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s 3.4.1.1.4 Budgets Element Mass Propellant mass (per stack) 70786 kg Propulsion dry mass (including margins) 9214 kg This mass includes the following estimation Structure 3561 kg Engines, tanks, actuators feed lines, valves and regulators 4777 kg Thermal control 843 kg Mechanisms 33 kg Table 3-58: TMI stack mass budget 3.4.1.2 Mars Orbit Injection (MOI) and Trans Earth Injection (TEI) modules HMM Assessment Study Report: CDF-20(A) February 2004 page 232 of 422 3.4.1.2.1 Requirements and design drivers The Mars orbit Injection (MOI) module is the propulsion module, that performs the injection into Mars orbit. The Trans Earth Injection (TEI) module is the propulsion module that brings the Habitation Module from Mars orbit to the Low Earth Orbit. The MOI is composed of four stacks fuelled by storable UDMH-NTO propellant. Two 80 tonne stacks for the first stage and two 50-tonne stacks for the second stage. The TEI is composed by the same propulsion system of the MOI first stage and uses the same engine components and storable propellant. The TEI module is composed only by one stack. As for the TMI module the stacks are injected in LEO and assembled in orbit. Due to launchers constraints each stack weighs a max 80 tonnes and, is enveloped in a cylinder of 6 metres diameter and a length of 35 m. The thrust level is dictated to minimise the gravitational losses. The MOI burn is divided into 2 burns and staged in two assemblies. Each stage is composed of two stacks. 3.4.1.2.2 Assumptions and trade-offs The MOI uses only storable NTO/UDMH liquid propellants. Semi-storable (LOX-Kerosene) engines were also considered in the analysis to increase the specific impulse and reduce propellant mass. The use of cryogenic (LOX-LH2) or partially cryo (LOX-Kerosene) propellant has been analysed and at the time of writing an assessment for LOX- Kerosene (or derivatives) is under evaluation. Baseline design A Russian RD 0212 engine has been selected as propulsion system for the MOI and TEI stack. The thruster has been developed for the third stage of K/M Proton launcher.
s The propulsion system and its characteristics are shown in Table 3-59: Characteristic Value number of thruster 1 for each stack Thrust 612 kN Isp 325 s Exit diameter 4150 mm Length 4000 mm Thruster mass 600 kg Propellant NTO/UDMH O/F ratio 2.4 Number of tanks 1+1 Bulkhead for each stack Tanks material Ti Max MEOP UDMH 5.5 bar Max MEOP NTO 6.5 bar Mass of UDMH tank 260 kg Mass of NTO tank 310 kg Table 3-59: MOI and TEI summary Figure 3-73: RD 0212 HMM Assessment Study Report: CDF-20(A) February 2004 page 233 of 422
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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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Page 213 and 214: s Angular separation SEM > 10º SEM
Page 215 and 216: s Figure 3-63: Communications MEV/M
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Page 249 and 250: s 4 MARS EXCURSION VEHICLE 4.1 Syst
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s sun flux (W/m2) 450 400 350 300 2
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s Insulation structure (external) F
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s cryocooler heat lift [W] cryocool
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s • a duty cycle value (duration
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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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