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s Returning the samples to the SHM raises the following issues: HMM Assessment Study Report: CDF-20(A) February 2004 page 322 of 422 • For SHM in situ analysis, a Category V-compliant ‘glovebox’ is required. • Equivalent to Bio-safety Level 4+ facilities on Earth (these are not even possible on Earth). • Specialist training required for Crew? • All analysis equipment contained and remains within the glovebox. Given the sample handling constraint the samples are to remain outside the habitable volume: • The ‘glovebox’ must be integrated onto the external wall of the facility (possibly in the airlock for additional safety) with external direct access for depositing samples or alternatively a sealed unit external to SHM with real-time manipulator arm (less preferable). • glovebox provides a direct barrier to Mars. • No bio-lock, glovebox access door or additional tooling required to place samples in ‘glovebox’. This methodology will lead to a complex and fairly massive system that must allow access for the EVA astronauts to place the samples inside, but also provide a complete barrier to the habitable volume whilst allowing the astronaut inside the habitable volume to be able to see, manipulate and test the samples. 4.3.9.2.1 Modifications to sample handling constraint Modifying the constraint will allow the samples to enter the habitable volume: • Samples transferred to internal ‘glovebox’ for analysis. • Glovebox becomes an isolated workbench in the habitable volume • All samples must be contained in hermetically sealed containers for transfer to the ‘glovebox’. • ‘Bio-lock’ required at the external wall for samples. • Additional tooling required within the glovebox to break container seal • Glovebox has a bio-lock door for access- larger contamination risk. Allowing the samples into the habitable volume for in situ analysis leads to a more complex system involving the requirement to seal and than access the samples once inside the ‘glovebox’. Due to complexity of sample handling (Integration of glovebox to external wall) and the Biosafety level requirement, in situ analysis of samples will be limited to (remote/EVA) microscope and IR spectrometry analysis to aid in the selection of appropriate samples. Returning the gathered samples to Earth requires the samples to be transferred between vehicles. If the sample handling constraint is obeyed, the following schematic for the sample transfer results, shown in Figure 4-63.
s Surface Surface Container MAV Container Launch Docking 1 st On-Orbit Quarantine Bio-Lock Processin Figure 4-63: Sample transfer schematic II ERC Transport HMM Assessment Study Report: CDF-20(A) February 2004 page 323 of 422 2 nd On-Orbit Quarantine 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. I. MAV Containers • External Storage bins or containers required on the MAV. � Containers require sealable caps (Level 1 sealing)- applied during EVA activities, no sealing verfication required. � Sample retention system required during MAV launch (especially for random shape rocks etc) i.e. foam inflatable filling bags. • Sample Environmental control required for externally mounted containers. • Access to containers required (difficulty for EVA ops) � Access Ladder along SHM and MAV required. � Access through potential MAV fairing required. • Storage Bins or Containers must be considered as contaminated (they are on the external surface of the module). II. 1st on-orbit quarantine period to verify Level 1 sealing (sample containers are however contaminated). • Sample containers detached from MAV and passed to External Bio-lock facility � Astronaut EVA Due to the external surface of the MAV being contaminated, EVA suit becomes contaminated and is therefore not allowed back in the habitable volume • Remote manipulator required- Mass penalty � Complex arm required for simple task- container transfer. � Arm becomes contaminated due to container handling and must therefore be jettisoned prior to return. • MAV Container Env. Control system no longer functional- No Power III. External ‘Bio-lock’ container sealing facility • Bio-Container principle has been developed mby JPL/NASA- Ref paper 001CES- 131, Dolgin, Sanok, Sevilla & Bement • ‘Biolock’ container sealing as per MSR study- Explosive weld sealing. � Environmental Containment Verification Level 2 � Container environmental control-Power. � Sealing Verifcation. • Inert gas pressurisation • Pressure and gas concentration monitoring
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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 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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