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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 ( 1375 )   PDF (419KB) ( 1287 )   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. Related Articles | Metrics

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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 ( 1542 )   PDF (399KB) ( 1244 )   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%. Related Articles | Metrics

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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 ( 1579 )   PDF (515KB) ( 909 )   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. Related Articles | Metrics

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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 ( 1383 )   PDF (556KB) ( 1188 )   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. Related Articles | Metrics

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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 ( 1397 )   PDF (391KB) ( 1187 )   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. Related Articles | Metrics

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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 ( 1565 )   PDF (472KB) ( 937 )   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. Related Articles | Metrics

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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 ( 1479 )   PDF (466KB) ( 912 )   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. Related Articles | Metrics

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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 ( 1259 )   PDF (414KB) ( 1088 )   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. Related Articles | Metrics

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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 ( 1494 )   PDF (355KB) ( 1154 )   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. Related Articles | Metrics

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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 ( 1243 )   PDF (360KB) ( 1016 )   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. Related Articles | Metrics

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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 ( 1377 )   PDF (281KB) ( 1154 )   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. Related Articles | Metrics

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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 ( 1224 )   PDF (308KB) ( 1062 )   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. Related Articles | Metrics