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s HMM Assessment Study Report: CDF-20(A) February 2004 page 248 of 422 pyrotechnic cord along the length of the joint which, when ignited, induces a failure along the joint. 3.4.4.4 Budgets Element 2: Trans Mars Injection 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 Berthing Mechanism-Structure. Active 1 158.9 To be developed 20 190.7 2.8 2.6 0.2 2 Berthing Mechanism-Structure. Passive 1 143.0 To be developed 20 171.6 2.8 2.6 0.3 3 Clamp-Band 1 43.8 To be developed 20 52.5 2.8 4 Ejection Mech- TMI Stage 1 57.56 To be modified 10 63.3 5 Propulsion Stack Berthing Mech 1 30.0 To be modified 10 33.0 6 Berthing Mechanism Electronics 1 8.0 To be developed 20 9.6 7 To be developed 20 0.0 - Click on button below to insert new unit To be developed 20 0.0 - ELEMENT 2 SUBSYSTEM TOTAL 6 441.2 18.0 520.7 Table 3-75: TMI mass budget Element 3: Mars Orbit Insertion Module MASS [kg] DIMENSIONS [m] Unit Element 3 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 Berthing Mechanism-Structure. Active 1 158.9 To be developed 20 190.7 2.8 2.6 0.2 2 Berthing Mechanism-Structure. Passive 1 143.0 To be developed 20 171.6 2.8 2.6 0.3 3 Clamp-Band 1 43.8 To be developed 20 52.5 2.8 4 Ejection Mech- MOI Stage 1 1 15.9 To be developed 20 19.1 5 Propulsion Stack Berthing Mech 1 30.0 To be developed 20 36.0 6 Berthing Mechanism Electronics 1 8.0 To be developed 20 9.6 7 Vertical Separation System 1 62.5 To be modified 10 68.8 - Click on button below to insert new unit To be developed 20 0.0 - ELEMENT 3 SUBSYSTEM TOTAL 7 462.0 18.6 548.2 Table 3-76: MOI mass budget Element 4: Trans Earth Injection Module MASS [kg] DIMENSIONS [m] Unit Element 4 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 Clamp-Band 1 31.3 To be developed 20 37.5 2.8 2 Ejection Mech- TEI 1 7.2 To be developed 20 8.6 3 To be developed 20 0.0 2.6 0.3 4 To be developed 20 0.0 5 To be developed 20 0.0 6 To be developed 20 0.0 - Click on button below to insert new unit To be developed 20 0.0 - ELEMENT 4 SUBSYSTEM TOTAL 2 38.4 20.0 46.1 Table 3-77: TEI mass budget
s 4 MARS EXCURSION VEHICLE 4.1 Systems…… HMM Assessment Study Report: CDF-20(A) February 2004 page 249 of 422 The Mars Excursion Module is the one that will allow the landing of a crew of three astronauts on the Martian surface. It has to provide life support systems for the crew for at least 30 days and the means to land and go back to orbit for a later rendezvous with the TV. It is composed of a Descent Module (DM), mainly the heat shield for the entry, deorbit engines and parachutes, the Surface Habitation Module (SHM) in which the astronauts will live during the stay on the surface and which provides the EVA infrastructure, and the Mars Ascent Vehicle (MAV), that will bring them back to orbit. 4.1.1 System requirements At the beginning of the study the following requirements were set: System Requirements Operational lifetime of the MEV shall be longer than 35 days MEV shall be as passive as possible during assembly and transfer to Mars Exploration and Science shall be performed on the surface 35 35.00 days The crew ascent cabin shall support the astronauts for a period of 5 days 5 5.00 days The surface habitat shall support the astronauts for a period of 30 days The MEV shall provide communication with EVA, THM , and Earth The propulsion stages of the MAV shall insert the crew cabin in a 500 x 500 orbit The MAV shall RvD with the TV No rover is required to improve the mobility of the astronauts once on the surface 30 30.00 days Mission Constraints The MEV shall fit (mass and size wise) in the fairing of the Energya-like launcher MEV maximum diameter Safety Requirements 6.00 6.00 m Rescue of the crew and/or abort of mission shall be possible during phases: TBD Single failure/fault/operator error tolerance for critical hazards. Two failure/fault/operator tolerance for catastrophic hazards. Failure detection, isolation and recovery means shall be provided (automatic and manual) MEV shall provide automatic detection means for at least the following hazards: * Fire * Depressurisation * Biohazards * Atmosphere degradation conditions * Radiation * Temperature * Food spoilage and water contamination The MEV shall provide a Caution and Warning System (C&W, this system must be able to receive system data, inform the crew of off-nominal events, and provide sufficient information to direct the crew to the correct response) Achieved? Max Min Ideal Units
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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 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 Figure 4-48: MAV Power Inputs HMM
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s 4.3.5.4.2 Power storage HMM Asses
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s Figure 4-52: Regenerative Fuel Ce
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s Figure 4-54: Solar irradiance on
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s 450.00 400.00 350.00 300.00 250.0
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s 4.3.6.1 Budgets HMM Assessment St
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s Surface Surface Container MAV Con
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s 4.3.9.3 Baseline design 4.3.9.3.1
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s Bio-Lock Masses: Core Samples No.
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s Figure 4-72: Entry Velocity (L) a
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s 2 3.9 233 923.1 347 923 12.3 352
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s Figure 4-85: Communications MEV/M
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s 4.4.5.3.2 GNC equipment HMM Asses
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s 4.4.5.4 Control laws generation H
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s Finally, the Figure 4-97 shown th
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s velocity (m/sec) altitude (km) 50
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s 4.5 Mars Ascent Vehicle 4.5.1 Tra
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s Term Value Unit Radius of equator
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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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