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s • Time of quarantine- remainder of Mars orbit period • Sealing Verification Levels 1 & 2 (& 3) i. Inert gas pressurisation ii. Pressure and gas concentration monitoring HMM Assessment Study Report: CDF-20(A) February 2004 page 326 of 422 The conclusion that can be drawn from the above discussion is: 1 Passing the samples into the habitable volume does not create any technological difficulties (beyond those already known) or pose a significant contamination risk. 2 Further characteristics are: • Early sealing of samples in transport containers • Early verification of sample containment (before leaving Mars) • Ability to replace samples (collect more) if an individual Bio-lock containment cannot be verified at Level 1 (due to limitation of the number of bio-locks, other samples may have to be sacrificed) • Multi-level (stepwise contamination mitigation approach) sealing can be applied with individual level sealing verification • No EVA required beyond those for collecting the samples • Easy transfer of samples between vehicles • Minimal contamination risk to habitable volume The baseline method for handling the samples will therefore be to transport them inside the habitable volume by using appropriate sealed containers. 4.3.9.2.3 Sample and container volumes (estimated mass) The EVA canister volume (surface and atmospheric samples) shall be 147 cm 3 - circular container of external dimension diameter 55 x 100 mm The number of individual samples per type is assumed as follows: Surface samples- x60, Typical individual sample volume 147 cm 3 . Atmospheric samples- x24, Typical individual sample volume 147 cm 3 . Subsurface samples- x20- Typical individual sample volume 9.72 cm 3 . Rocks- two canisters of internal volume 5890.5 cm 3 Assuming a sample mass density of 3100 kg/m 3 , this surface sample volume of 20 617 cm 3 equates to a mass of 63.9 Kg (assuming 100% packing density and realising in addition that the density is only taken as an informative number on the upper bound). The total volume of atmospheric sample is 3534 cm 3 . The total volume of subsurface samples is 194 cm 3 , mass estimate 0.6 kg. All mass estimates performed below will consider simple containers. This is deemed adequate to assess the mass impact at this stage.
s 4.3.9.3 Baseline design 4.3.9.3.1 Sample containers HMM Assessment Study Report: CDF-20(A) February 2004 page 327 of 422 Surface & atmospheric sample canisters shall be of the following size: OD (mm) ID (mm) Ext. Length (mm) Int. Length (mm) Material Unit Mass (kg) 55 50 100 75 Ti 0.405 Table 4-28: Surface and atmospheric sample canister characteristics Sub- Surface (core) sample canisters shall be of the following size: OD (mm) ID (mm) Ext. Length (mm) Int. Length (mm) Material Unit Mass (kg) 40 35 120 75 Ti 0.440 35 (drill Head) 75 Ti. Carbide 0.357 4.3.9.3.2 Bio-lock containers Table 4-29: Sub-surface (core) sample canister characteristics Type 1 Container- typically for core sample containers, shall be of the following size: OD (mm) ID (mm) Ext. Length (mm) Int. Length (mm) Material Unit Mass (kg) 250 200 200 130 Ti 25.7 Table 4-30: Type 1 (surface and atmosphere) container characteristics Type 2 Container - typically for surface and atmospheric sample containers, shall be of the following size: OD (mm) ID (mm) Ext. Length (mm) Int. Length (mm) Material Unit Mass (Kg) 310 260 200 110 Ti 41.5 Table 4-31: Type 2 (surface and atmosphere) container characteristics Type 3 Container - typically rock samples, shall be of the following size: OD (mm) ID (mm) Ext. Length (mm) Int. Length (mm) Material Unit Mass (Kg) 300 250 200 120 Ti 37 Table 4-32: Type 3 (surface and atmosphere) container characteristics 4.3.9.3.3 MAV transport containers Type 1 Container - typically for Surface and Rock Bio-containers, shall be of the following size: OD (mm) ID (mm) Ext. Length (mm) Int. Length (mm) Material Unit Mass (Kg) 720 710 220 210 Ti 28.8 Table 4-33: Type 1 container (surface and rock) characteristics
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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 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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