ESA Document - Emits - ESA

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s EOL End Of Life ERA European Robotic Arm ERC Earth Return Capsule <strong>ESA</strong> European Space Agency ETO Earth Transfer Orbit EVA Extra Vehicular Activity FER Frame Error Rate FOV Field Of View FPA Flight Path Angle GCR Galactic Cosmic Rays GEO Geostationary Earth Orbit GNC Guidance, Nivigation and Control GPS Global Positioning System HAB Habitation Module HEO High Eliptic Orbit HGA High Gain Antenna HMM Human Mission to Mars IBD Inflatable Breaking Device IEEE Institute of Electrical and Electronic Engineers IMU Inertial Measurement Unit IMV Inter Moule Ventilation IPN InterPlanetary Internet ISO International Organisation for Standardisation ISS International Space Station ITU International Telecommunications Union JPL Jet Propulsion Laboratory JSC Johnson Space Centre LAN Local Area Network LAT Latitude LEO Low Earth Orbit LGA Low Gain Antenna LMO Low Mars Orbit LMR Liquid Metal cooled Reactor LOX Liquid Oxygen LSS Life Support System MAV Mars Ascent Vehicle MCC Mission Control Center MCFC Molten Carbonate Fuel Cell MDM Mars Descent Module MEO Medium Earth Orbit MER Mars Eploration Rover MEV Mars Excursion Vehicle MEX Mars Express MGA Medium Gain Antenna MGS Mars Global Surveyvor MHD Magnetohydrodynamic MIL Military MIR Soviet Unions Space Station HMM Assessment Study Report: CDF-20(A) February 2004 page 420 of 422
s MLI Multi-Layer Insulation MMH Mono-Methyl Hydrazine MOD Meteorite and Orbital Debris shield MOI Mars Orbit Insertion MSR Mars Sample Return NCG Non-Condensable Gas NEP Nuclear Electric Propulsion NTO Nitrogen TetrOxide NTP Nuclear Thermal Propulsion OBC On-Board Computer OCC Operations Control Center ODP Ozone Depletion Fluid ODS Orbital Disconnect Struts OEM Orbiting Around Earth Mode OSR Optical Solar Reflector PAFC Phosphoric Acid Fuel Cell PCA Pressure Control Assembly PCI Peripheral Component Interconnect PCU Power Control Unit PDU Power Distribution Unit PEM Proton Exchange Membrane PEMFC Proton Exchange Membrane Fuel Cell PFE Portable Fire Extinguisher PFM Proto-Flight Model PLL Phase Locked Loop PMS Polymathyl Siloxane PVR Photovoltaic Radiator RAM Random Access Memory RCS Reaction Control System RSA Russian Space Agency RTU Radio Thermal Unit RVD RendezVous and Docking RWA Reaction Wheel Assembly RWL Reaction Wheels SEE Single Event Effects SEM Sun Earth Mars SEP Solar Electric Propulsion SEU Single Event Upset SHM Surface Habitation Module SOFC Solid Oxide Fuel Cell SPE Single Particle Event SRC Short Arm Centrifuge SRM Solid Rocket Motor SSM SuperAmine SSO Sun Synchronous Orbit STD Standard STM Structural Thermal Model STR Star Tracker HMM Assessment Study Report: CDF-20(A) February 2004 page 421 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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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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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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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
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Page 401 and 402: s 5 OVERALL CONCLUSIONS HMM Assessm
Page 403 and 404: s 6 APPENDIX A - MARTIAN SURFACE NU
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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: s 8 APPENDIX C - ACRONYMS AAA Avion
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