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s 4.3.2 Propulsion Figure 4-21: Plan of top level 4.3.2.1 Requirements and design drivers The MEV mass prior to the landing is 42 tonne. The gravitational acceleration is assumed 3.7 m/s 2 The engines for the descent are fired from a height of 2000 m from the Martian surface. 4.3.2.2 Assumptions and trade-offs HMM Assessment Study Report: CDF-20(A) February 2004 page 268 of 422 The starting descent velocity assumed feasible from the parachute design is 107 m/s and the maximum allowed impact velocity on the Martian surface is 2 m/s. The choice of the thrust is obtained excluding the contribution of the Martian atmosphere, therefore the drag is not considered and the thrust level is slightly oversized. The descent manoeuvre can be obtained with a thrust level of 280 kN with a short firing time of around 37 seconds. Due to the exceeding thrust a new design of the engine with high ability to perform full throttle (30-40 %) is required. Only storable bi-propellant has been considered. No attitude and steering manoeuvres have been considered.
s 4.3.2.3 Baseline design HMM Assessment Study Report: CDF-20(A) February 2004 page 269 of 422 Four YUZHNOYE RD 861-G gas generator bi-propellant NTO-UDMH thrusters have been chosen as propulsion system for this module. The engine derives from a well known thruster used in Tsyklon 2 nd and 3 rd stage. Recently this engine was improved with an increase of the Isp performances, a higher restart capability and reduced mass. This engine was also studied as possible application for the VEGA. The propulsion system for Surface Habitation Module presents the following characteristics: Characteristic Value Number of thruster 4 Thrust 76.5 kN Isp 325 sec Exit diameter 808 mm Length 1600 mm Thruster mass 185 kg Propellant UDMH/NTO O/F ratio 2.4 Number of tanks 2+2 Cylindrical Tanks material Ti Max MEOP 7 bar Mass of UDMH tank 11.1 kg (each) Mass of NTO tank 16.5 kg (each) Table 4-5: Landing propulsion system summary Figure 4-22: YUZHNOYE RD 861-G
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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 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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Page 277 and 278: s ECLS system mass: Figure 4-27: Ma
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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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