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Slide 1
SPACE POWER SYSTEMS FOR THE 21ST CENTURY
Vincent L. Teofilo, Ph.D.
(408) 743-2275
Lockheed Martin Space Systems Company
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Outline
Satellite Power Systems
Solar Array-Battery Power
Radioisotope Power
Space Nuclear Reactors
Advanced Concepts
Fusion
Matter-Anti-Matter
Vacuum Energy
Warp-Drive Worm Holes
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Corona [1959-70]
10,000 kg of AgO/Zn batteries
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TELEVISION INFRARED OBSERVATION SATELLITE
AMSUA1
AVHRR
ESA
HIRS
IMP
IMU
REA
SAD
SAR ANTENNAS
THERMAL CONTROLPINWHEEL LOUVERS
SOA
VRA
UDA
SBA
AMSU-B
1100 W SOLAR ARRAY
40 Ah BATTERY MODULESTED
SBUV
AMSU-A2
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Hubble Space Telescope
90 Ah NiH2
GaAs/Ge
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Mars Global Surveyor
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Mars Climate Orbiter
Characteristic Requirement Capability
Mission Life 5 Years1 Yr Cruise+AB2 Years Mapping
2 Years Relay
7 Years +
Orbital AvePwr
300 W @ MarsPerihelion
350 W (1600W @ 1AM0Beginning of Life)
EnergyStorage
~ 10,000 DODCycles (60% MaxDOD @ AB End-Game)
(1) 16 A-Hr NiH2 Battery(70% Max DODCapability)
Bus VoltageRange
22 36Vdc @User Load I/F
24 36 Vdc @ User LoadI/F
Redundancy No MissionCritical SinglePoint Failures(MCSPF)
Single NiH2 Battery hasCredible but Low-RiskMCSPF
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60 Ah NiH2 SPV
Battery
Communications
Section
Bus Section
Gateway
Antenna
1 kW eSolar Array
Main Mission
Antenna Panel
Cross LinkAntenna
Iridium Satellite
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IKONOS Satellite
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Solar Power System
IN-T3052
IN-T3055
IN-T3049
Solar Array Drive
Assemblies
(North & South) Fuse Box AssemblyPower Regulation Unit
Battery (North) Battery (South)
Power to
Payload &
HK Loads
Power to
Arcjets
Power to Pyros &
Earth & Sun Sensor
Assemblies
Solar Array
Load Load
SolarArray
SolarArray
Shunt(Fullor
Partial)
SeriesRegulator
ChargeRegulator
DischargeRegulatoror Diode
Battery Load
SeriesRegulator
= Optional EPS Elements= Energy Source/Storage Elements
LoadLoad LoadLoad
SolarArray
SolarArray
Shunt(Fullor
Partial)
SeriesRegulator
ChargeRegulator
DischargeRegulatoror Diode
Battery Load
SeriesRegulator
= Optional EPS Elements= Energy Source/Storage Elements
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A2100 EPS ComponentAccommodation
DUAL Ku-band GIMBALLED(50 diameter) ANTENNA TRANSPONDER SUPORT STRUTS
ACCESS PANELS
SOLAR ARRAY
SHEAR-TIE STRUTS
NORTH BATTERY MODULES
SOUTH BATTERY MODULES
SOLAR ARRAY
PANELS (NORTH)
SOLAR ARRAYPANELS (SOUTH)
BASE PANELS TRANSITIONSTRUCTURE
TRANSPONDER PANEL(NORTH) includes
PRU & FBA
Ref: A. Salim, IECEC, 2000
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Space Solar Cell Development Projections
3rd generation of Lattice matched multi-junction solar cells willreach practical limit of 40-45%. IMM cells on kapton are beingdeveloped at 50-100 um thickness
Thin film nano-crystaline cells will be introduced for cost andmass efficiency intitiallly at 13% efficiency with potential forachieving 20% in 5-10 years using MJ thin film techniques
10%
15%
20%
25%
30%
35%
40%
45%
1971 1975 1980 1985 1990 1995 2000
Year
Silicon
GaAsMulti-Junction
2005
40-45% in 10-15 years
1st Generation
2nd Generation
3rd Generation
20152010 2020
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Solar Panel Characteristics
PV Cell Technology
BOL
Efficiency W/m2
Cell W/kg
Panel
W/kg1
Thin Film [Triple-Junction (TJ)
amorphous Si on 1 mm Poly] 7.5 93 440 352
Thin Film [CIGS on 1.5 mm Al] 13 169 627 502
High Efficiency Si 17.5 128 182 60
GaAs Triple Junction 28 245 291 88
GaAs XJ (projected~2009) 34 298 353 107
GaAs TJ on Kapton Substrate 28 245 353 174
1 - Panel with interconnects and substrate or support framing
Boeing 100 kW Array (SPW-2006)
ATK 10 kW Array (SPW-2006)LM A2100 Solar Array Wing Assembly
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Thin Film Solar PV
Evaporation of elements simultaneously or in aprescribed sequence,
Sputtering of metals followed by selenization with H2Se, Reactive sputtering of metals with Se vapor,
Printing of metals from ink precursors followed by selenization[requires no vacuum]
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HIGH-EFFICIENCY III-V Thin MJ CELLS(SpectroLab)
thin-cell coupon on a 95-mm radius cylinder.
Ref: D. Law et al., Lightweight, Flexible, High-efficiency Iii-vMultijunction Cells, WCPEC 2006
Triple-junction structures were deposited by metalorganic vapor phase epitaxy (MOVPE) in 4 wafer
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PRIMARYREFLECTOR
32.4 m
PCM
THERMIONIC
CONVERTER
THERMALRECEIVER
SECONDARY
CONCENTRATOR
THERMIONICCONVERTER
THERMAL STORAGE
PRIMARYREFLECTOR
32.4 m
PCM
THERMIONIC
CONVERTER
THERMALRECEIVER
SECONDARY
CONCENTRATOR
THERMIONICCONVERTER
THERMAL STORAGE
Solar Thermal Thermionic Power System
Able to Operate in Van Allen Belts
Volume ~1/2 of SA/Batt Power
Mass ~1/3 of SA/ Batt Power at 75 W/m2
Using a new diffracting concentrator lenswhich weighs 0.5 kg/m2
BeO Phase Change Material used to heat TIelements to provide power during Eclipse
Satellite applications at > 30 kWe
NASA MSFC Ground Demo [Clark- STAIF 2006]
MSFC Ground Test
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Space Battery Cell Comparisons
0
100
200
300
400
500
0 50 100 150 200 250 300 350
Li-SPE
Li-Ion
AgO/ZnSecondary
Ni/H2
Ni/Cd
Pb/PbO
Ni/MH
ENERGYDENSITY
(Wh/l)
SPECIFIC ENERGY (Wh/kg)
AgO/Zn Primary
LiSO2
LiMnO2
400
Li(CF)x
LiSOCl 2
Advanced Li Polymer
Current Li Ion batteries using liquid electrolytes provide 100-125- W/kg Future Li Ion batttery cells with solid electrolytes and nano-structured electrodes will provide
> 200 Wh/kg batteries in 10 years
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Potential Spacecraft Energy Sources
2.4 x 10108cal/s-cc
ZPF
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Range of Energy Source Applications
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Solar Array-Battery Systems vs. Solar Array -Fuel Cell Hybrid System
Fuel Cells are not competitive with eletrochemical energy storage due tolower charge-discharge efficiency
15
20
25
30
35
40
45
50
200 400 600 800 1000
Peak Power (W)
Mass(kg
Fuel Cell Hybrid
Batteries - 1 day
Batteries - 1 week
Batteries - 1 month
Batteries - 6 months
Batteries - 1 year
[Teofilo- IECEC 2006]
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>40 RTGs flown for space science missionsfrom 3 W to 300 W
Design for Launch Safety against Pu238
release is major cost driver
Uses 20 General Purpose Heat Source AssembliesTo generate 290 W
Currently using of Russian Pu238 but in future
INL to produce Pu
238
Radioisotope Power
GPHS RTG
56 kg20 GPHS
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Planetary Science Mission S/C EPS
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NASA Missions That Have Used RTGs
NIMBUS B-1 1968 (Aborted) -- -- --III 1969 SNAP 19 (1) ~28 PbTe
APOLLO 11 1969 Heater Units -- --
12 1969 SNAP 27 (1) ~73 PbTe13 1970 (Aborted) -- -- --14 1971 SNAP 27 (1) ~73 PbTe15 1971 16 1972 17 1972
PIONEER 10 1972 SNAP 19 (4) ~40 PbTe/TAGS11 1973
VIKING 1 1975 SNAP 19 (2) ~35 PbTe/TAGS2 1975
VOYAGER 1 1977 MHW (3) ~150 SiGe
2 1977 GALILEO 1989 GPHS-RTG (2) ~285 SiGeULYSSES 1990 GPHS-RTG (2) ~285 SiGePATHFINDER 1996 Heater Units -- --CASSINI 1997 GPHS-RTG (3) ~285 SiGe
Power Level ThermoelectricsMissions Launch Year Type of RTG Per Unit (We) Used
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Radioisotope MissionsUsed safely on 24 missions since 1961
8 RTG Earth Orbit missions (Transit, Nimbus, LES) 7 RTG planetary missions (Pioneer, Voyager, Ulysses, Galileo, Cassini) 5 RTG moon missions (Apollo ALSEP) 2 RTG Mars missions (Viking 1&2) RHUs used on Apollo 11, Mars Pathfinder & MERs among others
MER (2003)
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Voyager Spacecraft
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Galileo Spacecraft
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Advanced Stirling RadioisotopeGenerator
DESIGN FEATURES
Power: 112 We (BOM)94 We (14 yrs)
Mass: 20 kg
System Efficiency: 30%
Dimensions: 88.9cm (length
26.7 (tip-tip)
Voltage: 28 + 0.2 Vdc
Fuel: 2 GPHS modules
Re-Programed: April 2006 to utilizeAdvanced Stirling
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Radioisotope Thermophotvoltaic
NASA Funded DevelopmentCreare Tested 100 We Engineering Test unitUses two GPHS modules producing
500WtDemonstrated Integrated System
Efficiency 17%Design Mass of 7.0 kg with Radiators for
specific energy of 14 W/kg
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Space Nuclear Reactors
Coolant In
Coolant Out
Fast Spectrum Reactors (>500keV)With high power density for compactness
External reflectors for mechanical simplicity
LiH Shield for low mass
Reflector
Shield
Fuel andModerator
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Space Nuclear Reactor History
500 We SNAP-10A 1965
SOVIET SPACENuclear Initiative
>30 reactors flownusing TE and TI(2)
1969-89 1.5 to 5 kWe
1st Space Nuclear Initiative1950-74
SP-100 Technolgy developed in 2nd Space Nuclear Initiative 1983-95
5 kWe TOPAZ
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Nuclear Thermal Propulsion
1 GWt nuclear reactor heats hydrogen to 2200-3000K
Generates 15,000 to 75,000 lb thrust in burns up to an hour
Can be configured to also provide steady state electrical power of
50-100kWe Bimodal or Trimodal designs
20 Reactor/Rockets designed, built and tested 1959-72 in Rover/Nerva Programfor ~$1.4B before termination in 1974 to fund Space Shuttle development
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STAR-C Thermionic Reactor
Solid Graphite Core with Thermionicelements Heated to 1800 K and rejecting heatto heat pipe radiator at 1000K 9000-1000 K
40 kWe unit ~1100 kg with PC and Radiator
Conversion Efficiency of 16% withTH = 1800K and TC= 1000 K
Develop High Efficiency Nano TechnogyTI Convertors with Lower TH and TC
STAR WARS STIMULATED SMALL REACTOR CONCEPTS
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Gas Cooled Reactor
Development Issue: He-Xe gas coolant replenishment over life
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Heat Pipe Reactor
Fission power is generated in uranium fuel-pins. The power is conducted toheatpipes which transfer the power to an ex-core power conversion system(orintermediate HX).
Heatpipes provide the efficiency of 2-phase liquid-metal heat transfer in apassive, simple, well-characterized volume.
HX can interface with any conversion system or heat pipes can go directly to
thermo-electric or thermophotvoltaic power conversion system.
100 kWe Reactor/Shield Mass ~ 1000 kg
Combined with Stirling engine yields specific power of 50 W/kg
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Jupiter Icy Moons Orbiter Space Craft
2003 Notional Concept (JPL)
2001 A Space Odyssey (Universal Studios)
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Proposed JIMO Configuration
MISSION/
AVIONICS
MODULE
HIGH GAIN ANTENNA
3.00 METER
XENON TANK
11314 Kg
SP100 STYLE
130KWe REACTOR
DEPLOYABLEFLAT RADIATOR
90 M2
ATLAS HLV
5 M FAIRING
DEPLOYING BOOM
PMAD
4 BOXES
TE CONV
12 PLCS
NEXT THRUSTER
36 PLCS (18/SIDE)
STOWED RADIATOR
2 PLCS
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S b d S l P (SBSP)
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Space-based Solar Power (SBSP)
Renewed interest in an old idea giventodays perspectives
Peak oil, global environmentalconcerns, and growing world-wideenergy demand
Attractive option within future energyportfolio
Very few clean, safe, inexhaustible,reliable, and affordable alternatives
Significant changes in recent yearsenabling improved
SBSP economics Technology advancements, emerging
applications, and market pricingrealities
CPV selected for high efficiency (>40%)But impact of radiator for cooling cellsprovides net W/kg
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Progress in Magnetic Confinement Fusion
DT Terrestrial Controlled Fusion requires (1) periodic vacuumconfinement and thermal blanket structural Materialreplacement and (2) breeding sufficient tritium to replace thatconsumed. This makes it uneconomical for commercial powergeneration. Advanced fuels (d,3) and (p,B11) would eliminateSuch requirements but require much higher confinementconditions obtainable by magnetic fields > 30 Tesla.
Inertial Electrostatic Confinement IEC
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Inertial Electrostatic Confinement IEC
University Of Wisconsin IEC Experimental FacilitySee: http://fti.neep.wisc.edu/publist?which=fdm50
Fusion Reactions vs Grid Bias
Magnetically Channeled Spherical IEC propulsion Experiment
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Inertial Electrostatic Confinement Space Thruster
Plasma Jet Grid
Xe Propellant Estimated Performance
Thrust = 34 mN, Isp = 3000 s, Accelerating = 500 W, t ~
62-68% , Voltage = 600V
p-B11 Propellant Estimated Performance
Thrust= > 1 N , Isp >104s , V = 150kV , tt > 1 N> 1 N
Miley et al, Technolgy of Fusion Energy, 2008
Magneto-Inertial Fusion (MIF)
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Magneto-Inertial Fusion (MIF)
plasma density intermediate betweenconventional MFE and ICF
Avoid huge, steady-state magnets ofconventional MFE,
Avoid the problem of extremely highpulsed power (1000s TW) Compactreactor
Offers potentially a low-cost R&D path
Lawsons criteria excessenergy, n > 1014 s.m-3
Material Liner
Solid
Liquid
Gaseous
Target Plasma
Magnetic fieldused to insulate
the target plasma
from the liner
Magneto-Kinetic Compression MIF
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Magneto Kinetic Compression MIF
Flowing Liquid Metal Heat Exchanger/ Breeder
~ 20 m
BURN CHAMBER
(Dch ~ 5 cm)
10-30 m
1 m
Magnetic
Expansion ChamberAccelerator Source
Current experiment to createinitial FRC plasmoid forfusion breakeven experiment
Advantages over ITER tokamak Minimum B field at highest plasma pressure (~1)
Simple linear system reactor wall is a steel pipe
Variable output power ~ 10-100 MW not multi-GW
Burn chamber well separated from plasmoidformation/heating.
Direct electric power conversion with expansion offusion heated plasmoid (Brayton cycle - > 90%)
Low mass system directly applicable to spacepropulsion
Key physics and scaling have been demonstrated
Developmental cost orders of magnitude less -
Proof-of-Principle experiment ~ 3 M$ / year
Energy required to achievefusion conditions is transferredto FRC plasmoid from array ofaxially sequenced coils.
Interplanetary Fusion Propulsion
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Interplanetary Fusion Propulsion
Reactions: d + t = He(3.52 Mev) + n (14 MeV)d + He3 = He4 + p [ 18.3 MeV]
Lawson Criteria: n > 1014 sec exceeded throughsteady state and pulsed magnetic confinement
Effective Exhaust Velocity, Ve (m/s)
Chem
Fission
Fusion
0.1 (kW/kg)
1.0
10.0
100.0
103
104
105
106
101
102
103
2000 2010 2020 2030 2040
PHYSICS DEMO
Tech Development
Ground DEMO
FLIGHT DEMO
MANNED MISSION
Interstellar Anti-matter Propulsion
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Interstellar Anti matter Propulsion
Fuel Mass for round-trip to Alpha Centauri at 0.1 c: 0.01 Msc / 0.1 (conversion eff.) = 0.1 Msc
For 100 ton Space Ship 10 tons of anti-protons cost $1021
~ 3 ng of p- produced /yr in 2002
Dark Energy and Matter
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Dark Energy and Matter
General Relativity Equation: r/r = 4G ( + 3p)/3Normal matter creates gravitational attraction and slows down cosmological expansion. Dark matter alsocauses attraction. For vacuum the situation is opposite: positive vacuum energy anti-gravitates, i.e.creates gravitational repulsion and its density is constant.
QUANTUM VACUUM ENERGY FIELD
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Q
Spectral Energy Density Planck ( 1911)
(, ) = 82 [h/( h/ 1) + h/2 ]c3
Heisenberg Uncertainty Principle: x v < hMin Energy at T = 0 : h/2 for each EM harmonic mode
up to Planck Frequency p = 1.9 x 1043 Hz
p = 22c /G2h = 10109 J/cc Einstein, Nernst study zero-point energy (1913-16)
Casimir identifies Quantum Zero point Field (ZPF) assource of force between parallel plates (1948)
Thought experiment by Forward shows principle oftapping zero-point energy (1984).
USAF Study identified ZPF experiments for furtherstudy (1996).
Casimir Force definitively measured by Lamoreaux(1997) and to 1% by Mohideen (2003)
Newtons Laws derived from Maxwells Equations byHaisch, Rueda and Puthoff (Phys. Rev 1994) and(Anal.Physik- 2005)
Casimir Force
Quantum Vacuum Plasma Thruster (QVPT)?
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( )
The local quantum vacuum density is related to local matter density?
- [ H. White STAIF 2007]
A QVPT, in principle, can be likened to a conventional plasma thruster that
uses crossed E and B fields to induce a plasma drift in the propellant whichfor the vacuum field are p+-p- and e+-e- pairs.
The difference arises in the fact that a QVPT uses quantum vacuumfluctuations as the fuel source mitigating the need to carry propellant.
This suggests much higher ISP is available for QVPT systems limited only bysupply power storage densities.
Shawyer EM Drive for Chinese QVPT
vaclocalm
vac
localm
vaclocalvac
_
_
_ ==
Energy for Warp Drive
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By creating the energy equivalent of negative mass the space in front of aspace ship can be contracted and that behind expanded with energy:
E = -3.5 x 1030 kg x vs/c
or x c2 = ( 3 x 106m/s)2
E = -3.15 x 1042 Joules
for each factor of the speed of light
Vacuum energy of p = 10109 J/cc may be more then enough to provide themass equivalence energy to Warp Space.
However, current vacuum energy extraction concepts may be limited to 50 W/kg
Advanced Radioisotope Power Systems will be needed for Lunarexploration using Stirling or TPV energy conversion
Nuclear reactors may be need for manned Lunar or Mars bases after ~2020
Nuclear Thermal Propulsion development interrupted in 1974 may becontinued for more efficient manned space transportation
Fusion power/propulsion may supplant nuclear fission due to greater
safety and implemeted early for replacing HCTs
Worm holes may be the only possible method to explore the universe
Future R&D in Advanced Space Power Sources
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Development of advanced thin film PV and Li Ion batteries
Development of Solar Thermal Thermionic Power system for high
power applications
Development of nuclear reactors and for Lunar Bases and SpaceCraft power/propulsion [2006-2030]
Research and Develop Space Fusion Power/PropulsionTechnology [2006-2040]
Research Physics and Technology for Interstellar Space Travel
[2006- 2???]
See: AIAA Frontiers in Propulsion Science [http://www.aiaa.org/content.cfm?pageid=360&id=1743 ]