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    25 August 2015, Volume 35 Issue 4 Previous Issue    Next Issue
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    ContactDynamicsModelofRefuelingDeviceandComplianceControlforSpaceRobots
    ZHANG Hai-Bo, WANG Da-Yi, WEI Chun-Ling
    2015, 35 (4):  1-9.  doi: 10.3780/j.issn.1000-758X.2015.04.001
    Abstract ( 1579 )   PDF (481KB) ( 1372 )   Save
    Force/positionhybridcompliantcontrollawwasproposedtoweakentheeffectonspacemanipulatorwhenanactivedevicewasinvolvedinacollisionwithapassivedevice.Firstly,usingthesecondkindofLagrangeequations,thefloatingbasespacemanipulatorkinematicsanddynamicsmodelwereconstructedconsideringthecontactenvironment.Secondly,apole-conetyperefuelingdevicewasgiven.Accordingtothecontactcharacteristicsoftheactiveandpassivedevice,apoint-surfacecontactcollisiondynamicsmodelwasestablished,andthecorrespondingcollisionforcecalculationmethodwasgiven.Then,refuelingdockingproblemwasformulatedforspacecraft-referencedendpointmotioncontrolproblem.Onthisbasis,thedesiredmanipulatorend-pointtrajectorywasplannedandthepositionloopcontrollawwasproposed.Thecollisionforcewasobtainedaccordingtothepositionbetweentherefuelingactiveandpassivedevices,andtheforce/torqueloopcontrollawwasproposed.Furthermore,combinedwithadaptationselectionmatrix,theforce/positionhybridcontrollerwasobtainedtoreducethecollisionimpactonspacerobot.Finally,simulationresultsshowthatthedockingdirectionpositionerrorreducestozerofromtheinitialvalue,andthecollisionforceislessthan10Nduringdocking,andjointtorquedoesnotexceed13Nm.Theactiveandpassivedevicescompletecompliantcontractbythedesignedforce/positionhybridcontroller.
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    ResearchonPerformanceAnalysisMethodofGlobalSatelliteNavigationSystemSignal
    ZHANG Jian-Jun, XUE Ming
    2015, 35 (4):  10-16.  doi: 10.3780/j.issn.1000-758X.2015.04.002
    Abstract ( 1052 )   PDF (285KB) ( 946 )   Save
    Sofar,computersimulationisthemainevaluationmethodforthecompatibilityperformanceofthesatellitenavigationsignals.Themodelingwasusedtosimulatethemeasuringconditionandstep,butitisimpossibletoreproducetheoperatingconditionoftherealnavigationsystem.Anyparameterchangewillleadtotheresimulation,averylargeamountofcomputationandanalysis,andlargeerrors.Basedonthesatellitenavigationreceiver,thecompatibilityofthenavigationsignalwasstudied.Firstly,themodelwasdeducedbytheratiooftheoutputsignalpowerofinstantcorrugatortothesumofthenoisepowerandtheinterferencepower,accordingtotheeffectoftheinterferencesignalonGNSSreceivercapture,carriertrackinganddataconditioning.Toobtaintheoptimalassessmentoftheinference,theequivalentcarriertonoiseratiomodelwasestablishedbyarelativelysimpleformula,basedonaspectralisolationfactor.Secondly,thepower,theantennagainandtheconstellationpowergainofthenavigationsignalswereanalyzedconcretelywhensignalarrivedatthegroundastheGPSC/Acodeself-disturbed.Finally,theattenuationtestingresultoftheequivalentcarriertonoiseratiowasshownwhentheGPSC/Acodeself-disturbed.Itprovidesreferenceforthesignaldesignofthenewsatellitenavigationsystem.
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    ImagingExperimentwithLongIntegratedTimeandCurvedTrajectoryforGeosynchronousObitSAR
    LI Cai-Pin, HE Ming-Yi, ZHU Ya-Lin, LI Guang-Ting, LIU Bo
    2015, 35 (4):  17-22.  doi: 10.3780/j.issn.1000-758X.2015.04.003
    Abstract ( 1120 )   PDF (1341KB) ( 1058 )   Save
    GeosynchronousorbitSAR(GEOSAR)haswideapplicationsinmilitaryandcivilianareasbecauseoftheadvantagesofwiderswathandshorterrevisitingperiod.AimingatthecompleximagingcharacteristicsoflongsyntheticaperturetimeandcurvedtrajectoryinGEOSAR,agroundexperimentmethodwasproposedtoverifytheimagingfeasibility.Thequantitativeanalysiscurvedtrajectorywithlongsyntheticaperturetimewasgiven,andtheexperimentplanwasputforward.Theexperimentresultsshowthatitcanachievelongsyntheticaperturetimebendingtrajectoryimaging.
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    AReliabilityValidationTestwithSmallSamplesforPyrotechnicCutters
    LIU Shi-Yi, LIU Zhi-Quan
    2015, 35 (4):  23-29.  doi: 10.3780/j.issn.1000-758X.2015.04.004
    Abstract ( 969 )   PDF (1391KB) ( 821 )   Save
    Areliabilityvalidationtestmethodandaconservativereliabilityassessmentmethodforpyrotechniccutterswereputforwardbasedoncharacteristicparametermeasurementswithsmallsamples.Ascharacteristicparameters,thepeakgas-pressuresofthecutterintheratedcondition(bilateralignition)andintheunilateralignitionconditionweremeasuredinthetest.Basedonthegeneralizedstrengthstresstheory,thereliabilityassessmentwascarriedoutbytestdatawithsmallsamples.Theproposedreliabilityvalidationtestmethodnotonlyavoidsconsumingmoretestproductstoobtaincriticalvaluedistributionofthecharacteristicparameters,butalsoutilizescharacteristicparametervariablesinsteadofcountingthesuccess numberofsamples.Besides,Thismethoddoesn′tneedartificialintensificationcoefficients.Hence,thereliabilityassessmentresultscanreflecttherealreliabilityleveloftheproductsintheworseworkingconditions.Anapplicationexamplewasgiven,inwhichonly60testsamplesofthepyrotechniccutterwereusedforthereliabilityvalidationtestandthereliabilityassessment.Themethodcontributestothesmallsamplereliabilityassessmentofpyrotechnicdevicesinspacecraft.
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    Thermal-mechanicalOptimizingAnalysisonMulti-scaleNumericalModelforCompositeStructureofSatellite
    MA Jian, ZHANG Hong-Yu, YAN Liang, RAN Zhi-Guo
    2015, 35 (4):  30-36.  doi: 10.3780/j.issn.1000-758X.2015.04.005
    Abstract ( 983 )   PDF (432KB) ( 831 )   Save
    Whenspacecraftworks,itwillsufferdifferenttemperatureenvironments,whiletemperaturedifferencewillalwaysintroducechangesofshapeandsizeofcompositestructures.However,somespacecraftpartsneedhighdimensionalstabilitytokeepitsrightfunction.Tillnow,themechanicalpropertiesofthecompositehavebeenwidelystudied,however,thethermalpropertiesofcompositeandoptimizationofcompositeconsideringboththermalandmechanicalpropertiesarefarfromwellstudied.Compositetubeswereoptimizedtoagivencoefficientofthermalexpansion(CTE),andthestiffnessofthosetubeswastakenintoconsiderationatthesametime.Firstly,multiscalenumericalmodelsweredevelopedtocalculatetheCTE.Inmicro-scalemode,theCTEofunidirectionalfiberreinforcedcompositewascalculatedbythefiberCTEthroughrepresentativevolumeelements(RVE).In macro-scale,acompositetubemodelwasgeneratedtopredictbothaxialandtransverseCTEofthetubebasedontheCTEcomputedbyRVE.Compositelaminatesandtubeswithgivenplieswereanalyzedandtested.Comparisonbetweenthepredictedresultsandtheexperimentaloneverifiedthemodel,whichmadethefoundationfortheoptimizationmode.Secondly,optimizationmodelsforcompositetrussstructurewerecreated.Theconjugategradientmethodwasadoptedtooptimizethepliesofcompositeparts,andthethermal-mechanicaloptimizingmethodwasdeveloped.Finally,thesatellitesupporttrussstructurewasanalyzedbythethermal-mechanicaloptimizingmethod.Analyzedresultsshowthatthisoptimizedsupportstructureandthewholeantennahaveanexcellentthermaldimensionalstability.Thethermalmechanicaloptimizingmethodcanbeusedforthermalstabilitydesignandanalysisofcompositesupporttrussstructures.
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    ResearchofOn-boardSoftwareComponentsBasedonNon-objectOrientedLanguage
    ZHANG Ya-Hang, GUO Jian, YU Jun-Hui
    2015, 35 (4):  37-45.  doi: 10.3780/j.issn.1000-758X.2015.04.006
    Abstract ( 1056 )   PDF (354KB) ( 705 )   Save
    Inordertofurtherimprovethereusabilityoftheonboardsoftwareandtosolvetheproblemoftheon-boardsoftwareinefficientdevelopment,thecharacteristicsofthespacecraftsoftwareandthesoftwarecomponenttechnologywereanalyzed.Thenadefinitionoftheonboardsoftwarecomponentwasgiven,andanon-boardsoftwarecomponentmodelsuitableforspacecraftwasproposedbasedonthenon-objectorientedlanguage.Theon-boardsoftwarecomponentsareindependent,integrate,assembleandfunctional.Besides,themethodfortheonboardsoftwarecomponentdesign,developandimplementwasdescribed.Itcanbetheguideoftheonboardsoftwarecomponentdevelopmentbasedonthenon-objectorientedlanguage.Someexamplesweregiven,inwhichthesoftwaresystemsweredevelopedaccordingtheproposedmethod.Theresultsshowthatspacecraftsoftwarecomponentdevelopmentmethodsareeffective,andthespacecraftsoftwaredevelopmentefficiencycanbeincreasedby200%~500%.
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    TransientThermalAnalysisofHeatPipeReceiverunderMicrogravity
    GUI Xiao-Hong, SONG Xiang-E
    2015, 35 (4):  46-52.  doi: 10.3780/j.issn.1000-758X.2015.04.007
    Abstract ( 947 )   PDF (464KB) ( 666 )   Save
    Hightemperatureheatpipereceiversarecommonlyusedasacorecomponentofspacesolardynamicpowersystem.Onthebaseofheatconductiongoverningdifferentialequationundermicrogravity,two-dimensionalnumericalanalysisofPCMcontainerwasconductedbyaenthalpymethod.Withbothvoidcavityandphasechangeconsidered,thermalperformanceofheatpipereceiverwasanalyzed.NumericalresultswerecomparedwithNASAresults.Theaccuracyofcalculationmodelundergravitywasverified.Theresultsindicatethatvoidcavityinfluencestheprocessofphasechange.ThevoidcavityreducestheutilityandthermalstorageabilityofPCM.ThetemperaturegradientofPCMzoneisverysignificantbecauseofthevoidcavity.ThePCMcontainedintheintegratedheatpipeperformstheaveragingfunctionoftheheatloads.Normalworkingofwickensurestheuniformityofheatpipe,thusheatpipereceiveralleviatesthermalspotandthermalratcheting.
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    PerformanceAnalysisforBeiDouRegionalNavigationSatelliteSystemofNPA
    LIU Rui-Hua, ZHAO Qing-Tian, 吕Xiao-Ping , DENG Ming-Zhi
    2015, 35 (4):  53-59.  doi: 10.3780/j.issn.1000-758X.2015.04.008
    Abstract ( 1218 )   PDF (1448KB) ( 1334 )   Save
    AprospectiveresearchforusingtheBeiDouRegionalNavigationSatelliteSystemtocivilaviationapplicationwasmadebasedonthecharacteristicsof“5GEO+5IGSO+4MEO” constellationandrequirementsofnonpreciseapproach(NPA)incivilaviation.Forthreeindexesthevisibilityofspacevehicle,dilutionofprecision(DOP)valuesandhorizontalprotectionlevel(HPL)value,thestatisticalcharacteristicsinAsiaPacificareaandthecomparisonofthreeindexesfor4designateduserlocationswerepresentedbysimulationandanalysis.TheresultsshowthattheBeiDouRegionalNavigationSatelliteSystemhastheabilitytoprovidetheidealnumberofsatelliteinsight,bettervaluesofDOPandHPL,andcanmeetthecurrentneedsoftheabovethreeindexesinNPAflightphase.
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    ResearchonReverberantLoadModelingMethodandItsSpatialCorrelationEffectonVibro-acousticAnalysis
    ZHU Wei-Hong, HAN Zeng-Yao, ZOU Yuan-Jie
    2015, 35 (4):  60-68.  doi: 10.3780/j.issn.1000-758X.2015.04.009
    Abstract ( 958 )   PDF (634KB) ( 813 )   Save
    Amodelingmethodofreverberantloadwhichmeetsthespatialcorrelationwasproposedforthevibro-acousticanalysisofspacecraft,whichcansimplifythemodelingprocessofvibro-acousticanalysisandbeconvenientforengineeringapplications.Firstly,thespatialcorrelationtheoreticalmodelofreverberantloadwasestablishedbasedonwavetheory,thencombinedtherequirementsofspacecraftengineering,thereverberantloadmodelwasdevelopedonthebasisofRayleighintegralandreciprocityrelationship,andthesatisfactionwithspatialcorrelationtheoreticalmodelwasproved.Finally,theavailabilityofthismethodwasguaranteedbytypicalsystemanalysis,andtheeffectofspatialcorrelationofreverberantloadonthevibro-acousticanalysiswasevaluated.
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    ResearchonTransonicWindTunnelTestsofMarsDisk-Gap-BandParachutes
    GAO Shu-Yi, GE Si-Cheng, LIANG Yan
    2015, 35 (4):  69-75.  doi: 10.3780/j.issn.1000-758X.2015.04.010
    Abstract ( 1041 )   PDF (343KB) ( 859 )   Save
    IntheMarsentrydeceleratelandingprogram,theparachuteisakeyinstrumentoftheaerodynamicdeceleratorsystem.BecauseoftheparticularityoftheMarsatmosphere,theparachuteusedfortheMarsmissondeploysunderthesupersonic,lowdensity,lowdynamicpressureconditions.SotheconstructionandsizingoftheMarsparachuteismuchimportant.TheMarsparachutetechnologywasinvestigatedandanalyzedbyfourtypesofparachute,consideringthediskbandarearatioandporosityofthecanopymaterial.Todeterminethedragandstaticstabilityofthevarioustypesofdisk-gap-bandparachutemodel,theMarsparachutetransoniccharacteristicstestinChinawasfirstlyconducted.Thefronttrussandwindtunnelbalancewasusedtomeasuretheaxisforceontheparachutemodel,andthephotographywasusedtoobservetheangleofattackoftheparachute.Thetestresultsshowthat,thetransonicdragcoefficientofthedisk-gap-bandparachuteaccordswiththetheoreticaloneandcansatisfytheMarsmissionrequirements.Itisalsoobservedthatthereductionofstabilityofthedisk-gap-bandparachuteisaccompaniedbytheincreasingofthedragperformance.
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    MeasurementAlgorithmBasedonMotorAlgebraforRelativePositionandAttitudeDeterminationofRVDSpacecraft
    CHEN Wei, CHEN Zhi-Ming, WANG Hui-南
    2015, 35 (4):  76-83.  doi: 10.3780/j.issn.1000-758X.2015.04.011
    Abstract ( 1172 )   PDF (1404KB) ( 955 )   Save
    Accuratemeasurementoftherelativepositionandattitudebetweentheactivespacecraftandthetargetspacecraftisthekeytothesuccessfulcompletionofrendezvousanddocking(RVD)mission.Inthetraditionalvectormeasurementmethods,thepositionandattitudeareusuallytreatedseparately,whichledtothedifficultyofalgorithmdesignandcomputationalcomplexity. AnewbinocularvisionmeasurementalgorithmbasedonmotoralgebrawasproposedtouniformlydescribetherelativepositionandtheattitudeofthetwoRVDspacecraft.Thisnewalgorithmhasamoreconciseformandsomecomputationaladvantagescomparedtothetraditionalmethods.Therelativepositionandattitudedeterminationproblemwassimplifiedtosolvingtwolinearequations.SimulationresultsshowthatthealgorithmcanmeetthemeasurementaccuracyrequirementsofRVDmissions.
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