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s FRONT COVER (The front cover shows schematic of the complete vehicle for a human mission to Mars) PROJECT Assessment Study Report: CDF-20(A) February 2004 page 2 of 422
s STUDY TEAM HMM Assessment Study Report: CDF-20(A) February 2004 page 3 of 422 This Assessment Study was performed in the ESTEC Concurrent Design Facility (CDF) by the following interdisciplinary team: TEAM LEADER A. Santovincenzo, TOS-ACD SYSTEMS D. Escorial, TOS-ACD AEROTHERMO- DYNAMICS S. Durrant, TOS-MMM S. Bayon, TOS-ACD M. A. Larsen, TOS-ACD F. Mazoue, TOS-MPA J. Kirchner, MSM-MX MISSION ANALYSIS M. Khan, TOS-GA M. Landgraf, TOS-GA POWER S. Zimmermann, TOS- EPS COMMUNICATIONS J. V. Perello, TOS-ET PROGRAMMATICS M. Braghin, TOS-MTC CONFIGURATION R. Westenberg, TOS-MCS B. Imhof (Liquifer) PROPULSION N. Kutufa, TOS-MPE COST P. Ponzio, IMT-ICE RADIATION H. Evans, TOS_EMA DATA HANDLING G. Furano, TOS-ESD RISK/SAFETY P. Villar, TOS-QQD GNC G. Ortega, TOS-ESN M. Sallusti, TOS-ECN SIMULATION L. Dwedari, TOS-EMM GROUND SEGMENT R. Timm, TOS-OS STRUCTURES C. Cabaco, TOS-MCS LIFE SUPPORT A. Rodriguez, TOS-MCT THERMAL D. Schwaller, TOS-MCT HUMAN FACTORS B. Houdou, MSM-MC TRAJECTORIES A. Martinez, TOS-EMZ MECHANISMS S. Durrant, TOS-MMM Under the responsibility of: L. Bessone, <strong>ESA</strong>/EAC/MSM-AT, Study Manager D. Vennemann, <strong>ESA</strong>/ESTEC/MSM-MF, Study Manager Additional contribution by: B. Parkinson, L. Summerer, A. Cawthorne, K. Legner, R. Condessa, G. Kminek, M. Vasile, U. Thomas, P. Rodriguez Contribution to the editing and compilation of this report has been provided by: J. Taylor, TOS-ACD M. Kruk-Strzelecki, TOS-ACD
Page 1: s HMM Assessment Study Report: CDF-
Page 5 and 6: s T A B L E O F C O N T E N T S HMM
Page 7 and 8: s HMM Assessment Study Report: CDF-
Page 9 and 10: s L I S T O F F I G U R E S HMM Ass
Page 15 and 16: s L I S T O F T A B L E S HMM Asses
Page 19 and 20: s 1 INTRODUCTION 1.1 Background HMM
Page 21 and 22: s 2 GENERAL ARCHITECTURE 2.1 Study
Page 25 and 26: s 2.2.4.2 Accelerations HMM Assessm
Page 27 and 28: s 2.2.4.4 Temperature and relative
Page 33 and 34: s Figure 2-10: Trajectory Overview
Page 35 and 36: s 2.4.3.5 TEI and planetary protect
Page 45 and 46: s Mars Excursion Vehicle Transfer H
Page 47 and 48: s 2.7.5.1 Mission elements dry mass
Page 49 and 50: s 2.7.5.8 MEV release The MEV is re
Page 51 and 52: s Total mission time (days) 1200 10
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s HMM Assessment Study Report: CDF-
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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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s Inclination (deg) 47.5 47 46.5 46
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s 4.5.3 Structures HMM Assessment S
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s 4.5.5 Thermal HMM Assessment Stud
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s 4.5.5.3 Baseline thermal design H
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s Crew Ingress/Egress Hatch: HMM As
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s Element 3: Mars Ascent Vehicle HM
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s 4.5.7.5 Budgets Characteristic Va
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s PER DAY PER MISSION DRINKING WATE
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s 5 OVERALL CONCLUSIONS HMM Assessm
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s 6 APPENDIX A - MARTIAN SURFACE NU
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s Figure 6-1: Example of buried rea
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s 7 APPENDIX B - REFERENCES [RD1] C
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s [RD26] IES2, Phase A0: Final Repo
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s [RD85] Mars Transportation Enviro
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s 8 APPENDIX C - ACRONYMS AAA Avion
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s MLI Multi-Layer Insulation MMH Mo
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