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s Figure 2-8: Allowable career Radiation Levels based on gender and age of the crew 2.2.4.6 Effect of microgravity HMM Assessment Study Report: CDF-20(A) February 2004 page 28 of 422 Physiological systems have to adapt to the Martian gravity environment after the long exposure to microgravity, and the reconditioning time varies for the different systems. The re-adaptation of these systems is shown in Figure 2-9, in which a tentative limit has been established to determine if some light physical work (walking on the surface of Mars for example) could be performed without risk. This limit has been set after extrapolation from today’s knowledge about the return to a 1-g environment. It can be seen in the graph that, with this extrapolation, the physical limitation would be present during the first 7 days after return to the gravity environment of Mars. index of deconditioning 9 8 7 6 5 4 3 2 1 0 Reconditioning after spaceflight (6 month duration) with normal rehabilitation techniques on Earth (1g) physical condition at which light physical work could be performed without risk 1 2 3 4 5 6 7 8 9 1011121314151617181920212223242526272829303132333435 days postlanding neuro vestibular cardio fluids red blood cell mass lean body mass bone muscle Figure 2-9: Assumed reconditioning time to Martian gravity environment
s HMM Assessment Study Report: CDF-20(A) February 2004 page 29 of 422 The most critical systems are the cardiovascular system (fainting), the neuro-vestibular system (dizziness, disorientation after quick turns), and the possibility of blood anemia (weakness). The muscles would be very weak during the first 3-4 days but would rapidly adapt. Regular exercising during transit and during the first days on the surface of Mars would have to be mandatory for fast adaptation. If no continuous artificial gravity is implemented, the following exercise equipment and countermeasures have been identified as necessary on-board: • Human centrifuge as a basis combined with a vibration platform as a possible countermeasure for bone and muscle loss (about 2 h/day/crew member as reference). • Endurance exercise: treadmill and cycle ergometer • Strength training: resistive exercise • Pharmacological countermeasures: bone loss, radiation, space anaemia, fluid loss 2.2.4.7 Health The autonomous medical capabilities required on-board have been identified as the following: • Periodic evaluation of health status • Preventive care • Countermeasures (drugs for effect of the environment) • Trauma care • Analysis and Diagnostics (blood, urine, air, water, imaging systems) • Medications • Reanimation & First Aid • Anaesthesia • Surgery and Intensive Care (“home doctor surgery”) • Hyperbaric treatment • Radiation dosimetry, protection • Information technology: on-board expert system 2.2.4.8 Psychology Psychological requirements other than the ones implicitly taken into account in the volume definition have not been defined. No crew composition requirement has been considered. 2.2.5 Planetary protection requirements No specific planetary protection regulations for human missions to Mars exist at the moment but there is currently a working group addressing this issue. For the vehicles involved in the mission and for the samples collected it is assumed that the COSPAR 2002 regulations apply. As regards Humans the assumptions taken for this study were the following: • Any contamination of the habitat has to be avoided to prevent any backward contamination to Earth. Therefore, elements that have “seen” Mars should not be introduced in the surface habitation module. • Strict isolation of the crew during and upon Earth return is not foreseen, as it would not be practicable and very difficult to implement. As regards Vehicles and Samples, the following applies:
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Page 9 and 10: s L I S T O F F I G U R E S HMM Ass
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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 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 3.3.6.2 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 4.3.9.3 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 Term Value Unit Radius of equator
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s Inclination (deg) 47.5 47 46.5 46
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s 4.5.5 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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