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s Further significant mission analysis contributions were in the following areas: • Abort capabilities • Aerobraking • MEV entry analysis HMM Assessment Study Report: CDF-20(A) February 2004 page 32 of 422 The mission analysis discussions on these additional topics are included in the chapters for the respective subsystems. 2.4.2 Assumptions and trade-offs As a first step, an analysis of the characteristics of all mission opportunities from 2028 to 2043 was required. Section 2.4.5 shows different mission durations arising from different launch dates, “Mission 2033” with launch in 2033 and return in 2035 was chosen as baseline. Threeweek windows are assumed for launch and return. 2.4.3 Baseline design 2.4.3.1 Basic trajectory design issues Figure 2-10 shows an overview of the trajectories for transfer to (red) and from (purple) Mars at the starts of the launch and return windows, respectively. Mars arrival is during the global dust storm season, which precludes an immediate landing on the surface. The TV must wait in orbit until the global dust storms (if any) have subsided. The return is safely before the start of the next global dust storm season. Figure 2-11 shows the Earth-Sun-spacecraft geometry for the transfer to Mars. The maximum Earth range is 0.9 AU, the maximum Sun range 1.4 AU. No superior conjunctions occur.
s Figure 2-10: Trajectory Overview for Mission 2033 Figure 2-11: Geometry for Earth-Mars Transfer HMM Assessment Study Report: CDF-20(A) February 2004 page 33 of 422 Figure 2-12 shows the Earth-Sun-Mars geometry for the Mars phase. The Earth range rises to almost 2.7 AU, the Sun range to 1.65 AU, as Mars passes its aphelion in late summer 2034. There is a superior conjunction in August 2034. During this time, communications with the Earth will be impeded and no terrestrial measurements are available for orbit determination. This may impose constraints on operations and preclude critical actions during this time.
Page 1 and 2: s HMM Assessment Study Report: CDF-
Page 3 and 4: s STUDY TEAM HMM Assessment Study R
Page 5 and 6: s T A B L E O F C O N T E N T S HMM
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
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Page 27 and 28: s 2.2.4.4 Temperature and relative
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Page 47 and 48: s 2.7.5.1 Mission elements dry mass
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Page 51 and 52: s Total mission time (days) 1200 10
Page 57 and 58: s stack 9 Propellant mass of the ne
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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 HMM Assessment Study Report: CDF-
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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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