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s 4.3.2.4 Budgets The propellant mass is 3227 kg and the propulsion dry mass (including margins) is 1338 kg. HMM Assessment Study Report: CDF-20(A) February 2004 page 270 of 422 This mass includes an estimation of thrusters mass, the tanks, and a rough estimation of feedlines, valves and regulators, propulsion thermal control, avionics, actuators. It does not consider the structure of the propulsion system, power and communication. 4.3.2.5 Options A possible option is to use a single engine of 240 kN. This has been preliminary discarded due to poor performances in thrust level and configuration issues due to the envelope. The engine selected was the Russian RD 0235 used in the Rockot second stage. 4.3.3 Environmental control and life support system The life support comprises the following subsystems: • Atmosphere Supply and Control • Atmosphere Revitalization • Temperature and Humidity Control • Water management • Waste management • Food management • EVA provisions • Hygiene • Crew accommodation • Medical equipment Crew accommodations have been added to the classical set of life support functions as the crew accommodation engineering domain does not have a separate workbook in the CDF study, in which hardware specifications could be added. 4.3.3.1 Requirements and design drivers The MEV complex consists of two main modules: the Surface Habitation Module (SHM) and the Mars Ascent Vehicle (MAV). The study required both modules to be equipped with life support systems, which are not interconnected. Therefore, two life support systems are presented here. The SHM life support system is designed to provide life support to a crew of three for 37 days. 4.3.3.2 Assumptions and trade-offs 4.3.3.2.1 Metabolic requirements of the crew The metabolic needs of the crew have been calculated using the correlations given in <strong>ESA</strong> standard PSS-03-406 and crosschecked with relevant sources. The entire calculations have been based on the energy expenditure of the crew. The schedule for crew activity is shown in Figure 4-23.
s Schedule in hours for the most active day Activity Astronaut 1 2 3 Sleep 8.00 8.00 8.00 Pre- and post sleep 1.50 1.50 1.50 Leisure activities 2.00 2.00 2.00 Personal hygiene 1.00 1.00 1.00 Eating 1.50 1.50 1.50 Exercise 0.00 0.00 0.00 Station keeping 1.88 1.88 1.88 Laboratory activities 7.10 7.10 7.10 Metabolic Cost of EVA EVA mission tasks 0.70 0.70 0.70 EMU donning/doffing 0.15 0.15 0.15 Egress/ingress 0.06 0.06 0.06 Pre-EVA setup & post EVA EMU care 0.12 0.12 0.12 TOTAL TIME (24hrs) 24 24 24 Figure 4-23: Crew activity schedule during Martian surface stay HMM Assessment Study Report: CDF-20(A) February 2004 page 271 of 422 Note that for the energy requirements computation that a 24-hour day has been used instead of a Martian day of 24 hours and 40 min. The error introduced is less than 3% and is covered by the contingencies. Based on the energy expenditure, the metabolic needs and products by the crew have been estimated and are shown in Figure 4-24: Per day Per mission Energy consumption (W*h) 2868.9 106147 Energy consumption (J) 10327860.0 382130820 Oxygen consumption (m3) 0.5 19 Oxygen consumption (kg) 0.7 27 Drinking water (m3) 0.0 0 Drinking water (kg) 8.5 315 Dry food (kg) 2.0 75 Carbon dioxide production (m3) 0.4 15 Metabolic water production (kg) 0.3 11 Urine production (kg) 4.3 158 Faecal liquids(kg) 0.2 9 Insensible water (kg) 4.3 158 Total solid waste production Faeces (kg) 0.2 8 HYGIENE WATER (kg) 3 111 GREY WATER (KG) 7 269 ADDITONAL SOLID INORGANIC TRASH 0 11 Figure 4-24: Metabolic needs and products of the crew
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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 225 and 226: s Element 1: Transfer Habitation Mo
Page 229 and 230: s Radiation Shielding Shielding Req
Page 233 and 234: s The propulsion system and its cha
Page 237 and 238: s Item Nr. Mass [kg] Margin [%] Mas
Page 247 and 248: s 3.4.4 Mechanisms HMM Assessment S
Page 249 and 250: s 4 MARS EXCURSION VEHICLE 4.1 Syst
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Page 275 and 276: s Figure 4-26: Total pressure vs. O
Page 277 and 278: s ECLS system mass: Figure 4-27: Ma
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Page 289 and 290: s Insulation structure (external) F
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Page 299 and 300: s Figure 4-48: MAV Power Inputs HMM
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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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