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    25 June 2014, Volume 34 Issue 3 Previous Issue    Next Issue
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    DistortionAnalysisonHighResolutionRangeProfileofSpaceTargetandMotionParameterEstimation
    DU Xiao-Yong, ZHANG Le-Feng, HU Wei-Dong
    2014, 34 (3):  1-7.  doi: 10.3780/j.issn.1000-758X.2014.03.001
    Abstract ( 1283 )   PDF (419KB) ( 1096 )   Save
    Aimingatthewidebandradarechosignalreturnedfromthesatellite,thepolynomialphasemodelwasanalyzedindetailduetoitshighspeedmotion.Asaresult,thedistortiononhighresolutionrangeprofilecausedbythreeorhigherdegreepolynomialcanbeneglected.Accordingtothewidthofspectrummainlobeatdifferentvelocities,aboundconditionwasderivedtocompensatethequadraticphase.Theresultindicatesthatthesatellitespeedismuchgreaterthanthederivedbound(near560m/s)withthetypicaloperatingparameters,andshouldbecompensatedbeforeimaging.Furthermore,basedonthesparsedistributioncharacteristicsofscatteringcenters,anL1-normbasedalgorithmwaspresentedtoestimatethesatellitevelocity.SimulationsshowthatthestandarddeviationoftheestimatorisclosetotheCramer-Raolowerbound,andtheestimationerrorismuchlessthanthederivedboundforcompensation.Theproposedalgorithmisapplicableforsatelliteimaging.
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    Sine  Vibration  Response  Model  Updating  Method  in  Classic  Damped  Structure
    QIN Yu-Ling, HAN Zeng-Yao, ZOU Yuan-Jie, WANG Jian-Min
    2014, 34 (3):  8-14.  doi: 10.3780/j.issn.1000-758X.2014.03.002
    Abstract ( 1253 )   PDF (399KB) ( 1093 )   Save
    Thesine-vibration-data-basedmodelupdatingmethodplaysanimportantrolein  improvingthefiniteelementmodelinglevelinspacecraftengineering. The  key  to  sine-vibration-data-based  modelupdatingmethodisthecoherenceofthemodalfrequenciesandtheresponsecurvesofthemodelbefore&afterupdated.  Firstly,theanalysismethodofthestructureresponsewasderivedbasedonthebaseexcitation.Secondly,theupdatingmethodwasstudiedintwosteps,whichmakesthemodalfrequenciesandtheresponsecurvesoftheanalysismodelconsistentwiththatofthetestmodel.Finally,theGARTUREtrussmodelwasusedtovalidatethetwostepupdatingmethod.Theresultsshowthatthefundamentalfrequenciesoftheanalysismodelagreewiththetestmodel,thefirsttenmodalfrequencyerrorisunder0.15%,andtheresponsepeakerrorofthetypicalpointsislessthan1%.
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    SolarRadiationPressureModelingMethodforComplexSpacecraft
    HUANG An-Yi, ZHANG Shao-Yu, LI Heng-Nian
    2014, 34 (3):  15-22.  doi: 10.3780/j.issn.1000-758X.2014.03.003
    Abstract ( 1125 )   PDF (515KB) ( 731 )   Save
    It′scomparativelydifficulttomodelthesolarradiationpressurewhencalculatingthepreciseorbitofthespacecraft.Especiallywhentheshapeofthespacecraftisinvolute,therewouldbesuperpositionandobscurationbetweendifferentmaterials,sothatthenormalexperimentalmethoddoesn′twork.Basedontheprecise3-DGeometricModel,thesimulativevisionwasusedtogetthesectionshapeofthespacecraftwhichperpendiculartotheSunvector,andthencalculatedtheequivalentSRPareaandthecoefficientwiththeSRPcharacteristicsofthematerial.Toreducetheamountofcalculation,anewmethodwasprovidedusingprior-calculatingandreal-time-interpolation.ConsideringthattheSRPcharacteristicswouldchangeinspace,thecalculationwastransformedintoasemi-empiricalformulasothecoefficientscouldbeestimatedbytheobservationdata.Thesimulationindicatesthattheanalysismethodcaneffectivelyreflecttheobscurationbetweenthepartsofthespacecraft.
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    RLVReentryMathematicalModeling
    Yu Guang-Xue, LI Zhao-Ying, LIN Ping
    2014, 34 (3):  23-31.  doi: 10.3780/j.issn.1000-758X.2014.03.004
    Abstract ( 1200 )   PDF (556KB) ( 1035 )   Save
    Areusablelaunchvehicle(RLV)reentryconceptualdesignandcontrolmodelingresearchwerepresentedforschemeanalysisinthepreliminarydesignstage.TheRLVaerodynamicconfigurationwasawingbodycombinationwithtwoelevonsatthewingtrailingedge,arudderontheverticaltailandaflapattheendofthebody.TheRCS/Aerosurfacescompoundcontrolmathematicalmodelwasdevelopedforattitudecontrol.Inordertorapidlyaccomplishthepreliminaryaerodynamicdatabases,theengineeringpredictionmethodwasappliedtocalculatetheaerodynamicforcesandmoments.Theaerodynamicregionsimplementedwasrarefiedflow,transitionalflow,andhypersoniccontinuumflow.Thecontrolanalysissupportedtheevolutionofthedesigntoprovideanoptimaldesign.AsixdegreesoffreedomreentrysimulationshowsthattheRLVaerodynamicandcontrolmodelhasthesameflightperformancesasthespaceshuttleorbiter.
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    SpacecraftTT&CSchedulingModelsandAlgorithms
    XU Xiao-Hui, HU Shao-Lin, GUO Xiao-Hong, ZHAO Zong-Yu
    2014, 34 (3):  32-37.  doi: 10.3780/j.issn.1000-758X.2014.03.005
    Abstract ( 1121 )   PDF (391KB) ( 1046 )   Save
    ThemainobjectiveofspacecraftTT&C(Track,Telemetry&Control)  resourcesschedulingproblemistomaximizethespacecrafttasksthroughTT&Cresourcesallocationwithsomeschedulingmethods.Atimewindow-orientedmodelwasproposedinreferencetothetaskorientedmodels.Furthermore,thebranchandboundalgorithmofthemodelanditscomplexityanalysisweregiven.Finally,thevalidityandpracticabilityofthealgorithmswereshowedbysimulation.
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    AerodynamicEngineeringPredictionMethodsforWingedReentryVehicles
    HAO Jia-Ao, JIANG Chong-Wen, GAO Zhen-Xun, LI Chun-Xuan
    2014, 34 (3):  38-45.  doi: 10.3780/j.issn.1000-758X.2014.03.006
    Abstract ( 1415 )   PDF (472KB) ( 827 )   Save
    Focusedonthecalculationinaccuracyofexistingengineeringpredictionmethodsforwingedreentryvehicles,amodifiedcomponentpartitionstrategyandpressuremethodselectionrationaleweredeveloped.ThroughcomparisonoftheexperimentaldataandtheengineeringpredictiononlongitudeaerodynamiccharacteristicsofspaceshuttleorbiterandaX-34likevehicle,itisshownthatthepredictionmethodcanmeettheaccuracyrequirementsatMach3.0orhigher.Themaximumrelativelyerrorislessthan10%forliftcoefficientsanddragcoefficients.Comparedwiththeexistingmethods,theproposedstrategyandrationaleimprovesthepredictionaccuracyinpitchingmomentcoefficient,withthesameaccuracyinliftanddragcharacteristics.Besides,thepredictivepressuredistributionisinagreementwiththenumericalresults.
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    ANovelDe-noisingAlgorithmBasedonUn-decimatedWaveletPacketTransform
    LU Wei-Tao, ZHANG Shu-Xian, YANG Wen-Ge, HONG Jia-Cai
    2014, 34 (3):  46-52.  doi: 10.3780/j.issn.1000-758X.2014.03.007
    Abstract ( 1304 )   PDF (466KB) ( 765 )   Save
    FilterprocessingisbeneficialtoimprovethequalityofreceivedsignalandthemeasuringperformanceofTT&Csystem.Ade-noisealgorithmusingShiftedUn-decimatedWaveletPacketTransform(SUWPT)wasmodified.InsteadofEnergyCompactionMeasure(ECM),thePowerFlatness(PF)wasusedinthenewalgorithmastheruletodecidewhetheranodewasneededtodecompose,andthedisadvantagesoftheoriginalones,suchasabortdecompositionbecauseofmisjudgmentorcomplexitybecauseofmanytimesdecompositionwereovercome.Meanwhile,theproblemthatthethresholdwashardtodeterminewasalsosolved.Simulationresultsshowthatcomparedwiththeoriginalalgorithm,themodifiedonehasabetterperformancewithlesscomplexity.Finally,thesimulationsignalandin-orbitsatellitedatawasprocessedwiththemodifiedalgorithm.Resultsshowthattheaccuracyofthedifferencephaseofthesimulationsignalisimprovedbyabout3timesandtheaccuracyofthein-orbitsatellitedataisimprovedby0.72times.
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    VerticalWeightlessMovementMethodBasedonEquivalentDynamics
    XU Zhi-Gang, WANG Hao, WANG Jun-Yi, BIAN Zhen-Zhen
    2014, 34 (3):  53-60.  doi: 10.3780/j.issn.1000-758X.2014.03.008
    Abstract ( 1123 )   PDF (414KB) ( 929 )   Save
    Forthedifficultyonspacecraftgroundsimulationofhighprecisionmicrogravity,averticalweightlessmovementmethodbasedonequivalentdynamicswasproposed.Theequivalentdynamicsanditsconditionswerebroughtforwardtoimplementhighprecisionverticalweightlessmovementsimulation. Then, thesimulatordesignrequirementsbasedontheproposedmethodwereanalyzed.Throughsimulationanalysisofthesimulationaccuracy,thepossibleproblemsofthedesignprinciplewerediscussed. Erroranalysisandsimulationcalculationresultsshowtheweightlessnesssimulationaccuracyisupto99%,whichcansatisfytherequirementsofthehighprecisionmicrogravitysimulationexperiment.
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    AnImprovedNon-uniformityCalibrationTechnologywithMulti-positionFusedData
    CAO Wei, DONG Shu-Li, LI Chun-Mei
    2014, 34 (3):  61-66.  doi: 10.3780/j.issn.1000-758X.2014.03.009
    Abstract ( 1258 )   PDF (355KB) ( 969 )   Save
    Thecalibrationaccuracydeclineswhenthereisrelativelocationchangebetweenthecameraandtheintegratingsphereintheprocessofnon-uniformitycalibration.Anewmethodofrelativeradiometriccalibrationusingmulti-positionfuseddatawasproposed.Toeliminatetheshortcomingofangularandfacialnon-uniformityoftheintegratingsphere,thecalibrationcoefficientswereobtainedbyalotofimagesfrommulti-positions.Experimentresultsshowthattheproposedmethodcandecreasetheeffectofnon-uniformityofthespherelightintensityonthecalibrationcoefficients,undertheconditionthatthelightintensityoftheintegratingsphereisunevenandtherelativepositionbetweenthecameraandthespherecannotbefixed.Thisnewmethodcanimprovethenon-uniformitycalibrationaccuracy.
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    ErrorModelingandEvaluationofUSBRangeandRange-rateMeasurements
    ZHENG Ai-Wu, SUN Jing, HU Song-Jie, ZHOU Jian-Ping
    2014, 34 (3):  67-72.  doi: 10.3780/j.issn.1000-758X.2014.03.010
    Abstract ( 1138 )   PDF (360KB) ( 865 )   Save
    TheUnifiedS-bandSystem(USB)isthemainTT&C(Telemetry,TrackingandCommand)networkusedinspacemissionsincludingmannedspacecraftandlunarexplorationprogramsofChina.Firstly,allkindsoferrorsexistedintheUSBrangeandrange-rate  measurementswereanalyzed,andtheerrorcorrectionmodelsoftroposphericrefractiondelay,ionosphericdelay,timetagbias,phasecentererror,channeldelayandsatelliteephemeriserrorwerepresented.Secondly,theaccuracyoftheUSBmeasurementswasevaluatedandobtainedbasedontheresidualanalysisoftheUSBrangeandrange-ratemeasurementsofarealspacemission.Finally,accordingtothecurrentactualityofdisposalandapplicationofUSBmeasurements,someadvicesthatshouldbenotedindataprocessingwereputforward.TheconclusionshaveimportantreferencevaluetoimprovetheaccuracyoforbitdeterminationbasedontheUSBsystemofChina.
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    AnalysisofParachuteDeploymentDeviationforMarsEntryUnderInitialConditionErrors
    CHEN Yang, SUN Hai-Bin, GUO Lei
    2014, 34 (3):  73-78.  doi: 10.3780/j.issn.1000-758X.2014.03.011
    Abstract ( 1310 )   PDF (281KB) ( 998 )   Save
    WiththedevelopmentoftheMarsexploremission,theproblemofpreciselandingisnowconsideredtobeanessentialchallenge.ForaMarslandingmission,theinitialconditionerrorswouldresultinthedeviationofparachutedeployment,sothelandingpointerrorswouldbelarger.TheMarsatmosphericentryphasewasintroduced,andthedynamicequationofthevehicleandthecorrespondingmathematicmodelswereproposed.A1000-runMonteCarlostudywasperformedtoanalyzetheparachutedeploymentdeviationundertheinitialconditionerrors.Thestudyshowsthatthedownrangeerroris20~40km, andthecrossrangeerroris5~10km.Somesuggestionsweregivenfortheparachutedeploymentprecision,andsomeentryguidancealgorithmswerealsointroduced.
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    EffectsofIonosphericScintillationonNavigationReceiverPerformance
    Liu Si-Hui
    2014, 34 (3):  79-83.  doi: 10.3780/j.issn.1000-758X.2014.03.012
    Abstract ( 1134 )   PDF (308KB) ( 917 )   Save
    Toquantitativelyanalyzetheeffectsoftheionosphericscintillationonthereceivertrackingloop,thesignalamplitude,thephaseofcarrierandcode,thecarriernoiseratio,andthetrackingofI/Qchannelwereanalyzed,basedontheequivalentchannelmodelofthesignaltransferunderthescintillationconditions.Theresultsshowthatthecarriernoiseratiocandeclinerapidly,causedbytheionosphericscintillation,evenreducingby5dBintheseverecases.Thiswillhavesignificanteffectsonthepositioningaccuracy.Furthermore,anarrowerbandwidthoftrackingloopwillleadtotheweakercycleslipofcarrierunderthesameionosphericscintillation.
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