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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 ( 615 )   PDF (6937KB) ( 405 )   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.
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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 ( 620 )   PDF (4554KB) ( 378 )   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.
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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 ( 719 )   PDF (3939KB) ( 378 )   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.
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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 ( 721 )   PDF (6338KB) ( 330 )   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.
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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 ( 729 )   PDF (3806KB) ( 296 )   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.
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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 ( 699 )   PDF (4537KB) ( 362 )   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.
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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 ( 758 )   PDF (6478KB) ( 639 )   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.
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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 ( 647 )   PDF (4303KB) ( 894 )   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.
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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 ( 625 )   PDF (3213KB) ( 887 )   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.
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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 ( 656 )   PDF (3815KB) ( 429 )   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.
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