nasa_power_space
TRANSCRIPT
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 116
NASArsquos ADVANCED ON-BOARD PROPULSION PROGRAMACTIVITIES AT JOHN H GLENN RESEARCH CENTER
DR JOHN W DUNNING
SCOTT BENSONSTEVEN OLESON
NATIONAL AERONAUTICS AND SPACE ADMINISTRATIONJOHN H GLENN RESEARCH CENTER AT LEWIS FIELD
CLEVELAND OHIO USA 44135
ADVANCED SPACE PROPULSION WORKSHOP
3-5 APRIL 2001HUNTSVILLE AL
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 216
Electric Propulsion -
Candidate Trajectory Approaches
bull High Power Hall Pump-Up
bull Hall Thruster Stage
Delivers Spacecraft to Near
Earth Escape
bull Chemical Propulsion toInject into direct trajectory to
Pluto
bull Continued Interplanetary
Use of Hall System May
Improve Mission
bull Low Power Ion Direct
bull Launch Vehicle Upper
Stage Kicks to High C3
Earth Escape
bull Ion Propulsion Used onDirect Trajectory to
Pluto Thrusting Out to
Uranus
EP Transfer
Chemical
TMI Burn
EP Transfer EP Transfer
Gravity Assist
EP Transfer
bull High Power IonGravity
Assists
bull Launch Vehicle Upper Stage
Kicks to Low C3 Earth Escape
bull Ion Propulsion Used DuringInner Solar System Cruise
bull Gravity Assist at Venus or
Earth
bull Ion Propulsion Continues
Out to Jupiter
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 316
High Pow er Elec t r ic Propuls ion
Enables Edge of Solar Syst em Probes
diams Achieve gt 550 au in 10 to 20 yearsdiams Explore Kuiper belt Oort Cloud Heliopause Deep Space observationhellipdiams High Isp propulsion needed for the High Energy Missiondiams Isps 10000 to 15000 sec to minimize launch mass
diams High PowerElectric Propulsion 01 - gt1 MW Optionsbull Ionbull MPDbull PIT
diams Use with nuclear power systemsdiams Similar to nuclear powered crewed planetary exploration vehicles
Proposed by RJ Lipinsk i etal
GRC MW-class MPD Thruster
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 416
High Power Propulsion SystembullSPT vs TAL vs HybridbullAnnular vs Racetrack Geometry
bullSingle vs Clusters vs Nested
Physical Processes ampEngineering Constraints
bullPerformance
bullMagnetic SystembullThermalbullMaterialsbullStability
Mission RequirementsbullIsp Thrust EfficiencybullThrottleability
bullLifetimebullEMIbullMass
High Power Facility IssuesbullThrust StandbullPumping Speed
bullChamber SizebullPower amp Feed SystemsbullThermal Limitations
Develop a high power Hall propulsion system based on existing design
heritage using mission and engineering constraints as inputs
Hall Propulsion
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 516
SOA NEAR TERM FAR TERM
Hall Thruster Roadmap
10 kW Dom estic
Engine
23 kW3 4 0 0 se c
2 - Sta g e
Concept
Eva lua t ion
100 W
Feasib i l i ty
Assessment
NASA 457M
50 kW Hall
Engine
T i m e
T
RL
L
ev
e
l
High Performance
45kW IHPRPT Ph 1
Life Test 200W Low Power Tests
8kW Bi-Modal
SBIR Ph2
Fakel 100W Demo Model
Modular Cluster for
gt 100kW Missions
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 616
LEO to GEO space
transportation Four Times
the Payload of Chemical
Systems In Four Weeks using
next generation Power levels
LunarMarsExploration
Eliminates need for
nuclear technology
Reduces Launch
Vehicle Fleet
ISS Drag MakeupSignificantly reduces required
refueling flights
Space Solar Power Reduces
number of launch vehicles required by a factor of 5 Deliveries in few
weeks to less than four monthsbullNeed Power Levels ~ 50 kW amp
Isps ~ 2500 sec
Hal l Propuls ion - 50 kW Thruster Appl icat ions
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 716
98 00 02 04 06 08 10 12
5-10 kW 30 cm ENGINE TESTBED
30 kW+ 75 cm ENGINE TESTBED
TITANIUM AND C-C ION OPTICS
DEEP-SPACE 1
HIGH-CURRENT CATHODES
NSTAR
50-100 KW INTERSTELLAR PRECURSOR AND
KUIPER BELT MISSION ENGINES
SUB-kW ENGINE -
OPTICS TESTBED
High-Power Ion Propulsion Road-Map
100 kW-class EPCathode
Thermaland lifelimits
assessed
5 kW PPUdesign
completed
10 kW prototypeengine
Titanium optics
C-C andadvanced-Mo
optics
20kW 50 cm TESTBED
VIPS
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 816
diams Major accomplishments
Design and fabrication of large-area dischargechamber completedDischarge operation characterized on krypton and xenon
propellantsPerformance characterized
diams Near Term Plans (FY01)Manufacture large-area high-voltage ion opticsDemonstrate engine operation at gt 10000 seconds Isp
Ion Propuls ion - In ters t e l la r Prec ursor Tec hnology
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 916
Ion Propuls i on - 5 kW Next -Generat ion Ion Tec hnology
diams Near Term Plans
Conduct design and performance analysis ofnext-generation large-area thrusterComplete detailed mechanical design of thruster
Fabricate and assemble prototype thruster and conductpreliminary performance testing
Sizecomparisonof NSTARand Next-Generation
thruster
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1016
ldquoMicrordquo Ion Engine TechnologyDevelop Prototype
FEASIBILITY OF A HOLLOW-CATHODE-BASED
MICRO ION THRUSTER FOR MICROSPACECRAFT
RELIES ON HIGH IONIZATION EFFICIENCIES DEMONSTRATED WITH
SMALL GRC HIGH ASPECT RATIO HOLLOW CATHODES
GOAL gt25 EFFICIENCY gt1500 S Isp 5-25 W
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1116
00 01 02 03 04 05 06 07
Sub-kW Ion Propulsion Technology Road-Map options
Advanced Moly or Titanium optics
20 kg Xe Throughput
C-C Optics30 kg Xe
Throughput
08 09 10 11 12
05 sccm
Cathode
No Flow Cathode
Moly optics
12 kg Xe Throughput
Regulated 28v PPU
300 W
2800 sec
49 Efficient
12 kg Xe Throughput
300 W
2800 sec
49 Efficient
20 kg Xe Throughput
300 W
3300 sec
56 Efficient
30 kg Xe
Throughput
Thermal and life
limits
assessed
Thermal and life
limits
assessed
Thermal and life
limitsassessed
rsquo06 Option
rsquo09 Option
rsquo12 Option
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1216
HHHH iiii gggg hhhh PPPPoooowwww eeee rr r r PPPPrr r r oooo ppppuuuu llll ssss iiii oooo nnnn
Potential transportation systems includebull Electric and Plasma Propulsion
minus 100 KW LEO to GEO deliver 6000 kg in 60
days
minus 100 KW powered Interstellar precursor
mission 10 times payload increase
minus 1 MW Jupiter mission (1 year trip time)
minus Multi-MW class fast Human planetary mission
(1 year round trip to Mars)
minus Options include ion thrusters Hall thrusters
MPD Pulsed Inductive Thrusters and
VASMIR
KEY TECHNOLOGIES Electrode lifetimes power conditioning high energy density
capacitors sputter resistant materials lightweight magnets magnetic nozzle work
thermal control and propellant management
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1316
Magnetoplasmadynamic (MPD) Thrusters
bull RobustSimple design and constru ction canoperate w ith various propellants
bull High Pow er Capab i l ity w ithLow Volume Requirements
Steady- state devices tested to 500-kW pulsed devices tested to severalMW
bull Potential High Performance30- kW tests demonstra ted 70
efficiency at 5000 s using appliedmagnetic fields and l ithiumpropellant (Gianinni Scientific CorpNASA GRC cir ca 1968)
Benef i t s
bull Thruster L i fet ime
Electrode erosion at high
currents
bull MW- Class Oper a t i o nAddress high pow er thermaldesign issues improve thrusterefficiencies
Power management and
distributionPropellant handl ing
Chal lenges
NASA GRC 01 MW- Class MPD Cir ca 1989
NASA GRC 01 MW Steady- State Hel ium MPD Cir ca 1989
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1416
MPD THRUSTER PROGRAM PLANS
USE NUMERICAL MODELING
AND PULSED MW-CLASS MPDTHRUSTER EXPERIMENTS TO
ESTABLISH EFFICIENT MPD
THRUSTER DESIGNS
TRANSITION EFFICIENT
DESIGNS TO MW-CLASSSTEADY-STATE FACILITY
EVALUATE MPD THRUSTER
LIFETIME AND EFFICIENCY
bull 50 EFFICIENCY
bull 5000 HOURS LIFE
bull 2500 s - 7000 s Isp
ENGINEERING MODEL
MPD THRUSTER
FY01-02 FY03-05 FY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1516
PULSED INDUCTIVE THRUSTER PROGRAM PLANS
NUMERICAL
MODELING AND
FABRICATION OF
MULTIPLE REP-RATE
PIT DESIGN
(GRCTRWMSFC)
bull 60 EFFICIENCY
bull HIGH REP-RATE
bull 2500 s - 7500 s Isp
ENGINEERING MODEL
PIT THRUSTER
SINGLE-SHOT
AND MULTIPLE
REP-RATE
EVALUATION
OF PIT
PERFORMANCE
SOLID STATE SWITCH
DEVELOPMENT ANDINTEGRATION INTO
MULTIPLE REP-RATE
THRUSTER
FY01-02 FY03-04 FY05-06 gtFY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1616
CCCCoooo mmmm bbbb iiii nnnn eeee dddd BBBB eeee nnnn eeee ff f f iiii tttt ssss oooo ff f f PPPPrr r r oooo pppp uuuu llll ssss iiii oooo nnnn aaaa nnnn dddd PPPPoooo wwww eeee rr r r
ff f f oooo rr r r PPPPllll uuuu tttt oooo FFFFllll yyyy bbbb yyyy (((((St udy Requested b y Code S Fal l 20 00)))))
Electric Prop-
8cm Ionthrusters
Radioisotope
with StirlingConverters
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
Electric
Propulsion andStirling
RadioisotopeConverters
Direct RTG
bullRadioisotope
Electric Propulsion
bullAdd Electric
Propulsion to
increase PayloadbullNo launch window
constraints direct
fast trajectories
bullStirling Converter
Reduces required
of Pu Modules
bullCombination of Ion
thrusters and
Stirling Converters
bullDoubles
Useable SCPayload and
Power at Flyby
Pluto Flyby Spacecraft Net Mass and Power at Flyby
0
50
100
150
200
250
300
350
400
450
SOA Adv EP Only Adv Stirling Only Adv EP and Stirling
SC Net Mass (kg)or Power (W)
at Flyby
Net Delivered SC Mass SC Power Available at Flyby
Power (BOM) 290 W 474 W 250 W 474 W
Power (Flyby) 230 W 376 W 230 W 435 W
EP Propellant 84 kg 84 kg
Power mass 56 kg 92 kg 29 kg 60 kg
Propulsion mass 29 kg 29 kg
Net SC Mass 121 kg 212 kg 148 kg 243 kg
of Pu Modules 2 7 4 3 6 1 0
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 216
Electric Propulsion -
Candidate Trajectory Approaches
bull High Power Hall Pump-Up
bull Hall Thruster Stage
Delivers Spacecraft to Near
Earth Escape
bull Chemical Propulsion toInject into direct trajectory to
Pluto
bull Continued Interplanetary
Use of Hall System May
Improve Mission
bull Low Power Ion Direct
bull Launch Vehicle Upper
Stage Kicks to High C3
Earth Escape
bull Ion Propulsion Used onDirect Trajectory to
Pluto Thrusting Out to
Uranus
EP Transfer
Chemical
TMI Burn
EP Transfer EP Transfer
Gravity Assist
EP Transfer
bull High Power IonGravity
Assists
bull Launch Vehicle Upper Stage
Kicks to Low C3 Earth Escape
bull Ion Propulsion Used DuringInner Solar System Cruise
bull Gravity Assist at Venus or
Earth
bull Ion Propulsion Continues
Out to Jupiter
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 316
High Pow er Elec t r ic Propuls ion
Enables Edge of Solar Syst em Probes
diams Achieve gt 550 au in 10 to 20 yearsdiams Explore Kuiper belt Oort Cloud Heliopause Deep Space observationhellipdiams High Isp propulsion needed for the High Energy Missiondiams Isps 10000 to 15000 sec to minimize launch mass
diams High PowerElectric Propulsion 01 - gt1 MW Optionsbull Ionbull MPDbull PIT
diams Use with nuclear power systemsdiams Similar to nuclear powered crewed planetary exploration vehicles
Proposed by RJ Lipinsk i etal
GRC MW-class MPD Thruster
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 416
High Power Propulsion SystembullSPT vs TAL vs HybridbullAnnular vs Racetrack Geometry
bullSingle vs Clusters vs Nested
Physical Processes ampEngineering Constraints
bullPerformance
bullMagnetic SystembullThermalbullMaterialsbullStability
Mission RequirementsbullIsp Thrust EfficiencybullThrottleability
bullLifetimebullEMIbullMass
High Power Facility IssuesbullThrust StandbullPumping Speed
bullChamber SizebullPower amp Feed SystemsbullThermal Limitations
Develop a high power Hall propulsion system based on existing design
heritage using mission and engineering constraints as inputs
Hall Propulsion
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 516
SOA NEAR TERM FAR TERM
Hall Thruster Roadmap
10 kW Dom estic
Engine
23 kW3 4 0 0 se c
2 - Sta g e
Concept
Eva lua t ion
100 W
Feasib i l i ty
Assessment
NASA 457M
50 kW Hall
Engine
T i m e
T
RL
L
ev
e
l
High Performance
45kW IHPRPT Ph 1
Life Test 200W Low Power Tests
8kW Bi-Modal
SBIR Ph2
Fakel 100W Demo Model
Modular Cluster for
gt 100kW Missions
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 616
LEO to GEO space
transportation Four Times
the Payload of Chemical
Systems In Four Weeks using
next generation Power levels
LunarMarsExploration
Eliminates need for
nuclear technology
Reduces Launch
Vehicle Fleet
ISS Drag MakeupSignificantly reduces required
refueling flights
Space Solar Power Reduces
number of launch vehicles required by a factor of 5 Deliveries in few
weeks to less than four monthsbullNeed Power Levels ~ 50 kW amp
Isps ~ 2500 sec
Hal l Propuls ion - 50 kW Thruster Appl icat ions
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 716
98 00 02 04 06 08 10 12
5-10 kW 30 cm ENGINE TESTBED
30 kW+ 75 cm ENGINE TESTBED
TITANIUM AND C-C ION OPTICS
DEEP-SPACE 1
HIGH-CURRENT CATHODES
NSTAR
50-100 KW INTERSTELLAR PRECURSOR AND
KUIPER BELT MISSION ENGINES
SUB-kW ENGINE -
OPTICS TESTBED
High-Power Ion Propulsion Road-Map
100 kW-class EPCathode
Thermaland lifelimits
assessed
5 kW PPUdesign
completed
10 kW prototypeengine
Titanium optics
C-C andadvanced-Mo
optics
20kW 50 cm TESTBED
VIPS
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 816
diams Major accomplishments
Design and fabrication of large-area dischargechamber completedDischarge operation characterized on krypton and xenon
propellantsPerformance characterized
diams Near Term Plans (FY01)Manufacture large-area high-voltage ion opticsDemonstrate engine operation at gt 10000 seconds Isp
Ion Propuls ion - In ters t e l la r Prec ursor Tec hnology
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 916
Ion Propuls i on - 5 kW Next -Generat ion Ion Tec hnology
diams Near Term Plans
Conduct design and performance analysis ofnext-generation large-area thrusterComplete detailed mechanical design of thruster
Fabricate and assemble prototype thruster and conductpreliminary performance testing
Sizecomparisonof NSTARand Next-Generation
thruster
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1016
ldquoMicrordquo Ion Engine TechnologyDevelop Prototype
FEASIBILITY OF A HOLLOW-CATHODE-BASED
MICRO ION THRUSTER FOR MICROSPACECRAFT
RELIES ON HIGH IONIZATION EFFICIENCIES DEMONSTRATED WITH
SMALL GRC HIGH ASPECT RATIO HOLLOW CATHODES
GOAL gt25 EFFICIENCY gt1500 S Isp 5-25 W
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1116
00 01 02 03 04 05 06 07
Sub-kW Ion Propulsion Technology Road-Map options
Advanced Moly or Titanium optics
20 kg Xe Throughput
C-C Optics30 kg Xe
Throughput
08 09 10 11 12
05 sccm
Cathode
No Flow Cathode
Moly optics
12 kg Xe Throughput
Regulated 28v PPU
300 W
2800 sec
49 Efficient
12 kg Xe Throughput
300 W
2800 sec
49 Efficient
20 kg Xe Throughput
300 W
3300 sec
56 Efficient
30 kg Xe
Throughput
Thermal and life
limits
assessed
Thermal and life
limits
assessed
Thermal and life
limitsassessed
rsquo06 Option
rsquo09 Option
rsquo12 Option
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1216
HHHH iiii gggg hhhh PPPPoooowwww eeee rr r r PPPPrr r r oooo ppppuuuu llll ssss iiii oooo nnnn
Potential transportation systems includebull Electric and Plasma Propulsion
minus 100 KW LEO to GEO deliver 6000 kg in 60
days
minus 100 KW powered Interstellar precursor
mission 10 times payload increase
minus 1 MW Jupiter mission (1 year trip time)
minus Multi-MW class fast Human planetary mission
(1 year round trip to Mars)
minus Options include ion thrusters Hall thrusters
MPD Pulsed Inductive Thrusters and
VASMIR
KEY TECHNOLOGIES Electrode lifetimes power conditioning high energy density
capacitors sputter resistant materials lightweight magnets magnetic nozzle work
thermal control and propellant management
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1316
Magnetoplasmadynamic (MPD) Thrusters
bull RobustSimple design and constru ction canoperate w ith various propellants
bull High Pow er Capab i l ity w ithLow Volume Requirements
Steady- state devices tested to 500-kW pulsed devices tested to severalMW
bull Potential High Performance30- kW tests demonstra ted 70
efficiency at 5000 s using appliedmagnetic fields and l ithiumpropellant (Gianinni Scientific CorpNASA GRC cir ca 1968)
Benef i t s
bull Thruster L i fet ime
Electrode erosion at high
currents
bull MW- Class Oper a t i o nAddress high pow er thermaldesign issues improve thrusterefficiencies
Power management and
distributionPropellant handl ing
Chal lenges
NASA GRC 01 MW- Class MPD Cir ca 1989
NASA GRC 01 MW Steady- State Hel ium MPD Cir ca 1989
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1416
MPD THRUSTER PROGRAM PLANS
USE NUMERICAL MODELING
AND PULSED MW-CLASS MPDTHRUSTER EXPERIMENTS TO
ESTABLISH EFFICIENT MPD
THRUSTER DESIGNS
TRANSITION EFFICIENT
DESIGNS TO MW-CLASSSTEADY-STATE FACILITY
EVALUATE MPD THRUSTER
LIFETIME AND EFFICIENCY
bull 50 EFFICIENCY
bull 5000 HOURS LIFE
bull 2500 s - 7000 s Isp
ENGINEERING MODEL
MPD THRUSTER
FY01-02 FY03-05 FY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1516
PULSED INDUCTIVE THRUSTER PROGRAM PLANS
NUMERICAL
MODELING AND
FABRICATION OF
MULTIPLE REP-RATE
PIT DESIGN
(GRCTRWMSFC)
bull 60 EFFICIENCY
bull HIGH REP-RATE
bull 2500 s - 7500 s Isp
ENGINEERING MODEL
PIT THRUSTER
SINGLE-SHOT
AND MULTIPLE
REP-RATE
EVALUATION
OF PIT
PERFORMANCE
SOLID STATE SWITCH
DEVELOPMENT ANDINTEGRATION INTO
MULTIPLE REP-RATE
THRUSTER
FY01-02 FY03-04 FY05-06 gtFY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1616
CCCCoooo mmmm bbbb iiii nnnn eeee dddd BBBB eeee nnnn eeee ff f f iiii tttt ssss oooo ff f f PPPPrr r r oooo pppp uuuu llll ssss iiii oooo nnnn aaaa nnnn dddd PPPPoooo wwww eeee rr r r
ff f f oooo rr r r PPPPllll uuuu tttt oooo FFFFllll yyyy bbbb yyyy (((((St udy Requested b y Code S Fal l 20 00)))))
Electric Prop-
8cm Ionthrusters
Radioisotope
with StirlingConverters
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
Electric
Propulsion andStirling
RadioisotopeConverters
Direct RTG
bullRadioisotope
Electric Propulsion
bullAdd Electric
Propulsion to
increase PayloadbullNo launch window
constraints direct
fast trajectories
bullStirling Converter
Reduces required
of Pu Modules
bullCombination of Ion
thrusters and
Stirling Converters
bullDoubles
Useable SCPayload and
Power at Flyby
Pluto Flyby Spacecraft Net Mass and Power at Flyby
0
50
100
150
200
250
300
350
400
450
SOA Adv EP Only Adv Stirling Only Adv EP and Stirling
SC Net Mass (kg)or Power (W)
at Flyby
Net Delivered SC Mass SC Power Available at Flyby
Power (BOM) 290 W 474 W 250 W 474 W
Power (Flyby) 230 W 376 W 230 W 435 W
EP Propellant 84 kg 84 kg
Power mass 56 kg 92 kg 29 kg 60 kg
Propulsion mass 29 kg 29 kg
Net SC Mass 121 kg 212 kg 148 kg 243 kg
of Pu Modules 2 7 4 3 6 1 0
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 316
High Pow er Elec t r ic Propuls ion
Enables Edge of Solar Syst em Probes
diams Achieve gt 550 au in 10 to 20 yearsdiams Explore Kuiper belt Oort Cloud Heliopause Deep Space observationhellipdiams High Isp propulsion needed for the High Energy Missiondiams Isps 10000 to 15000 sec to minimize launch mass
diams High PowerElectric Propulsion 01 - gt1 MW Optionsbull Ionbull MPDbull PIT
diams Use with nuclear power systemsdiams Similar to nuclear powered crewed planetary exploration vehicles
Proposed by RJ Lipinsk i etal
GRC MW-class MPD Thruster
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 416
High Power Propulsion SystembullSPT vs TAL vs HybridbullAnnular vs Racetrack Geometry
bullSingle vs Clusters vs Nested
Physical Processes ampEngineering Constraints
bullPerformance
bullMagnetic SystembullThermalbullMaterialsbullStability
Mission RequirementsbullIsp Thrust EfficiencybullThrottleability
bullLifetimebullEMIbullMass
High Power Facility IssuesbullThrust StandbullPumping Speed
bullChamber SizebullPower amp Feed SystemsbullThermal Limitations
Develop a high power Hall propulsion system based on existing design
heritage using mission and engineering constraints as inputs
Hall Propulsion
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 516
SOA NEAR TERM FAR TERM
Hall Thruster Roadmap
10 kW Dom estic
Engine
23 kW3 4 0 0 se c
2 - Sta g e
Concept
Eva lua t ion
100 W
Feasib i l i ty
Assessment
NASA 457M
50 kW Hall
Engine
T i m e
T
RL
L
ev
e
l
High Performance
45kW IHPRPT Ph 1
Life Test 200W Low Power Tests
8kW Bi-Modal
SBIR Ph2
Fakel 100W Demo Model
Modular Cluster for
gt 100kW Missions
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 616
LEO to GEO space
transportation Four Times
the Payload of Chemical
Systems In Four Weeks using
next generation Power levels
LunarMarsExploration
Eliminates need for
nuclear technology
Reduces Launch
Vehicle Fleet
ISS Drag MakeupSignificantly reduces required
refueling flights
Space Solar Power Reduces
number of launch vehicles required by a factor of 5 Deliveries in few
weeks to less than four monthsbullNeed Power Levels ~ 50 kW amp
Isps ~ 2500 sec
Hal l Propuls ion - 50 kW Thruster Appl icat ions
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 716
98 00 02 04 06 08 10 12
5-10 kW 30 cm ENGINE TESTBED
30 kW+ 75 cm ENGINE TESTBED
TITANIUM AND C-C ION OPTICS
DEEP-SPACE 1
HIGH-CURRENT CATHODES
NSTAR
50-100 KW INTERSTELLAR PRECURSOR AND
KUIPER BELT MISSION ENGINES
SUB-kW ENGINE -
OPTICS TESTBED
High-Power Ion Propulsion Road-Map
100 kW-class EPCathode
Thermaland lifelimits
assessed
5 kW PPUdesign
completed
10 kW prototypeengine
Titanium optics
C-C andadvanced-Mo
optics
20kW 50 cm TESTBED
VIPS
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 816
diams Major accomplishments
Design and fabrication of large-area dischargechamber completedDischarge operation characterized on krypton and xenon
propellantsPerformance characterized
diams Near Term Plans (FY01)Manufacture large-area high-voltage ion opticsDemonstrate engine operation at gt 10000 seconds Isp
Ion Propuls ion - In ters t e l la r Prec ursor Tec hnology
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 916
Ion Propuls i on - 5 kW Next -Generat ion Ion Tec hnology
diams Near Term Plans
Conduct design and performance analysis ofnext-generation large-area thrusterComplete detailed mechanical design of thruster
Fabricate and assemble prototype thruster and conductpreliminary performance testing
Sizecomparisonof NSTARand Next-Generation
thruster
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1016
ldquoMicrordquo Ion Engine TechnologyDevelop Prototype
FEASIBILITY OF A HOLLOW-CATHODE-BASED
MICRO ION THRUSTER FOR MICROSPACECRAFT
RELIES ON HIGH IONIZATION EFFICIENCIES DEMONSTRATED WITH
SMALL GRC HIGH ASPECT RATIO HOLLOW CATHODES
GOAL gt25 EFFICIENCY gt1500 S Isp 5-25 W
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1116
00 01 02 03 04 05 06 07
Sub-kW Ion Propulsion Technology Road-Map options
Advanced Moly or Titanium optics
20 kg Xe Throughput
C-C Optics30 kg Xe
Throughput
08 09 10 11 12
05 sccm
Cathode
No Flow Cathode
Moly optics
12 kg Xe Throughput
Regulated 28v PPU
300 W
2800 sec
49 Efficient
12 kg Xe Throughput
300 W
2800 sec
49 Efficient
20 kg Xe Throughput
300 W
3300 sec
56 Efficient
30 kg Xe
Throughput
Thermal and life
limits
assessed
Thermal and life
limits
assessed
Thermal and life
limitsassessed
rsquo06 Option
rsquo09 Option
rsquo12 Option
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1216
HHHH iiii gggg hhhh PPPPoooowwww eeee rr r r PPPPrr r r oooo ppppuuuu llll ssss iiii oooo nnnn
Potential transportation systems includebull Electric and Plasma Propulsion
minus 100 KW LEO to GEO deliver 6000 kg in 60
days
minus 100 KW powered Interstellar precursor
mission 10 times payload increase
minus 1 MW Jupiter mission (1 year trip time)
minus Multi-MW class fast Human planetary mission
(1 year round trip to Mars)
minus Options include ion thrusters Hall thrusters
MPD Pulsed Inductive Thrusters and
VASMIR
KEY TECHNOLOGIES Electrode lifetimes power conditioning high energy density
capacitors sputter resistant materials lightweight magnets magnetic nozzle work
thermal control and propellant management
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1316
Magnetoplasmadynamic (MPD) Thrusters
bull RobustSimple design and constru ction canoperate w ith various propellants
bull High Pow er Capab i l ity w ithLow Volume Requirements
Steady- state devices tested to 500-kW pulsed devices tested to severalMW
bull Potential High Performance30- kW tests demonstra ted 70
efficiency at 5000 s using appliedmagnetic fields and l ithiumpropellant (Gianinni Scientific CorpNASA GRC cir ca 1968)
Benef i t s
bull Thruster L i fet ime
Electrode erosion at high
currents
bull MW- Class Oper a t i o nAddress high pow er thermaldesign issues improve thrusterefficiencies
Power management and
distributionPropellant handl ing
Chal lenges
NASA GRC 01 MW- Class MPD Cir ca 1989
NASA GRC 01 MW Steady- State Hel ium MPD Cir ca 1989
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1416
MPD THRUSTER PROGRAM PLANS
USE NUMERICAL MODELING
AND PULSED MW-CLASS MPDTHRUSTER EXPERIMENTS TO
ESTABLISH EFFICIENT MPD
THRUSTER DESIGNS
TRANSITION EFFICIENT
DESIGNS TO MW-CLASSSTEADY-STATE FACILITY
EVALUATE MPD THRUSTER
LIFETIME AND EFFICIENCY
bull 50 EFFICIENCY
bull 5000 HOURS LIFE
bull 2500 s - 7000 s Isp
ENGINEERING MODEL
MPD THRUSTER
FY01-02 FY03-05 FY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1516
PULSED INDUCTIVE THRUSTER PROGRAM PLANS
NUMERICAL
MODELING AND
FABRICATION OF
MULTIPLE REP-RATE
PIT DESIGN
(GRCTRWMSFC)
bull 60 EFFICIENCY
bull HIGH REP-RATE
bull 2500 s - 7500 s Isp
ENGINEERING MODEL
PIT THRUSTER
SINGLE-SHOT
AND MULTIPLE
REP-RATE
EVALUATION
OF PIT
PERFORMANCE
SOLID STATE SWITCH
DEVELOPMENT ANDINTEGRATION INTO
MULTIPLE REP-RATE
THRUSTER
FY01-02 FY03-04 FY05-06 gtFY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1616
CCCCoooo mmmm bbbb iiii nnnn eeee dddd BBBB eeee nnnn eeee ff f f iiii tttt ssss oooo ff f f PPPPrr r r oooo pppp uuuu llll ssss iiii oooo nnnn aaaa nnnn dddd PPPPoooo wwww eeee rr r r
ff f f oooo rr r r PPPPllll uuuu tttt oooo FFFFllll yyyy bbbb yyyy (((((St udy Requested b y Code S Fal l 20 00)))))
Electric Prop-
8cm Ionthrusters
Radioisotope
with StirlingConverters
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
Electric
Propulsion andStirling
RadioisotopeConverters
Direct RTG
bullRadioisotope
Electric Propulsion
bullAdd Electric
Propulsion to
increase PayloadbullNo launch window
constraints direct
fast trajectories
bullStirling Converter
Reduces required
of Pu Modules
bullCombination of Ion
thrusters and
Stirling Converters
bullDoubles
Useable SCPayload and
Power at Flyby
Pluto Flyby Spacecraft Net Mass and Power at Flyby
0
50
100
150
200
250
300
350
400
450
SOA Adv EP Only Adv Stirling Only Adv EP and Stirling
SC Net Mass (kg)or Power (W)
at Flyby
Net Delivered SC Mass SC Power Available at Flyby
Power (BOM) 290 W 474 W 250 W 474 W
Power (Flyby) 230 W 376 W 230 W 435 W
EP Propellant 84 kg 84 kg
Power mass 56 kg 92 kg 29 kg 60 kg
Propulsion mass 29 kg 29 kg
Net SC Mass 121 kg 212 kg 148 kg 243 kg
of Pu Modules 2 7 4 3 6 1 0
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 416
High Power Propulsion SystembullSPT vs TAL vs HybridbullAnnular vs Racetrack Geometry
bullSingle vs Clusters vs Nested
Physical Processes ampEngineering Constraints
bullPerformance
bullMagnetic SystembullThermalbullMaterialsbullStability
Mission RequirementsbullIsp Thrust EfficiencybullThrottleability
bullLifetimebullEMIbullMass
High Power Facility IssuesbullThrust StandbullPumping Speed
bullChamber SizebullPower amp Feed SystemsbullThermal Limitations
Develop a high power Hall propulsion system based on existing design
heritage using mission and engineering constraints as inputs
Hall Propulsion
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 516
SOA NEAR TERM FAR TERM
Hall Thruster Roadmap
10 kW Dom estic
Engine
23 kW3 4 0 0 se c
2 - Sta g e
Concept
Eva lua t ion
100 W
Feasib i l i ty
Assessment
NASA 457M
50 kW Hall
Engine
T i m e
T
RL
L
ev
e
l
High Performance
45kW IHPRPT Ph 1
Life Test 200W Low Power Tests
8kW Bi-Modal
SBIR Ph2
Fakel 100W Demo Model
Modular Cluster for
gt 100kW Missions
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 616
LEO to GEO space
transportation Four Times
the Payload of Chemical
Systems In Four Weeks using
next generation Power levels
LunarMarsExploration
Eliminates need for
nuclear technology
Reduces Launch
Vehicle Fleet
ISS Drag MakeupSignificantly reduces required
refueling flights
Space Solar Power Reduces
number of launch vehicles required by a factor of 5 Deliveries in few
weeks to less than four monthsbullNeed Power Levels ~ 50 kW amp
Isps ~ 2500 sec
Hal l Propuls ion - 50 kW Thruster Appl icat ions
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 716
98 00 02 04 06 08 10 12
5-10 kW 30 cm ENGINE TESTBED
30 kW+ 75 cm ENGINE TESTBED
TITANIUM AND C-C ION OPTICS
DEEP-SPACE 1
HIGH-CURRENT CATHODES
NSTAR
50-100 KW INTERSTELLAR PRECURSOR AND
KUIPER BELT MISSION ENGINES
SUB-kW ENGINE -
OPTICS TESTBED
High-Power Ion Propulsion Road-Map
100 kW-class EPCathode
Thermaland lifelimits
assessed
5 kW PPUdesign
completed
10 kW prototypeengine
Titanium optics
C-C andadvanced-Mo
optics
20kW 50 cm TESTBED
VIPS
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 816
diams Major accomplishments
Design and fabrication of large-area dischargechamber completedDischarge operation characterized on krypton and xenon
propellantsPerformance characterized
diams Near Term Plans (FY01)Manufacture large-area high-voltage ion opticsDemonstrate engine operation at gt 10000 seconds Isp
Ion Propuls ion - In ters t e l la r Prec ursor Tec hnology
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 916
Ion Propuls i on - 5 kW Next -Generat ion Ion Tec hnology
diams Near Term Plans
Conduct design and performance analysis ofnext-generation large-area thrusterComplete detailed mechanical design of thruster
Fabricate and assemble prototype thruster and conductpreliminary performance testing
Sizecomparisonof NSTARand Next-Generation
thruster
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1016
ldquoMicrordquo Ion Engine TechnologyDevelop Prototype
FEASIBILITY OF A HOLLOW-CATHODE-BASED
MICRO ION THRUSTER FOR MICROSPACECRAFT
RELIES ON HIGH IONIZATION EFFICIENCIES DEMONSTRATED WITH
SMALL GRC HIGH ASPECT RATIO HOLLOW CATHODES
GOAL gt25 EFFICIENCY gt1500 S Isp 5-25 W
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1116
00 01 02 03 04 05 06 07
Sub-kW Ion Propulsion Technology Road-Map options
Advanced Moly or Titanium optics
20 kg Xe Throughput
C-C Optics30 kg Xe
Throughput
08 09 10 11 12
05 sccm
Cathode
No Flow Cathode
Moly optics
12 kg Xe Throughput
Regulated 28v PPU
300 W
2800 sec
49 Efficient
12 kg Xe Throughput
300 W
2800 sec
49 Efficient
20 kg Xe Throughput
300 W
3300 sec
56 Efficient
30 kg Xe
Throughput
Thermal and life
limits
assessed
Thermal and life
limits
assessed
Thermal and life
limitsassessed
rsquo06 Option
rsquo09 Option
rsquo12 Option
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1216
HHHH iiii gggg hhhh PPPPoooowwww eeee rr r r PPPPrr r r oooo ppppuuuu llll ssss iiii oooo nnnn
Potential transportation systems includebull Electric and Plasma Propulsion
minus 100 KW LEO to GEO deliver 6000 kg in 60
days
minus 100 KW powered Interstellar precursor
mission 10 times payload increase
minus 1 MW Jupiter mission (1 year trip time)
minus Multi-MW class fast Human planetary mission
(1 year round trip to Mars)
minus Options include ion thrusters Hall thrusters
MPD Pulsed Inductive Thrusters and
VASMIR
KEY TECHNOLOGIES Electrode lifetimes power conditioning high energy density
capacitors sputter resistant materials lightweight magnets magnetic nozzle work
thermal control and propellant management
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1316
Magnetoplasmadynamic (MPD) Thrusters
bull RobustSimple design and constru ction canoperate w ith various propellants
bull High Pow er Capab i l ity w ithLow Volume Requirements
Steady- state devices tested to 500-kW pulsed devices tested to severalMW
bull Potential High Performance30- kW tests demonstra ted 70
efficiency at 5000 s using appliedmagnetic fields and l ithiumpropellant (Gianinni Scientific CorpNASA GRC cir ca 1968)
Benef i t s
bull Thruster L i fet ime
Electrode erosion at high
currents
bull MW- Class Oper a t i o nAddress high pow er thermaldesign issues improve thrusterefficiencies
Power management and
distributionPropellant handl ing
Chal lenges
NASA GRC 01 MW- Class MPD Cir ca 1989
NASA GRC 01 MW Steady- State Hel ium MPD Cir ca 1989
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1416
MPD THRUSTER PROGRAM PLANS
USE NUMERICAL MODELING
AND PULSED MW-CLASS MPDTHRUSTER EXPERIMENTS TO
ESTABLISH EFFICIENT MPD
THRUSTER DESIGNS
TRANSITION EFFICIENT
DESIGNS TO MW-CLASSSTEADY-STATE FACILITY
EVALUATE MPD THRUSTER
LIFETIME AND EFFICIENCY
bull 50 EFFICIENCY
bull 5000 HOURS LIFE
bull 2500 s - 7000 s Isp
ENGINEERING MODEL
MPD THRUSTER
FY01-02 FY03-05 FY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1516
PULSED INDUCTIVE THRUSTER PROGRAM PLANS
NUMERICAL
MODELING AND
FABRICATION OF
MULTIPLE REP-RATE
PIT DESIGN
(GRCTRWMSFC)
bull 60 EFFICIENCY
bull HIGH REP-RATE
bull 2500 s - 7500 s Isp
ENGINEERING MODEL
PIT THRUSTER
SINGLE-SHOT
AND MULTIPLE
REP-RATE
EVALUATION
OF PIT
PERFORMANCE
SOLID STATE SWITCH
DEVELOPMENT ANDINTEGRATION INTO
MULTIPLE REP-RATE
THRUSTER
FY01-02 FY03-04 FY05-06 gtFY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1616
CCCCoooo mmmm bbbb iiii nnnn eeee dddd BBBB eeee nnnn eeee ff f f iiii tttt ssss oooo ff f f PPPPrr r r oooo pppp uuuu llll ssss iiii oooo nnnn aaaa nnnn dddd PPPPoooo wwww eeee rr r r
ff f f oooo rr r r PPPPllll uuuu tttt oooo FFFFllll yyyy bbbb yyyy (((((St udy Requested b y Code S Fal l 20 00)))))
Electric Prop-
8cm Ionthrusters
Radioisotope
with StirlingConverters
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
Electric
Propulsion andStirling
RadioisotopeConverters
Direct RTG
bullRadioisotope
Electric Propulsion
bullAdd Electric
Propulsion to
increase PayloadbullNo launch window
constraints direct
fast trajectories
bullStirling Converter
Reduces required
of Pu Modules
bullCombination of Ion
thrusters and
Stirling Converters
bullDoubles
Useable SCPayload and
Power at Flyby
Pluto Flyby Spacecraft Net Mass and Power at Flyby
0
50
100
150
200
250
300
350
400
450
SOA Adv EP Only Adv Stirling Only Adv EP and Stirling
SC Net Mass (kg)or Power (W)
at Flyby
Net Delivered SC Mass SC Power Available at Flyby
Power (BOM) 290 W 474 W 250 W 474 W
Power (Flyby) 230 W 376 W 230 W 435 W
EP Propellant 84 kg 84 kg
Power mass 56 kg 92 kg 29 kg 60 kg
Propulsion mass 29 kg 29 kg
Net SC Mass 121 kg 212 kg 148 kg 243 kg
of Pu Modules 2 7 4 3 6 1 0
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 516
SOA NEAR TERM FAR TERM
Hall Thruster Roadmap
10 kW Dom estic
Engine
23 kW3 4 0 0 se c
2 - Sta g e
Concept
Eva lua t ion
100 W
Feasib i l i ty
Assessment
NASA 457M
50 kW Hall
Engine
T i m e
T
RL
L
ev
e
l
High Performance
45kW IHPRPT Ph 1
Life Test 200W Low Power Tests
8kW Bi-Modal
SBIR Ph2
Fakel 100W Demo Model
Modular Cluster for
gt 100kW Missions
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 616
LEO to GEO space
transportation Four Times
the Payload of Chemical
Systems In Four Weeks using
next generation Power levels
LunarMarsExploration
Eliminates need for
nuclear technology
Reduces Launch
Vehicle Fleet
ISS Drag MakeupSignificantly reduces required
refueling flights
Space Solar Power Reduces
number of launch vehicles required by a factor of 5 Deliveries in few
weeks to less than four monthsbullNeed Power Levels ~ 50 kW amp
Isps ~ 2500 sec
Hal l Propuls ion - 50 kW Thruster Appl icat ions
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 716
98 00 02 04 06 08 10 12
5-10 kW 30 cm ENGINE TESTBED
30 kW+ 75 cm ENGINE TESTBED
TITANIUM AND C-C ION OPTICS
DEEP-SPACE 1
HIGH-CURRENT CATHODES
NSTAR
50-100 KW INTERSTELLAR PRECURSOR AND
KUIPER BELT MISSION ENGINES
SUB-kW ENGINE -
OPTICS TESTBED
High-Power Ion Propulsion Road-Map
100 kW-class EPCathode
Thermaland lifelimits
assessed
5 kW PPUdesign
completed
10 kW prototypeengine
Titanium optics
C-C andadvanced-Mo
optics
20kW 50 cm TESTBED
VIPS
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 816
diams Major accomplishments
Design and fabrication of large-area dischargechamber completedDischarge operation characterized on krypton and xenon
propellantsPerformance characterized
diams Near Term Plans (FY01)Manufacture large-area high-voltage ion opticsDemonstrate engine operation at gt 10000 seconds Isp
Ion Propuls ion - In ters t e l la r Prec ursor Tec hnology
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 916
Ion Propuls i on - 5 kW Next -Generat ion Ion Tec hnology
diams Near Term Plans
Conduct design and performance analysis ofnext-generation large-area thrusterComplete detailed mechanical design of thruster
Fabricate and assemble prototype thruster and conductpreliminary performance testing
Sizecomparisonof NSTARand Next-Generation
thruster
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1016
ldquoMicrordquo Ion Engine TechnologyDevelop Prototype
FEASIBILITY OF A HOLLOW-CATHODE-BASED
MICRO ION THRUSTER FOR MICROSPACECRAFT
RELIES ON HIGH IONIZATION EFFICIENCIES DEMONSTRATED WITH
SMALL GRC HIGH ASPECT RATIO HOLLOW CATHODES
GOAL gt25 EFFICIENCY gt1500 S Isp 5-25 W
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1116
00 01 02 03 04 05 06 07
Sub-kW Ion Propulsion Technology Road-Map options
Advanced Moly or Titanium optics
20 kg Xe Throughput
C-C Optics30 kg Xe
Throughput
08 09 10 11 12
05 sccm
Cathode
No Flow Cathode
Moly optics
12 kg Xe Throughput
Regulated 28v PPU
300 W
2800 sec
49 Efficient
12 kg Xe Throughput
300 W
2800 sec
49 Efficient
20 kg Xe Throughput
300 W
3300 sec
56 Efficient
30 kg Xe
Throughput
Thermal and life
limits
assessed
Thermal and life
limits
assessed
Thermal and life
limitsassessed
rsquo06 Option
rsquo09 Option
rsquo12 Option
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1216
HHHH iiii gggg hhhh PPPPoooowwww eeee rr r r PPPPrr r r oooo ppppuuuu llll ssss iiii oooo nnnn
Potential transportation systems includebull Electric and Plasma Propulsion
minus 100 KW LEO to GEO deliver 6000 kg in 60
days
minus 100 KW powered Interstellar precursor
mission 10 times payload increase
minus 1 MW Jupiter mission (1 year trip time)
minus Multi-MW class fast Human planetary mission
(1 year round trip to Mars)
minus Options include ion thrusters Hall thrusters
MPD Pulsed Inductive Thrusters and
VASMIR
KEY TECHNOLOGIES Electrode lifetimes power conditioning high energy density
capacitors sputter resistant materials lightweight magnets magnetic nozzle work
thermal control and propellant management
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1316
Magnetoplasmadynamic (MPD) Thrusters
bull RobustSimple design and constru ction canoperate w ith various propellants
bull High Pow er Capab i l ity w ithLow Volume Requirements
Steady- state devices tested to 500-kW pulsed devices tested to severalMW
bull Potential High Performance30- kW tests demonstra ted 70
efficiency at 5000 s using appliedmagnetic fields and l ithiumpropellant (Gianinni Scientific CorpNASA GRC cir ca 1968)
Benef i t s
bull Thruster L i fet ime
Electrode erosion at high
currents
bull MW- Class Oper a t i o nAddress high pow er thermaldesign issues improve thrusterefficiencies
Power management and
distributionPropellant handl ing
Chal lenges
NASA GRC 01 MW- Class MPD Cir ca 1989
NASA GRC 01 MW Steady- State Hel ium MPD Cir ca 1989
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1416
MPD THRUSTER PROGRAM PLANS
USE NUMERICAL MODELING
AND PULSED MW-CLASS MPDTHRUSTER EXPERIMENTS TO
ESTABLISH EFFICIENT MPD
THRUSTER DESIGNS
TRANSITION EFFICIENT
DESIGNS TO MW-CLASSSTEADY-STATE FACILITY
EVALUATE MPD THRUSTER
LIFETIME AND EFFICIENCY
bull 50 EFFICIENCY
bull 5000 HOURS LIFE
bull 2500 s - 7000 s Isp
ENGINEERING MODEL
MPD THRUSTER
FY01-02 FY03-05 FY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1516
PULSED INDUCTIVE THRUSTER PROGRAM PLANS
NUMERICAL
MODELING AND
FABRICATION OF
MULTIPLE REP-RATE
PIT DESIGN
(GRCTRWMSFC)
bull 60 EFFICIENCY
bull HIGH REP-RATE
bull 2500 s - 7500 s Isp
ENGINEERING MODEL
PIT THRUSTER
SINGLE-SHOT
AND MULTIPLE
REP-RATE
EVALUATION
OF PIT
PERFORMANCE
SOLID STATE SWITCH
DEVELOPMENT ANDINTEGRATION INTO
MULTIPLE REP-RATE
THRUSTER
FY01-02 FY03-04 FY05-06 gtFY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1616
CCCCoooo mmmm bbbb iiii nnnn eeee dddd BBBB eeee nnnn eeee ff f f iiii tttt ssss oooo ff f f PPPPrr r r oooo pppp uuuu llll ssss iiii oooo nnnn aaaa nnnn dddd PPPPoooo wwww eeee rr r r
ff f f oooo rr r r PPPPllll uuuu tttt oooo FFFFllll yyyy bbbb yyyy (((((St udy Requested b y Code S Fal l 20 00)))))
Electric Prop-
8cm Ionthrusters
Radioisotope
with StirlingConverters
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
Electric
Propulsion andStirling
RadioisotopeConverters
Direct RTG
bullRadioisotope
Electric Propulsion
bullAdd Electric
Propulsion to
increase PayloadbullNo launch window
constraints direct
fast trajectories
bullStirling Converter
Reduces required
of Pu Modules
bullCombination of Ion
thrusters and
Stirling Converters
bullDoubles
Useable SCPayload and
Power at Flyby
Pluto Flyby Spacecraft Net Mass and Power at Flyby
0
50
100
150
200
250
300
350
400
450
SOA Adv EP Only Adv Stirling Only Adv EP and Stirling
SC Net Mass (kg)or Power (W)
at Flyby
Net Delivered SC Mass SC Power Available at Flyby
Power (BOM) 290 W 474 W 250 W 474 W
Power (Flyby) 230 W 376 W 230 W 435 W
EP Propellant 84 kg 84 kg
Power mass 56 kg 92 kg 29 kg 60 kg
Propulsion mass 29 kg 29 kg
Net SC Mass 121 kg 212 kg 148 kg 243 kg
of Pu Modules 2 7 4 3 6 1 0
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 616
LEO to GEO space
transportation Four Times
the Payload of Chemical
Systems In Four Weeks using
next generation Power levels
LunarMarsExploration
Eliminates need for
nuclear technology
Reduces Launch
Vehicle Fleet
ISS Drag MakeupSignificantly reduces required
refueling flights
Space Solar Power Reduces
number of launch vehicles required by a factor of 5 Deliveries in few
weeks to less than four monthsbullNeed Power Levels ~ 50 kW amp
Isps ~ 2500 sec
Hal l Propuls ion - 50 kW Thruster Appl icat ions
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 716
98 00 02 04 06 08 10 12
5-10 kW 30 cm ENGINE TESTBED
30 kW+ 75 cm ENGINE TESTBED
TITANIUM AND C-C ION OPTICS
DEEP-SPACE 1
HIGH-CURRENT CATHODES
NSTAR
50-100 KW INTERSTELLAR PRECURSOR AND
KUIPER BELT MISSION ENGINES
SUB-kW ENGINE -
OPTICS TESTBED
High-Power Ion Propulsion Road-Map
100 kW-class EPCathode
Thermaland lifelimits
assessed
5 kW PPUdesign
completed
10 kW prototypeengine
Titanium optics
C-C andadvanced-Mo
optics
20kW 50 cm TESTBED
VIPS
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 816
diams Major accomplishments
Design and fabrication of large-area dischargechamber completedDischarge operation characterized on krypton and xenon
propellantsPerformance characterized
diams Near Term Plans (FY01)Manufacture large-area high-voltage ion opticsDemonstrate engine operation at gt 10000 seconds Isp
Ion Propuls ion - In ters t e l la r Prec ursor Tec hnology
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 916
Ion Propuls i on - 5 kW Next -Generat ion Ion Tec hnology
diams Near Term Plans
Conduct design and performance analysis ofnext-generation large-area thrusterComplete detailed mechanical design of thruster
Fabricate and assemble prototype thruster and conductpreliminary performance testing
Sizecomparisonof NSTARand Next-Generation
thruster
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1016
ldquoMicrordquo Ion Engine TechnologyDevelop Prototype
FEASIBILITY OF A HOLLOW-CATHODE-BASED
MICRO ION THRUSTER FOR MICROSPACECRAFT
RELIES ON HIGH IONIZATION EFFICIENCIES DEMONSTRATED WITH
SMALL GRC HIGH ASPECT RATIO HOLLOW CATHODES
GOAL gt25 EFFICIENCY gt1500 S Isp 5-25 W
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1116
00 01 02 03 04 05 06 07
Sub-kW Ion Propulsion Technology Road-Map options
Advanced Moly or Titanium optics
20 kg Xe Throughput
C-C Optics30 kg Xe
Throughput
08 09 10 11 12
05 sccm
Cathode
No Flow Cathode
Moly optics
12 kg Xe Throughput
Regulated 28v PPU
300 W
2800 sec
49 Efficient
12 kg Xe Throughput
300 W
2800 sec
49 Efficient
20 kg Xe Throughput
300 W
3300 sec
56 Efficient
30 kg Xe
Throughput
Thermal and life
limits
assessed
Thermal and life
limits
assessed
Thermal and life
limitsassessed
rsquo06 Option
rsquo09 Option
rsquo12 Option
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1216
HHHH iiii gggg hhhh PPPPoooowwww eeee rr r r PPPPrr r r oooo ppppuuuu llll ssss iiii oooo nnnn
Potential transportation systems includebull Electric and Plasma Propulsion
minus 100 KW LEO to GEO deliver 6000 kg in 60
days
minus 100 KW powered Interstellar precursor
mission 10 times payload increase
minus 1 MW Jupiter mission (1 year trip time)
minus Multi-MW class fast Human planetary mission
(1 year round trip to Mars)
minus Options include ion thrusters Hall thrusters
MPD Pulsed Inductive Thrusters and
VASMIR
KEY TECHNOLOGIES Electrode lifetimes power conditioning high energy density
capacitors sputter resistant materials lightweight magnets magnetic nozzle work
thermal control and propellant management
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1316
Magnetoplasmadynamic (MPD) Thrusters
bull RobustSimple design and constru ction canoperate w ith various propellants
bull High Pow er Capab i l ity w ithLow Volume Requirements
Steady- state devices tested to 500-kW pulsed devices tested to severalMW
bull Potential High Performance30- kW tests demonstra ted 70
efficiency at 5000 s using appliedmagnetic fields and l ithiumpropellant (Gianinni Scientific CorpNASA GRC cir ca 1968)
Benef i t s
bull Thruster L i fet ime
Electrode erosion at high
currents
bull MW- Class Oper a t i o nAddress high pow er thermaldesign issues improve thrusterefficiencies
Power management and
distributionPropellant handl ing
Chal lenges
NASA GRC 01 MW- Class MPD Cir ca 1989
NASA GRC 01 MW Steady- State Hel ium MPD Cir ca 1989
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1416
MPD THRUSTER PROGRAM PLANS
USE NUMERICAL MODELING
AND PULSED MW-CLASS MPDTHRUSTER EXPERIMENTS TO
ESTABLISH EFFICIENT MPD
THRUSTER DESIGNS
TRANSITION EFFICIENT
DESIGNS TO MW-CLASSSTEADY-STATE FACILITY
EVALUATE MPD THRUSTER
LIFETIME AND EFFICIENCY
bull 50 EFFICIENCY
bull 5000 HOURS LIFE
bull 2500 s - 7000 s Isp
ENGINEERING MODEL
MPD THRUSTER
FY01-02 FY03-05 FY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1516
PULSED INDUCTIVE THRUSTER PROGRAM PLANS
NUMERICAL
MODELING AND
FABRICATION OF
MULTIPLE REP-RATE
PIT DESIGN
(GRCTRWMSFC)
bull 60 EFFICIENCY
bull HIGH REP-RATE
bull 2500 s - 7500 s Isp
ENGINEERING MODEL
PIT THRUSTER
SINGLE-SHOT
AND MULTIPLE
REP-RATE
EVALUATION
OF PIT
PERFORMANCE
SOLID STATE SWITCH
DEVELOPMENT ANDINTEGRATION INTO
MULTIPLE REP-RATE
THRUSTER
FY01-02 FY03-04 FY05-06 gtFY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1616
CCCCoooo mmmm bbbb iiii nnnn eeee dddd BBBB eeee nnnn eeee ff f f iiii tttt ssss oooo ff f f PPPPrr r r oooo pppp uuuu llll ssss iiii oooo nnnn aaaa nnnn dddd PPPPoooo wwww eeee rr r r
ff f f oooo rr r r PPPPllll uuuu tttt oooo FFFFllll yyyy bbbb yyyy (((((St udy Requested b y Code S Fal l 20 00)))))
Electric Prop-
8cm Ionthrusters
Radioisotope
with StirlingConverters
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
Electric
Propulsion andStirling
RadioisotopeConverters
Direct RTG
bullRadioisotope
Electric Propulsion
bullAdd Electric
Propulsion to
increase PayloadbullNo launch window
constraints direct
fast trajectories
bullStirling Converter
Reduces required
of Pu Modules
bullCombination of Ion
thrusters and
Stirling Converters
bullDoubles
Useable SCPayload and
Power at Flyby
Pluto Flyby Spacecraft Net Mass and Power at Flyby
0
50
100
150
200
250
300
350
400
450
SOA Adv EP Only Adv Stirling Only Adv EP and Stirling
SC Net Mass (kg)or Power (W)
at Flyby
Net Delivered SC Mass SC Power Available at Flyby
Power (BOM) 290 W 474 W 250 W 474 W
Power (Flyby) 230 W 376 W 230 W 435 W
EP Propellant 84 kg 84 kg
Power mass 56 kg 92 kg 29 kg 60 kg
Propulsion mass 29 kg 29 kg
Net SC Mass 121 kg 212 kg 148 kg 243 kg
of Pu Modules 2 7 4 3 6 1 0
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 716
98 00 02 04 06 08 10 12
5-10 kW 30 cm ENGINE TESTBED
30 kW+ 75 cm ENGINE TESTBED
TITANIUM AND C-C ION OPTICS
DEEP-SPACE 1
HIGH-CURRENT CATHODES
NSTAR
50-100 KW INTERSTELLAR PRECURSOR AND
KUIPER BELT MISSION ENGINES
SUB-kW ENGINE -
OPTICS TESTBED
High-Power Ion Propulsion Road-Map
100 kW-class EPCathode
Thermaland lifelimits
assessed
5 kW PPUdesign
completed
10 kW prototypeengine
Titanium optics
C-C andadvanced-Mo
optics
20kW 50 cm TESTBED
VIPS
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 816
diams Major accomplishments
Design and fabrication of large-area dischargechamber completedDischarge operation characterized on krypton and xenon
propellantsPerformance characterized
diams Near Term Plans (FY01)Manufacture large-area high-voltage ion opticsDemonstrate engine operation at gt 10000 seconds Isp
Ion Propuls ion - In ters t e l la r Prec ursor Tec hnology
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 916
Ion Propuls i on - 5 kW Next -Generat ion Ion Tec hnology
diams Near Term Plans
Conduct design and performance analysis ofnext-generation large-area thrusterComplete detailed mechanical design of thruster
Fabricate and assemble prototype thruster and conductpreliminary performance testing
Sizecomparisonof NSTARand Next-Generation
thruster
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1016
ldquoMicrordquo Ion Engine TechnologyDevelop Prototype
FEASIBILITY OF A HOLLOW-CATHODE-BASED
MICRO ION THRUSTER FOR MICROSPACECRAFT
RELIES ON HIGH IONIZATION EFFICIENCIES DEMONSTRATED WITH
SMALL GRC HIGH ASPECT RATIO HOLLOW CATHODES
GOAL gt25 EFFICIENCY gt1500 S Isp 5-25 W
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1116
00 01 02 03 04 05 06 07
Sub-kW Ion Propulsion Technology Road-Map options
Advanced Moly or Titanium optics
20 kg Xe Throughput
C-C Optics30 kg Xe
Throughput
08 09 10 11 12
05 sccm
Cathode
No Flow Cathode
Moly optics
12 kg Xe Throughput
Regulated 28v PPU
300 W
2800 sec
49 Efficient
12 kg Xe Throughput
300 W
2800 sec
49 Efficient
20 kg Xe Throughput
300 W
3300 sec
56 Efficient
30 kg Xe
Throughput
Thermal and life
limits
assessed
Thermal and life
limits
assessed
Thermal and life
limitsassessed
rsquo06 Option
rsquo09 Option
rsquo12 Option
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1216
HHHH iiii gggg hhhh PPPPoooowwww eeee rr r r PPPPrr r r oooo ppppuuuu llll ssss iiii oooo nnnn
Potential transportation systems includebull Electric and Plasma Propulsion
minus 100 KW LEO to GEO deliver 6000 kg in 60
days
minus 100 KW powered Interstellar precursor
mission 10 times payload increase
minus 1 MW Jupiter mission (1 year trip time)
minus Multi-MW class fast Human planetary mission
(1 year round trip to Mars)
minus Options include ion thrusters Hall thrusters
MPD Pulsed Inductive Thrusters and
VASMIR
KEY TECHNOLOGIES Electrode lifetimes power conditioning high energy density
capacitors sputter resistant materials lightweight magnets magnetic nozzle work
thermal control and propellant management
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1316
Magnetoplasmadynamic (MPD) Thrusters
bull RobustSimple design and constru ction canoperate w ith various propellants
bull High Pow er Capab i l ity w ithLow Volume Requirements
Steady- state devices tested to 500-kW pulsed devices tested to severalMW
bull Potential High Performance30- kW tests demonstra ted 70
efficiency at 5000 s using appliedmagnetic fields and l ithiumpropellant (Gianinni Scientific CorpNASA GRC cir ca 1968)
Benef i t s
bull Thruster L i fet ime
Electrode erosion at high
currents
bull MW- Class Oper a t i o nAddress high pow er thermaldesign issues improve thrusterefficiencies
Power management and
distributionPropellant handl ing
Chal lenges
NASA GRC 01 MW- Class MPD Cir ca 1989
NASA GRC 01 MW Steady- State Hel ium MPD Cir ca 1989
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1416
MPD THRUSTER PROGRAM PLANS
USE NUMERICAL MODELING
AND PULSED MW-CLASS MPDTHRUSTER EXPERIMENTS TO
ESTABLISH EFFICIENT MPD
THRUSTER DESIGNS
TRANSITION EFFICIENT
DESIGNS TO MW-CLASSSTEADY-STATE FACILITY
EVALUATE MPD THRUSTER
LIFETIME AND EFFICIENCY
bull 50 EFFICIENCY
bull 5000 HOURS LIFE
bull 2500 s - 7000 s Isp
ENGINEERING MODEL
MPD THRUSTER
FY01-02 FY03-05 FY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1516
PULSED INDUCTIVE THRUSTER PROGRAM PLANS
NUMERICAL
MODELING AND
FABRICATION OF
MULTIPLE REP-RATE
PIT DESIGN
(GRCTRWMSFC)
bull 60 EFFICIENCY
bull HIGH REP-RATE
bull 2500 s - 7500 s Isp
ENGINEERING MODEL
PIT THRUSTER
SINGLE-SHOT
AND MULTIPLE
REP-RATE
EVALUATION
OF PIT
PERFORMANCE
SOLID STATE SWITCH
DEVELOPMENT ANDINTEGRATION INTO
MULTIPLE REP-RATE
THRUSTER
FY01-02 FY03-04 FY05-06 gtFY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1616
CCCCoooo mmmm bbbb iiii nnnn eeee dddd BBBB eeee nnnn eeee ff f f iiii tttt ssss oooo ff f f PPPPrr r r oooo pppp uuuu llll ssss iiii oooo nnnn aaaa nnnn dddd PPPPoooo wwww eeee rr r r
ff f f oooo rr r r PPPPllll uuuu tttt oooo FFFFllll yyyy bbbb yyyy (((((St udy Requested b y Code S Fal l 20 00)))))
Electric Prop-
8cm Ionthrusters
Radioisotope
with StirlingConverters
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
Electric
Propulsion andStirling
RadioisotopeConverters
Direct RTG
bullRadioisotope
Electric Propulsion
bullAdd Electric
Propulsion to
increase PayloadbullNo launch window
constraints direct
fast trajectories
bullStirling Converter
Reduces required
of Pu Modules
bullCombination of Ion
thrusters and
Stirling Converters
bullDoubles
Useable SCPayload and
Power at Flyby
Pluto Flyby Spacecraft Net Mass and Power at Flyby
0
50
100
150
200
250
300
350
400
450
SOA Adv EP Only Adv Stirling Only Adv EP and Stirling
SC Net Mass (kg)or Power (W)
at Flyby
Net Delivered SC Mass SC Power Available at Flyby
Power (BOM) 290 W 474 W 250 W 474 W
Power (Flyby) 230 W 376 W 230 W 435 W
EP Propellant 84 kg 84 kg
Power mass 56 kg 92 kg 29 kg 60 kg
Propulsion mass 29 kg 29 kg
Net SC Mass 121 kg 212 kg 148 kg 243 kg
of Pu Modules 2 7 4 3 6 1 0
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 816
diams Major accomplishments
Design and fabrication of large-area dischargechamber completedDischarge operation characterized on krypton and xenon
propellantsPerformance characterized
diams Near Term Plans (FY01)Manufacture large-area high-voltage ion opticsDemonstrate engine operation at gt 10000 seconds Isp
Ion Propuls ion - In ters t e l la r Prec ursor Tec hnology
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 916
Ion Propuls i on - 5 kW Next -Generat ion Ion Tec hnology
diams Near Term Plans
Conduct design and performance analysis ofnext-generation large-area thrusterComplete detailed mechanical design of thruster
Fabricate and assemble prototype thruster and conductpreliminary performance testing
Sizecomparisonof NSTARand Next-Generation
thruster
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1016
ldquoMicrordquo Ion Engine TechnologyDevelop Prototype
FEASIBILITY OF A HOLLOW-CATHODE-BASED
MICRO ION THRUSTER FOR MICROSPACECRAFT
RELIES ON HIGH IONIZATION EFFICIENCIES DEMONSTRATED WITH
SMALL GRC HIGH ASPECT RATIO HOLLOW CATHODES
GOAL gt25 EFFICIENCY gt1500 S Isp 5-25 W
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1116
00 01 02 03 04 05 06 07
Sub-kW Ion Propulsion Technology Road-Map options
Advanced Moly or Titanium optics
20 kg Xe Throughput
C-C Optics30 kg Xe
Throughput
08 09 10 11 12
05 sccm
Cathode
No Flow Cathode
Moly optics
12 kg Xe Throughput
Regulated 28v PPU
300 W
2800 sec
49 Efficient
12 kg Xe Throughput
300 W
2800 sec
49 Efficient
20 kg Xe Throughput
300 W
3300 sec
56 Efficient
30 kg Xe
Throughput
Thermal and life
limits
assessed
Thermal and life
limits
assessed
Thermal and life
limitsassessed
rsquo06 Option
rsquo09 Option
rsquo12 Option
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1216
HHHH iiii gggg hhhh PPPPoooowwww eeee rr r r PPPPrr r r oooo ppppuuuu llll ssss iiii oooo nnnn
Potential transportation systems includebull Electric and Plasma Propulsion
minus 100 KW LEO to GEO deliver 6000 kg in 60
days
minus 100 KW powered Interstellar precursor
mission 10 times payload increase
minus 1 MW Jupiter mission (1 year trip time)
minus Multi-MW class fast Human planetary mission
(1 year round trip to Mars)
minus Options include ion thrusters Hall thrusters
MPD Pulsed Inductive Thrusters and
VASMIR
KEY TECHNOLOGIES Electrode lifetimes power conditioning high energy density
capacitors sputter resistant materials lightweight magnets magnetic nozzle work
thermal control and propellant management
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1316
Magnetoplasmadynamic (MPD) Thrusters
bull RobustSimple design and constru ction canoperate w ith various propellants
bull High Pow er Capab i l ity w ithLow Volume Requirements
Steady- state devices tested to 500-kW pulsed devices tested to severalMW
bull Potential High Performance30- kW tests demonstra ted 70
efficiency at 5000 s using appliedmagnetic fields and l ithiumpropellant (Gianinni Scientific CorpNASA GRC cir ca 1968)
Benef i t s
bull Thruster L i fet ime
Electrode erosion at high
currents
bull MW- Class Oper a t i o nAddress high pow er thermaldesign issues improve thrusterefficiencies
Power management and
distributionPropellant handl ing
Chal lenges
NASA GRC 01 MW- Class MPD Cir ca 1989
NASA GRC 01 MW Steady- State Hel ium MPD Cir ca 1989
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1416
MPD THRUSTER PROGRAM PLANS
USE NUMERICAL MODELING
AND PULSED MW-CLASS MPDTHRUSTER EXPERIMENTS TO
ESTABLISH EFFICIENT MPD
THRUSTER DESIGNS
TRANSITION EFFICIENT
DESIGNS TO MW-CLASSSTEADY-STATE FACILITY
EVALUATE MPD THRUSTER
LIFETIME AND EFFICIENCY
bull 50 EFFICIENCY
bull 5000 HOURS LIFE
bull 2500 s - 7000 s Isp
ENGINEERING MODEL
MPD THRUSTER
FY01-02 FY03-05 FY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1516
PULSED INDUCTIVE THRUSTER PROGRAM PLANS
NUMERICAL
MODELING AND
FABRICATION OF
MULTIPLE REP-RATE
PIT DESIGN
(GRCTRWMSFC)
bull 60 EFFICIENCY
bull HIGH REP-RATE
bull 2500 s - 7500 s Isp
ENGINEERING MODEL
PIT THRUSTER
SINGLE-SHOT
AND MULTIPLE
REP-RATE
EVALUATION
OF PIT
PERFORMANCE
SOLID STATE SWITCH
DEVELOPMENT ANDINTEGRATION INTO
MULTIPLE REP-RATE
THRUSTER
FY01-02 FY03-04 FY05-06 gtFY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1616
CCCCoooo mmmm bbbb iiii nnnn eeee dddd BBBB eeee nnnn eeee ff f f iiii tttt ssss oooo ff f f PPPPrr r r oooo pppp uuuu llll ssss iiii oooo nnnn aaaa nnnn dddd PPPPoooo wwww eeee rr r r
ff f f oooo rr r r PPPPllll uuuu tttt oooo FFFFllll yyyy bbbb yyyy (((((St udy Requested b y Code S Fal l 20 00)))))
Electric Prop-
8cm Ionthrusters
Radioisotope
with StirlingConverters
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
Electric
Propulsion andStirling
RadioisotopeConverters
Direct RTG
bullRadioisotope
Electric Propulsion
bullAdd Electric
Propulsion to
increase PayloadbullNo launch window
constraints direct
fast trajectories
bullStirling Converter
Reduces required
of Pu Modules
bullCombination of Ion
thrusters and
Stirling Converters
bullDoubles
Useable SCPayload and
Power at Flyby
Pluto Flyby Spacecraft Net Mass and Power at Flyby
0
50
100
150
200
250
300
350
400
450
SOA Adv EP Only Adv Stirling Only Adv EP and Stirling
SC Net Mass (kg)or Power (W)
at Flyby
Net Delivered SC Mass SC Power Available at Flyby
Power (BOM) 290 W 474 W 250 W 474 W
Power (Flyby) 230 W 376 W 230 W 435 W
EP Propellant 84 kg 84 kg
Power mass 56 kg 92 kg 29 kg 60 kg
Propulsion mass 29 kg 29 kg
Net SC Mass 121 kg 212 kg 148 kg 243 kg
of Pu Modules 2 7 4 3 6 1 0
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 916
Ion Propuls i on - 5 kW Next -Generat ion Ion Tec hnology
diams Near Term Plans
Conduct design and performance analysis ofnext-generation large-area thrusterComplete detailed mechanical design of thruster
Fabricate and assemble prototype thruster and conductpreliminary performance testing
Sizecomparisonof NSTARand Next-Generation
thruster
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1016
ldquoMicrordquo Ion Engine TechnologyDevelop Prototype
FEASIBILITY OF A HOLLOW-CATHODE-BASED
MICRO ION THRUSTER FOR MICROSPACECRAFT
RELIES ON HIGH IONIZATION EFFICIENCIES DEMONSTRATED WITH
SMALL GRC HIGH ASPECT RATIO HOLLOW CATHODES
GOAL gt25 EFFICIENCY gt1500 S Isp 5-25 W
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1116
00 01 02 03 04 05 06 07
Sub-kW Ion Propulsion Technology Road-Map options
Advanced Moly or Titanium optics
20 kg Xe Throughput
C-C Optics30 kg Xe
Throughput
08 09 10 11 12
05 sccm
Cathode
No Flow Cathode
Moly optics
12 kg Xe Throughput
Regulated 28v PPU
300 W
2800 sec
49 Efficient
12 kg Xe Throughput
300 W
2800 sec
49 Efficient
20 kg Xe Throughput
300 W
3300 sec
56 Efficient
30 kg Xe
Throughput
Thermal and life
limits
assessed
Thermal and life
limits
assessed
Thermal and life
limitsassessed
rsquo06 Option
rsquo09 Option
rsquo12 Option
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1216
HHHH iiii gggg hhhh PPPPoooowwww eeee rr r r PPPPrr r r oooo ppppuuuu llll ssss iiii oooo nnnn
Potential transportation systems includebull Electric and Plasma Propulsion
minus 100 KW LEO to GEO deliver 6000 kg in 60
days
minus 100 KW powered Interstellar precursor
mission 10 times payload increase
minus 1 MW Jupiter mission (1 year trip time)
minus Multi-MW class fast Human planetary mission
(1 year round trip to Mars)
minus Options include ion thrusters Hall thrusters
MPD Pulsed Inductive Thrusters and
VASMIR
KEY TECHNOLOGIES Electrode lifetimes power conditioning high energy density
capacitors sputter resistant materials lightweight magnets magnetic nozzle work
thermal control and propellant management
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1316
Magnetoplasmadynamic (MPD) Thrusters
bull RobustSimple design and constru ction canoperate w ith various propellants
bull High Pow er Capab i l ity w ithLow Volume Requirements
Steady- state devices tested to 500-kW pulsed devices tested to severalMW
bull Potential High Performance30- kW tests demonstra ted 70
efficiency at 5000 s using appliedmagnetic fields and l ithiumpropellant (Gianinni Scientific CorpNASA GRC cir ca 1968)
Benef i t s
bull Thruster L i fet ime
Electrode erosion at high
currents
bull MW- Class Oper a t i o nAddress high pow er thermaldesign issues improve thrusterefficiencies
Power management and
distributionPropellant handl ing
Chal lenges
NASA GRC 01 MW- Class MPD Cir ca 1989
NASA GRC 01 MW Steady- State Hel ium MPD Cir ca 1989
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1416
MPD THRUSTER PROGRAM PLANS
USE NUMERICAL MODELING
AND PULSED MW-CLASS MPDTHRUSTER EXPERIMENTS TO
ESTABLISH EFFICIENT MPD
THRUSTER DESIGNS
TRANSITION EFFICIENT
DESIGNS TO MW-CLASSSTEADY-STATE FACILITY
EVALUATE MPD THRUSTER
LIFETIME AND EFFICIENCY
bull 50 EFFICIENCY
bull 5000 HOURS LIFE
bull 2500 s - 7000 s Isp
ENGINEERING MODEL
MPD THRUSTER
FY01-02 FY03-05 FY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1516
PULSED INDUCTIVE THRUSTER PROGRAM PLANS
NUMERICAL
MODELING AND
FABRICATION OF
MULTIPLE REP-RATE
PIT DESIGN
(GRCTRWMSFC)
bull 60 EFFICIENCY
bull HIGH REP-RATE
bull 2500 s - 7500 s Isp
ENGINEERING MODEL
PIT THRUSTER
SINGLE-SHOT
AND MULTIPLE
REP-RATE
EVALUATION
OF PIT
PERFORMANCE
SOLID STATE SWITCH
DEVELOPMENT ANDINTEGRATION INTO
MULTIPLE REP-RATE
THRUSTER
FY01-02 FY03-04 FY05-06 gtFY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1616
CCCCoooo mmmm bbbb iiii nnnn eeee dddd BBBB eeee nnnn eeee ff f f iiii tttt ssss oooo ff f f PPPPrr r r oooo pppp uuuu llll ssss iiii oooo nnnn aaaa nnnn dddd PPPPoooo wwww eeee rr r r
ff f f oooo rr r r PPPPllll uuuu tttt oooo FFFFllll yyyy bbbb yyyy (((((St udy Requested b y Code S Fal l 20 00)))))
Electric Prop-
8cm Ionthrusters
Radioisotope
with StirlingConverters
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
Electric
Propulsion andStirling
RadioisotopeConverters
Direct RTG
bullRadioisotope
Electric Propulsion
bullAdd Electric
Propulsion to
increase PayloadbullNo launch window
constraints direct
fast trajectories
bullStirling Converter
Reduces required
of Pu Modules
bullCombination of Ion
thrusters and
Stirling Converters
bullDoubles
Useable SCPayload and
Power at Flyby
Pluto Flyby Spacecraft Net Mass and Power at Flyby
0
50
100
150
200
250
300
350
400
450
SOA Adv EP Only Adv Stirling Only Adv EP and Stirling
SC Net Mass (kg)or Power (W)
at Flyby
Net Delivered SC Mass SC Power Available at Flyby
Power (BOM) 290 W 474 W 250 W 474 W
Power (Flyby) 230 W 376 W 230 W 435 W
EP Propellant 84 kg 84 kg
Power mass 56 kg 92 kg 29 kg 60 kg
Propulsion mass 29 kg 29 kg
Net SC Mass 121 kg 212 kg 148 kg 243 kg
of Pu Modules 2 7 4 3 6 1 0
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1016
ldquoMicrordquo Ion Engine TechnologyDevelop Prototype
FEASIBILITY OF A HOLLOW-CATHODE-BASED
MICRO ION THRUSTER FOR MICROSPACECRAFT
RELIES ON HIGH IONIZATION EFFICIENCIES DEMONSTRATED WITH
SMALL GRC HIGH ASPECT RATIO HOLLOW CATHODES
GOAL gt25 EFFICIENCY gt1500 S Isp 5-25 W
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1116
00 01 02 03 04 05 06 07
Sub-kW Ion Propulsion Technology Road-Map options
Advanced Moly or Titanium optics
20 kg Xe Throughput
C-C Optics30 kg Xe
Throughput
08 09 10 11 12
05 sccm
Cathode
No Flow Cathode
Moly optics
12 kg Xe Throughput
Regulated 28v PPU
300 W
2800 sec
49 Efficient
12 kg Xe Throughput
300 W
2800 sec
49 Efficient
20 kg Xe Throughput
300 W
3300 sec
56 Efficient
30 kg Xe
Throughput
Thermal and life
limits
assessed
Thermal and life
limits
assessed
Thermal and life
limitsassessed
rsquo06 Option
rsquo09 Option
rsquo12 Option
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1216
HHHH iiii gggg hhhh PPPPoooowwww eeee rr r r PPPPrr r r oooo ppppuuuu llll ssss iiii oooo nnnn
Potential transportation systems includebull Electric and Plasma Propulsion
minus 100 KW LEO to GEO deliver 6000 kg in 60
days
minus 100 KW powered Interstellar precursor
mission 10 times payload increase
minus 1 MW Jupiter mission (1 year trip time)
minus Multi-MW class fast Human planetary mission
(1 year round trip to Mars)
minus Options include ion thrusters Hall thrusters
MPD Pulsed Inductive Thrusters and
VASMIR
KEY TECHNOLOGIES Electrode lifetimes power conditioning high energy density
capacitors sputter resistant materials lightweight magnets magnetic nozzle work
thermal control and propellant management
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1316
Magnetoplasmadynamic (MPD) Thrusters
bull RobustSimple design and constru ction canoperate w ith various propellants
bull High Pow er Capab i l ity w ithLow Volume Requirements
Steady- state devices tested to 500-kW pulsed devices tested to severalMW
bull Potential High Performance30- kW tests demonstra ted 70
efficiency at 5000 s using appliedmagnetic fields and l ithiumpropellant (Gianinni Scientific CorpNASA GRC cir ca 1968)
Benef i t s
bull Thruster L i fet ime
Electrode erosion at high
currents
bull MW- Class Oper a t i o nAddress high pow er thermaldesign issues improve thrusterefficiencies
Power management and
distributionPropellant handl ing
Chal lenges
NASA GRC 01 MW- Class MPD Cir ca 1989
NASA GRC 01 MW Steady- State Hel ium MPD Cir ca 1989
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1416
MPD THRUSTER PROGRAM PLANS
USE NUMERICAL MODELING
AND PULSED MW-CLASS MPDTHRUSTER EXPERIMENTS TO
ESTABLISH EFFICIENT MPD
THRUSTER DESIGNS
TRANSITION EFFICIENT
DESIGNS TO MW-CLASSSTEADY-STATE FACILITY
EVALUATE MPD THRUSTER
LIFETIME AND EFFICIENCY
bull 50 EFFICIENCY
bull 5000 HOURS LIFE
bull 2500 s - 7000 s Isp
ENGINEERING MODEL
MPD THRUSTER
FY01-02 FY03-05 FY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1516
PULSED INDUCTIVE THRUSTER PROGRAM PLANS
NUMERICAL
MODELING AND
FABRICATION OF
MULTIPLE REP-RATE
PIT DESIGN
(GRCTRWMSFC)
bull 60 EFFICIENCY
bull HIGH REP-RATE
bull 2500 s - 7500 s Isp
ENGINEERING MODEL
PIT THRUSTER
SINGLE-SHOT
AND MULTIPLE
REP-RATE
EVALUATION
OF PIT
PERFORMANCE
SOLID STATE SWITCH
DEVELOPMENT ANDINTEGRATION INTO
MULTIPLE REP-RATE
THRUSTER
FY01-02 FY03-04 FY05-06 gtFY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1616
CCCCoooo mmmm bbbb iiii nnnn eeee dddd BBBB eeee nnnn eeee ff f f iiii tttt ssss oooo ff f f PPPPrr r r oooo pppp uuuu llll ssss iiii oooo nnnn aaaa nnnn dddd PPPPoooo wwww eeee rr r r
ff f f oooo rr r r PPPPllll uuuu tttt oooo FFFFllll yyyy bbbb yyyy (((((St udy Requested b y Code S Fal l 20 00)))))
Electric Prop-
8cm Ionthrusters
Radioisotope
with StirlingConverters
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
Electric
Propulsion andStirling
RadioisotopeConverters
Direct RTG
bullRadioisotope
Electric Propulsion
bullAdd Electric
Propulsion to
increase PayloadbullNo launch window
constraints direct
fast trajectories
bullStirling Converter
Reduces required
of Pu Modules
bullCombination of Ion
thrusters and
Stirling Converters
bullDoubles
Useable SCPayload and
Power at Flyby
Pluto Flyby Spacecraft Net Mass and Power at Flyby
0
50
100
150
200
250
300
350
400
450
SOA Adv EP Only Adv Stirling Only Adv EP and Stirling
SC Net Mass (kg)or Power (W)
at Flyby
Net Delivered SC Mass SC Power Available at Flyby
Power (BOM) 290 W 474 W 250 W 474 W
Power (Flyby) 230 W 376 W 230 W 435 W
EP Propellant 84 kg 84 kg
Power mass 56 kg 92 kg 29 kg 60 kg
Propulsion mass 29 kg 29 kg
Net SC Mass 121 kg 212 kg 148 kg 243 kg
of Pu Modules 2 7 4 3 6 1 0
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1116
00 01 02 03 04 05 06 07
Sub-kW Ion Propulsion Technology Road-Map options
Advanced Moly or Titanium optics
20 kg Xe Throughput
C-C Optics30 kg Xe
Throughput
08 09 10 11 12
05 sccm
Cathode
No Flow Cathode
Moly optics
12 kg Xe Throughput
Regulated 28v PPU
300 W
2800 sec
49 Efficient
12 kg Xe Throughput
300 W
2800 sec
49 Efficient
20 kg Xe Throughput
300 W
3300 sec
56 Efficient
30 kg Xe
Throughput
Thermal and life
limits
assessed
Thermal and life
limits
assessed
Thermal and life
limitsassessed
rsquo06 Option
rsquo09 Option
rsquo12 Option
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1216
HHHH iiii gggg hhhh PPPPoooowwww eeee rr r r PPPPrr r r oooo ppppuuuu llll ssss iiii oooo nnnn
Potential transportation systems includebull Electric and Plasma Propulsion
minus 100 KW LEO to GEO deliver 6000 kg in 60
days
minus 100 KW powered Interstellar precursor
mission 10 times payload increase
minus 1 MW Jupiter mission (1 year trip time)
minus Multi-MW class fast Human planetary mission
(1 year round trip to Mars)
minus Options include ion thrusters Hall thrusters
MPD Pulsed Inductive Thrusters and
VASMIR
KEY TECHNOLOGIES Electrode lifetimes power conditioning high energy density
capacitors sputter resistant materials lightweight magnets magnetic nozzle work
thermal control and propellant management
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1316
Magnetoplasmadynamic (MPD) Thrusters
bull RobustSimple design and constru ction canoperate w ith various propellants
bull High Pow er Capab i l ity w ithLow Volume Requirements
Steady- state devices tested to 500-kW pulsed devices tested to severalMW
bull Potential High Performance30- kW tests demonstra ted 70
efficiency at 5000 s using appliedmagnetic fields and l ithiumpropellant (Gianinni Scientific CorpNASA GRC cir ca 1968)
Benef i t s
bull Thruster L i fet ime
Electrode erosion at high
currents
bull MW- Class Oper a t i o nAddress high pow er thermaldesign issues improve thrusterefficiencies
Power management and
distributionPropellant handl ing
Chal lenges
NASA GRC 01 MW- Class MPD Cir ca 1989
NASA GRC 01 MW Steady- State Hel ium MPD Cir ca 1989
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1416
MPD THRUSTER PROGRAM PLANS
USE NUMERICAL MODELING
AND PULSED MW-CLASS MPDTHRUSTER EXPERIMENTS TO
ESTABLISH EFFICIENT MPD
THRUSTER DESIGNS
TRANSITION EFFICIENT
DESIGNS TO MW-CLASSSTEADY-STATE FACILITY
EVALUATE MPD THRUSTER
LIFETIME AND EFFICIENCY
bull 50 EFFICIENCY
bull 5000 HOURS LIFE
bull 2500 s - 7000 s Isp
ENGINEERING MODEL
MPD THRUSTER
FY01-02 FY03-05 FY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1516
PULSED INDUCTIVE THRUSTER PROGRAM PLANS
NUMERICAL
MODELING AND
FABRICATION OF
MULTIPLE REP-RATE
PIT DESIGN
(GRCTRWMSFC)
bull 60 EFFICIENCY
bull HIGH REP-RATE
bull 2500 s - 7500 s Isp
ENGINEERING MODEL
PIT THRUSTER
SINGLE-SHOT
AND MULTIPLE
REP-RATE
EVALUATION
OF PIT
PERFORMANCE
SOLID STATE SWITCH
DEVELOPMENT ANDINTEGRATION INTO
MULTIPLE REP-RATE
THRUSTER
FY01-02 FY03-04 FY05-06 gtFY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1616
CCCCoooo mmmm bbbb iiii nnnn eeee dddd BBBB eeee nnnn eeee ff f f iiii tttt ssss oooo ff f f PPPPrr r r oooo pppp uuuu llll ssss iiii oooo nnnn aaaa nnnn dddd PPPPoooo wwww eeee rr r r
ff f f oooo rr r r PPPPllll uuuu tttt oooo FFFFllll yyyy bbbb yyyy (((((St udy Requested b y Code S Fal l 20 00)))))
Electric Prop-
8cm Ionthrusters
Radioisotope
with StirlingConverters
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
Electric
Propulsion andStirling
RadioisotopeConverters
Direct RTG
bullRadioisotope
Electric Propulsion
bullAdd Electric
Propulsion to
increase PayloadbullNo launch window
constraints direct
fast trajectories
bullStirling Converter
Reduces required
of Pu Modules
bullCombination of Ion
thrusters and
Stirling Converters
bullDoubles
Useable SCPayload and
Power at Flyby
Pluto Flyby Spacecraft Net Mass and Power at Flyby
0
50
100
150
200
250
300
350
400
450
SOA Adv EP Only Adv Stirling Only Adv EP and Stirling
SC Net Mass (kg)or Power (W)
at Flyby
Net Delivered SC Mass SC Power Available at Flyby
Power (BOM) 290 W 474 W 250 W 474 W
Power (Flyby) 230 W 376 W 230 W 435 W
EP Propellant 84 kg 84 kg
Power mass 56 kg 92 kg 29 kg 60 kg
Propulsion mass 29 kg 29 kg
Net SC Mass 121 kg 212 kg 148 kg 243 kg
of Pu Modules 2 7 4 3 6 1 0
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1216
HHHH iiii gggg hhhh PPPPoooowwww eeee rr r r PPPPrr r r oooo ppppuuuu llll ssss iiii oooo nnnn
Potential transportation systems includebull Electric and Plasma Propulsion
minus 100 KW LEO to GEO deliver 6000 kg in 60
days
minus 100 KW powered Interstellar precursor
mission 10 times payload increase
minus 1 MW Jupiter mission (1 year trip time)
minus Multi-MW class fast Human planetary mission
(1 year round trip to Mars)
minus Options include ion thrusters Hall thrusters
MPD Pulsed Inductive Thrusters and
VASMIR
KEY TECHNOLOGIES Electrode lifetimes power conditioning high energy density
capacitors sputter resistant materials lightweight magnets magnetic nozzle work
thermal control and propellant management
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1316
Magnetoplasmadynamic (MPD) Thrusters
bull RobustSimple design and constru ction canoperate w ith various propellants
bull High Pow er Capab i l ity w ithLow Volume Requirements
Steady- state devices tested to 500-kW pulsed devices tested to severalMW
bull Potential High Performance30- kW tests demonstra ted 70
efficiency at 5000 s using appliedmagnetic fields and l ithiumpropellant (Gianinni Scientific CorpNASA GRC cir ca 1968)
Benef i t s
bull Thruster L i fet ime
Electrode erosion at high
currents
bull MW- Class Oper a t i o nAddress high pow er thermaldesign issues improve thrusterefficiencies
Power management and
distributionPropellant handl ing
Chal lenges
NASA GRC 01 MW- Class MPD Cir ca 1989
NASA GRC 01 MW Steady- State Hel ium MPD Cir ca 1989
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1416
MPD THRUSTER PROGRAM PLANS
USE NUMERICAL MODELING
AND PULSED MW-CLASS MPDTHRUSTER EXPERIMENTS TO
ESTABLISH EFFICIENT MPD
THRUSTER DESIGNS
TRANSITION EFFICIENT
DESIGNS TO MW-CLASSSTEADY-STATE FACILITY
EVALUATE MPD THRUSTER
LIFETIME AND EFFICIENCY
bull 50 EFFICIENCY
bull 5000 HOURS LIFE
bull 2500 s - 7000 s Isp
ENGINEERING MODEL
MPD THRUSTER
FY01-02 FY03-05 FY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1516
PULSED INDUCTIVE THRUSTER PROGRAM PLANS
NUMERICAL
MODELING AND
FABRICATION OF
MULTIPLE REP-RATE
PIT DESIGN
(GRCTRWMSFC)
bull 60 EFFICIENCY
bull HIGH REP-RATE
bull 2500 s - 7500 s Isp
ENGINEERING MODEL
PIT THRUSTER
SINGLE-SHOT
AND MULTIPLE
REP-RATE
EVALUATION
OF PIT
PERFORMANCE
SOLID STATE SWITCH
DEVELOPMENT ANDINTEGRATION INTO
MULTIPLE REP-RATE
THRUSTER
FY01-02 FY03-04 FY05-06 gtFY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1616
CCCCoooo mmmm bbbb iiii nnnn eeee dddd BBBB eeee nnnn eeee ff f f iiii tttt ssss oooo ff f f PPPPrr r r oooo pppp uuuu llll ssss iiii oooo nnnn aaaa nnnn dddd PPPPoooo wwww eeee rr r r
ff f f oooo rr r r PPPPllll uuuu tttt oooo FFFFllll yyyy bbbb yyyy (((((St udy Requested b y Code S Fal l 20 00)))))
Electric Prop-
8cm Ionthrusters
Radioisotope
with StirlingConverters
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
Electric
Propulsion andStirling
RadioisotopeConverters
Direct RTG
bullRadioisotope
Electric Propulsion
bullAdd Electric
Propulsion to
increase PayloadbullNo launch window
constraints direct
fast trajectories
bullStirling Converter
Reduces required
of Pu Modules
bullCombination of Ion
thrusters and
Stirling Converters
bullDoubles
Useable SCPayload and
Power at Flyby
Pluto Flyby Spacecraft Net Mass and Power at Flyby
0
50
100
150
200
250
300
350
400
450
SOA Adv EP Only Adv Stirling Only Adv EP and Stirling
SC Net Mass (kg)or Power (W)
at Flyby
Net Delivered SC Mass SC Power Available at Flyby
Power (BOM) 290 W 474 W 250 W 474 W
Power (Flyby) 230 W 376 W 230 W 435 W
EP Propellant 84 kg 84 kg
Power mass 56 kg 92 kg 29 kg 60 kg
Propulsion mass 29 kg 29 kg
Net SC Mass 121 kg 212 kg 148 kg 243 kg
of Pu Modules 2 7 4 3 6 1 0
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1316
Magnetoplasmadynamic (MPD) Thrusters
bull RobustSimple design and constru ction canoperate w ith various propellants
bull High Pow er Capab i l ity w ithLow Volume Requirements
Steady- state devices tested to 500-kW pulsed devices tested to severalMW
bull Potential High Performance30- kW tests demonstra ted 70
efficiency at 5000 s using appliedmagnetic fields and l ithiumpropellant (Gianinni Scientific CorpNASA GRC cir ca 1968)
Benef i t s
bull Thruster L i fet ime
Electrode erosion at high
currents
bull MW- Class Oper a t i o nAddress high pow er thermaldesign issues improve thrusterefficiencies
Power management and
distributionPropellant handl ing
Chal lenges
NASA GRC 01 MW- Class MPD Cir ca 1989
NASA GRC 01 MW Steady- State Hel ium MPD Cir ca 1989
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1416
MPD THRUSTER PROGRAM PLANS
USE NUMERICAL MODELING
AND PULSED MW-CLASS MPDTHRUSTER EXPERIMENTS TO
ESTABLISH EFFICIENT MPD
THRUSTER DESIGNS
TRANSITION EFFICIENT
DESIGNS TO MW-CLASSSTEADY-STATE FACILITY
EVALUATE MPD THRUSTER
LIFETIME AND EFFICIENCY
bull 50 EFFICIENCY
bull 5000 HOURS LIFE
bull 2500 s - 7000 s Isp
ENGINEERING MODEL
MPD THRUSTER
FY01-02 FY03-05 FY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1516
PULSED INDUCTIVE THRUSTER PROGRAM PLANS
NUMERICAL
MODELING AND
FABRICATION OF
MULTIPLE REP-RATE
PIT DESIGN
(GRCTRWMSFC)
bull 60 EFFICIENCY
bull HIGH REP-RATE
bull 2500 s - 7500 s Isp
ENGINEERING MODEL
PIT THRUSTER
SINGLE-SHOT
AND MULTIPLE
REP-RATE
EVALUATION
OF PIT
PERFORMANCE
SOLID STATE SWITCH
DEVELOPMENT ANDINTEGRATION INTO
MULTIPLE REP-RATE
THRUSTER
FY01-02 FY03-04 FY05-06 gtFY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1616
CCCCoooo mmmm bbbb iiii nnnn eeee dddd BBBB eeee nnnn eeee ff f f iiii tttt ssss oooo ff f f PPPPrr r r oooo pppp uuuu llll ssss iiii oooo nnnn aaaa nnnn dddd PPPPoooo wwww eeee rr r r
ff f f oooo rr r r PPPPllll uuuu tttt oooo FFFFllll yyyy bbbb yyyy (((((St udy Requested b y Code S Fal l 20 00)))))
Electric Prop-
8cm Ionthrusters
Radioisotope
with StirlingConverters
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
Electric
Propulsion andStirling
RadioisotopeConverters
Direct RTG
bullRadioisotope
Electric Propulsion
bullAdd Electric
Propulsion to
increase PayloadbullNo launch window
constraints direct
fast trajectories
bullStirling Converter
Reduces required
of Pu Modules
bullCombination of Ion
thrusters and
Stirling Converters
bullDoubles
Useable SCPayload and
Power at Flyby
Pluto Flyby Spacecraft Net Mass and Power at Flyby
0
50
100
150
200
250
300
350
400
450
SOA Adv EP Only Adv Stirling Only Adv EP and Stirling
SC Net Mass (kg)or Power (W)
at Flyby
Net Delivered SC Mass SC Power Available at Flyby
Power (BOM) 290 W 474 W 250 W 474 W
Power (Flyby) 230 W 376 W 230 W 435 W
EP Propellant 84 kg 84 kg
Power mass 56 kg 92 kg 29 kg 60 kg
Propulsion mass 29 kg 29 kg
Net SC Mass 121 kg 212 kg 148 kg 243 kg
of Pu Modules 2 7 4 3 6 1 0
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1416
MPD THRUSTER PROGRAM PLANS
USE NUMERICAL MODELING
AND PULSED MW-CLASS MPDTHRUSTER EXPERIMENTS TO
ESTABLISH EFFICIENT MPD
THRUSTER DESIGNS
TRANSITION EFFICIENT
DESIGNS TO MW-CLASSSTEADY-STATE FACILITY
EVALUATE MPD THRUSTER
LIFETIME AND EFFICIENCY
bull 50 EFFICIENCY
bull 5000 HOURS LIFE
bull 2500 s - 7000 s Isp
ENGINEERING MODEL
MPD THRUSTER
FY01-02 FY03-05 FY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1516
PULSED INDUCTIVE THRUSTER PROGRAM PLANS
NUMERICAL
MODELING AND
FABRICATION OF
MULTIPLE REP-RATE
PIT DESIGN
(GRCTRWMSFC)
bull 60 EFFICIENCY
bull HIGH REP-RATE
bull 2500 s - 7500 s Isp
ENGINEERING MODEL
PIT THRUSTER
SINGLE-SHOT
AND MULTIPLE
REP-RATE
EVALUATION
OF PIT
PERFORMANCE
SOLID STATE SWITCH
DEVELOPMENT ANDINTEGRATION INTO
MULTIPLE REP-RATE
THRUSTER
FY01-02 FY03-04 FY05-06 gtFY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1616
CCCCoooo mmmm bbbb iiii nnnn eeee dddd BBBB eeee nnnn eeee ff f f iiii tttt ssss oooo ff f f PPPPrr r r oooo pppp uuuu llll ssss iiii oooo nnnn aaaa nnnn dddd PPPPoooo wwww eeee rr r r
ff f f oooo rr r r PPPPllll uuuu tttt oooo FFFFllll yyyy bbbb yyyy (((((St udy Requested b y Code S Fal l 20 00)))))
Electric Prop-
8cm Ionthrusters
Radioisotope
with StirlingConverters
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
Electric
Propulsion andStirling
RadioisotopeConverters
Direct RTG
bullRadioisotope
Electric Propulsion
bullAdd Electric
Propulsion to
increase PayloadbullNo launch window
constraints direct
fast trajectories
bullStirling Converter
Reduces required
of Pu Modules
bullCombination of Ion
thrusters and
Stirling Converters
bullDoubles
Useable SCPayload and
Power at Flyby
Pluto Flyby Spacecraft Net Mass and Power at Flyby
0
50
100
150
200
250
300
350
400
450
SOA Adv EP Only Adv Stirling Only Adv EP and Stirling
SC Net Mass (kg)or Power (W)
at Flyby
Net Delivered SC Mass SC Power Available at Flyby
Power (BOM) 290 W 474 W 250 W 474 W
Power (Flyby) 230 W 376 W 230 W 435 W
EP Propellant 84 kg 84 kg
Power mass 56 kg 92 kg 29 kg 60 kg
Propulsion mass 29 kg 29 kg
Net SC Mass 121 kg 212 kg 148 kg 243 kg
of Pu Modules 2 7 4 3 6 1 0
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1516
PULSED INDUCTIVE THRUSTER PROGRAM PLANS
NUMERICAL
MODELING AND
FABRICATION OF
MULTIPLE REP-RATE
PIT DESIGN
(GRCTRWMSFC)
bull 60 EFFICIENCY
bull HIGH REP-RATE
bull 2500 s - 7500 s Isp
ENGINEERING MODEL
PIT THRUSTER
SINGLE-SHOT
AND MULTIPLE
REP-RATE
EVALUATION
OF PIT
PERFORMANCE
SOLID STATE SWITCH
DEVELOPMENT ANDINTEGRATION INTO
MULTIPLE REP-RATE
THRUSTER
FY01-02 FY03-04 FY05-06 gtFY06
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1616
CCCCoooo mmmm bbbb iiii nnnn eeee dddd BBBB eeee nnnn eeee ff f f iiii tttt ssss oooo ff f f PPPPrr r r oooo pppp uuuu llll ssss iiii oooo nnnn aaaa nnnn dddd PPPPoooo wwww eeee rr r r
ff f f oooo rr r r PPPPllll uuuu tttt oooo FFFFllll yyyy bbbb yyyy (((((St udy Requested b y Code S Fal l 20 00)))))
Electric Prop-
8cm Ionthrusters
Radioisotope
with StirlingConverters
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
Electric
Propulsion andStirling
RadioisotopeConverters
Direct RTG
bullRadioisotope
Electric Propulsion
bullAdd Electric
Propulsion to
increase PayloadbullNo launch window
constraints direct
fast trajectories
bullStirling Converter
Reduces required
of Pu Modules
bullCombination of Ion
thrusters and
Stirling Converters
bullDoubles
Useable SCPayload and
Power at Flyby
Pluto Flyby Spacecraft Net Mass and Power at Flyby
0
50
100
150
200
250
300
350
400
450
SOA Adv EP Only Adv Stirling Only Adv EP and Stirling
SC Net Mass (kg)or Power (W)
at Flyby
Net Delivered SC Mass SC Power Available at Flyby
Power (BOM) 290 W 474 W 250 W 474 W
Power (Flyby) 230 W 376 W 230 W 435 W
EP Propellant 84 kg 84 kg
Power mass 56 kg 92 kg 29 kg 60 kg
Propulsion mass 29 kg 29 kg
Net SC Mass 121 kg 212 kg 148 kg 243 kg
of Pu Modules 2 7 4 3 6 1 0
872019 NASA_Power_space
httpslidepdfcomreaderfullnasapowerspace 1616
CCCCoooo mmmm bbbb iiii nnnn eeee dddd BBBB eeee nnnn eeee ff f f iiii tttt ssss oooo ff f f PPPPrr r r oooo pppp uuuu llll ssss iiii oooo nnnn aaaa nnnn dddd PPPPoooo wwww eeee rr r r
ff f f oooo rr r r PPPPllll uuuu tttt oooo FFFFllll yyyy bbbb yyyy (((((St udy Requested b y Code S Fal l 20 00)))))
Electric Prop-
8cm Ionthrusters
Radioisotope
with StirlingConverters
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
All CasesAtlas IIIbStar48V
2009 Launch
2020 flyby
Electric
Propulsion andStirling
RadioisotopeConverters
Direct RTG
bullRadioisotope
Electric Propulsion
bullAdd Electric
Propulsion to
increase PayloadbullNo launch window
constraints direct
fast trajectories
bullStirling Converter
Reduces required
of Pu Modules
bullCombination of Ion
thrusters and
Stirling Converters
bullDoubles
Useable SCPayload and
Power at Flyby
Pluto Flyby Spacecraft Net Mass and Power at Flyby
0
50
100
150
200
250
300
350
400
450
SOA Adv EP Only Adv Stirling Only Adv EP and Stirling
SC Net Mass (kg)or Power (W)
at Flyby
Net Delivered SC Mass SC Power Available at Flyby
Power (BOM) 290 W 474 W 250 W 474 W
Power (Flyby) 230 W 376 W 230 W 435 W
EP Propellant 84 kg 84 kg
Power mass 56 kg 92 kg 29 kg 60 kg
Propulsion mass 29 kg 29 kg
Net SC Mass 121 kg 212 kg 148 kg 243 kg
of Pu Modules 2 7 4 3 6 1 0