UNBUNDLINGSPACEPOWER
SYSTEMSTOFOSTER
SPACE-TO-SPACEPOWER
BEAMINGAPPLICATIONS
IEEEWiSEE2015
SpaceSolarPowerWorkshop2015
December14,2015
Presenter: GaryPearceBarnhard,President&CEO
XtraordinaryInnovaGveSpacePartnerships,Inc.
(XISP-Inc)
gary.barnhard@xisp-inc.com
www.xisp-inc.com
1
Ø MissionDefiniGon
Ø
Ø
Ø
Ø
Outline
TheProblem
ThePotenGalImpacts...
RelevancetoNASA&Others...
Whatareweunbundling?
Ø ExperimentOutline
Ø
Ø
Ø
Ø
ObjecGves
TestBedExperiments
CommercialRequirements
WorkVectors
Ø TechnologicalChallenges
Ø OurTeamCircaToday
Ø NextSteps
Ø Conclusion
Ø BackupSlides(intendedforofflinediscussiononly)
2
What’sNewwiththeSSPBMission?
Ø MissionDefiniGon
Ø  ConceptofOperaGonsismoredetailed
Ø TechnicalTeam
Ø  LinktoCubeQuestChallengeTeamAlphaCubeSat
Ø  InterestfromallsectorsconGnuestogrow
Ø  ArchitecGngandmakingcollaboraGonworkisachallenge
Ø Resources&Schedule
Ø  NASAhasclassifiedSSPBasaCommercialMission
Ø  NASA’slevelandtypeofparGcipaGonisundernegoGaGon
Ø  NASAhasacknowledgedandiscognizantofformalCASISresourcerequest
(missiondevelopment,integraGon,launch,ISSequipment,andISScrewGme).
Ø ExperimentDetails
Ø  Socialmediavideos,
Ø  FlightTestArGcleDesigns
Ø  TestbedExperiments
Ø CommercialRequirements
Ø  Newandbeaerdefinedrequirements
3
TheProblem...
XISP-Inchashypothesizedthatunbundlingpower
systems(i.e.,theseparaGonofpowergeneraGon,
transmission,control,storage,andloads)can:
•reducespacecraecomplexity,massand/orvolume
•allowreallocaGonofspacecraemassand/orvolume
•alterthecadenceofspacecraemissionoperaGons
•reduceoreliminatesolarpoinGngrequirements
•impartaddiGonaldelta-Vtospacecrae/debris -indirectly(poweraugmentaGon) -directly(momentumtransfer)
4
ThePotenGalImpacts...
•  MiGgaGngriskscanyieldmoremissionsandmoresuccessfulones
•  Fosteringthedevelopmentoflooselycoupledmodular
structures
•  enableslargescaleadaptablespacestructures
•  minimizesconductedthermaland/orstructuralloads
•  FacilitaGngtheformaGonflyingofmulGplespacecrae
•  enablesinterferometricgroups,swarms,andredundancy
•  createsnewdatafusionandpaaernrecogniGonopGons
•  Simplifieddistributedpayloadandsubsysteminfrastructure
•  enablesmulGpleplug-inandplug-outinterfaces
•  opensnewopportuniGesforsharedorbitalplahorms
•  communicaGons
•  remotesensing
•  navigaGon
•  power
5
RelevancetoNASA&Others-1
6
RelevancetoNASA&Others-2
•
•
ThisworkispartofanoverarchingSpaceActUmbrella
AgreementundernegoGaGonbetweenNASAHeadquarters
andXISP-Inc,forwhichtheCommercialSpace-to-Space
PowerBeaming(SSPB)missionisanAnnex,aswellasaninplaceNASAARCSpaceActAgreementforMission
OperaGonsControlApplicaGons(MOCA).
TheXISP-IncCommercialSSPBmissionusingcubesattargets
todemonstratepowerbeamingfromISSrequiresthe
cooperaGonofNASA,Industry,academia,andinternaGonal
partners.
Theworkwillresultinaneartermdemonstra2onof
space-to-spacepowerbeaming,andprovideatestbed
toallowfortherapiditera2onofdesignsand
experiments.
7
RelevancetoNASA&Others-3
•  EstablishingafuncGoningISSpowerbeamingtestbedcould
allowexperimentaGonandvalidaGonofcomponentsof
largerpowerbeamingsystems,andreducetheriskofthe
developmentofthelargerdedicatedsystems.
•  AlthoughtheexperimentswithISSandcubesatswouldbe
smallscale,therecouldbeimmediateapplicaGonsfor
subsatellitesnearISS,repurposedlogisGcscarriersservingas
co-orbiGngfree-flyermanufacturingcells,aswellasdesigns
fordistributedpayloadsandsensorsfordeepspacemissions
includinglunarandasteroidalassaywork.
TheISSisanextraordinaryresourcethatcan
beleveragedtodrama2callylowerthecostof
spacesolarpowertechnologydevelopment.
8
PowerSystemBlockDiagram
Sources
Transducers
Storage
Transmission/
Distribution/Conversion
Loads
INSTRUMENTATION/SENSORS
ACTUATORS/MECHANISMS/THERMALSINK/GROUNDING
COMMAND&CONTROL/FLOWLOGIC
SYSTEMMANAGEMENT
9
SSPBExperimentOverlay
•
•
•
•
PrimarySource:Solarflux,LEO
Transducer:ISSPowerSystem,photovoltaiccells
Storage:ISSPowerSystem,baaeries
Transmission:ISSPowerSystem,PMADtoJEMEFUGlityPort
---------------------
•  InputPower:3Kw,JEMExposedFacilityPort
•  DCPowertoMicrowaveConversion
•  BeamFormingAntenna
•  FreeSpaceTransmission
•  RecepQonConversiontoDC
•  DeliveredPowertoSpacecraRPowerSystemBus
---------------------
•  SpacecraeLoads
10
ExperimentObjecGves
(1)Demonstratespace-to-spacepowerbeamingbypowering
mulGpleco-orbiGngspacecraeiniGallyusingoneormore
InternaGonalSpaceStaGon(ISS)basedKa-bandtransmiaers.
(2)DemonstratethesuccessfulcharacterizaGonaswellasthe
directandindirectuseofradiantenergy“beam”components.
(3)Reducethecost,schedule,andtechnicalriskassociatedwith
theuseofthespacesolarpowertechnologytobeaeraddress
themissionchallengesforanewspacecraeand/or
infrastructure.
11
ExperimentDescripGon
Thisexperimentsetwillgivemissionusersanenhancedalternate
powersupplyandsubstanGatefurtherdevelopmentofpower
beamingtechnology.
Thisexperimentisanopportunitytocraeviabletechnology
demonstraGonsthatwillestablishthebasisforaconfluenceof
interestbetweenrealmissionusersandthetechnology
developmenteffort.
TheresultsofthiseffortwillleadtotheeffecGveuseofbeamed
energytosupport:
•  sustainedoperaGons,
•  directlyand/orindirectlyaugmentedpropulsion,and
•  looselycoupledmodularstructures,
•  newopportuniGesforadvancedmodularinfrastructure
12
SSPBTestBedExperiments
Ø TestBedExperiments
Ø End-to-End&PiecewiseEfficiencyOpGmizaGon
Ø  DC===>Microwave,
Ø  BeamForming,Transmission,Rectenna
Ø  Microwave===>DC
Ø Far/NearFieldEffects&Boundaries
Ø FormaGonFlying/Alignment/LooselyCoupled
Structures
Ø OpGmizaGon/Scaling/EfficacyoftheSoluGonSet
Wheredoesitmakesensetousethetechnology?
13
SSPB&CommercialRequirements
Ø CommercialRequirements
Ø AsteroidalAssay
Ø Co-orbiGngFree-flyers
Ø Propulsion(delta-VaugmentaGon)
Ø Plug-In/Plug-OutInfrastructurePlahorms
Ø OperaGonalCadence/CycleEvoluGon
Ø InternaGonalLunarDecadeSupport
14
MathemaGcsofPowerBeaming*-PowerDensity
pd =​𝐴𝑡𝑃𝑡/λ2𝐷2 pdisthepowerdensityatthecenterofthereceivinglocaGon
𝑃𝑡 isthetotalradiatedpowerfromthetransmiaer
𝐴𝑡 isthetotalareaofthetransmixngantenna
λ2isthewavelengthsquared
𝐷2
istheseparaGonbetweentheaperturessquared
*WilliamC.Brown,LifeFellow,IEEE,andE.EugeneEves,
BeamedMicrowavePowerTransmissionanditsApplicaGonto
Space,IEEETransacGonsOnMicrowaveTheoryandTechniques,
Vol.40,No.6.June1992
15
PowerDensity*-MoreOpGmalSoluGons
XISP-IncCommercialSpace-to-SpacePowerBeamingMission
CASE1-KaLow26.5GHz
CASE2-KaTarget36GHz
Distance
Power
Received
PowerDensity
(waas/cm**2)
RectennaArea
(cm**2)
Pr
=
Pd
*
Ar
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
=
=
=
=
=
=
=
=
=
=
=
=
=
=
=
0.009643
0.009643
0.009643
0.009643
0.009643
0.009643
0.009643
0.009643
0.009643
0.009643
0.009643
0.009643
0.009643
0.009643
0.009643
*
*
*
*
*
*
*
*
*
*
*
*
*
*
*
100
200
300
400
500
600
1000
4000
5000
6000
6219
7000
7500
8000
9000
=
=
=
=
=
=
=
=
=
=
=
=
=
=
=
0.96
1.93
2.89
3.86
4.82
5.79
9.64
38.57
48.21
57.86
59.97
67.50
72.32
77.14
86.79
200m
Pr
= 0.00964 * 10000 = 96.43 wads 200m
PowerReceived
Distance
Power
Received
PowerDensity
(waas/cm**2)
RectennaArea
(cm**2)
Pr
=
Pd
*
Ar
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
= 0.0177449
= 0.0177449
= 0.0177449
= 0.0177449
= 0.0177449
= 0.0177449
= 0.0177449
= 0.0177449
= 0.0177449
= 0.0177449
= 0.0177449
= 0.0177449
= 0.0177449
= 0.0177449
= 0.0177449
*
*
*
*
*
*
*
*
*
*
*
*
*
*
*
100
200
300
400
500
600
1000
4000
5000
6000
6219
7000
7500
8000
9000
=
=
=
=
=
=
=
=
=
=
=
=
=
=
=
1.77
3.55
5.32
7.10
8.87
10.65
17.74
70.98
88.72
106.47
110.36
124.21
133.09
141.96
159.70
PowerReceived
Distance
waas waas waas waas waas waas waas waas waas waas waas waas waas waas waas CASE3-WTarget95GHz
Power
Received
PowerDensity
(waas/cm**2)
RectennaArea
(cm**2)
PowerReceived
waas waas waas waas waas waas waas waas waas waas waas waas waas waas waas Pr
=
Pd
*
Ar
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
=
=
=
=
=
=
=
=
=
=
=
=
=
=
=
0.123307
0.123307
0.123307
0.123307
0.123307
0.123307
0.123307
0.123307
0.123307
0.123307
0.123307
0.123307
0.123307
0.123307
0.123307
*
*
*
*
*
*
*
*
*
*
*
*
*
*
*
100
200
300
400
500
600
1000
4000
5000
6000
6219
7000
7500
8000
9000
=
=
=
=
=
=
=
=
=
=
=
=
=
=
=
12.33
24.66
36.99
49.32
61.65
73.98
123.31
493.23
616.54
739.84
766.85
863.15
924.81
986.46
1109.77
waas
waas
waas
waas
waas
waas
waas
waas
waas
waas
waas
waas
waas
waas
waas
Pr = 0.01774 * 10000 = 177.45 wads 200m Pr = 0.12331 * 10000 = 1233.07 wads
AssumesuseofanInternaGonalSpaceStaGonKibo
ExposedFacility(KEF)GimbalMountedPhased
ArrayTransmiaer,18”DiameterAperture(min),
3000Waasoutputpower(max)
16
RectennaDesignElements
•  RectennaAreas–100cm2(1U)to1m2(100U)
•  RectennaTypes–2DRectangular,PolarizedSpiral,Fractal,
etc.
–3DPyramid,Conical,Fractal,etc.
–ReflectarrayandphotovoltaiccombinaGons
•  BuildOpGons–Earthmanufactured,deployedon-orbit
–Earthmanufactured,assembledon-orbit
–3DPrintedon-orbit
17
TetrahedralTarget&FormaGon
•  Tetrahedron–mostfundamentallocked3dimensional
structure.
•  AllowsforfixedlocalposiGon/orientaGon.
•  ApplicabletobothindividualphysicaltargetsandformaGons.
•  BothtargetandformaGonscalefactorsmustbe
experimentallydeterminedbasedonthesensible
combinaGonoffarfieldandnearfieldeffectsobserved.
18
BeamtoTetrahedralFormaGon
Far&NearFieldInteracGons
I
S
S
19
JAXAInter-orbitCommunicaGonsSystem(ICS-EF)
20
JEMExposedFacilityAccommodaGons
21
Terrestrial95GHzTransmiaer(AFRLDesign)
22
XISP-Inc/DSI3USSPBFlightTestArGcleConcept*
*3-DCADmodelwithbodymountedsolararraysremoved,theactualSSPBflight
testarGcleswillalsoincorporateRectennaswhicharenotshown.
23
AlphaCubeSatDerivedFlightTestArGcles*
*Alternate6UflighttestarGcleconceptderivedfromNASACubeQuestChallenge
TeamAlphaCubeSatdesign
24
CyclopsConceptofOperaGons
25
JEMAirlock&CubeSatLauncher
26
ExperimentProcedure-1
Theproposedexperimenthasthreephases:
•  PhaseIisgroundtestbedwork,
•  PhaseIIison-orbittestbedworkwithminimalaugmentaGon
andISS/interoperaGngequipmentinterfacerequirements,
and
•  PhaseIIIison-orbitworkwithaugmentaGon/opGmizaGonas
neededtoaccommodatemoreextensiveISS/interoperaGng
equipmentinterfacerequirements.
27
ExperimentProcedure-2
EachPhasewillhavesixtaskelementswhichwillbeiteratedand
areintendedtoleveragetherecursivebenefitofboththe
iteraGonsandevolvingunderstandingofcustomerrequirements.
•  Task0
MissionDefiniGon,Planning&Management
•  Task1
RequirementsDefiniGon
•  Task2
InterfaceDefiniGon/CharacterizaGon
•  Task3
TestbedImplementaGon
•  Task4
ApplicaGonCoding&HardwareDefiniGon
•  Task5
VerificaGon&ValidaGon
•  Task6
TechnologyDemonstraGon
•  Task7
ReporGng,PresentaGons,andIdenGficaGonof
Follow-onWork
28
ExperimentWorkVectors
(1)  DeepSpaceIndustrieswillprovideiniGalflighttestarGclesin
returnfortesGngtotheirasteroidassayrequirements.
(2)  AvailableMCT/WARPsoewaretoolkitwillbeextendedto
supportintegratedend-to-endmissionoperaGonscontrol
applicaGonsfortechnologydevelopmentresearch.
(3)  MulGpleuniversity&commercialresearchandtechnology
developmenteffortsonrectennadesignandmicrowave
transmiaeropGmizaGonwillbeleveragedtoassistindesign.
(4)  MulGpleuniversity&NASAcubesatresearchandtechnology
developmenteffortsonspacecraeopGmizaGonwillbe
recursivelyextendedbycreaGngtestbedopportuniGes.
(5)  EnhancedflighttestarGclesderivedfromtheTeamAlpha
CubeSatmissionwillsupportfurthercommercial/scienceuse.
(6)  TestbedworkisthefoundaGonforISSco-orbiGngfreeflyers.
29
TechnologicalChallenges
•  Thefirstprinciplesphysicsofbothnearfieldandfarfield
energyeffectsareconsideredwellunderstood.
•  However,theuseofradiantenergy(bydefiniGonaFarfield
effect,a.k.a.“Beaming”)totransfer(power,data,force,
heat)eitherdirectlyand/orbyinducingnearfieldeffectsat
adistanceislessunderstoodatleastfromthestandpoint
ofpracGcalapplicaGons.
•  Accordingly,thisisappliedengineeringwork,(a.k.a.
technologydevelopment),notnewphysics.
Toop2mizebeamingapplica2onsweneedto
beAerunderstandhoweachofthecomponents
ofradiantenergycanbemadetointeractina
controlledmanner.
30
TechnologicalChallenges-2
•  Radiantenergycomponentsinclude
•
•
•
•
•
Electrical
MagneGc
Linear&AngularMomentum
Thermal
Data
•  TherearepotenGaldirectandindirectusesforeachbeam
component
Useofanycombina2onofthesecomponentshas
implica2onsforallspacecraCsystems(e.g.,power,
data,thermal,communica2ons,naviga2on,
structures,GN&C,propulsion,payloads,etc.)
31
TechnologicalChallenges-3
•  Intheory,theuseofthecomponentinteracGonscanenable:
•  IndividualknowledgeofposiGonandorientaGon
•  Sharedknowledgeloosecoupling/interfacesbetween
relatedobjects
•  Nearnetworkcontrol(sizetosense/proporGonalityto
enabledesiredcontrol)
•  Fixedand/orrotaGngplanarbeamprojecGons
•  GeneraGngnetvelocityalonganyspecifiedvector
Intheory,thereisnodifferencebetween
theoryandprac2ce–butinprac2ce,thereis.
–JanL.A.vandeSnepscheut
computerscien2st
32
TheEvolvingSSPBTeam...
•  XtraordinaryInnovaGveSpacePartnerships,Inc.
•  GaryBarnhard,et.al.
•  DeepSpaceIndustries,Inc
•  DanielFaber,et.al.
•  CenterfortheAdvancementofScienceInSpace(CASIS)–ChadBrinkley
•  UniversityofNewMexicoConfigurableSpaceMicrosystemsInnovaGons
andApplicaGonsCenter(COSMIAC)-ChristosChristodoulou,et.al.
•  UniversityofMarylandSpaceSystemsLab-DavidAkin,et.al
•  UniversityofNorthDakotaSpaceSystemsLab-SimaNoghanian,et.al.
•  SaintLouisUniversitySpaceSystemsLab–MichaelSwartwout,et.al.
•  ZeroGravitySoluGons-RichGodwin,et.al.
•  NavalSystemsResearchLab-PaulJaffe,et.al
•  OtherAdvisors–PaulWerbos,SethPoaer,JosephRauscher,et.al.
•  MulGpleNASACenterswillhavesomecooperaGngrole–NASAARC,et.al.
•  NASAHeadquartersHumanExploraGon&OperaGonsMissionDirectorate
•  AdvancedExploraGonSystemsDivision,JasonCrusan,et.al.
•  SpaceCommunicaGonsandNavigaGonOffice,JimSchier,et.al.
Mul2pleothercommercial,educa2onal,andnon-
profitexpressionsofsubstan2veinterestreceived
33
NextSteps
•  SSPBacommercialmissionthatiscooperaGngwithNASA.
•  NASAisparGcipaGngthroughacombinaGonofin-place(NASA
ARC)andproposed(NASAHQ)SpaceActAgreements.
•  FormalrequestforsupportisinthethirdroundofCASISreview.
•  AddiGonalpartners/parGcipantsarebeingsoughtinthe
commercial,academic,non-profit,andgovernmentsectors.
•  OpportuniGesforinternaGonalcooperaGonleveragingtheISS
IntergovernmentalAgreementwillbeexploredanddeveloped.
UseofISShelpsensurethatthisisan
interna2onalcoopera2ve/collabora2ve
researcheffort.
34
Conclusion
SuccessfuldemonstraGonofspacesolarpowerbeaminghelpspave
thewayforit’suseinarangeofspace-to-space,space-to-lunar/
infrastructuresurface,andspace-to-EarthapplicaGonsbyreducing
theperceivedcost,schedule,andtechnicalriskofthetechnology.
CommercialspaceapplicaGonsincludemissionenhancingand/or
missionenablingexpansionofoperaGonalmissionGme/
capabiliGes,enhancedspacecrae/infrastructuredesignflexibilityas
wellasout-boundorbitaltrajectoryinserGonpropulsion.
35
BackupSlides
36
ISSKeepOutSphere200mRadius
X
SSPBpreferredlocaGonfordeployedflighttestarGclesisRAM(forward)–Starboard
withaZenith(awayfromEarth)bias.
37
38
JEMExposedFacilityAccommodaGons
•Mass:500kg(10StandardSites,massw/PIU)
•Mass:2500kg(3HeavySites,massw/PIU)
•Volume:1.5m3(1.85mx1mx0.8m)
•Power:3kW/6kW,113-126VDC
•Thermal:3kW/6kWcooling
•Data: LowRate:1MbpsMIL-STD-1553
HighRate:43Mbps(shared)
Ethernet:100Base-TX
39
Whatareweunbundling?
•  ThePowerSystemblockdiagramprovidesatoplevel
viewofthesubsystems/funcGonalcomponentsofa
spacecraeelectricalpowersystem.
•  Thisisnotamundaneacademicexercise.
Thereisaneedtostructureandorder
theknowledgeofwhatisknown,as
wellaswhatisknowntobeunknownin
ordertomakethisanalysistractable.
40
MathemaGcsofPowerBeaming*-Efficiency
DCto
Microwave
Conversion
Circa1992
70–90%
BeamForming
Antenna
Circa1992
70–97%
FreeSpace
Transmission
Circa1992
5–95%
RecepGon
Conversionto
DC
Circa1992
85–92%
MaximumPossibleDCtoDCEfficiency---76%
ExperimentalDCtoDCEfficiency---54%
Circa1992
*WilliamC.Brown,LifeFellow,IEEE,andE.EugeneEves,
BeamedMicrowavePowerTransmissionanditsApplicaGonto
Space,IEEETransacGonsOnMicrowaveTheoryandTechniques,
Vol.40,No.6.June1992
41
RelevancetoNASA&Others-7
•  AprimarymissionofXISP-Incistodevelop
cooperaGvearrangementswithdifferentpartsof
NASAandinnovaGvepartners.
•  TheearlyimplementaGonofapowerbeam
demonstraGononISS,coordinatedbyXISP-Inc,
couldenhanceandenablethedemonstraGonof
otherpowerbeamingdesigns.
Thereisrealworkthatcanbedonenow
tomovespacebasedsolarpower
technologydevelopmentforwardwhere
eachincrementofinvestmentyields
somethingofdemonstrablevalue.
42
ISSOperaGonal/SafetyConsideraGons
Ø SoePackLaunchConsideraGons
Ø  WithinscopeofnormaloperaGons
Ø  Safetyrequirementswelldefined
Ø JEMAirlock/Cyclops/MobileServicingCentreDeploy
Ø  WithinscopeofnormaloperaGons
Ø  Safetyrequirementsevolvingbuttractable
Ø Co-orbiGngOutsideSpaceStaGonZoneofExclusion
Ø  NovelextensionofnormaloperaGons
Ø  Safetyrequirementsevolvingbuttractable
Ø ExperimentOperaGonalModesLeverageProvenTasks
Ø
Ø
Ø
Ø
MobileServicingCenterHeld
MobileServicingCenterDeployed(single)
MobileServicingCenterDeployed(formaGon)
CommercialCargoCarrierReuse
43
PossibleArchitectures–SpacecraeasInfrastructure
•  Allthreetestcasesapplicable
•  ReducGonincomplexity
•  ReducGoninmassand/orvolume
•  ProvidedeltaV
•  Supportslooselycoupledsystemsofsystemsapproach
•  Beaming(power,data,force,heat)as:
•  externalinputs/outputsthatchangewithmissionsegment
•  internalmanagedinterfaces
•  Plug-in/Plug-outtechnologyandinterfacemanagement
•  InfrastructureConcepts
•  LEO/MEO/GEO“Telco”centraloffice(s)
•  Cis-lunarshareduserelay/operaGonssupportplahorms
•  L1/L2/L4/L5orotherlunarHaloOrbits
•  CantransformlunaroperaGonsto24x7
44
XISP-Inc/DSI3USSPBFlightTestArGcleConcept*
*3-DCADmodelshows25Ufacescoveredwithsolararrays,theSSPBactualflight
testarGcleswillalsoincorporateRectennaswhichwillbebetween1Uand100U
whendeployed.
45
CyclopsJEMAirlockDeploymentVolume
46
CyclopsDeploymentMechanism
47
NASABEAM
48
Cygnus&DragonFreeflyers
49
NoGonalCubesatSwarm
50
PowerDensity*-SCaNTestBed(STB)SoluGon
AnGcipatedPowerDensityforSeveralDistancesofinterestUsingSCANTestBed(STB)SoluGon
Pd
=
Ai
Pi
/
λ**2
D
D
(waas/cm**2)
(cm**2)
(waas)
(cm**2)
(cm)
(cm)
Pd
(waas/cm**2)
10km
Pd
=
1642
40
/
1.2769
1000000
1000000
=
0.00000005
1km
Pd
=
1642
40
/
1.2769
100000
100000
=
0.00000514
200m
Pd
=
1642
40
/
1.2769
20000
20000
=
0.00012857
1m
Pd
=
1642
40
/
1.2769
100
100
=
5.14286861
*On-OrbitSCaNTestBed(STB)KaBand
Transmiaer,18”Diameter,40Waasoutputpower,
26.5GHz
51
PowerReceived*-SCaNTestBed(STB)SoluGon
AnGcipatedPowerReceivedforvariousrectennaareas
Power
Rectenna
Power
Received
Density(waas/cm**2)
Area(cm**2)
Pr
=
Pd
*
Ar
*
*
*
*
*
*
*
*
*
*
*
*
*
*
*
*
100
200
300
400
500
600
1000
4000
5000
6000
6219
7000
7500
8000
9000
10000
=
=
=
=
=
=
=
=
=
=
=
=
=
=
=
=
0.01
0.03
0.04
0.05
0.06
0.08
0.13
0.51
0.64
0.77
0.80
0.90
0.96
1.03
1.16
1.29
waas
waas
waas
waas
waas
waas
waas
waas
waas
waas
waas
waas
waas
waas
waas
waas
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
200m
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
Pr
=
=
=
=
=
=
=
=
=
=
=
=
=
=
=
=
0.000128572
0.000128572
0.000128572
0.000128572
0.000128572
0.000128572
0.000128572
0.000128572
0.000128572
0.000128572
0.000128572
0.000128572
0.000128572
0.000128572
0.000128572
0.000128572
*On-OrbitSCaNTestBed(STB)KaBand
Transmiaer,18”Diameter,40Waasoutputpower,
26.5GHz
52
PossibleArchitectures–ExoSpheresToolKit
•  Allthreetestcasesapplicable
•  ReducGonincomplexity
•  ReducGoninmassand/orvolume
•  ProvidedeltaV
•  MulGpleunpressurizedandpressurizedlaunchopportuniGes
•  JAXAKobeBack-Porchlaunch&retrieve
•  ExpressPayloadRacklaunch&retrieve
•  ReusableelementofEVARoboGcsToolKit
•  Experimentasinfrastructureproofofconcept
53
SPHERESSatellite
54
RealityCheck
•
•
Reducingthenumberofperceived“impossiblethingsthathave
tobeacceptedbeforebreakfast”*isawayofincrementally
disabusingpeopleofunfoundednoGons.
Doingsomethingrealwiththetechnologythatisof
demonstrablevaluecanhelptoestablishtheconfluenceof
interestsnecessarytomaturethetechnologyformore
advancedapplicaGons.
*Allusionto“AliceinWonderland”byLewisCarroll.
"Alicelaughed:"There'snousetrying,"shesaid;"one
can'tbelieveimpossiblethings."
"Idaresayyouhaven'thadmuchpracGce,"saidthe
Queen."WhenIwasyounger,Ialwaysdiditforhalf
anhouraday.Why,someGmesI'vebelievedasmany
assiximpossiblethingsbeforebreakfast."
55
Conclusion-2
•
Thesuccessfuldevelopmentofspacesolarpowersystemsfor
space-to-space,space-to-lunar/asteroidsurface,and/orspaceto-Earthuserequiresthesuspensionofdisbeliefacross
mulGplecommuniGesofinterest.
•
Therearenon-trivialsystemsengineeringchallengesthatmust
bemustbeaddressedinanyapplicaGonofspacesolarpower.
•
Indeferencetooneofourmostspiritedcolleaguesand
infamouscontrarianonthesubjectofspacesolarpower...
56
Conclusion-3
Wehavesomeserious“frogkissing”
todotogetthisright.
57
PowerSystemTradeSpaceTaxonomy-2
1.
EnergySources
1.01 Mechanical
1.02 Chemical
1.03 Nuclear
1.03.01
RadioacGveDecay
1.03.02
Fission
1.03.03
Fusion
1.03.03.01 Solarflux
1.03.03.01.01 DirectSolarfluxatdefinedpoint
1.03.03.01.02 ConcentratedSolarFluxatdefinedpoint
1.04 Beamed
1.04.01
Microwave
1.04.02
Laser
58
PowerSystemTradeSpaceTaxonomy-3
2.  EnergyTransducers
2.01 SolarCells
(Flux==>electricity)
2.02 SolarDynamic
(Flux==>heat==>electricity)
2.03 FlywheelGenerator
(kineGc==>electricity)
2.04 Baaery
(chemical==>electricity)
2.05 RadioisotopeThermalGenerator-RTG
(RadioAcGveDecay ==>heat==> electricity)
2.06 AdvancedSGrlingRadioisotopeGenerator-ASRG
(RadioAcGveDecay==>heat ==>kineGc==>electricity)
59
PowerSystemTradeSpaceTaxonomy-4
3
EnergyTransmission
3.01 Electricity
3.01.01
AC
3.01.02
DC
3.02 Microwave
3.03 Laser
4
EnergyManagement
4.01 StateMonitoring
4.02 SystemCharacterizaGon
4.03 FlowManagement
5
Loads
5.01 StateMonitoring
5.02 SystemCharacterizaGon
5.03 FlowManagement
60
OpGmizaGonMetrics-1
TestCaseOne-ReducQoninComplexity
Hypothesis:ifthedesignofapowersystemforaspacecraCemerges
asadrivingfactorinincreasingthecomplexityoftheoverallflight
systemtobesupported,thedecoupling/unbundling/
reappor2onmentofthepowersystemcouldsignificantlyimpact
cost,schedule,andtechnicalrisk.
61
OpGmizaGonMetrics-2
TestCaseTwo-ReducGoninMassand/orVolume
Hypothesis:iftheavailablemassandvolumebudgetsassignedtoa
powersystemandtheirappor2onmenttothesubsystemsthatmake
upthatsystem,materiallyimpactthedesignoftheoverallflight
systemtobesupported,theirreappor2onmentcouldsignificantly
impactcost,schedule,andtechnicalrisk.
62
OpGmizaGonMetrics-3
TestCaseThree-AddiGonaldelta-V
Hypothesis:ifthebeamingofenergytoaspacecraCcanbe
translatedintoaddi2onaldelta-Vthroughincreasingtheavailable
electricalpowerand/orprovidinganauxilarysourceofheat,the
designoftheoverallflightsystemtobesupportedcouldbeimpacted
inamannerthatismissionenhancingifnotmissionenabling.
63
Whydoesthismaaer?-ReducGoninComplexity
•  Thepostulateisthatunbundlingpowersystems
cansignificantlyreducethedesign,integraGon,
operaGons,maintenance,enhancement,and/or
evoluGonchallengesforaspacecrae.
•  AswetransiGonfrombuildingone-offspacecraeto
enduringinfrastructuremanagingthecost,
schedule,andtechnicalriskofeachofthese
aspectsofaprogrambecomesevermorecriGcal.
64
Whydoesthismaaer?-ReduceMassand/orVolume
•
•
Themassandvolumeassociatedwiththepowersystemofa
spacecraeisamaterialfracGonoftheoverallbudgetsfor
thespacecrae.
AmaterialreducGoncanfacilitatedoingmorewithless.
•  MorefrequentandvariedflightopportuniGes,
•  goingfurtherand/orgoingfaster,
•  moreresources/experiments/capabiliGes
65
Whydoesthismaaer?ProvideAddiGonaldelta-V
•
•
TheabilitytoopGmizeapowersystemofaspacecraeto
provideanaddiGonalchangeinvelocityatopportune
momentscanmateriallyaltertheoperaGonalconstraints
onaspacecrae.
AddiGonaldelta-Vcanfacilitatedoingmorewithless.
•  MorefrequentandvariedflightopportuniGes,
•  goingfurtherand/orgoingfaster,
•  moreresources/experiments/capabiliGes
66
TestCase1-Complexity
Source:
Fusion,SolarFlux,LEO
Transducer: SolarCells(ISSPowerSystem)
Storage:
Baaeries(ISS),
Keep-Alive(Co-OrbiGngFreeFlyer)
Transmission: expresspayloadpalletmounted
variablefrequencymicrowave
transmiaerwithcollimaGon
Loads: passive/acGvealignmenttarget/
signal,rectenna
SystemMgmt:apporGonedasneeded,bi-direcGonalcommand, control,andtelemetry
67
TestCase1–Complexity(Cont’d)
FlightSystem:Deployable,crewtendedfree-flyerwithdockingport
andaccommodaGonsformicro-gravitytestandmanufacturingcells
aswellasotherhighlydisturbancesensiGveexperiments.Supports
powerdatagrapplefixtureinterfaceforberthing.Supports
Modular,AdapGve,ReconfigurableSystem(MARS)implementaGon
forbackupstabilizaGonandaxtudecontrol.
OpGmizaGonObjecGve:
Reducethecomplexityoftheoverall
free-flyersystemwhilemeeGngorexceedingtherequirementsfor
theclassesofpayloadsintendedtobeserved.
68
TestCase2–Mass/Volume
Source:
Fusion,SolarFlux,LEO
Transducer: SolarCells(ISSPowerSystem)
Storage:
Baaeries(ISS),
Keep-Alive(Co-OrbiGngFreeFlyer)
Transmission: expresspayloadpalletmounted
variablefrequencymicrowave
transmiaerwithcollimaGon
Loads: passive/acGvealignmenttarget/
signal,rectenna
SystemMgmt:apporGonedasneeded,bi-direcGonalcommand, control,andtelemetry
69
TestCase2–Mass/Volume(Cont’d)
FlightSystem:Deployable,cubesat/exospherelikesystem
incorporaGngmulGplesoluGonsforenergyrecepGonandnearnetworkrelaGonshipmanagement
OpGmizaGonObjecGve:
Reducethemassand/orvolumeofthe
overallfree-flyersystemwhilemeeGngorexceedingthe
requirementsfortheclassesofpayloadsintendedtobeserved.
70
TestCase3–deltaV
Source:
Fusion,SolarFlux,LEO
Transducer: SolarCells(ISSPowerSystem)
Storage:
Baaeries(ISS),
Keep-Alive(Co-OrbiGngFreeFlyer)
Transmission: expresspayloadpalletmounted
variablefrequencymicrowave
transmiaerwithcollimaGon
Loads: passive/acGvealignmenttarget/
signal,rectenna
SystemMgmt:apporGonedasneeded,bi-direcGonalcommand, control,andtelemetry
71
TestCase3–deltaV(Cont’d)
FlightSystem:Deployable,cubesat/exospherelikesystem
incorporaGngmulGplesoluGonsforenergyrecepGon,electric
propulsion/aaracGon,andnear-networkrelaGonshipmanagement.
OpGmizaGonObjecGve:
Demonstratethatbeamedenergycan
provideamaterialincreaseinoutbounddeltaVandinsomecases
anaaracGveforce,therebyaugmenGngtheresourcesavailablefor
propulsiononanappropriatelyprovisionedspacecrae.
72
SCaNTestbedonISS
•
TheRadioFrequency(RF)SubsystemiscomprisedofaTraveling
WaveTubeAmplifier(TWTA),CoaxialTransferSwitches,
Antennas,Diplexers,anRFIsolator,anRFAaenuator,and
transmissionlinestointerconnecttheRFSubsystem
componentswiththeradios.
•
TheRFSubsystemradiatesRFsignalsintendedforTDRSandthe
ground;andreceivesRFsignalsfromTDRS,theground,andthe
GPSsystem.
•
ThearchitectureoftheSCaNTestbedhastheabilitytosendRF
signalsfromtwoseparateSDRstotwoantennassimultaneously.
73
SCaNTestbedonISS
•
•
•
•
TheabilitytosendRFsignalsfromtwoseparateSDRstothe
sameantennaorfromasingleradiototwodifferentantennasis
notsupportedbythearchitectureandcannothappendueto
switchposiGonsrequired.
TheRFSubsystemcontainsfouracGvedevices:theTWTAand
threeswitches.
AllcomponentsthatcompriseeachofthethreeRFpaths;Kaband,S-band,andL-bandareshowninFigure3-5.
TheRFSubsysteminterfaceswiththeAvionicSubsystem,the
FlightEnclosure,theAntennaPoinGngSubsystem,andthethree
Radios.
74
SCaNTestbedonISS
•
•
TheTWTAisaKa-bandhighpoweramplifierthatcangenerate
upto40waasofmicrowaveRFpower.
TheAvionicsSubsystemcontrolstheTWTAthroughbotha
discretelogiccommandinterfaceandthe28Vdcpowersupplied
fromtheTWTAPowerSupplyUnit(PSU).
•
TheTWTAwasdevelopedandprovidedbyL-3CommunicaGons.
•
TheTWTAPSUconverts120VdcfromISSto28Vdcforusebythe
TWTA.
•
TheTWTAmustbeacGvelycommandedbytheAvionics
Subsystemtooperate.
75
ISSSCaNTestbedComponents
76
ISSSCaNTestbedLocaGon
77
SCaNTestbedSystemOverview
78
PossibleArchitectures–CubesatSwarm
•  Allthreetestcasesapplicable
•  ReducGonincomplexity
•  ReducGoninmassand/orvolume
•  ProvidedeltaV
•  MulGpleunpressurizedandpressurizedlaunchopportuniGes
•  LogisGcsCarrierDeployment
•  JAXAJEMKiboBack-Porchlaunch&retrieve
•  ExpressPayloadRacklaunch&retrieve
•  Consumableaswellasrepeatablelowcostexperiments
•  PotenGalfor3-DprinGngexperimentopGmizaGon
•  LowestcostflightopportuniGesthatsupportrapidprototyping
•  LeverageSTEMasa“maker”project
79
JAXAKiboroboGcarmdeployingcubesats
80
CubesatConsideraGons
1Unit(U)=10cmx10cmx11cm
Canbe1U,2U,3U,or6Uinsize
RawfacingSurfaceAreaof100cm2perU
Abilitytoaugmentsurfaceareabydeployableand/or3
dimensionalantennastructures.
•  TypicalPowerBudgetis12.5WaasperU
•  Minimumpowerbeamingdistancetodeliverusablepower
mustexceedtheISSzoneofexclusion.
•  Abilitytoreachagiventargetmaybesubjecttostructural
occlusionandoperaGonsGming/sequencingconsideraGons.
•
•
•
•
81
PhaseI–GroundTestbedWork
Defineandimplement/prototypeascalableparametricmodelforunbundled
powersystemsforsustainedfree-flyeroperaGonsextensibletopropulsion,
surface,and/orinfrastructureoperaGons.
Exercisethemodeltodemonstrate:
•  anunderstandingofthetradespace,
•  anyinteracGonsbetweenandwithunbundledpowersystemelements,
bothintermsofwhatisknownandwhatisknowntobeunknown,
•  unbundledpowersystemelementspecificaGons,aswellas
•  acharacterizaGonofallrequiredinterfaces.
DemonstrateandtestexperimentasamixedmodesimulaGonusingthe
groundwithincreasingfidelitytobothvalidatetheparametricmodelandall
requiredphysicalinterfacesforPhaseII&IIIwork.
82
PhaseII-On-orbitWork(FuncGonalTest)
WeproposetouseanonorbitKaBandtransmiaer,drivenatit’smaximumpower
raGngstarGngwithastandardKaBandcommunicaGonswaveformfromtheavailable
library.
Thetransmiaerwillbeprogrammedtogenerateauniformcharacterizablebeamthat
canbeacGvelypointedatdefinedtesGngtargetslocatedsomedistancefromthe
staGonforvariousdefinedperiodsofGme.
Resourceavailabilitypermixngthelibraryofalternatewaveformswillbetestedto
determinemeasurablevariabilityinperformance.
TheobjecGveistoprovidesomelevelofaugmentedpower,communicaGons,and
axtudecontrol/posiGoningservices.TheanGcipatedtargetsareISSand/or
cooperaGngvehiclelaunchedcubesats.
ThiscombinaGonofequipmentallowsforpowertransmission,communicaGons,far
field/nearfieldeffectanalysisandmanagement,testofsystemelementinteracGons
(separatelyandasasystem),formaGonflying/alignment,andvariouspropulsion
approachestobetestedandusedtothebenefitofmulGpleexperiments.
83
PhaseIII-On-orbitworkwithAugmentaGon/OpGmizaGon
(ExpandPerformanceEnvelope)
WeproposetouseoneormoreonorbitKaBandand/orWbandtransmiaers,driven
attheirmaximumpowerraGngandopGmizedwaveformstoprovideaugmented
power,communicaGons,andsomelevelofaxtudecontrol/posiGoningservicestoone
ormoreco-orbiGngcooperaGngspacecrae/elements(e.g.,BEAM,Dragon,Cygnus,
Progress,etc.).
Thetransmiaerwillbeprogrammedtogenerateauniformcharacterizablebeamthat
canbeacGvelypointedattheappropriatelyaugmentedspacecrae/elementswhile
locatedsomedistancefromthestaGonforvariousdefinedperiodsofGmeandona
priorityoverridebasisduringingressoregressfromtheISSsphereofexclusion.
ThiscombinaGonofequipmentallowsforadifferentscaleofpowertransmission,far
field/nearfieldeffectanalysisandmanagement,formaGonflying/alignment,and
variouspropulsionapproachestobetestedandusedtothebenefitofmulGple
experiments.
ItisanGcipatedthatthiscombinaGonofequipmentcouldberepurposedascrewtendedfree-flyersforextendedduraGonmicro-g/producGonmanufacturingcellruns
andotheracGviGes.
84
WhatistheProposedSoluGon-1
•  Space-to-spacepowerbeamingisanapplicaGonofSpace
SolarPowertechnologywhichcouldbetested/implemented
nowtoimmediatebenefitaswellasserveasameansof
incrementallymaturingthetechnologybase.
•  XISP-InchasbroughttogetheratrulyinnovaGvepartnership
ofinterestparGestoaccomplishtechnologydevelopment
workinthisareaincludingbothgovernment,commercial,
university,andnon-profitsectors.Manyformalleaersof
interesthavebeensubmiaedtoNASAand/orXISP-Incand
areavailableonrequest.
85
WhatistheProposedSoluGon-2
•  Thismissionstartswiththedesignandimplement/prototypeaparametric
modelforunbundledpowersystemsforspacecraepropulsionand/or
sustainedfreeflyer/surfaceoperaGonsinconjuncGonwiththeNASAARC
MissionControlTechnologiesLaboratoryandotherinterestedparGes.
•  TheopportunitytocraeviabletechnologydemonstraGonswillestablishthe
basisforaconfluenceofinterestbetweenrealmissionusersandthe
technologydevelopmenteffort.
•  ThiscouldleadtoarangeoftechnologydevelopmentmissionsontheISS
andsubsequentfightopportuniGesthatcanmakeefficientandeffecGve
useofbeamedenergyforpropulsionand/orsustainedoperaGons.
•  Thishascometopassandthereisnowaconcertedefforttomoveforward
withmissiondevelopment.
86
WhatistheProposedSoluGon-3
•  SeveralpotenGalresearchopportuniGeshaveemergedthatcouldmakeuse
ofacombinaGonofresourcescurrentlyavailableorthatcanbereadily
addedtoISS:
•  OfparGcularinterestistheuseofoneormoreoftheavailableKaband(27
to40Ghz)communicaGonstransmiaersonISSaswellasthepotenGalfor
addingoneormoreopGmizedWbandtransmiaers(75to110GHz).
•  TheuseofsimplifieddeliverytoISSofenhanceequipmentand/orflight
testarGclesassoepackcargofromEarth,theJapaneseKibolaboratory
airlocktotransiGonflightsystemstotheEVAenvironment,theMobile
ServicingCenterforram-starboarddeploymentposiGoningwithazenith
bias,andsimplifieddeploymentmechanismscanserveasausefulfirststep
towarddemonstraGnganabilityofISStosupportco-orbiGngfreeflyer
spacecraesystems.
87
WhatistheProposedSoluGon-4
•  ThiscombinaGonofequipmentallowsforpowertransmission,farfield/
nearfieldeffectanalysisandmanagement,formaGonflying/alignment,and
variouspropulsionapproachestobetestedandusedtothebenefitof
mulGpleexperiments;aswellasprovideaugmentedpower,
communicaGons,andsomelevelofaxtudecontrol/posiGoningservicesto
aco-orbiGngfree-flyersand/orotherelements(e.g.,BEAM,Dragon,
Cygnus,etc.).
•  ThiscombinaGonofequipmentcouldberepurposedascrew-tendedfreeflyersforsomenumberofextendedduraGonmicro-g/producGon
manufacturingcellruns.
•  Also,commercialspaceapplicaGonsincludemissionenhancements,
expansionofoperaGonalmissionGme,andout-boundorbitaltrajectory
inserGonpropulsion.
88
PossibleArchitectures–Co-orbiGngFree-Flyers
•  Allthreetestcasesapplicable
•  ReducGonincomplexity
•  ReducGoninmassand/orvolume
•  ProvidedeltaV
•  RepurposinglogisGcscraeashostsforcrewtended
manufacturingcells
•  CommercialCargo(Space-X,Orbital)
•  InternaGonalCargoCarriers(asapplicable)
•  CommercialOpportunityforopGmizedco-orbiGngfreeflyers
•  NASABigelowExpandableAcGvityModule(BEAM)
89
CrewTendedFreeflyerConsideraGons
•  Minimumpowerbeamingdistancetodeliverusablepower
mustexceedtheISSzoneofexclusion
•  Abilitytoaugmentrectennasurfaceareabydeployableand/
or3dimensionalantennastructuresmayberequired.
•  Abilitytoreachagiventargetmaybesubjecttostructural
occlusionandoperaGonsGming/sequencingconsideraGons.
90
PowerSystemTradeSpace-
Taxonomy
•  Spacecraesurvivalisdependentonthepowersystem
funcGoninginalmostallcases.
•  AnyinnovaGonmustbeunderstandableinthecontext
oftheknowntradespaceandcrossdisciplineaccessible
oritwillnotfly.
•  TheinnovaGonmusteither:
--Reducecost,schedule,and/or
technicalrisk;
--Demonstrablyenhancethe
mission;or
--Enablethemission
91
RelevancetoNASA&Others-1
Space-to-spacepowerbeamingisanapplicaGonofspace
solarpowertechnologywhichcould:
1.  betested/implementednowtoimmediatebenefit,
and
2.  serveasameansofincrementallymaturingthe
technologybase.
92
PowerDensity*-MoreOpGmalSoluGons
CASE1
Pd
=
Ai
Pi
(waas/cm**2) (cm**2) (waas)
10km
Pd
= 1641.732
3000
1km
Pd
= 1641.732
3000
200m
Pd
= 1641.732
3000
1m
Pd
= 1641.732
3000
CASE2
Pd
=
Ai
Pi
(waas/cm**2) (cm**2) (waas)
10km
Pd
= 1641.732
3000
1km
Pd
= 1641.732
3000
200m
Pd
= 1641.732
3000
1m
Pd
= 1641.732
3000
/
λ**2
D
D
(cm**2)
(cm)
(cm)
/ 0.693889 1000000 1000000
/ 0.693889 100000 100000
/ 0.693889
20000
20000
/ 0.693889
100
100
/
λ**2
D
D
(cm**2)
(cm)
(cm)
/ 0.099856 1000000 1000000
/ 0.099856 100000 100000
/ 0.099856
20000
20000
/ 0.099856
100
100
Pd
Ai
(waas/cm**2) Source
=
7.09796E-06 STB
=
0.000709796 STB
=
0.017744901 STB
= NEARFIELD
STB
Pd
Ai
(waas/cm**2) Source
=
4.9323E-05 STB
=
0.004932299 STB
=
0.12330748 STB
= NEARFIELD
STB
Pi
Source
ELC/KEF
ELC/KEF
ELC/KEF
ELC/KEF
Pi
Source
ELC/KEF
ELC/KEF
ELC/KEF
ELC/KEF
λ**2
Source
Ka-Target
Ka-Target
Ka-Target
Ka-Target
λ**2
Source
W-Target
W-Target
W-Target
W-Target
*CASE1-ExpressLogisGcsCarrier/KiboExposed
Facility(ELC/KEF)MountedKaBandTransmiaer,18”
DiameterAperture,3000Waasoutputpower,36
GHz
CASE2-ELC/KEFMountedWBandTransmiaer,18”
DiameterAperture,3000Waasoutputpower,95
GHz
93
WhySolvetheProblem?
è Reducingcost,schedule&technicalrisk
è Missionenhancingtechnology
èMissionenablingtechnology
94