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Mitigating Long Duration Biomedical Constraints
With Innovative Mission Architecture
James S. Logan, M.D.Group Manager, Human Test Support
Clinical Services Branch/SD3NASA Johnson Space Center
A Design Reference Mission Suite
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Mitigating Long Duration Biomedical Constraints
With Innovative Mission Architecture
Dan AdamoIndependent Astrodynamics Consultant
Special Acknowledgment
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> 270 Missions
> 500 People
> 100 Person-years
2011 Will Be Year 50 of human spaceflight!!
What are the implications of the EVIDENCE?
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Potential Lunar Long Duration Showstoppers*
Lunar Dust Wild Card Wild Card
RadiationEVA Hab
Surface
(EVA)Depth
Surface
(EVA)Depth
Hypogravity Nonstarter Nonstarter
SynergisticEffects
Element Sortie Outpost Settlement Frontier
* Assuming current technology and goal of civilization
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From Apollo Experience Report Protection Against Radiation
NASA TN D-7080 (1973)
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Risk of Exposure Induced Death
REID is a statistical approach pegged to a single radiation effect:
DEATH from cancer directly attributable to the exposure
In 1989 NASA accepted National Committee on Radiation Protection
(NCRP) recommendation of career dose limits corresponding to a
lifetime increase of 3% in cancer mortality
In 2000, NCRP kept that same 3% recommendation but alsosignificantly reduced the dose expected to reach the 3% lifetime risk.
45 y.o. male astronauts 10 year 3% career limit went from
325 rem in 1989 to 150 rem in 2000
35 y.o. female astronauts 10 year 3% career limit went from
175 rem in 1989 to 60 rem in 2000
This is NOT being more conservative, this is a realization that
radiation is more harmful than predicted
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New Radiation Protection Scale
RP100 Same radiation protection as Earth at sea level(1030 g/cm2 radiation shield equivalent or 100%)
RP50 Radiation shield equivalent to 18,000 ft altitude
RP2 Best ISS locations ~ 2% Earth protection
RP0.005 Radiation protection equivalent of space suit
(one-half of 1% Earth equivalent)
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X
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X X
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Implications
Moon/Mars may never more than sortie destinations*
Habitats must be shielded or underground Repeat EVAs (same crew) will be severely constrained
Robotic precursor missions must scout destinations
and prepare sites for human presence
Must determine Gravity Prescription for people,
plants, animals and multiple generations
*At least not without significant new investments
in research and enabling technology
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We need to stop this obsessive
preoccupation with spherical bodies at
the bottom of gravity wells with basicallyno atmosphere and no magnetic field.
These places just arent good for us - - at
least not as settlement, frontier orcivilization destinations.
James S. Logan, MD
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The Perfect Place
Low Delta-V
Lots of RESOURCES!
Little or No GRAVITY WELL
At or Near Earth Normal GRAVITY for
People, Plants and Animals
Natural RADIATION Protection
Permit Large Redundant Ecosystem(s)
Staging Area for Exploration and Expansion
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Round-Trip v To SomeNearby Destinations
Daniel R. Adamo 23 May 2010 21
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Accessible NEOs On 1 March 2010
Daniel R. Adamo 23 May 2010 22
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33 by 13 Km; 2,900 Cubic Kilometers
3% metals (gold, aluminum, platinum,zinc., iridium, etc.)
$20,000,000,000,000
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Virtues of DEIMOSThird Largest NEO (12.6 km mean diameter)
Less Delta-V than Moon, Phobos, Eros
(escape velocity of 12.5 mph (5.6 m/s; 20 km/h)!!
Only 20,000 km from Martian surface
Just above aerosynchronous orbit
Launch window every 2.14 years
Visualize all of Mars except extreme polar regions
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Virtues of DEIMOSRound trip light time of 0.13 seconds
Locked orbit around Mars
Couldbe captured carbonaceous chondrite
Low average density (1.471 g/cm2)
Could achieve all Mars surface explorationobjectives via short range human telepresence(ref.NASA Mars Design Reference Architecture [DRA] 5.0,
Section 3: Goals and Objectives)
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Duration of DEIMOS Mission
Outbound Leg : 240 Days (24%)
DEIMOS Stay Time: 469 Days (46.9%)
Return Leg: 249 Days (24%)
Total 949 Days
5.1% Pad (consumables) 1000 Days (100%)
~1000 Days is unacceptable re: RADIATION!
Therefore you must implement an RP100 environment at Deimos.
This will reduce your exposed days by half
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Mission Architecture Elements Series of Robotic Precursor Missions (RPMs) for
reconnaissance and habitat site preparation
Pre-emplacement of stay time, return consumables
as well as return entry vehicle at destination
(i.e. must rendezvous with Deimos)
Earth Parking Orbit (EPO) functions as fuel depot
Incremental build up of Mars Transit Vehicle
Abort To Destination (ATD) only option after TMI No aerobraking for Mars capture KISS principle
Direct entry upon Earth return
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Consumables Mass Estimate Calculations
Method Two (modified Logan method)
NASA Open Loop Life Support and modified ISS experience for
1000 days
Water: 18,000 kg
Oxygen: 2,170
Food: 5,700
Crew Supplies: 2,071Gasses Lost to Space: 2,071
Systems Maintenance 2,071
TOTAL 32,084
Outbound + Pad (Crew Vehicle): 9,336 kg
Preemplacement at DEIMOS: 22,747 kg
TOTAL 32,084
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Innovative Architecture
Elements:RADIATION PROTECTION
Radical redesign of Human Element (HE) vehicle toleverage all infrastructure mass (includingpropellant)
for radiation protection
At least RP5 required during transit (~50g/cm2)
Minimize radiation exposure by reducing Exposed
Days
Habitat site at destination mustprovide RP100
Use of NTM for radiation protection on return leg
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Destination Deimos Mars Transfer Vehicle (MTV)
Assumptions Propulsion stages made up of 15.7% structure
(tankage, plumbing,...)
A launch package is limited to 187.7 mT IMLEO(think Ares V i.e. real Heavy Lift not wimpy Heavy Lift)
Pre-emplace all return consumables at Deimos, including a crewEarth-return vehicle required for direct atmospheric entry
First heavy-lift launch package: Cargo Element #1 (CE1) First half of hypergolic propulsion stage required for Mars orbit
insertion (MOI) and Deimos rendezvous
Payload mass = 50.9 mT; IMLEO = 134.0 mT
Additional payload mass = 21.6 mT available (likely forhypergolic propellant supporting Earth orbit loiter to await laterlaunch packages)
CE2 is identical to CE1 and completes assembly of MOIstage
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Destination Deimos Mars Transfer Vehicle (MTV)
CE3 is unique Inflatable TransHab module (28.1 mT) plus open-loop crew
consumables for 8 months + 5.1% margin (9.4 mT) plus
additional radiation shielding (23.0 mT) to achieve RP5 Payload mass = 60.4 mT; IMLEO = 157.6 mT
Fourth heavy-lift launch package: Human Element (HE)
Cryogenic trans-Mars injection (TMI) stage (46.9 mT) plus crewexploration vehicle (CEV, 18.6 mT)
Payload mass = 65.5 mT; IMLEO = 170.3 mT
Without nuclear propulsion, there are no Earth return optionspost-TMI. Therefore, the CEV nominally undocks from the
MTV after the crew enters TransHab and is GO for TMI.Following successful TMI, the CEV is deorbited.
Total IMLEO = 595.8 mT (current ISS mass = 370.2 mT,
but this is not the IMLEO associated with ISS assembly)
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Mars Orbit Insertion andDeimos Rendezvous
Core Size: 0.460 km by 12 km
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Core Volume: 1.99 km3
Mean Density: 1.471 gm/cm
3
Core Mass: 2,927,290,000,000 kg
1% H2O => 29 Billion Liters
3% H2O => 88 Billion Liters
5% H2O => 146 Billion Liters
7% H2O => 205 Billion Liters
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The Art & Science of BIONEERING:
Turning this
I t thi
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Into this
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Questions?