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International Space Station: Transitional Platform for Moon and Mars Mike Greenisen (NASA Johnson Space Center) 23 September 2004 Northern Illinois University.

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Presentation on theme: "International Space Station: Transitional Platform for Moon and Mars Mike Greenisen (NASA Johnson Space Center) 23 September 2004 Northern Illinois University."— Presentation transcript:

1 International Space Station: Transitional Platform for Moon and Mars Mike Greenisen (NASA Johnson Space Center) 23 September 2004 Northern Illinois University

2 2 NASA’s Human Life Sciences Critical Path Roadmap

3 3 Critical Path Objectives Identify and assess risks for human space exploration Prioritize research and technology and communicate those priorities Guide solicitation, selection, and development of NASA research (ground and flight) and allocation of resources Assess progress toward reduction and management of risks Define operating bands (acceptable levels of risk)

4 4 Disciplines & Cross-Cutting Areas Bone loss Muscle alterations & atrophy Neurovestibular adaptation Cardiovascular alterations Immunology, infection & hematology Environmental effects Clinical capabilities Psychosocial adaptation Sleep & circadian rhythms Neuropsychological Space human factors – cognitive capabilities Radiation effects Advanced life support Advanced environmental monitoring Advanced food technology Advanced EVA Space human factors – physical capabilities Human Health & Countermeasures Radiation Health Behavioral Health & Performance Advanced Human Support Technologies Autonomous Medical Care

5 5 Reference Missions DRM1 Year ISSLunarMars Crew Size2 +4 – 66 Launch Date2005?NET 2015, NLT 2020NET 2025 – 2030 Mission Duration12 months10 – 44 days30 months Outbound Transit2 days3 – 7 days4 – 6 months On-Site Duration12 months4 – 30 days18 months Return Transit2 days3 – 7 days4 – 6 months Communication lag time 0+1.3 seconds +3 – 20 minutes + Hypogravity0 g1/6g (.1666g/5.33 ft./sec. 2 ) 1/3g (.389g/12.448 ft./sec. 2 ) Internal Environment ~ 14.7 psiTBD EVA0 – 4 per mission2 – 3/week; 4 – 15/person 2 – 3/week; 180/person

6 6 Timetable 2004: Announcement of new vision for space exploration 2005: Countermeasure hardware requirements (Phase A) 2006: Initial flight experiments; countermeasure hardware design & prototype development (Phase B) 2007-8: First unmanned test flight of CEV 2010: STS to be retired: end heavy lift/return 2010-13: Final ground demo of countermeasures 2013-16: In-flight demo/validation of integrated countermeasure suite(s) 2015-20: Moon human landing/exploration testbed 2016: End ISS validation of countermeasures 2025: First piloted Mars mission

7 7 Risk Mitigation Status Technology Readiness Level (TRL) & Countermeasures Readiness Level (CRL) TRL DefinitionCRL DefinitionCRL category Basic principles observedPhenomenon observed and reported Problem defined Basic research Technology concept and/or application formulated Hypothesis formed, preliminary studies to define parameters. Demonstrate feasibility Analytical and experimental critical function/proof-of-concept Validated hypothesis. Understanding of scientific processes underlying problem Research to prove feasibility Component and/or breadboard validation in lab Formulation of countermeasures concept based on understanding of phenomenon Counter- measure develop- ment Component and/or breadboard in relevant environment Proof of concept testing and initial demonstration of feasibility and efficacy System/subsystem model or prototype demonstration in relevant environment Laboratory/clinical testing of potential countermeasure in subjects to demonstrate efficacy of concept Subsystem prototype in a space environment Evaluation with human subjects in controlled laboratory simulating operational space flight environment Counter- measure demonstration System completed and flight qualified through demonstration Validation with human subjects in actual operational space flight to demonstrate efficacy and operational feasibility System flight proven through mission operations Countermeasure fully flight-tested and ready for implementation Countermeasure operations

8 8 LowModerateHigh Crewmember Health In-flight No more than temporary discomfort Short-term incapacitation or impairment Death, significant health issue requiring mission abort or long-term incapacitation or impairment Crewmember Performance In-flight Delays of mission objectives Loss of some mission objectives Inability to perform critical mission functions, or total loss of mission objectives Crewmember Health Post- mission Limited increase in post-mission rehabilitation Impairment but no long term reduced quality of life Significant permanent disability or significantly reduced lifespan, or significant long term impairment or reduced quality of life Severity of Consequences (for example) Types of Consequences (for example) Human Health Risk Assessment Criteria (examples)

9 9 Rating Analysis Human Health and Countermeasure Risks –Most microgravity physiology risks are modest –ISS should be used to mitigate those risks Behavioral Health and Performance Risks –Critical for exploration –ISS only moderately useful to mitigate risks –Research should be done in integrated test facilities Radiation Risks –Radiation protection is essential for exploration –Most research should be done on Earth

10 10 Human Health and Countermeasures Risks

11 11 Human Health and Countermeasures Risks (continued)

12 12 Human Health and Countermeasures Risks (continued)

13 13 Autonomous Medical Care

14 14 Behavioral Health and Performance

15 15 Radiation Risks

16 16 Credits: John Charles Deputy Chief Scientist Bioastronautics Kent Joosten Exploration Systems Engineering Office

17 17 Mars Mission

18 18

19 19

20 20 MARS NOTES Earth to Mars –Average short 48M Miles –Average Long 235M Miles –With eccentricity short varies between 35M + 63M Miles Mars Equator Diameter – 4,214 Miles Earth Equator Diameter – 7,921 Miles One Astronautical Unit AU – 93M Miles (92,960,000 miles) –Solar System Measurement One Light Year – 63M AU (63,241 AU’s) –Star Distance Measurement

21 21 Example Short-Stay Missions Characterized by: –High-propulsive requirements –Large variation in energy requirements across mission opportunities –Venus swing-by or deep-space Maneuvers –Close perihelion passage –Short to long total mission durations –Majority (90+%) of crew time spent in deep-space environment Sun  Arrive Mars 12/16/31 Depart Mars 1/25/32 MISSION TIMES Outbound313 days Stay40 days Return308 days Total Mission661 days Depart Earth 2/6/31 Arrive Earth 11/28/32 Example Short-Stay Mission

22 22 Example Long-Stay Missions Characterized by: –Lower-propulsive requirements –Small variation in energy requirements across mission opportunities –All mission > 1 Au –Short transits separated by long- surface mission –Long total mission durations –Majority (50+%) of crew time spent on Mars Sun  Depart Earth 5/11/18 Depart Mars 6/14/20 Arrive Earth 12/11/20 MISSION TIMES Outbound180 days Stay545 days Return180 days Total Mission945 days Arrive Mars 11/7/18 Example Long-Stay Mission

23 23 Mars Mission & Propulsion Options: constant acceleration Plasma rocket: variable specific impulse magnetoplasma rocket, VASIMIR Continuous acceleration ~0.01 g –Not biologically protective g-level –Benefit: short trip time, reduced exposure to weightlessness, radiation, other risks Round-trip: ~8 month –3 month outbound –1 month at Mars –3 month Return Supercritical H2 propellant also serves as radiation shield

24 24 VASIMIR Trajectory Note: van Allen belts < 6 Re

25 25 Mission Architecture Assumptions Transit from Earth to Mars:Transit from Earth to Mars: →4-8 months →Possibly entirely in weightlessness Deconditioning similar to that seen in ISS crewsDeconditioning similar to that seen in ISS crews Protective effects of Artificial Gravity (AG) now under investigationProtective effects of Artificial Gravity (AG) now under investigation

26 26 How Do We Get There? Understand crew capabilities after simulated Mars transitUnderstand crew capabilities after simulated Mars transit →Post-flight evaluations of ISS crewmembers Increase crew capabilities on arrival at MarsIncrease crew capabilities on arrival at Mars →Develop effective crew conditioning in transit Artificial Gravity if possibleArtificial Gravity if possible →Crew rehabilitation after landing (if necessary) Decrease operational requirements on crew during post-arrival adaptation periodDecrease operational requirements on crew during post-arrival adaptation period →Automate entry/landing →Minimize crew workload immediately after landing →Increase crew extravehicular mobility (pressure suit; rover, etc.)

27 27 Physical Conditioning during Transit Resistive Exercise Artificial Gravity (Short-Axis Centrifuge) Aerobic Exercise Rehabilitation may also be required before on-planet EVAs. Rehabilitation may also be required before on-planet EVAs.

28 28 Crew Performance Requirements after Mars Landing Don/doff pressure suit without assistanceDon/doff pressure suit without assistance Physical rehabilitationPhysical rehabilitation –Walk, balance, stretch, light cardio & resistive exercise Descend and climb stairsDescend and climb stairs –Function of post-landing time –Wearing pressure suit AmbulateAmbulate –Function of post-landing time –Wearing pressure suit –Across uneven or irregular surface Text courtesy of Steve Hoffman and NASA JSC Exploration Office 2003

29 29 SpiritL+11D Spirit L+0 Recommendation Crewmember adjustment to Mars surface environment may require:Crewmember adjustment to Mars surface environment may require: →3-4 days minimum →10 days in extreme cases Any vehicle intended for crew landing on Mars should support:Any vehicle intended for crew landing on Mars should support: →One week habitation by whole crew →Crewmember rehabilitation as required →Surface EVA preparations

30 30 Previously Recommended First Mars landing crew should not conduct a surface EVA before day 7, and then only local traverses during a surface stay of about 60 daysFirst Mars landing crew should not conduct a surface EVA before day 7, and then only local traverses during a surface stay of about 60 days

31 31 One Day After Landing? Or One Week After Landing?

32 32 Point/Counterpoint: EARLY vs. DELAYED Egress? Minimize ascent vehicle mass (if crew landing vehicle).Minimize ascent vehicle mass (if crew landing vehicle). Possible operational need for earlier egress.Possible operational need for earlier egress. Limited time on-planet.Limited time on-planet. Psychological impacts of delayed egress.Psychological impacts of delayed egress. →Crew vehicle must have margins for off- nominal and contingency operational and crew health situations. →Operational requirements always supercede recommendations. →Maybe not so limited—18 months? →Crew more efficient if better adapted. AG in transit to minimize rehabilitation.AG in transit to minimize rehabilitation. →Crew cognizant of issues. →Crew not idle: vehicle reconfiguration, EVA preparations, landing site reconnaissance.

33 33 Mars Design Reference Mission No earlier than 2025-2030 –Oct.2024; Nov.2026; Jan.2029; Feb.2031 30-month round-trip –4-6 months in transit –18 months on Mars 180+ EVAs per person Gravity/acceleration –Hypogravity 3/8 g on Mars 0 g in transit (unless AG) 4 1 3 2

34 34 Land in either of two distinct vehiclesLand in either of two distinct vehicles →Habitat No abort-to-orbit capabilityNo abort-to-orbit capability Well-equipped for long habitationWell-equipped for long habitation –No early surface EVA required OR →Ascent vehicle Abort to orbit if required (then what?)Abort to orbit if required (then what?) Limited life support capabilityLimited life support capability –Early surface EVA required to reach habitat →Separate vehicles required for reasons of landed mass Mission Architecture Assumptions

35 35 approx 500 m Habitat Ascent vehicle Vehicles no more than 500 meters apartVehicles no more than 500 meters apart Mission Architecture Assumptions

36 36 Soyuz TMA-2 landing mimicked Mars landing:Soyuz TMA-2 landing mimicked Mars landing: →5½-month simulated transit. →Piloted aerobraking entry, descent and landing. →Safed lander. →Egressed vehicle unassisted. →Erected recovery aids. Case Study: ISS Expedition 6

37 37 Provided strong evidence FOR human functionality after Mars- like transit.Provided strong evidence FOR human functionality after Mars- like transit. Qualitatively demonstrated decrements in crew performance.Qualitatively demonstrated decrements in crew performance. →All three crewmembers exhibited reduced capability, up to voluntary immobility. →Thirty minutes worth of work in about five hours, but no need to hurry. →Note: unencumbered weight on Earth approximates Mars weight wearing projected pressure suit. (Mark III zero-prebreathe suit: 95 kg on Earth = 36 kg on Mars) Case Study: Expedition 6 (cont.)

38 38 Where do we need to be? ?Anticipated Mission requirements for early on-planet operations √Dexterity →Tool fastener operation √Hand-eye coordination →Driving rover →Teleoperating robotic aides √Strength, flexibility, agility →Pressure suit doff/don →Habitat egress/ingress √Complex actions →Deploy solar array →Erect habitat

39 39 BEAT Bowling Green!!


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