ESA Document - Emits - ESA

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s T total maximum = 1031 days in 2043 T total minimum = 956 days in 2033 Difference = 75 days Deep Space maximum = 655 days in 2041 Deep Space minimum = 413 days in 2033 Difference = 242 days Around Mars maximum = 553 days in 2033 Around Mars minimum = 342 days in 2039 Difference = 211 days Duration (days) Duration (days) 70 60 50 40 30 20 10 0 1200 1000 800 600 400 200 0 1200 1000 800 600 400 200 0 43 Mission 2028 Mission 2028 Mission 2028 49 Mission 2031 Mission 2031 Around Mars Deep Space Mission 2031 Mission 2033 Mission 2033 58 Mission 2033 Mission 2035 Mission 2035 54 Mission 2035 Mission 2037 Mission 2037 37 Mission 2037 Mars to Earth Around Mars Earth to Mars Mission 2039 Mission 2039 % Around Mars Mission 2041 Mission 2041 Mission 2043 Mission 2043 35 36 38 Mission 2039 Mission 2041 Mission 2043 HMM Assessment Study Report: CDF-20(A) February 2004 page 52 of 422 Figure 2-20: Total mission duration, trip duration and stay time around Mars and ratio The total mission duration varies only slightly during the whole cycle, but the trip durations and the stay duration around Mars do have significant variations, particulary the ratio time around Mars over trip duration. From this point of view, the 2033 opportunity offers the longest stay
s HMM Assessment Study Report: CDF-20(A) February 2004 page 53 of 422 duration around Mars, and also the highest ratio, increasing the exploration opportunities. This opportunity also minimises the time spent in deep space. The following shows an example of difference in energy requirements for the different dates: TMI+MOI+TEI max = 8593 m/s in 2037 TMI+MOI+TEI min = 7721 m/s in 2041 Difference = 872 m/s TMI max = 4005 m/s in 2037 TMI min = 3619 m/s in 2041 Difference = 386 m/s MOI max = 2613 m/s in 2031 MOI min = 2010 m/s in 2041 Difference = 603 m/s TEI max = 2595 m/s in 2035 TEI min = 1955 m/s in 2043 Difference = 640 m/s ∆V (m/s) ∆V (m/s) 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 4500 4000 3500 3000 2500 2000 1500 1000 500 0 7892 Mission 2028 Mission 2028 TMI+MOI+TEI 8299 8383 8388 8593 Mission 2031 Mission 2031 Mission 2033 Mission 2033 Mission 2035 Mission 2035 Mission 2037 Mission 2037 8014 7721 7753 Mission 2039 Mission 2039 Figure 2-21: Energy requirements The difference during the cycle is slight, around 10%. Therefore, any of the trip opportunities is representative enough for the mission case. Concerning the entry velocity at Earth arrival the differences are: V entry max = 12515 m/s in 2028 V entry min = 11472 m/s in 2037 Difference = 1043 m/s Apollo Entry Velocity = 11200 m/s Mission 2041 Mission 2041 Mission 2043 TMI MOI TEI Mission 2043
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
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: s Total mission time (days) 1200 10
Page 57 and 58: s stack 9 Propellant mass of the ne
Page 65 and 66: s The core supporting structure has
Page 67 and 68: s 2.7.7.1.3 Mars excursion module S
Page 69 and 70: s 2.7.7.1.4 Earth return capsule HM
Page 71 and 72: s Mission Phase Description Event s
Page 73 and 74: s Mission Phase Description Event s
Page 75 and 76: s 2.7.10 Mission performance Table
Page 77 and 78: s Days on Martian surface 450 400 3
Page 83 and 84: s Maximum manoeuvre duration 6 mont
Page 85 and 86: s % of loss from baseline 20 18 16
Page 87 and 88: s 2.7.15 Sensitivity analysis HMM A
Page 89 and 90: s 2.7.15.4 Influence of the mass of
Page 93 and 94: s Parameters used: • No Shuttle
Page 95 and 96: s 2.8.3.3 Launch 3- Front node Figu
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s HMM Assessment Study Report: CDF-
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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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