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25 December 2015, Volume 35 Issue 6 Previous Issue    Next Issue

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ApproachPlanningandControlMethodforRendezvouswithNoncooperativeTargetinanEllipticalOrbit XU Li-Jia, HU Yong 2015, 35 (6):  1.  doi: 10.3780/j.issn.1000-758X.2015.06.001 Abstract ( 786 )   PDF (6937KB) ( 554 )   Save Theproblemsofapproachplanningandcontrolmethodforrendezvouswithanuncontrolledtumblingnoncooperativetargetinanellipticalorbitwerestudied.Onthepartofapproachplanning,thechaserandtargetspacecraftrendezvousedfromadistancetoasafeberthpoint,whichwasdesignedbyconsideringthestructureofthetargetspacecraft.Aftertheobservationattheberthpointforaperiodoftime,thegrasppointwasdeterminedandtheattitudemotionofthetargetspacecraftcanbepredicted.Then,asafeapproachtrajectoryfromtheberthpointtotheimplementpointforgraspingwasdesignedfortracking.Onthepartofcontrolmethod,byusingthemeasurementsoftherelativepositionandconsideringtheuncertaintiesoftheactualsystem,adaptivecontrollawsbasedonthecharacteristicmodelwereproposedforthewholerendezvousandapproachprocess.Finally,anexamplewasgiventoshowtheeffectivenessoftheproposedapproachplanningandcontrolmethod. Related Articles | Metrics

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DesignandPerformanceAnalysisofSelfadaptionTemperatureControlColdPlate ZHANG Hong-Sheng, LI Yun-Ze, WANG Sheng-Nan, NING Xian-Wen 2015, 35 (6):  12.  doi: 10.3780/j.issn.1000-758X.2015.06.002 Abstract ( 771 )   PDF (4554KB) ( 530 )   Save Toimprovethetemperaturecontrolreliabilityofspacecraftthermalcontrolsystem,aselfadaptiontemperaturecontrolcoldplatewasdesignedbasedonthevolumechangecharacteristicsoftheparaffinwaxduetothephasechangeasitstemperaturechanged.Thedesignmodeloftheselfadaptiontemperaturecontrolcoldplatewasbuilt,andthethermalnetmodelofthesinglephasefluidloopwiththecoolplatewasgiven.Theperformanceofthecoldplateandthesinglephasefluidloopwasanalyzed.Resultsshowthatthecoldplatedesignedhastheabilityofselfadaptiontemperaturecontrol,anditmaybewidelyusedinthetemperaturecontrolfortheelectronicdevicesatgroundandheatloadsonspacecraft. Related Articles | Metrics

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AdaptiveControlforStabilizingtheCouplingSystemwithDisturbanceafterCapturingSpacecraft WANG Yi-Ping, ZHAO Yu-Shan, SHI Peng, ZHENG Han-Qing 2015, 35 (6):  20.  doi: 10.3780/j.issn.1000-758X.2015.06.003 Abstract ( 943 )   PDF (3939KB) ( 564 )   Save Anadaptivecontrolbasedondynamicsmodelforstabilizingthecouplingsystemwasproposed，forthecouplingsystemmaybeunstableduetothechangeinmasscharacteristicsandmomentumofthecouplingsystem.Thedynamicsofsystemwasmodelledandthevelocitiesofcouplingsystemwerederivedfromtheimpactmodel.Basedonthedynamicmodeldeveloped,thelinearfeedbackcontrollerwasdesigned.Becauseoftheuncertaintyonthedynamicparametersanddisturbance,thedynamicmodelwaslinearlyparametricwithrespecttoagroupofunknowndynamicparametersandunknowndisturbance.Then,theadaptivelinearfeedbackcontrollerwasdesigned.UsingathreeDOFplanarspacemanipulator,thenumericalsimulationwascarriedout.Thesimulationresultsconfirmthecontrollerisfeasibleandeffective. Related Articles | Metrics

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ResearchonMinimumFuelControlofRelativeEllipsePhaseinInPlaneCompanionFlying WU Hui-Ying, ZHOU Mei-Jiang, QI Jin-Ling 2015, 35 (6):  29.  doi: 10.3780/j.issn.1000-758X.2015.06.004 Abstract ( 811 )   PDF (6338KB) ( 509 )   Save Itisessentialtosavefuelinorbitcontrolformicro/nanocompanionsatelliteduetothelackofresources.TheminimumfuelcontrolstrategyoftherelativeellipsephaseininplanecompanionflyingwasstudiedbasedontheHillequationandtheextremevaluetheoryofdualfunction. Whenthephaseneededtochangeisacuteangle , andthevelocityincrementislessthantheresultthatmultiplieshalfoforbit′smeanangularbytherelativeellipsesemiminoraxis(ΔV<05nb),thetheoreticalanalysisresultsshowthatthemostefficientcontrolmethodoftherelativeellipsephaseisimpulsivecontrolparalleltothelateraldirection, thevelocityincrementistheresultthatmultiplieshalfoforbit′smeanangular,therelativeellipsesemiminoraxisbytheabsoluteofphase′scosine(ΔV=05nb|cosΘ|,andthephasewillbetheleft（thephaseisπ/2）orright（thephaseis-π/2）pointofrelativeellipseaftercontrol.Therelativeellipsesemiminoraxiscanbereducedatthesametime. Whenthephaseneededtochangeisnotacuteangle, itisneededtobedividedintoseveralacuteanglesforsavingfuel. Furthermore,theorbitcontrolstrategyofacompanyingsatellite′sphasecontrolwasgainedbyapplyingthetheory. Related Articles | Metrics

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PredictiononPerformanceDegradationofThermalControlCoatingBasedonSatelliteTemperatureonOrbit SONG Xin, ZHANG You-Wei, LIU Zi-Jun, SI Dong-Bo 2015, 35 (6):  40.  doi: 10.3780/j.issn.1000-758X.2015.06.005 Abstract ( 938 )   PDF (3806KB) ( 525 )   Save Amethodwasproposedtopredicttheperformancedegradationofthermalcontrolcoatingbasedontemperaturedataonorbit.Amathematicalmodelwhichwasconstructedtostudythe degradationofthermalcontrolcoatingperformancespanningintegeryears wasverifiedbynumericalsimulations.Thecalculationdatameetthetruevaluewell,indicatingthatthemathematicalmodelisvalid. Related Articles | Metrics

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CharacteristicsAnalysisofaOnewayMicroExpansionTypeHeatSwitchforSpaceApplication MA Ming-Chao, GUO Liang, ZHANG Xu-Sheng, WU Qing-Wen 2015, 35 (6):  48.  doi: 10.3780/j.issn.1000-758X.2015.06.006 Abstract ( 895 )   PDF (4537KB) ( 467 )   Save Inordertoimprovethetemperaturecontrolprecisionofthedetectorandother spacecraftandreducethetemperaturefluctuationaccuracy,aonewaymicroexpansiontypeheatswitchwasdesignedbasedonthermalexpansionandcontractionofmetal.Thecharacterizationparameterwasgettoanalysisthetwodimensionalsteadystatethermalmodeling. Then, anexperimental setupwasdesignedtosimulatetheactualworkingconditionsofthermalswitch,andswitchoperatingstatusandrelatedperformanceparametersweremeasuredunderdifferentheatpower.Whenthepowerisupto04W,disconnectedresistanceis23046K/W.Thepowerisupto30W,theclosedthermalresistanceofswitchis03022K/W,andswitchratiois7626.Theresultsshowntheexperimentdataareingoodagreementwiththetheoreticalcalculations. Related Articles | Metrics

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DetectingandTrackingMethodforSpaceTargetGraspingBasedonContourFeaturesDetection KANG Ru-Fei, WANG Shi-Cheng, LIU Zhi-Guo, YANG Dong-Fang 2015, 35 (6):  57.  doi: 10.3780/j.issn.1000-758X.2015.06.007 Abstract ( 1012 )   PDF (6478KB) ( 821 )   Save Duetothecomplexbackground,changesoftheilluminationandrelativemotions,betterperformancesineffectivenessandrobustnessareneededformovingtargetgraspingtasks.Anewdetectingandtrackingmethodbasedondynamiccontourfeatureswasproposed.Thegraygradientmethodandtheactivecontourmodelwereintegratedinthismethod.Atfirst,onthebasisofthetraditionalgraygradientmethod,animprovedgraygradientmethodwasproposed,whichincludedshapematching,areascreeningandadaptiveadjustmentofgraythreshold.Accordingtothedetectingresultsoftargetcontour,thetimedomainconstraintsbetweenimagesequenceswerealsoinvolved.ThedetectingresultswereaddedintheGVFsnakemethodtoimprovethemeasuringaccuracyandeffectiveness.Intheend,consideringtherealtimedemandofthegraspingtasks,thetrackingmethodswasparallelwithCUDAcalculationarchitectureandanexperimentwasconductedwithabundleofsequentialimages.Theresultshowsthatthetrackingratecanreach10framespersecond,improvingthetrackingspeedwithoutsacrificingtheaccuracy. Related Articles | Metrics

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LunarSurfaceSamplingDeviceCollisionAvoidancePlanningBasedonArtificialPotentialFieldMethod ZHENG Yan-Hong, DENG Xiang-Jin, PENG Jing, YAO Meng, ZHAO Zhi-Hui 2015, 35 (6):  66.  doi: 10.3780/j.issn.1000-758X.2015.06.008 Abstract ( 808 )   PDF (4303KB) ( 1064 )   Save Thesurfacesamplingtechnologyisanimportantmethodforgettingsoilsample.Itisakeytechnologyforcollisionavoidancetrajectoryplanningwithcomplexlunarterrain,uncertainlandingattitudeandirregularlunarprobeenvelope.Accordingtothedesignoffourdegreeoffreedomsurfacesamplingdevice，kinematicsandinversekinematicswereanalyzed.Consideringtheconstraintsofdynamicandstaticobjectpoints,therestrictionspacewasdividedintoavailablecollisiondetectabilityareaandunreachableset.Toexpeditetheplanningspeed,thedynamicavailablecollisiondetectabilityareaandunreachablesetwereintroducedtotheartificialpotentialfieldmethod.Andthecollisionavoidanceplanningalgorithmwasproposed.Thesimulationresultprovesthatalgorithmiseffectiveforsurfacesamplingtrajectoryplanning，anditcanbeusedtosupportsurfacesamplingdesign. Related Articles | Metrics

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AnOnlineIndividualChannelInterrelationMethodStudyofAntennaArrayCalibration LIU Han-Chao, LIANG Hao 2015, 35 (6):  75.  doi: 10.3780/j.issn.1000-758X.2015.06.009 Abstract ( 828 )   PDF (3213KB) ( 1003 )   Save Duetotheclockfrequencydifferencebetweenthetransmitterandthereceiver, itisdifficultforthemultiantennasatellitemobilecommunicationchannelcalibrationinlowsignalnoiseratiol(SNR). Anonlineindividualchannelmulticycleinteraccumulationmethodwasproposed, whichcouldsolvethedifficultyofchannelcalibrationinlowSNR.Thiscalibrationspreadspectrumsignalwasproducedfromgroundcalibrationstation, whichcouldreducethecomplexityofsatellitedesignandrealizeonlinecalibrationwithoutinterruptingthecommunicationforusers. Thismethodsolvestheproblemofcodeoffsetandfrequencyoffsetthroughmarkingthevaliddata, matchingrate,andsoon. TheresultsshowthattheSNRis-30dBunderthespreadingradioof1023,whichis 03dBworsethanthatofthetheorySNR. Thestudycanprovidetechnicalsupportforthemultiantennasatellitemobilecommunication. Related Articles | Metrics

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OptimalEntryTrajectoryDesignofWingedMarsProbe LIU Tao, NAN Ying , HU Hai-Long 2015, 35 (6):  82.  doi: 10.3780/j.issn.1000-758X.2015.06.010 Abstract ( 794 )   PDF (3815KB) ( 724 )   Save ThispaperprovidesanoptimalentrytrajectoryofthewingedMarsprobe,rightafteritchangedtheorbitintotheMartianatmospherebrakedbyreversethrustengine.ThispaperestablishesMartianatmospheremodelandgravitationalfieldmodelcorrespondingonthedensityoftheMartianatmosphereandgravitationalfieldparameters,anddeterminedthedynamicequationsoftheMarsprobe.Withinalltheconstraintconditionsintheenteringprocess,thispaperdesignsanoptimalentrytrajectorybasedonthegeneticalgorithm.Inaddition,thispaperprovidesdifferentthrustengineschemethroughcomparingthem.Theresultsshowthatthesecondschemecanachievetheoptimalperformanceindexandthelandingspeedis136m/s,ultimatelyrealizingtheminimumconsumptionofenergyandaerodynamicheatemissionstructurequalityintheprocessofenteringandsoftlanding. Related Articles | Metrics