ESA Document - Emits - ESA

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s [RD72] Non-Nuclear Energy Storage Systems For Various Applications on Mars or other Planetary Missions Max. Schautz, 6th March 2001, ESA [RD73] Polar Platform: Solar Array: Solar Array Mass Status Report 22nd February 1999, FOKKER Space, PPF-FO-SA-TN-206, Issue 11 HMM Assessment Study Report: CDF-20(A) February 2004 page 416 of 422 [RD74] The Columbus Solar Array Mechanisms R. Zwanenburg, Fokker Space & Systems, 5th European Space Mechanisms and Tribology Symposium, ESTEC, Noordwijk, 28-30 October 1992 [RD75] The Qualification Test Programme of the Envisat Solar Array Mechanism, R. Zwanenburg, Fokker Space & Systems, 6th European Space Mechanisms and Tribology Symposium, Zurich, 4-6 October 1995 [RD76] The Corrugated thin film solar cell design R. Zwanenburg, Dutch Space, Thin Film Solar Arrays Workshop, 27-28 Feb 2003, ESA, Noordwijk [RD77] Flywheels Ready To Fly Spacedaily, 10 April 2000 [RD78] Aerospace Flywheel Development Technical Details Power & Propulsion Office, NASA Glenn Research Center, http://spacepower.grc.nasa.gov/ppo/projects/flywheel/techdet.html [RD79] IEEE Spectrum Avril 2002: Flywheel Batteries Come Around Again R. Hebner & J. Beno (University of Texas), A. Walls (Science Applications International Corp.) [RD80] IES2, Phase A0: Final Report: New Power Sytem Concept for Future High Power Satellites ETCA, 19th August 2003, IES2-ETCA-TN-0001 [RD81] Thin-Film And Crystalline Solar Cell Array System Performance Comparisons D.M. Murphy, M.I. Eskenazi, S.F. White, B.R. Spence, AEC-Able Engineering, Goleta (CA) [RD82] Fuel Cell Power System Options for Mars Rovers: Quaterly Report 04/2003 S. Fraser, Graz University, ESTEC/Contract No. 16853/02/NL/MV [RD83] The Martian Climate Database Available on the website: http://www-Mars.lmd.jussieu.fr/ [RD84] Solar cells selection for Mars G.A. Landis, Proceedings of the 2nd World Conference on Photovoltaic Energy Conversion, Vol III, pp. 3695-3698 (1998)
s [RD85] Mars Transportation Environment Definition Document M. Alexander, Marshall Space Flight Centers, Alabama, March 2001 [RD86] Young; Budynas; “Roark’s Formulas for Stress and Strain”, McGrawHill, Seventeen Edition [RD87] Fisher, Faupel; “Engineering Design 2D – A synthesis of stress analysis and materials engineering”, Wiley – Interscience, 1981 [RD88] Young; Budynas; “Roark’s Formulas for Stress and Strain”, McGrawHill, Seventen Edition [RD89] Prediction and Validation of Mars Pathfinder Hypersonic Aerodynamic Database P.A. Gnoffo, R. W. Powell, AIAA 98-2445, 1998 [RD90] AIAA 98-2850 Mars Ascent Vehicle Flight Analysis [RD91] Young; Budynas; “Roark’s Formulas for Stress and Strain”, McGrawHill, Seventen Edition [RD92] Human Spaceflight, Mission Analysis and Design HMM Assessment Study Report: CDF-20(A) February 2004 page 417 of 422 [RD93] 1999-01-2137, Habitability as a Tier One Criterion in Advanced Space Vehicle, Design: Part One—Habitability, Constance M. Adams, AIAA [RD94] “Psychology of Spaceflight”, Albert Holland, Human Spaceflight, Mission Analysis and Design p174 [RD95] AIAA-96-4467, Habitat Distinctions: Planetary versus Interplanetary Architecture, Marc M. Cohen [RD96] 981800, Space Habitat Design Integration Issues, Marc M. Cohen [RD97] FredSmith in an interview with Barbara Imhof about BIOPLEX and the isolations test of 1997, RADIO ORANGE 26.8.2003 [RD98] SAE 2001-01-2174 Martian surface Habitats: Architectural designs and concepts for planetary outposts, Imhof/Schartner [RD99] Bioplex study, “For a future life on extraterrestial planets”, Barbara Imhof (JSC-NASA, Flight Crew Support Division), 1997
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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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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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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
Page 391 and 392: s Element 3: Mars Ascent Vehicle HM
Page 393 and 394: s 4.5.7.5 Budgets Characteristic Va
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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
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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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