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s IV. Bio-Lock Sample containers placed in ERC Containers • Externally mounted transport containers � Transfer performed by Astronaut EVA � Explosive weld sealing. • Environmental Containment Verification Level 3 � Sealing Verification • Inert gas pressurisation • Pressure and gas concentration monitoring HMM Assessment Study Report: CDF-20(A) February 2004 page 324 of 422 V. Environmental Containment Verification Level 3 • Quarantine period during Mars orbit to verify Level 2 & 3 sealing (prior to EOI). • Both powered and monitored through ERC I/F 4.3.9.2.2 Conclusions • Maintaining the samples outside the habitable volume leads to a complex sample transfer system having the following non-preferable characteristics: � External Ladder access to MAV required through the potential fairing. � Contaminated Sample containers transported to the orbiting TV. � TV mounted external ‘Bio-lock’ facility required- extra mass � Remote manipulator required to transfer sample containers from the MAV to the ‘Bio-lock’ facility. 1 Large disadvantage due to required complexity for such a ‘simple’ ge associated mass. � EVA required to transfer and install Bio-containers on the ERC. � (Small) risk of contamination being transferred to external surface of ERC. � Sample containment verification done in Mars Orbit 1 Any non-conformance means loss of samples with no possibility of replacement. Performing a similar analysis with a modified sample handling constraint to allow the samples to be transported internally in the MAV leads to the following. Figure 4-64 shows a schematic for the sample transfer: Surface Surface Container Bio-Lock Processing 1 st On-Mars Quarantine MAV Container Launch 2 nd On-Mars Quarantine Docking ERC Transport On-Orbit Quarantine Figure 4-64: Sample transfer schematic II The first two steps are performed by the EVA astronaut on the surface and are described briefly in the above text. The sequence will then continue as above. The steps and the consequences are briefly outlined below.
s HMM Assessment Study Report: CDF-20(A) February 2004 page 325 of 422 I. ‘Bio-lock’ container sealing facility mounted to external wall of SHM: Bio-Container principle has been developed by JPL/NASA- Ref paper 001CES- 131, Dolgin, Sanok, Sevilla & Bement • ‘Bio-lock’ provides sample handling link through SHM wall • Samples placed into container by EVA Astronaut • ‘Biolock’ container sealing as per MSR study- 1st Level. • Double walled containment vessel • Explosive welding & I/F fracture i. Environmental Containment Verification Level 1 II. 1st Quarantine period on Mars to verify seal before transfer to MAV: • Container environmental control-Power connection provided by SHM • Minimum available quarantine time is the 7 day launch preparation • Sealing Verification- Level 1. i. Inert gas pressurisation ii. Pressure and gas concentration monitoring III. Bio-Containers transferred from the quarantine enclosure to transport containers in the MAV: • Manually transferred by astronaut internally from SHM to MAV • MAV Transport Containers Sealed • Explosive welding i. Environmental Containment Verification Level 2 • Container environmental control-Power connection provided by MAV- 1st & 2nd Levels IV. 2nd quarantine period, on Mars to verify seal before MAV launch: • Container environmental control-Power connection provided by MAV • Time of quarantine is dependent upon when the last samples are transferred from SHM to MAV, suggest minimum of a couple of days • Sealing Verification Levels 1 & 2 i. Inert gas pressurisation ii. Pressure and gas concentration monitoring. V. MAV Transport Containers transferred from the MAV to the ERC: • Manually transferred by Astronaut internally from the MAV to the ERC. • ERC Transport Containers Sealed- 3rd Level • Clamping seal i. Environmental Containment Verification Level 3 ii. (Explosive welding possible if required for risk mitigation/safety) VI. 3rd quarantine period to verify seals before return: • Container environmental control-Power connection provided by ERC- 1st & 2 nd Levels:
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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 4.5.3 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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