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s Acceleration, g 100.00 10.00 Limits on Linear Acceleration for Unconditioned, Properly Restrained Crew 1.00 0.00 2.00 4.00 6.00 8.00 10.00 12.00 Time of exposure (min) Figure 2-5: Requirements for sustained g-loads -Gz +/- Gy +Gz -Gx +Gx HMM Assessment Study Report: CDF-20(A) February 2004 page 26 of 422 The requirements on the impact g-loads (dynamic) depend again on the time of exposure to the impact. Figure 2-6 represents the tolerance to short duration –Gz accelerations (worst case). 2.2.4.3 Noise Figure 2-6: Tolerance to short-duration –Gz accelerations The requirements for noise levels were established to be the following: • Maximum noise exposure for 8 hours: 84dB (NASA-STD-3000) • Maximum noise exposure for impulse sound: 140dB (NASA-STD-3000) • Maximum ambient noise level during daytime: 60dB • Maximum ambient noise level during night time: 55dB
s 2.2.4.4 Temperature and relative humidity HMM Assessment Study Report: CDF-20(A) February 2004 page 27 of 422 The temperature and relative humidity requirements were determined in compliance with Figure 2-7. As a consequence, the temperature in the habitable environment shall be between 18 and 27 °C at all times, for all the habitable volumes (THM, SHM, MAV, ERC). 2.2.4.5 Radiation Figure 2-7: Temperature and Humidity levels The requirements for radiation doses depend on various factors such as the anatomical part exposed, age and gender of the astronauts. The limits taken as a reference for the different anatomical parts are listed in Table 2-1: Anatomical NCRP Report No. 98 (Sv) 1 year Location 30 day limit limit Eye 1.00 2.00 Skin 1.50 3.00 BFO 0.25 0.50 Table 2-1: Radiation dose limits (BFO: Blood Forming Organs) Figure 2-8 shows the maximum radiation dose levels allowable depending on the crew age and gender, for the BFO. The selection of the age of the astronauts plays a very important role in the dose tolerance and, therefore, in shielding mass. According to the calculations, no extra shielding is required for the case of a 55-year-old male while 13 g/cm 2 are required for a 25-year-old woman.
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 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 Days on Martian surface 450 400 3
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s HMM Assessment Study Report: CDF-
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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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