. These type of decontamination steps could be considered if the decontamination fluid is through in specific channels within the latch/seal. 4.3.8.3 Baseline design 4.3.8.3.1 Crew egress hatches Sealable hatches are required for the following I/Fs
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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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s flux [W/m2] 250 200 150 100 50 0
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s Figure 3-38: Power required to ma
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s 3.3.4.3 Assumptions and trade-off
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s 3.3.4.3.3 Power conditioning and
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s 3.3.5 AOCS HMM Assessment Study R
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s Configuration Length (m) Total ma
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s 3.3.5.5 ACS for TMI 1 st HMM Asse
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s 3.3.6.2 Baseline design HMM Asses
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s 5 Reduce 2dB pointing precision t
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s 70-m antenna 70-m antenna 3.3.7.5
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s Angular separation SEM > 10º SEM
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s Figure 3-63: Communications MEV/M
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s Element 1: Transfer Habitation Mo
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s Radiation Shielding Shielding Req
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s The propulsion system and its cha
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s Item Nr. Mass [kg] Margin [%] Mas
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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 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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