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s HMM Assessment Study Report: CDF-20(A) February 2004 page 410 of 422
s 7 APPENDIX B – REFERENCES [RD1] COSPAR Planetary Protection Policy (20. October 2002). HMM Assessment Study Report: CDF-20(A) February 2004 page 411 of 422 [RD2] Human Mars Mission Project, Human Surface Operations on Mars, Aurora/GK/EE/004, Issue 1, 23 February 2004. [RD3] Future Power Systems for Space Exploration: Executive Summary Adam M Baker, February 2002, Qinetiq [RD4] Future Power Systems for Space Exploration Technical Note 2: Technology Inventory Adam M Baker, November 2001, Qinetiq, QINETIQ/KIS/SPACE/TN011164 [RD5] Future Power Systems for Space Exploration Technical Note 4: Architectural Design of Mars Surface power system Adam M Baker, February 2002, Qinetiq, QINETIQ/KIS/SPACE/TN010446 [RD6] Future Power Systems for Space Exploration Technical Note: System Requirements & Constrains Adam M Baker, April 2001, Qinetiq, DERA/KIS/SPACE/TN010704 [RD7] Aurora Long Term Plan: Primes Support: Progress Review – Introduction L Bessone, 6th March 2003, <strong>ESA</strong>, Slides [RD8] Aurora Long Term Plan: Primes Support - Analysis 3: Power on the Mars surface F. Cogo, 23rd July 2003, Alenia Spazio, Slides [RD9] Aurora Long Term Plan: Primes Support: Analysis 7&8: Transfer Strategy and Transfer Stage S. Kemble, R. Foerstner, G. Limouzin, 4th September 2003, Astrium, Slides [RD10] Technologies for Exploration: Aurora Programme Proposal: Annex D <strong>ESA</strong>, November 2001, SP-1254 [RD11] Human Exploration of Mars: The Reference Mission of the NASA Mars Exploration Study Team Stephen J. Hoffman, David I. Kaplan, July 1997, Lyndon B. Johnson Space Centre, NASA Special Publication 6107 [RD12] Human Spaceflight: Analysis and Design, Chap 20: Designing Power Systems Edited by Larson and Pranke to be published by McGraw-Hill, May 99 [RD13] Solar Electric Power System Analyses for Mars Surface Missions Thomas W Kerslake, Lisa L. Kohout, July 1999, Glenn Research Center, NASA/TM-1999- 209288
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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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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 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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