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    25 October 2013, Volume 33 Issue 5 Previous Issue    Next Issue
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    DesignMethodofHighPrecisionPerimeterTrussAntennaonBoard
    ZHANG Hua-Zhen, MA Xiao-Fei, SONG Yan-Ping, CHEN Guo-Hui, LI Tuan-Jie
    2013, 33 (5):  1-6.  doi: 10.3780/j.issn.1000-758X.2013.05.001
    Abstract ( 1452 )   PDF (422KB) ( 1389 )   Save
    Owingtoitslightweight,highprecisionandhighstiffness,theperimetertrussantennaisthecurrentstateofartofthelargedeployableantenna.Theantennaprecisionisbecomingmoreandmorecriticalwiththeadvancementoftheinspaceapplications.Firstly,thecompositionandfundamentaltorealizethehighprecisionperimetertrussantennawasintroduced.Basedontherealengineeringrealization,considerationsofachievingthehighprecision,designanalysismethod,onorbitthermaldeformationwasdiscussedindetail.Secondly,themethodologyoftwomeshtensionsymmetrylayoutandellipseperimetertrussforimprovingantennaprecisionwasproposed.Symmetrylayoutcangetgoodstressdistributionandsystemstiffness.Sothermalenvironmentcan′tchangethesurfacecoordinationevidently.Ellipseperimetertrusscanrealizeallnodeontherigidpoint,onthesametime,ellipsestructureismorestablethanthecyclestructure.Therearetwointersectionstylesbetweentheellipseandcyclestructures,suchasinclinationanduprightnessintersection,andinclinationstylecanrotateangelarbitrarilysothatsomediversenodeassignmentcombinationcanbeselected.  
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    OnMidcourseCorrectionofMoonEarthReturnTrajectoryBasedonExplicitGuidance
    HU Jun, ZHOU Liang
    2013, 33 (5):  7-14.  doi: 10.3780/j.issn.1000-758X.2013.05.002
    Abstract ( 1474 )   PDF (437KB) ( 1236 )   Save
    TheresearchonthemidcoursecorrectionofMoonEarthreturntrajectoryisnecessary,asnominalorbitisperturbedbyseveraldisturbancesourcesandboundaryconstraintsiscomplicated.Thesolutionofcharacteristicvelocitywasgotthroughtheexplicit guidancemethodbyusingtheiterationsalgorithmbasedonthedifferencebetweenthetwobody orbitandprecisetrajectory.Asthemidcoursecorrectionstrategywasdividedintomoonsectionandearthsection,theexplicitguidancecorrectionschemesofMoonEarthreturntrajectorybasedonsubsectionlocationpointspredictionwaspresented.Theschemecansatisfythereentrypointparametersconstraintsandcanbeusedwidelyinpractice,asthealgorithmissimplifiedtoovercomedisadvantagesofthedifferentialcorrectionalgorithmwhichrequiresanumericalJacobianmatrix.Finally,theadaptabilityoftheschemewasvalidatedbynumericalsimulationandMonteCarlosimulation.
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    LimitEquationsforHypervelocityImpacts onHoneycombSandwichPanels
    JIA Guang-Hui, OUYANG Zhi-Jiang
    2013, 33 (5):  15-21.  doi: 10.3780/j.issn.1000-758X.2013.05.003
    Abstract ( 1683 )   PDF (477KB) ( 1170 )   Save
    Toexplorethepredictiveabilityforthepenetrationcharacteristicsoftheimpact limitequationsabouthoneycombsandwich, 3typesofballisticlimitequations,equivalentmethodsonthepanelthickness, and131CFRPexperimentaldatahadbeeninvestigated, andthepredictiveabilityoftheequationshadbeencalculated. TheresultsshowthatthepredictedprobabilitiesofMETequationtootherdatasourceareallover80%, soMETequationcanbepreferredintheengineeringpredictionfortheprotectivestructure. ThesafetypredictionratesofSRLquationtootherdatasourceandselfdatasourceareallreach100%, soSRLequationsuitsforthedesignofhighreliabilityprotectionstructure. Finally, theideaofoptimizingcoefficientsandspeedcutoffvaluefortheimpactlimitequationswasstudiedtoimprovethepredictiveability.
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    Pulsar/CNSIntegratedNavigationMethodBasedonImprovedKinematicandStaticFilterforDeepSpaceExplorer
    WANG Yi-Di, ZHENG Wei, AN Xue-Ying, SUN Shou-Ming
    2013, 33 (5):  22-28.  doi: 10.3780/j.issn.1000-758X.2013.05.004
    Abstract ( 1369 )   PDF (435KB) ( 862 )   Save
    APulsar/CNSintegratednavigationalgorithmbasedontheimprovedkinematicandstaticfilterwasproposedThemeasurementofpulsarandthestellaranglemeasurementwerefusedbytheimprovedkinematicandstaticfilter,inwhichtheUKFwasusedasthekinematicfiltertodealwiththestellaranglemeasurementatafastsamplingvelocityandtheEKFwasusedasthestaticfiltertodealwiththepulsarmeasurementataslowsamplingvelocityTheproposedimprovedkinematicandstaticfiltercanavoidthecorrelationsbetweenthefusiondatasetsofdifferentsensors.Thesimulationresultsshowthattheproposedintegratednavigationsystemcanimprovetheperformanceoftheautonomousnavigationsystemadoptedbydeepspaceexplorer.
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    InfluenceofMagneticComponentDistributionofSatelliteonEliminatingRemanantMagneticFieldbyGradientMethod
    ZHOU Bin, WANG Jin-Dong
    2013, 33 (5):  29-34.  doi: 10.3780/j.issn.1000-758X.2013.05.005
    Abstract ( 1594 )   PDF (363KB) ( 1119 )   Save
    Errorcoefficientofdualprobegradientmethodcanreach0.5to0.3inengineering,thatmeansonly50%to70%ofthesatelliteremanenceinterferencecanbeeliminated.Theprincipleofthedualprobegradientmethodwaspresentedtoeliminatesatelliteremanenceandthesourcesofdualprobegradientmethoderrorwereinvestigated.Furthermore,theinfluenceofthesatelliteremanencecomponentdistributiononthemagneticcorewasanalyzed.Andthekeyroleofpositionalrelationshipbetweenthemagneticcoreanddualprobeonthedualprobegradientmethodwasdescribed.Undertheconditionthatthemagneticcorepositionwasdeterminedandthedualprobeinstallationdirectionpointedtothecore,theerrorsofthedualprobegradientmethodwasminimized.Simulationresultsshowthatthedualprobegradientmethoderrorcoefficientcandecreasefrom0.4to0.03orlessbyoptimizingremanencecomponentdistributionanddualprobeinstallationlocation.
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    AsymptoticStabilizationforDeploymentandRetrievalofaTetheredSatelliteSystem
    YU Ben-Song, JIN Dong-Ping
    2013, 33 (5):  35-42.  doi: 10.3780/j.issn.1000-758X.2013.05.006
    Abstract ( 1422 )   PDF (419KB) ( 1169 )   Save
    Anasymptoticstabilitystrategyfordeploymentandretrievalofatetheredsatellitesysteminellipticalorbitswasstudied.Firstly,thestabilityofaninplanetetheredsatellitesystemmovinginanellipticalorbitwasanalyzed,anovelratecontrolforstabilizingthedeploymentandretrievalwasobtained,andthestabilityconditionsforthecontrolweregivenbasedonLyapunovstabilitytheory.Then,aratebasedcontrolmethodtosuppressthelargeswingaroundthelocalverticalpositionoftetheredsatellitesystemwaspresented.Undersuchcontrolstrategy,thedeploymentandretrievalofthetethermadeanasymptoticstablemotiontowardstothepreassignedpitchangle.Theresultsshowthatthereexistsanorbitalregion,onwhichtheretrievalprocesscankeepasymptoticstability.Tooptimizetheeffectofretrievalcontrol,thepartitioningandsegmentingstrategiesontheorbitwereproposed.Finally,theproposedcontrollaw,stabilityconditions,andcontrolstrategiesweredemonstratedbythenumericalsimulations.
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    ResearchonLargeRangeHighprecisionAngleMeasurementAlgorithminRVDMicrowaveDockingRadar
    YAN Qi, YANG Rui-Qiang, ZONG Nian-Ke, ZHANG Peng, CAI Chun-Gui
    2013, 33 (5):  43-48.  doi: 10.3780/j.issn.1000-758X.2013.05.007
    Abstract ( 1208 )   PDF (336KB) ( 1241 )   Save
    Thetraditionalanglemeasurementmethodsofmicrowaveradararedifficulttosatisfyaccuracyrequirementsundertherendezvousanddockingnearfieldconditions.Toachievethehighprecisionanglemeasuringinawiderangeincludingnearfieldaswellasfarfield,anewalgorithmbasedonphasedifferencecomplexvectormatchingwasproposed.Firstly,anobjectfunctionwasdefinedtoquantifythesimilarityofthephasedifferencecomplexvector.Secondly,anonlinearprogrammingmodelwasestablishedtoestimatetheazimuthandelevationanglesandthesolvingstepsofthemodelweredescribedindetail.Finally,theresultsofnumericalsimulation,airborneflighttestandanechoicchamberexperimentprovetheeffectivenessofthealgorithmwithahighprecisionof0.12°.
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    AttitudeDeterminationofSpacecraftBasedonIRAPFAlgorithms
    LI Hai-Jun, ZHAO Guo-Rong
    2013, 33 (5):  49-55.  doi: 10.3780/j.issn.1000-758X.2013.05.008
    Abstract ( 1345 )   PDF (361KB) ( 1070 )   Save
    AimingatthelargeinitialerrorandthestrongnonlinearproblemexistedinSpacecraftattitudedetermination,animprovedregularizedauxiliaryparticlefilter(IRAPF)algorithmwasproposed.TheregularizedParticleFilter (RPF) waslinkedwiththeauxiliaryparticlefilter(APF),andthefastGausstransform(FGT)wasintroducedintothealgorithmtoimproveconvergenceefficiency.Thisalgorithmcanrestrainparticledegenerating,optimizingsamplingbyusingthenewestobservedparticles.ByintroducingFGT,thecalculationwasreduced30%comparedwithRAPFmethodandtherealtimefeaturewasimproved.Simulationresultsprovethevalidityofthealgorithm.
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    H-ModeGasIonizationModelforPassiveSpaceborneHydrogenMaserandParametersOptimization
    WANG Yong, QIU Shi, LI Jian-Qing
    2013, 33 (5):  56-61.  doi: 10.3780/j.issn.1000-758X.2013.05.009
    Abstract ( 1401 )   PDF (381KB) ( 913 )   Save
    AnH-modeionizationsystemwasdesignedfortherequirementsoflowpowerconsumptionandlowelectromagneticinterferenceofthepassivespacebornehydrogenmaser,whichadoptingaplanarrolledcoilantennatosupplypower.Andamathematicmodelofionizationwasbuilt.Firstly,thedistributionmodelofelectromagneticfieldintheionizationbubbleandtheionizationmechanismofthecertainmethodwerededucedfromtheMaxwellequations.Andthen,theionizationpunctureconditioncriterionanditsmathematicmodelwereacquired.Finally,parametersofionizationdevicewereoptimizedbythecriterionequation.Bothsimulationandmeasurementshowthattheionizationmodeliseffective,andtheoptimizeddesignparametershaveimprovedtheperformanceofpowerconsumptionandelectromagneticinterference,andthetotalDCpowercanbelessthan2W.
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    ASetofNovelOrbitalElementsModelingApproachUsingQuaternion
    CAO Jing, YUAN Jian-Ping, LUO Jian-Jun
    2013, 33 (5):  62-68.  doi: 10.3780/j.issn.1000-758X.2013.05.010
    Abstract ( 1426 )   PDF (294KB) ( 1402 )   Save
    Focusedonthesingular,indeterminationandthecalculationinefficiencyoftraditionalorbitalelementsbasedonEulerangles,asetofnovelorbitalelementsusingquaternionwasproposed.Therelationshipsofthenovelelementsandtheclassicorbitalelements,aswellasthenovelelementsandthepositionandvelocityintheinertialcoordinatewerebuilt.TheGaussperturbationequationswerederivedbasedonthenovelelements.Thevalidityandadvantageswerevalidatedbythepropagationoftheorbitunder J2 rturbation.Theresultsshowthatthenovelelementscannotonlyavoidthesingularandindeterminationincircularandequatorialorbit,butalsowithhighercalculationefficiencyandaccuracyforitsoperationwithouttrigonometricfunction.
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    SOSDesignforControlofLargeAttitudeManeuversofSatellites
    HE Zhen, MENG Fan-Wei, WANG Guang-Xiong, ZHOU Di
    2013, 33 (5):  69-75.  doi: 10.3780/j.issn.1000-758X.2013.05.011
    Abstract ( 1319 )   PDF (365KB) ( 1342 )   Save
    Becauseofthecouplingeffectbetweentheangularvelocitiesofeachaxis,thenonlineardynamicsofthesatellitemustbeconsideredforthecontroloflargeattitudemaneuvers.Besides,thekinematicsdifferentialequationoftheattituderepresentationisalsononlinear.Thesumofsquares(SOS)approachwasproposedasasynthesismethodforthenonlinearcontrolsystemdesign.ItisshownthatthefinalresultoftheSOSdesignhasclearphysicalmeanings,thoughitisanumericalmethod.Infact,theresultingcontrollawcanbeviewedasanonlinearversionofthePDcontrol.ToavoidthepeakvalueofthecontrolinputcausedbytheintrinsicpropertiesoftheMRPs,asaturationdesignwasproposed.Theconvergenceofthetimeresponseundersaturationcanbeprovedbythepassivitynatureofthesystem.AdiagonaldominanceprocedurewasalsoproposedtoreducethenumericalerrorsoftheSOSapproach.TheproposedSOSmethodcanbeusedtosolveanalyticallyunsolvablenonlinearproblemsandwouldhaveawideareaofapplicationsinthenearfuture.
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    EffectofParts′StiffnessonGeneralStiffnessofSpaceManipulatorJoint
    WEI Qing-Qing, WANG Yao-Bing, LIU Zhi-Quan
    2013, 33 (5):  76-81.  doi: 10.3780/j.issn.1000-758X.2013.05.012
    Abstract ( 1607 )   PDF (319KB) ( 1295 )   Save
    Thespacemanipulatorjointhastoadoptthehighreductionrategearbox.TheFEMshoweditsdisadvantageinthestiffnessanalysisandjointweightreductionduetothecomplexityofthegearbox.Thestiffnessmodelwasestablishedwiththelumpedparametermethodandthestiffnessseriesprinciple.Theinfluenceofallparts′stiffnessonthegeneralstiffnessofthespacemanipulatorjointwasanalyzedandanewwaytooptimizethehighreductionratejointwasgiven.
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