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s HMM Assessment Study Report: CDF-20(A) February 2004 page 318 of 422 • SHM to MAV The hatch diameter is sized to about 800 mm. The hatch will potentially require latch and seal mechanisms. Mass estimates shall be realised using a ‘simple geometry’ model. The astronaut enters the EVA suits via a hatch in the airlock wall. Once the astronaut is ready, the airlock hatch door is closed which also closes the EVA suit by closing and sealing the life support back-pack unit. Once the suit has been verified as sealed, the suit is released from its mounting on the outside of the SHM module. Exiting the suit is the reverse process. The suit is first latched to the SHM outer wall at the location of the hatch. The hatch is then opened, which opens the rear of the EVA suit allowing the astronaut to exit the suit. The mass of such a device has been estimated. No detail design has been considered. 4.3.8.3.2 Vehicle separation The separation of the MAV from the SHM prior to launch shall be realized with a pyrotechnic operated clamp-band of about 1.5 m. 4.3.8.3.3 Bio-lock quarantine facility This is a circular enclosure, integral to the SHM outer wall, which houses the individual bio-lock facilities. The enclosure will provide a sealed area allowing the application of the explosive seal to the container and providing a quarantine volume to allow for seal verification. The quarantine volumes are shown in Table 4-24: OD (mm) ID (mm) Ext. Length Int. Length Material Unit Mass (mm) (mm) (Kg) 360 (volume) 350 270 250 Ti 15.4 200 (lid) 50 Ti 7 4.3.8.3.4 Landing system lock Table 4-24: Quarantine volume This device will block the damping system of the legs due to reentry loading on the heat shield mounted to the landing system feet. No specific design has been considered. A mass estimate was used. 4.3.8.3.5 Communication antenna Current APM systems are able to meet the pointing requirements for the antenna. A suitable unit has been chosen and an estimate of the deployable boom mass has been made. 4.3.8.4 Budgets
s HMM Assessment Study Report: CDF-20(A) February 2004 page 319 of 422 Element 2: Surface Habitation Module MASS [kg] DIMENSIONS [m] Unit Element 2 Unit Name Quantity Mass per Maturity Level Margin Total Mass Dim1 Dim2 Dim3 Click on button below to insert new unit quantity incl. margin Length Width Height 1 Antenna Pointing Mechanism 2 1.0 To be modified 10 2.2 0.15 0.15 0.15 2 Deployment Boom 2 2.0 To be modified 10 4.4 3 Hatch Door- Airlock 1 28.5 To be developed 20 34.2 0.9 4 Hatch Door Locking Mechanisms- Airlock 1 120.0 To be developed 20 144.0 0.95 0.8 0.05 5 Hatch Door- EVA Suit 4 34.20 To be developed 20 164.2 6 Hatch Door Locking Mechanisms- EVA Suit 4 144.0 To be developed 20 691.2 7 Sample Bio-Lock- Quarantine Chamber 10 22.4 To be developed 20 268.8 360.0 270.0 8 Clamp-band- SHM/MAV I/F 1 15.6 To be modified 10 17.2 1.2 9 APM Electronics 1 1.0 To be modified 10 1.1 10 Landing Leg Locking System 4 5.0 To be developed 20 24.0 - Click on button below to insert new unit To be developed 20 0.0 - ELEMENT 2 SUBSYSTEM TOTAL 10 1128.0 19.8 1351.3 Table 4-25: Mass budget Note that the masses stated for the EVA and egress hatch and locking mechanisms are bestestimate figures. Element 2: Surface Habitation Module PPEAK AND POWER SPECIFICATION PER MODE Unit Element 2 Unit Name Quantity Ppeak DESM DESM DESM SDAYM SDAYM SDAYM SNGM SNGM SNGM Click on button below to insert new unit Pon Pstby Dc Pon Pstby Dc Pon Pstby Dc 1 Antenna Pointing Mechanism 2 10.0 100.0 10.0 100.0 2 Deployment Boom 2 3 Hatch Door- Airlock 1 4 Hatch Door Locking Mechanisms- Airlock 1 5 Hatch Door- EVA Suit 4 6 Hatch Door Locking Mechanisms- EVA Suit 4 7 Sample Bio-Lock- Quarantine Chamber 10 8 Clamp-band- SHM/MAV I/F 1 9 APM Electronics 1 5.0 100.0 5.0 100.0 10 Landing Leg Locking System 4 - Click on button below to insert new unit - ELEMENT 2 SUBSYSTEM TOTAL 10 0.0 0.0 0.0 15.0 0.0 15.0 0.0 4.3.8.5 Options Table 4-26: Power budget Further study of the lock and sealed I/F of the externally mounted EVA suits is required. Suitable decontamination methods need to be considered to guarantee no contamination can enter the habitable volume. 4.3.9 Sample handling 4.3.9.1 Requirements and design drivers The following requirements are imposed upon the samples and the sample handling systems 1 COSPAR Planetary Protection rules apply: • Category V applicable- In summary the following text applies: • Category V missions comprise all Earth-return missions. The concern for these missions is the protection of the terrestrial system, the Earth and the Moon. For Category V missions, in a subcategory defined as “restricted Earth return,” the highest degree of concern is expressed by the absolute prohibition of destructive impact upon return, the need for containment throughout the return phase of all returned hardware which directly contacted the target body or un-sterilzed material from the body, and the need for containment of any un-sterilised sample
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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 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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