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25 December 2013, Volume 33 Issue 6 Previous Issue    Next Issue

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ResearchonCompoundControlforSolarSailSpacecraftAttitudeManeuvering ZHAI Kun, ZHANG Jin, WANG Tian-Shu 2013, 33 (6):  1-8.  doi: 10.3780/j.issn.1000-758X.2013.06.001 Abstract ( 1838 )   PDF (406KB) ( 1752 )   Save Theinputshapingmethodscan′teliminateflexiblevibrationsduringtheattitudemaneuvering.Theresidualflexiblevibrationwillchangethestructureparametersofthelargeflexiblesolarsailspacecraftandinfluencethecontrolprecisionofattitudemaneuvering.Therefore,thecompoundcontrolmethodwasproposedtoeliminatetheflexiblevibrationduringtheattitudemaneuvering,basedonthecombinationoftwokindsofcontrolways.Thecouplingdynamicmodelsofsolarsailattitudemotionsandflexiblevibrationswereestablishedbythemethodoftakingthesailmembranesqualityequivalenttobooms.Consideringofreducingtheexternalforcesofvibrationmodes,twokindsofcompoundcontrolstrategieswereobtainedbythesimplifieddynamicmodels.Accordingtothesimulationresults,themaneuveringtimeofthesecondcompoundcontrolmethodisfewerthanthatoftheinputshapingmethod.Thesecondcompoundcontrolmethodcanreduceflexiblevibrationsto5%duringtheattitudemaneuveringprocessandmaketheprecisionofthemaneuveringanglebetterthan0.003°.Becauseofjustusingthoseexistedcontrolways,thealgorithmsofthecompoundcontrolmethodaresimpleandsuitabletothepracticalapplications. Related Articles | Metrics

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RemoteSensingImageChangeDetectionBasedonWaveletandKernelIndependentComponentAnalysis WU Yi-Quan, CAO Zhao-Qing 2013, 33 (6):  9-16.  doi: 10.3780/j.issn.1000-758X.2013.06.002 Abstract ( 1316 )   PDF (654KB) ( 1192 )   Save Inordertofurtherimprovetheaccuracyofchangedetectionofremotesensingimagesbasedonindependentcomponentanalysis(ICA)andtosolvetheuncertaintyproblemofsequenceofimagecomponentsseparatedbyICA,achangedetectionmethodbasedonwavelettransformandkernelindependentcomponentanalysis(KICA)wasproposed.Firstly,theremotesensingimagesweredecomposedbywavelettransform,andpartitionedvectorscomposedofhigh-frequencycomponentsandlow-frequencycomponentswereobtained.Thenthepartitionedvectorsweremappedintoahigh-dimensionalfeaturespacebythekernelfunction,andthemutuallyindependentvectorswereseparatedbyICAinthisspace.Finally,accordingtothedifferencesbetweenthehigh-frequencycomponentsoftheseparatedvectors,thechangecomponentwasdistinguishedautomatically.Experimentalresultsoftheproposedmethodandotherthreechangedetectionmethodsproposedrecentlybasedontheprincipalcomponentanalysis(PCA),ICA,KICAweregiven.Andsomeanalysisandquantitativecomparisonsweredone.Alargenumberofexperimentalresultsshowthattheproposedmethodcanseparatechangeinformationofremotesensingimageswithhigheraccuracy,andtheintelligentchangedetectionisrealized. Related Articles | Metrics

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Earth-to-MarsTransferOrbitOptimizationBasedonMeshRefinement GU Liang-Xian, ZHAO Ji-Song 2013, 33 (6):  17-25.  doi: 10.3780/j.issn.1000-758X.2013.06.003 Abstract ( 1461 )   PDF (469KB) ( 1170 )   Save Ageneralnonsmoothtrajectoryoptimizationapproachwaspresented.Themeshrefinementprocedurebasedondatacompressondyadicgridswasimprovedtoincreasetheefficiency,usabilityandflexibility,andwasthencombinedwiththelocalcollocationmethodwhichtookadvantageofscaling,sparsityanddifferentnumericaldifferentiationofnonlinearprogramming(NLP).NumericalsimulationonEarth-to-Marstransferorbitoptimizationdemonstratesthattheapproachcapturesnonsmoothregionsexactlywithdensitymeshandhasthepotentialofon-boardoptimization.Furthermore,theapproachcapturesnon-smoothregionsofstateseventhoughthemeshisrefinedaccordingtothecontrolvariables.ForEarth-to-Marstransferorbitoptimization,itisbettertodefinethethrustanglein[0,360°)thanthatin[-180°,180°). Related Articles | Metrics

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SensorlessControlStrategyforSGCMGHighSpeedRotor LU Ming, TIAN Li-Mei, LI Lian-Xiang, ZHAI Bai-Chen, HU Yue-Wei 2013, 33 (6):  26-32.  doi: 10.3780/j.issn.1000-758X.2013.06.004 Abstract ( 1674 )   PDF (407KB) ( 1195 )   Save Sensorlesscontrolstrategyforrotorsystemofthesinglegimbalcontrolmomentgyro(SGCMG)couldreducecomplexityandpromotereliabilityofthewholeset.Themethodsbasedonthebackelectromotiveforce(EMF)detectionofthehalfbridgedrivebrushlessDCmotor(BLDC)andthedisturbanceeliminatingmethodswithoutlowpassfilterwereproposed,whichcouldachieveshighdetectionprecision.Forthestartupprocess,afoursegmentstrategywasproposedincludingorientationsegment,I/fstartupsegment,speedestimationstartupsegmentandswitchsegment,whichrealizedareliablestartupprocess.Simulationsandexperimentsprovetheeffectivenessoftheproposedmethod.ReliableandaccuratesensorlesssystemforSGCMGhighspeedrotorisrealized. Related Articles | Metrics

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Vision-BasedRelativeNavigationforRendezvousandDockingofSpacecraft LIU Yong, XU Peng, XU Shi-Jie 2013, 33 (6):  33-40.  doi: 10.3780/j.issn.1000-758X.2013.06.005 Abstract ( 1423 )   PDF (469KB) ( 1245 )   Save Forthefinalphaseofspacecraftautonomousrendezvousanddocking,thevisionrelativenavigationmethodbasedontheinformationofthespecificreferencelightsourceswaspresented.Undertheassumptionofsmallattitudeangle,therelativenavigationmodelswerededuced.Theclosed-formsolutionforrelativeattitudeandpositionparametersbasedonthevisionnavigationmodelswasderived.ThereducedorderUnscentedKalmanFiltering(UKF)algorithmwasdesignedtoestimatetheinformationofrelativeattitudeangleandrelativeattitudeanglevelocity.Simulationresultsshowthattheproposedapproachprovidesaconvenientwayforobtainingtheinformationofrelativepositionandrelativeattitude,andthereducedorderUKFcanimprovetheaccuracyoftherelativeattitudedetermination. Related Articles | Metrics

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CombinedControlforQuickManeuverofElasticSatellite RAO Wei-Dong, XU Li-Jia 2013, 33 (6):  41-48.  doi: 10.3780/j.issn.1000-758X.2013.06.006 Abstract ( 1493 )   PDF (471KB) ( 894 )   Save Acombinedcontrolmethodwhichconsistsoffeedbackcontrolandfeedforwardcontrolwaspresented.Thefeedbackloopeliminatesrigidbody′sattitudeerroraroundtargetattitude,whilefeedforwardcontrolpreventsfromelasticvibration.Forfeedbackloop,thetraditionalPDcontrolwasadopted.Forfeedforwardcontrol,thesuboptimalsinusoidalcontrolwasadopted.Suboptimalsinusoidalcontrolconsistsofseriesofsinusoidsexcitinglittlevibrationofelasticmodesfromlowordertohighorder.Numericalsimulationwascarriedouttoverifythemethod.Theresultsshowthat,byusingthecombinedcontrol,themaneuvertaskcanbefulfilledeffectivelyinthepresenceofdynamicaluncertaintiesanddisturbance. Related Articles | Metrics

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NewMethodforAttitudeDeterminationofSpinSatelliteBasedon  ContinuousStarMapObservation NING Xiao-Lin, BAI Xin-Bei, JIANG Li-Wei 2013, 33 (6):  49-57.  doi: 10.3780/j.issn.1000-758X.2013.06.007 Abstract ( 1790 )   PDF (516KB) ( 984 )   Save Traditionalmethodsforspinsatelliteattitudedeterminationusuallyutilizeearthsensorandsunsensorasthemeasurementinstruments.Thegeneratedsystemerrorsandinstallationerrorandsoonwillleadtolargespinattitudeerrors.Consideringthisproblem，anewmethodusingcontinuousstarmapacquiredbyastarsensortoestimatethespinattitudeparametersofthesatellitewasproposed.Inthismethod,thespinaxisandtheangularvelocityofthesatellitewereusedasstatevariables,andthepixelcoordinatesofstarsobtainedthroughstarmapmatchingbetweenadjacenttimewereusedasmeasurements.ThespinattitudeparametersofthesatellitewereestimatedbyunscentedKalmanfilter.Simulationresultsshowthatwiththestarsensoraccuracyof3″,theestimationaccuracyofthespinaxisislessthan0.3448″andtheestimationaccuracyofspinangularvelocityisof10-4(°)/smagnitude. Related Articles | Metrics

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ARateControlSchemeforCCSDS-IDCBasedonPriorityandR-DModel LI Ze-Hui, XIE Xiao-Fang, LIU Yong 2013, 33 (6):  58-66.  doi: 10.3780/j.issn.1000-758X.2013.06.008 Abstract ( 1656 )   PDF (895KB) ( 885 )   Save Targetareasaremuchmoreconcernedthanotherpartsoftheimagesinmanyremote-sensingapplications.Itisanidealwaytoperformdifferentcompressionratio  todecreasedatavolumeinanimage.AmodifiedbitrateallocationschemewasproposedtoextendthecapacityoftheConsultativeCommitteeforSpaceDataCompressionStandard(CCSDS-IDC)  forthemilitarypurpose.Anewsegmentregroupingandrankingschemewasusedtoallocatethebytesaccordingtoprioritiesofthesegments,theratioofhigh-prioritysegmentsandtheratedistortionmodel.Theresultsshowthatboththelocalpeaksignaltonoiseratioandthevisualeffectofthereconstructedimageareimprovedbythescheme. Related Articles | Metrics

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LEOSpacecraftMagnetismPropulsionandItsCapabilityEstimation XIAO Xin-Xin, LI Wen-Hao, ZHANG Heng, LIU Kai-Lei 2013, 33 (6):  67-73.  doi: 10.3780/j.issn.1000-758X.2013.06.009 Abstract ( 1372 )   PDF (427KB) ( 1406 )   Save Accordingtothecharacteristicsofthemagneticfielddistributionintheearthspace,thepropulsiontechnologywithoutpropellantconsumptionwasproposedtomaintainorchangetheLEOspacecraftaltitude.Themagneticthrustdynamicswasmodeledbasedonthefundamentalmagnetics,themagnetismpropulsionprinciplewithcontinuousthrustbutnopropellantconsumptionwasclarified,andthetrackingcontrolstrategyofgeomagneticlineofforcefordecouplingthemagneticmomentwasproposed.Theflightenvelopeofmagnetismpropulsionandtypicalcalculationsfortheorbitaltitudemaintenanceorchangeswascarriedout.Theresultsshowthatthemagneticmomentofthespacecraftcanbeusedtomaintainorchangethespacecraftaltitudefrom600kmto1000kminlowearthorbit(LEO)whenitisupto106Am2.Furthermore,thetechnicalfeasibilityofobtaininghighmagneticmomentisbrieflyanalyzed. Related Articles | Metrics

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ModelAnalysisofPLLSwingScanningControlSystem TANG En-Sheng, YUAN Jin-Peng 2013, 33 (6):  74-80.  doi: 10.3780/j.issn.1000-758X.2013.06.010 Abstract ( 1464 )   PDF (412KB) ( 1309 )   Save Thephaselockedloop(PLL)swingscanningcontrolmethodisextensivelyappliedforaerospaceopticsscanningremotesensor,whichcanberealizedwithsimpleandreliablecontrolcircuit.However,thecontrolsystemmodeliscomplicatedforphasedetectornon-linearityandswitcheffectofspringslices,anditisdifficulttoanalysisanddesignforthiscontrolsystem.Thevariousnonlinearcharactersin PLL swingscanningcontrolsystemwereanalyzed,andalinearizedmodelwasobtainedbyapplyingsmall-signalanalyticmethod,whichwasconvenientforanalysisanddesign.Basedontheproposedmodel,thecontrollerdesignrulewasalsodiscussed，andanexperimentwascarriedouttoconfirmtheanalysisconclusion. Related Articles | Metrics