fusion-enabled pluto orbiter and lander pluto orbiter and lander ... • h or d is used as a...
TRANSCRIPT
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Fusion-EnabledPlutoOrbiterandLander
MichaelPaluszekPrincetonSatelliteSystems,Inc.
US-JapanCT2016August22-24
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OutlineofTalk
● Electricpropulsion● Plutomissionoverview● Missiondesign● Spacecraftdesign● DFDoverviewandstatus
⁃ FRCwithodd-parityRFheating
⁃ D–3Hefuel● DFDsubsystems● Workinprogressandconclusions
SupportedbyNASAInnovativeAdvancedConceptsProgramunderawardNNX16AK28G
SimulationofDFDPlutoApproach
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ElectricPropulsion
● Criticalrelations⁃ Power/thrustrelationship⁃ Rocketequationwithspecificpower
● Specificpoweristhekeytoperformance⁃ Ratioofpowerinthethrusttoengine
mass● Exhaustvelocitydeterminesachievablevelocitychange
Exhaustvelocityofengine
Totalvelocitychange
Massoffuel
MassofpayloadandengineFractionofmassproportionaltofuel
Thrust
DFDgetstoPlutoin4yearsThisisjustthePlutoorbitinsertionmaneuver
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SpecificPower
● Plotonrightbasedonworkdoneassumingdirectinsertion
● Otherelectricpropulsionsystems⁃ Solar–notapplicabletoouterplanetmissions
⁃ FissionElectric
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Destination:PlutoOrbit
PutaspacecraftinorbitaroundPluto,poweralanderusingopticaltransmission,returnhigh-definitionvideo–
andgetthereinonly4years!
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PlutoMission
● Deliverpayload1000kgoforbiterandlander
● 1158Lof3Hefortheentiremission● Arrivesinjust4years● Provides2MWofelectricalpower
⁃ Beam30kWdowntolander● Launchmasscanbeaccommodatedbyalmostanylaunchvehicle
● 3Hefuelcanbepurchasedinsufficientquantitiesnowfromavailablesuppliers
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PlutoMissionComparison
Parameter NewHorizons DFDMission
TraveltimetoPluto 9.5years 4years
Delta-V 290m/s 70,000m/s
PoweratPluto 200W 2,000,000W
DataratetoEarth 1kbit/s >1,000,000kbit/s
Fuel Plutonium D-3He
Trajectory JupiterSwingby Direct
Missiontype Flyby Orbit
Lander No Yes
BottomLine:Youcan’tdotheproposedmissiontoPlutowithanyothertechnology.
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MissionOutline
● Earthdeparture ● Acceleration–Coast–Deceleration
⁃ Dependsonavailablethrust● InsertionintoPlutoflybyorbit● Orbitinsertion● Orbitoperations
⁃ Landerdeployment⁃ Plutoobservations⁃ Landerpowerfromorbit
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Spacecraft
● WiderangeofscientificinstrumentsforPlutoorbitsurveyandalander
● Largeradiatorsforwasteheatrejection
● CylindricalstructureissunshadewithMLI
● OpticalcommunicationsforHDTVbandwidthtoEarth
● Fullyautonomousguidance,navigationandcontrol
ComparisonwithHubbleSpaceTelescope
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SpacecraftSubsystems
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Guidance,NavigationandControl(GN&C)
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GN&C
● Opticalnavigationusedthroughout⁃ ReducesrelianceonDeepSpaceNetwork
⁃ Providescontinuousupdatesduringburns
⁃ OperatesinheliocentricorPlutocentricmodes
● Reactionwheelsforattitudecontrol
● Steeredplasmaplumesforpitchandyawmomentumunloadingandcontrolduringburns
● Attitudecontrolthrustersforrollcontrolandunloading
UKFisUnscentedKalmanFilter
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DeparturefromEarth
● Twooptions⁃ Directinsertionintoheliocentrictrajectory
⁃ DeparturefromLEO● Directinsertion(rocketputsthevehicledirectlyintoheliocentricorbit)requiresaDeltaIVHeavyclasslauncher⁃ $350Mlaunchcost
● Departurefromlowearthparkingorbit⁃ $60Mlaunchcost⁃ Requiresadditionalfuel⁃ Allowsforon-orbitcheckout
SimulationofDFDPlutoVehiclenearISSpriortodeparture
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DepartureTrajectory
● AssumeISSorbit⁃ Allowsastronautcheckoutpriortodeparture
● Burnalongvelocityvector⁃ Notoptimal
● 40Nthrustassumed● Orbitbecomeshyperbolicin7.5days⁃ eisorbiteccentricity⁃ >1ishyperbolic
● Majorcostsavings● On-orbitcheckoutreducesmissionrisk
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ArrivalatPluto
● Optimaltrajectory⁃ UsesMATLAB’sfmincon
▪ Bruteforcedirectmethod▪ Thereareothermethods
⁃ Twodimensionalproblem⁃ Inequalityconstraintonaccelerationmagnitude
⁃ Startsinflybyhyperbola⁃ Usestwicethevelocitychangeofanimpulsiveburnatclosestapproach
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PrincetonFieldReversedConfiguration(PFRC)
8/19/16
● RFheatingwithrotatingmagneticfieldsnaturallylimitsreactorsize⁃ Plasmaradiusinrange20-40cm⁃ Powerof1-10MWisidealforspace
● Confinementwithsuperconductingcoils
● Ultralowradiation
• Linearconfigurationallowsforconfigurationasarocketengine
● FlowmoreD+toaugmentthrust● Exitviamagneticnozzle● Variableexhaustvelocity
● 50to20,000km/s● P=0.5Tue/η,thrust~10-50N
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StatusofPFRCDevelopment
8/19/16
● PrincetonPlasmaPhysicsLaboratoryperformingexperimentswithDept.ofEnergyfunding⁃ ConcludedPFRC-1a,b,cin2011⁃ PFRC-2operatingnow;goaltodemonstratekeVplasmas
withpulselengthsto0.3s⁃ Computationalstudiesonplasmadetachmentinnozzle
● PrincetonSatelliteSystemsperformingmissionandtrajectorydesign,spacebalanceofplantstudiesunderIR&DandnowNIAC⁃ FourjointPPPL/PSSpatents
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DFDDiagram
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DFDSubsystems
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HeatRecycling
● Braytoncycleheatengine⁃ Heathighpressuregastodowork
● UsedinHighTemperatureGasCooledFissionReactors
● Heliumworkingfluid● Pairedcompressor/turbinesets
withcounter-rotatingturbinesandcompressors
● Commonshaftforcompressor,turbineandgenerator
● Needformultiplecompressorandturbinestagesandrecuperatortobedetermined
● Largeradiatorwings
HTGCR
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SuperconductingCoilsDesignedforSpace
● AlphaMagneticSpectrometer-02● Lookingforanti-matteranddarkmatter
● Cooledwithsuperfluidhelium
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SuperconductingCoils
● Eightdiscretecoilsina4mmachine⁃ Someripplewhichwouldbereducedbytheplasmafield
● AxialfieldcompatiblewithHTSandNbTiLTS● Forcesbetweencoilsare5.7×106N
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PowerGenerationandDistribution
● Powergeneratedbya3phaseaxial-fluxHalbachGenerator⁃ Distributionis3phasetoRFdrive⁃ 98%efficientatdesignpoint⁃ AC/DCconvertersand3phasetoonephaseconvertersasneeded
● AverysmallHalbachmotor/generatordevelopedatPrincetonSatelliteSystemsforanArmysatellite
Driverconfiguredasmotor
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Radio-FrequencyHeating
● Odd-parityrotatingmagneticfield● ClassEpowerRFamplifiers
⁃ Transistoroperatesasonon/offswitch⁃ Loadnetworkshapeswaveformsothatthecurrentandvoltagedonotsimultaneouslypeakthusminimizedpowerdissipation(P=IV)
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ThrustVectoring
● 1to2degreedeflectionneededtopointthrustvectorthroughthecenterofmass
● Options⁃ Fixedsteeringcoilsafterthemagneticnozzle
⁃ Gimbaledengine⁃ Movingmass
Fieldlinesasdeflectedbyasteeringcoil
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InstrumentationandControl
● Triplyredundant● Radiationhardprocessors
⁃ BAE5545Multi-Core⁃ Fordeepspaceenvironment
● Plasmameasurements● Powersystemmeasurements● Interactswiththespacecraftcontrolsystem
● UsesPPPLCentralInstrumentationandControlSystem(CPCS)datahandlingsystem⁃ BasedonEPICS,Experimental
PhysicsIndustrialControlSystem⁃ SpaceWireusedfornetworking
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Structure
● Handleslaunchloadsandsuperconductingcoilloads⁃ Engineandspacecraftmustundergoshockandvibrationtesting⁃ Fuelsloshisaconsideration
● DeltaIV⁃ Launchloadsaretypically5-6gaxial⁃ Sinusoidalvibration
▪ Thrust:1.27cm5to6.2Hz,1g6.2to100Hz▪ Lateral:0.7g5to100Hz
⁃ Acoustic⁃ Shockatseparation
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ThrustAugmentation
• H or D is used as apropellant- it flows along the magnetic field lines outside of the separatrix;scrape-offlayer(SOL)e-areheatedbythefusionproductsthatareejectedintotheSOL; e-energytransferredtoionsinplumeexpansion
• This reduces the exhaust velocity of the fusion products from 25,000 km/s to ~50 km/s andincreasesthrustto>20N
• Thrust/Ispisadjustablebasedonratethatgasisinjectedintothegasbox• The exhaust plume is directedby amagnetic nozzle, consistingof a throat coil andnozzle coils toacceleratetheflow.
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Startup
● Fusionengineneedstobestartedandrestartedinspace⁃ Initiatenuclearfusion⁃ Chargethesuperconductingcoils⁃ Roughly100secondsofpowerrequired
● EmployscombustorburningD2andO2carriedonboard⁃ D2Ocanberecycledviaelectrolysis
▪ Wehavepowertospare
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FuelStorage
● Storecryogenicdeuteriumandhelium-3● Super-insulatedtanksandpropellantlines
⁃ UsesMulti-layerInsulation(MLI)● Cryocoolerstorecyclevaporthatisnotneededforpropulsion⁃ Samecryocoolersusedforcoilcooling
NASAZeroBoil-offExperiment
Spacecraftwithoutsunshield
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VacuumVessel
● Presentsfirstwalltoplasma⁃ Mustminimizecontamination
● Supportsinstrumentation● Keepsspacecraftdebrisandoutgassingoutsidethefusionchamber
● Pressuredifferentialverysmall
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Shielding
● Protectfromneutronsandradiation⁃ Superconductingcoilsaresusceptibletoneutrondamage
● BremsstrahlungandsynchrotronradiationmustberecycledfortheRMFdrive⁃ Absorbedbytungstenliningthereactorcoolingtubes
● BoronCarbideforneutronshielding● Someshieldingmayberequiredforthepayloadandforoperationinlow-earthorbitnearastronauts
● Wanttominimizeshielding⁃ Reducesspecificpower⁃ Increasesradiusofsuperconductingcoils
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OtherMissions
Marshumanorbitalmission
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Conclusions/WorkinProgress
● Specificpoweriscritical⁃ Thrustpowertomass⁃ Totalelectricplusthrustpowertomass
● Thrust/massdeterminestriptime● Massofallsubsystemsneedstobequantified● Writingadesigndocument
⁃ Preliminarydesignlevelofinformation⁃ Willallowdesigntocriticaldesignlevelinnextphase