ESA Document - Emits - ESA

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s Characteristic Value number of thrusters 4 number of tanks 2+2 Thrust 33 kN/each (restartable) Isp 330 sec exit diametre 1070 lengh 1730 mm thruster mass 120 kg propellant MMH/NTO O/F ratio 2.05 tank material Ti max MEOP 7 bar Mass of UDMH tank 17.1 kg (each) Mass of NTO tank 21.1 kg (each) 4.5.7.4 Baseline design 2nd stage Table 4-64: Propulsion system for the first stage Figure 4-121: AESTUS Engine HMM Assessment Study Report: CDF-20(A) February 2004 page 392 of 422 Four YUZHNOYE RD 869 pump-fed thruster have been chosen as propulsion system for this module. The thruster is under development for 4 th stage of the European VEGA Launcher. The propulsion system presents the following characteristics.
s 4.5.7.5 Budgets Characteristic Value Number of thruster 4 Thrust 5 kN (pump- fed) Isp 325 sec exit diameter 325 mm length 600 mm thruster mass 34 kg propellant UDMH/NTO O/F ratio 2.1 number of tanks 2+2 Tanks material Ti max MEOP 7 bar Mass of UDMH tank 5 kg (each) Mass of NTO tank 5.8 kg (each) Table 4-65: Propulsion system for the second stage Propellant mass 2986 kg Propulsion Dry mass (including margins) 267 kg HMM Assessment Study Report: CDF-20(A) February 2004 page 393 of 422 This mass includes an estimation of thrusters mass, the tanks, and a roughly estimation of feedlines, valves and regulators, propulsion thermal control, avionics, actuators and does not consider the structure of the propulsion system, power and communication. 4.5.8 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 • Safety • EVA Provisions • Hygiene • Crew Accommodations Crew accommodations have been added to the classical set of life support functions as the crew accommodation engineering domain does not posses a separate workbook in the CDF study, in which hardware specifications could be added.
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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 4.3.1.5.3 Top level Figure 4-20:
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s Schedule in hours for the most ac
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s 4.3.3.6 Waste production HMM Asse
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s Figure 4-26: Total pressure vs. O
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s ECLS system mass: Figure 4-27: Ma
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s Figure 4-28: Mars albedo (L), ars
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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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Page 345 and 346: s Figure 4-85: Communications MEV/M
Page 349 and 350: s 4.4.5.3.2 GNC equipment HMM Asses
Page 351 and 352: s 4.4.5.4 Control laws generation H
Page 355 and 356: s Finally, the Figure 4-97 shown th
Page 361 and 362: s velocity (m/sec) altitude (km) 50
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Page 373 and 374: s Inclination (deg) 47.5 47 46.5 46
Page 379 and 380: s 4.5.3 Structures HMM Assessment S
Page 383 and 384: s 4.5.5 Thermal HMM Assessment Stud
Page 385 and 386: s 4.5.5.3 Baseline thermal design H
Page 389 and 390: s Crew Ingress/Egress Hatch: HMM As
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Page 395 and 396: s PER DAY PER MISSION DRINKING WATE
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Page 403 and 404: s 6 APPENDIX A - MARTIAN SURFACE NU
Page 407 and 408: s Figure 6-1: Example of buried rea
Page 411 and 412: s 7 APPENDIX B - REFERENCES [RD1] C
Page 413 and 414: s [RD26] IES2, Phase A0: Final Repo
Page 417 and 418: s [RD85] Mars Transportation Enviro
Page 419 and 420: s 8 APPENDIX C - ACRONYMS AAA Avion
Page 421 and 422: s MLI Multi-Layer Insulation MMH Mo
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