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s 4.3.9.3.4 Bio-lock quarantine enclosure - SHM mounted. HMM Assessment Study Report: CDF-20(A) February 2004 page 328 of 422 The quarantine container shall be of the following size: OD (mm) ID (mm) Ext. Length (mm) Int. Length (mm) Material Unit Mass (Kg) 360 (enclosure) 350 270 250 Ti 15.4 200 (lid) 50 Ti 7.0 Table 4-34: Quarantine container characteristics Figure 4-65 shows the bio-lock principle. In summary, the sample containers are placed in the internal volume. A lid is placed on the container. An explosive charge is set off which welds the I/F between the lid and Bio-lock container wall and fractures the connection to the outer support. As stated above, this principle is based upon the Bio-Container principle developed by JPL/NASA- Ref paper 001CES-131, Dolgin, Sanok, Sevilla & Bement and is adopted for this study. Inert Gas Press. & Sensor(s) 4.3.9.4 Budgets Cat. V compliant Quarantine enclosure Explosive Sealing and Break of Contact Figure 4-65: Bio-lock principle From the above design, the following mass budget is applicable Individual canister masses: Sealed I/F Drill Head Canister 0.44 kg Drill Head Mass 0.36 kg 0.80 kg Surface (soil) Sample Mass 0.46 kg Sample Canister 0.40 kg 0.86 kg Atmospheric Sample Canister 0.40 kg
s Bio-Lock Masses: Core Samples No./Bio-Container Mass Container Mass 25.681 25.68 Core Sample Canister 0.80 10 7.975 Atmospheric Sample Canister 0.40 3 1.21 Bio-Lock Mass Surface Samples No./Bio-Container Container Mass 41.461 41.46 Atmospheric Sample Canister Mass 0.40 3 1.21 HMM Assessment Study Report: CDF-20(A) February 2004 page 329 of 422 No. of Bio- Containers 34.87 2 69.75 Surface Sample Canister Mass 0.86 10 8.61 Bio-Lock Mass Rock Samples Container Mass 36.941 36.94 No. of Bio- Containers 51.29 6 307.73 Typical Sample Mass in Bags 18.261 18.26Bio-Lock Mass MAV Transport Containers Type 1 No./Transport Container Mass Container Mass 28.811 28.81 Core Sample Bio-Container 34.87 0 Surface Sample Bio-Container 51.292 102.58 No. of Bio- Containers 55.20 2 110.41 Rock Sample Bio-Container 55.201 55.20 Trans. Cont. Mass Type 2 No./Transport Container Mass Container Mass 28.801 28.80 Core Sample Bio-Container 34.872 69.75 Surface Sample Bio-Container 51.292 102.57 No. of Transport Containers 186.59 2 373.18 Rock Sample Bio-Container 55.200 0 Trans. Cont. Mass No. of Transport Containers 201.13 1 201.13
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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 3.3.3.1 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 4.3.1.5.3 Top level Figure 4-20:
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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 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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