A series of outlines and graphs describing NASA's Space Exploration Initiative (SEI) technology prioritization are presented. Prioritization criteria and preliminary critical technology priorities for a first lunar outpost and a Mars and permanently-manned lunar mission are addressed

Dula, Alex

English

NASA Technical Reports Server

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EXPLORATION TECHNOLOGY PRIORITIZATION
NASA INTEGRATED TECHNOLOGY PLAN INPUT
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REVISED PRIORITIZATION CRITERIA FOR THE
NEAR-TERM SEI TECHNOLOGIES
Office of Exploration "=
Assumptions
Two priofitized list are developed: one for early manned Lunar missions and one for
permanently manned Lunar missions and Mars
No priority is implied within a group
First Lunar outpost, missions and design guidelines dated 1/7/92 and SEI Strategic Plan Dated
12/10/91 are used for mission requirements
Early manned Lunar mission by 1999 with up to 45 day stay capability for a crew of 4
No long-term cryo storage required lor initial Lunar missions (storable return propulsion)
Emphasize common Lunar mission - Mars mission technology and H/W and S/W
All technology will be developed to TRL 5 or 6 prior to project start (Phase C/D)
Required permanent Lunar and Mars technology/advanced development willbe initiated .
between now and 2000
All technology/advanced development must have clearly defined cost/benefit justification or
mandatory mission need rationale
NTR development in critical path for manned Mars mission
Mars missions will include stays of up to 500-600 days at Mars
For each project advanced development starts before project start at Phase C/D and terminates
within the year PDR is held
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PRIORITIZATION CRITERIA
"=" N_J_ ...... . 1 _ 7. • ,L = , Office of Exploration
NOTE: This chart is used to develop the technology needs for the SEI missions
• Mission Leverage High
Performance leverage of technology to system,
mission, and crew
Ability of technology to reduce risk to crew
and mission
Ability of technology to reduce cost by reducing
Earth delivered mass and life cycle costs
Evolution capability
Abilityto support multiple missions (commonality)
Timing
Development time to reach TRL 5 (years)
Time needed before project start (years)
Special Factors
Transportability/spin-off to commercial sector
Abilityto stimulate universities and public for
support of mission
Medium Low
Long Medium Short
T>=8 3<T<7 T<=3
T>=8 3<T<7 T<=3
Medium LowHigh
I Office of Exploration
1992 - 1995
CRITICAL TECHNOLOGIES
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PRELIMINARY CRITICAL TECHNOLOGY PRIORITIZATION
FIRST LUNAR OUTPOST (1992- 1995)
_Jj_j_ , - _ .......... _ office of Exploration
Category 1 Priority (Near Term)
Lunar EVA Systems
Durable, lightweight, high mobility suit
and EVA gloves
LightweigSt, serviceable, PLSS
Autonomous Terminal Landing
Sensors
SNV algorithms
Hazardavoidance
Life Support
Contamination and particulate control
Trash & waste/collection & processing
Loop closure
• Surface Power- Non Nuclear
High efficiency thermal to electric conversior_
Heat rejection
Long life energy storage
• Cryo Fluid Systems
Cryo storage
C_o transfer (zero-g)
Quick disconnect couplings
Zero-g gaging
• NTP
Category 1A Priority
(Mars and Permanently Manned Lunar Missions)
Fuel development
Turbo pumps
st facility
Reactor development
Surface nuclear power
Power conversion
Radiators
Surface Habs and construction
Radiation shielding
Dust control
• ISRU ('Technology demo capability)
- Oxygen process chemistry
- Mining
Construction material test
Vw 1,131,_
N/ A
(1995 + )
CRITICAL TECHNOLOGIES
F-_-3
PRELIMINARY CRITICAL TECHNOLOGY PRIORITIZATION
PERMANENTLY MANNED LUNAR AND MARS MISSIONS
(1995 + )
== N_A =_ ..... I r Office o! Exploration
• NTP
Category I (Highest Priority)
• Mars EVA Systems •
Durable, lightweight,
high mobility suit and EVA gloves
Lightweight, serviceable, PLSS
• Life Support Systems/Thermal Control Systems
(Long-term use)
Radiation Protection
Light weight shielding
SPE prediction
Transport code validation
• Surface Power-Nuclear • ISRU
Telerobotics
Sensors
Vision
End effectors
Liquefaction
Malerials compatibility
Electrolysis technologies
Category II
Planetary Rovers ....
Motors lubricants (Long-term use)
Dust control
Power
Aerobraking
TPS
CFD codes
High temperature structural material
Adaptive GN&C
TECHNOLOGY NEEDS
- NASA •'
Technology Category
• EVA Systems
Technology Areas
Office of Exploration -=
• Durable lightweight dexterous high mobility suit
• Lightweight, serviceable PLSS
• Environmentaldust control
• Highly dexterous gloves
Benefits/Leverage
• Increase crew safety and EVA productivity
• Reduce suit servicing time
• Enabling for use on surface
• Lower life cycle cost
• Evolvable technology baseline for Mars
Performance Goals
• EVA system lifetime: ;_5 yrs
• Duty cycle: > 200 days/yr @ 6-8 hrs/day
• Suit oper. pressure: 3.8- 6 PSIA
• Lunar EVA system mass: < 110 Kg venting
<_125 Kg regen.
Mars EVA system mass: <_90 kg venting
_<70 kg regen.
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Technology Readiness Dates
• Current TRL: 3 - 4
• Required time to reach TRL 5:3 years
Need dates: Lunar: 1996
Mars: 2000
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TECHNOLOGY NEEDS
- RI/LSA Office of Exploration
Technology Category
• Surface power-non nuclear
Technology Areas
• Long-life energy storage, eg., regenerative fuel
cells (RFCs)
• Power management and distribution(low mass,
long duty cycle, low maintenance)
• Thermal control (high efficiency, long dutycycle,
long-lived, low maintenance)
• Generation: solar PV
Benefits/Leverage
• Reduced mass
• Reduced maintenance
• Improved reliability, lifetime
• Increased performance
• Applicationsto terrestrial systems
Performance Goals
• RFCs: Specific energy: 67w0._.;.__('Lunar)
Kg
200-_--HR (Mars)
• Specific power: 250 w/kg (Lud_r and Mars)
• System efficiency: 65% FC, 90% electrolyzer
• Lifetime: 500- 4000 hrs (SOA)
>20,000 hrs (advanced)
• PMAD: 20 kg/kW
• Generation: PV arrays 300 W/kg (Lunar)
80 w/kg (Mars)
;_40,000 hr.lifetime
Technology Readiness Dates
• Current TRL: 3- 4 Storage
4 PMAD
4 Thermal
4 Generation
• Years to TRL 6:4 - 6
VII I11.314_
-- N/ A
Technology Category
• Autonomous terminallanding
Technology Areas
• Hazard avoidance
• Sensors
• S/W algorithms
• Adaptive mechanisms and effectors
Benefits/Leverage
• Reduce ground support
• Reduce EVA support for vehicle mating
• Allow landing ifcrew unable to manually
perform task
• Land at predefined coordinates
• Robotic Mars missions to return samples
from rover is enabled
TECHNOLOGY NEEDS
Office of Exploration _
Performance Goals
• Landing accuracy: < 100 m
• Hazard avoidance: > I m (surface hazards)
• Hazard endurance: _<1 m (surface hazards)
• Reliability: _ 99% probability of safe landing
Technology Readiness Dates
• TRL: 3- 4
• 2-4yearstoTRL5
Need dates: Lunar: Robotic: 1993
Oulpost; 1995
Mars: 2000
TECHNOLOGY NEEDS
-- NASA,, " Office of Exploration
Technology Category
• Cryogenic Fluid Systems
Technology Areas
• Cryo storage (Thermal & Pressure Control)
• Cryo management for propellant slosh control and
acquisition
• Cryo transfer for In-space fueling/refueling
• Cryo zero-leak quick disconnect coupling and
zero-G gaging system
• Cryo production on planet surface
Benefits/Leverage
• Enabling for in-space assembled space transfer
vehicles (all Mars concepts)
• On-orbit fueling/refueling enables reusable vehicle
concepts and significantly reduces vehicle
departure mass
• IMLEO reduction of 25-30% for cryogenic
propulsion system used for return from Lunar
surface when compared to storables for direct
Lunar injected missions
Performance Goals
• Cryogens: Hydrogen and oxygen
• Cryo system acceleration environment: 0 to high
G level
• Lunar boil-off rate: 2 to 6%/month (mission
dependent)
o Mars boil-off rate:_<l°/_month
• Transfer losses: < 5%
• Unusable propellants (residuals):_<2%
Technology Readiness Dates
• Thermal control is TRL 4/5
• All other areas are TRL 2/3
• Cryo transfer and 0-G pressure control are 8 yrs.
to TRL 6
• Thermal control is 3 yrs. to TRL 6
• All other areas require up to 5 yrs. to TRL 6
Need dates: Lunar: 1998
Mars: 2000
TECHNOLOGY NEEDS
-- N/ A- '
Technology Category
• Life support systems crew accommodations
Technology Areas
• Contamination and particulate control
• Trash and waste collection and processing
• Water management
• Bio regeneration
• Food management and biomass production
Benefits/Leverage
• Saves up to 40 lbs/day resupply
• Reduce trash build-up
• Integration of biological and physiochemicai
regenerative systems
r II I Office of Exploration P
Performance Goals
• System lifetime: 7 - 15 yrs (Lunar)
3 + yrs (Mars)
• System closure (water): 95%
• System closure (air): 95%
• System closure (total): TBD
• System power req: TBD kW/person
• Operating environment: Lunar/Mars
Minimal servicing
Technology Readiness Dates
, TRL: 2- 4
• Development to TRL 5:5 - 6 yrs
Need dates: Lunar: 1995
Mars: 2000
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Technology Category
• ISRU
Technology Areas
• Oxygen process chemistry
• Mining
• Electrolysis technologies
• Materials compatibility
• Liquefaction
• Construction material test
Benefits/Leverage
• Reduce resupply "
• Make up oxygen for safety and redundancy
• Increase stay time
TECHNOLOGY NEEDS
Office of Exploralion :
Performance Goals
• Equipment life time: ;zl0 years
• Liquidoxygen production: initial: .5 - 10 mT/yr
OPS: 10 - 25 mT/yr
• Regolith mined annually: < 5 KmT/yr
• Duty cycle: _>90% (day/night)
• System mass: OPS < 15 mT
• Power: TBD KWe
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Technology Readiness Dates
• TRL: 2-4
• 4 - 6 years to TRL 6
Need dates: Lunar: 1995
Mars: 2000
Lunar robotic (demo): 1993
TECHNOLOGY NEEDS
-- I IASA Office of Exploration
Technology Category
• NTP(Solidcore)
Technology Areas
• Fuel development
• Turbo pumps
• Test facility design/construction
• Shielding and control systems
• Pressure vessels and nozzle technology
• High temperature materials
• Reactor development
Benefits/Leverage
• Significant reduction in Earth delivered mass
• Reduce Mars trip times
• Crew safety
• Operational flexibility
Performance Goals
• Liletime: 5 - 15 years, multiple flights
• Thrust: 25- 75 k Ibs
• Specific impulse: 900- 1000 sec
• Specific mass: 120-240 kW/kg
• Thrust-to-mass: > 3 to 30
• Space base, limited servicing, multiple restart
Technology Readiness Dates
• TRL: 4-5
• 5-10 years to TRL 6 (uprated NERVA technology)
Need date: Mars: 2000
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Technology Category
• Surface power - nuclear
TECHNOLOGY NEEDS
Office of Exploration "==
Technology Areas
• High efficiency thermal to electric conversion
• Power conditioning and transmission
• Heat rejection/radiator concepts
• Dust effects on system performance
• Generation: Reactor and isotope/Heat sources
Performance Goals
• Stationary applicalions: 50 kg/kWe @ 100 kWe
(static conversion)
25 kg/kWe @ 500-800 kWe
(dynamic conversion)
Benefits/Leverage
• Mobile applications:
• Lifetime:
5 W/kg @ 300 We (RTG)
7 W/kg @ 2.5 kWe (DIPS)
7 - 15 yrs
Technology Readiness Dates
• Current TRL: 3 - 4 SP - 100
4 - 5 DIPS
> 5 RTG
• Years to TRL - 6:6 - 10 depending on syslem,
subsystem
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TECHNOLOGY NEEDS
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Technology Category
• Surface habs and construction
Technology Areas
• Autonomous deployment of systems
• Surface/stability determination
• Dust control
• Hab to Hab IVA interface
• inflatable structures
Benefits/Leverage
• increase crew living/working area
• Allow building of large structures
• Prepare landing site
• Enhance crew productivity/safety
- Reduce launch mass volume
Performance Parameters
• Habit_atlifetime: > 10-15 years
• Habitat environmentalpressure: "I'BD
• Heat rejection requirement: TBD
• Construction equipment load: TBD
• Set up time: TBD
• Crew required for set up: TBD
Technology Readiness Dates
• TRL: 1-2
• 4-5 years to TRL 5
Need dates: Lunar: 1997
Mars: 2000
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TECHNOLOGY NEEDS
[ • J I .
Technology Category:
TRadiat(on protection
ecnnology Areas:
Shielding materials (light weight)
Prediction of SPE and monitoring -_
Crew high z, high energy limits
Transport codes enhancement & validation
Active crew persona( dosimeter
Panicle Spectrometer for GCR and solar flare particles
Tissue Equivatent Proportional counter for charged
particle detection
Neutron Energy Spectrum spectrometer
BenefitslLeverage
Performance Goals:
Office of Exploration _--
ShieJding lifetime: > 10-_5 years
Shielding requirement: 20 gmtsq, cm. (200
grNsq.cm, s#aep quarters)
Prediction error: <20% (initial)
<10% (final Mars)
SPE pre_lion: TBD hrs. prior to occurrence
Technology Readiness Dates
- Crew protection from solar and cosmic
radiation during transit and on sudace
- Data (o determine appropriate shielding
strategy for crew and electronics to reduce
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Vet
TRL: 3
Development to TRL 6:5-7 years
Need dates: Lunar: 2000
Mars: 2000
Technology Category
• Telerobotics
TECHNOLOGY NEEDS
Technology Areas
• Joint actuators
• Sensors
• Vision
. Man-machine interface
• End effectors
• Intelligent controls
Benefits Leverage
• Reduce crew exposure to EVA
• Perform operations at a distance
• Servicing of hazardous systems
:_ _! . . ,, r, I _ : Office of Exploration ==
Performance Goals
• Manipulator dexlerily: TBD
• Manipulator loading: TBD
• Radiation field: TBD
Technology Readiness Dates
• TRL: 3- 4
• 3-5yearstoTRL5
Need dates: Lunar: 1996
Mars: 2000
F_.E-9
TECHNOLOGY NEEDS
Office of Exploration '=_
Performance Goals
• Semi-autonomous traverse: _>10M (early)
_>100M (interim)
• Mobility (obstacle endurance): _<1M
• Power system: _>5W {kg (robotic)}
• Lifetime: 1-2 years
• Life support requirement: TBD
• Range robotic: t00 km
• Range manned: _<100 km
- N/L A 1 T
Technology Category
• Planetary Rovers (Long-term autonomous use)
Technology Areas
• Motors/lubricants (Long-term use)
• Dust control
° Power
Benefits/Leverage
• Allow extended operations from base
• Support science investigation
Technology Readiness Dates
• TRL: 2-3
• 4-6 years to TRL 5
Needdates: Lunar: Outpost: 1996
Mars: 2000
TECHNOLOGY NEEDS
- Ili/ A--
TechnologyCategory:
Aerobraking
Technology Areas:
• Reusable and ablative TPS material
• Validated CFD Codes
• Adaptive GN&C
• Lightweight, launchablestructures
Benefits/Leverage
• Required Ior Mars entry/landing and Earth
entry/landing
• Enables Mars quick return trajectories
• Enhances all-chemical propulsive mission
performance, reduces IMLEO
• Can backup or compliment NTP
-- I I
Performance Goals:
• Entry velocity range
Lunar return -- 11 km/s
Mars entry -- 5 to 6 km/s
Mars aerocapture -- 6 to 10 km/s
Mars return to Earth -o 12 to 15 km/s
• Aerobrake mass fraction < 20%
• L/D ratio: 0 to 1.5 (Varies with mission
application)
• Reuse for lunar permanent base - 7 flights
Technology Readiness Dates
• TRL: 3-4
• Lunar: 4 years to TRL 6
• Mars: 8yearstoTRL6
Need dates:
Lunar early: 1995
Lunar permanent: 2000
Mars: 2000
Office of Exploration
'alu:rev 1/28/92 Vor 2:2/" 'ele revision
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Exploration technology prioritization

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