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s HMM Assessment Study Report: CDF-20(A) February 2004 page 414 of 422 [RD45] Sub-microradian Pointing for Deep Space Optical Telecommunications Network. Gerry G. Ortiz, Shinhak Lee, and James W. Alexander. 19th AIAA International Communications International Systems Conference, Toulousse, France (2001) [RD46] ‘Radio frequency and modulation systems, Part.1: Earth Stations and Spacecrat’. Recommendation CCSDS 401x0b11. [RD47] ‘Deep Space Optical Communications Downlink Budget from Mars: System Parameters’. A. Biswas and S. Piazzolla. IPN Progress Report 42-154. NASA [RD48] ‘Frequency assignment guidelines for communications in the Mars region’. Space Frequency Coordination Group, recommendation 22-1R1 [RD49] ‘A Ten Meter Ground station telescope for deep-space optical communication: a preliminary design’. M. Britcliffe, D. Hoppe, W. Roberts, N. Page. JPL-NASA IPN progress report 42-147. November 2001. [RD50] ’Comparative Study of optical and radio-frequency communication systems for a deepspace mission’. H. Hemmati, K. Wilson, M.K. Sue, L.J. Harck. JPL-NASA IPN progress report 42-147. February 1997. [RD51] ‘Cavity-dumped communication laser design’. W.T. Roberts. JPL-NASA IPN progress report 42-147. February 2003 [RD52] “Downlink Budget for Mars: Modulation and Coding”. B. Moision and J. Hamkins. The Interplanetary Network Progress Report 42-154, April–June 2003, Jet Propulsion Laboratory,Pasadena,California,pp.1 –28,August 15,2003. [RD53] http://ipnpr.jpl.nasa.gov/progress report/42-154/154K.pdf [RD54] ‘Turbo codes for APD-detected PPM’. John Hamkins and Meera Srinivasa. JPL, California Institute of Technology. [RD55] http://hitf.jsc.nasa.gov/hitfpub/analysis/mars1.html [RD56] http://www.mmm.com/market/industrial/ceramics/pdfs/CeramicFabric.pdf [RD57] Future Power Systems for Space Exploration: Executive Summary Adam M Baker, February 2002, Qinetiq [RD58] Future Power Systems for Space Exploration Technical Note 2: Technology Inventory Adam M Baker, November 2001, Qinetiq, QINETIQ/KIS/SPACE/TN011164 [RD59] 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
s HMM Assessment Study Report: CDF-20(A) February 2004 page 415 of 422 [RD60] Future Power Systems for Space Exploration Technical Note: System Requirements & Constrains Adam M Baker, April 2001, Qinetiq, DERA/KIS/SPACE/TN010704 [RD61] Aurora Long Term Plan: Primes Support: Progress Review – Introduction L Bessone, 6th March 2003, ESA, Slides [RD62] Aurora Long Term Plan: Primes Support - Analysis 3: Power on the Mars surface F. Cogo, 23rd July 2003, Alenia Spazio, Slides [RD63] 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 [RD64] Technologies for Exploration: Aurora Programme Proposal: Annex D ESA, November 2001, SP-1254 [RD65] 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 Center, NASA Special Publication 6107 [RD66] Human Spaceflight: Analysis and Design, Chap 20: Designing Power Systems Edited by Larson and Pranke to be published by McGraw-Hill, May 99 [RD67] Solar Electric Power System Analyses for Mars Surface Missions Thomas W Kerslake, Lisa L. Kohout, July 1999, Glenn Research Center, NASA/TM-1999- 209288 [RD68] Regenerative Solid Oxide Fuel Cell for Mars Applications S. Fasoulas, M. Kuznecov, P. Otschik, T. Schmiel, December 2002, Institute for Aerospace Engineering, Fraunhofer Institute for Ceramic Technologies and Sintered Materials, Dresden, Germany, ILR-RSN02P05 [RD69] Regenerative Solid Oxide Fuel Cells for Mars Exploration K.R. Sridhar (University of Arizona), R. Foerstner (Universität Stuttgart), Journal of Propulsion and Power, Vol.16, No. 6, Nov-Dec 2000 [RD70] Mars In Situ Oxygen Production, 18-9065 Danny M. Deffenbaugh, Michael A. Miller, Steven T. Green, 1998, Southwest Research Institute [RD71] In Situ Production of Fuel and Oxidant for a small solid Oxide Fuel Cell on Mars, T. Pipoli (Graz University of Technology), J.O. Besenhard (Graz Unitversity of Technology), M. Schautz (ESA)
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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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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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