Table of Content

25 August 2015, Volume 35 Issue 4 Previous Issue    Next Issue

For Selected:

Download Citations EndNote Reference Manager ProCite BibTeX RefWorks

Toggle Thumbnails

Select

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 ( 1723 )   PDF (481KB) ( 1525 )   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. Related Articles | Metrics

Select

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 ( 1216 )   PDF (285KB) ( 1106 )   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. Related Articles | Metrics

Select

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 ( 1313 )   PDF (1341KB) ( 1226 )   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. Related Articles | Metrics

Select

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 ( 1306 )   PDF (1391KB) ( 960 )   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. Related Articles | Metrics

Select

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 ( 1298 )   PDF (432KB) ( 1081 )   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. Related Articles | Metrics

Select

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 ( 1191 )   PDF (354KB) ( 859 )   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%． Related Articles | Metrics

Select

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 ( 1109 )   PDF (464KB) ( 820 )   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. Related Articles | Metrics

Select

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 ( 1424 )   PDF (1448KB) ( 1533 )   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. Related Articles | Metrics

Select

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 ( 1143 )   PDF (634KB) ( 987 )   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. Related Articles | Metrics

Select

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 ( 1219 )   PDF (343KB) ( 1078 )   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. Related Articles | Metrics

Select

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 ( 1347 )   PDF (1404KB) ( 1086 )   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. Related Articles | Metrics