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    25 June 2013, Volume 33 Issue 3 Previous Issue    Next Issue
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    HybridSteeringLawwithFeedbackandFeedforwardforSingleGimbalControlMomentGyroscopes
    WU Zhong, DENG Shi-Long, WEI Kong-Ming, GUO Lei
    2013, 33 (3):  1-7.  doi: 10.3780/j.issn.1000-758X.2013.03.001
    Abstract ( 1933 )   PDF (414KB) ( 1247 )   Save
    Inordertoimprovetheperformanceinsingularityavoidanceandescapeofthedynamicsteeringlawforsinglegimbalcontrolmomentgyroscopes(SGCMGs),ahybridsteeringlawwithfeedbackandfeedforwardwasproposed.WhenSGCMGswasnotsingular,thedynamicsteeringlawwithfeedbackwasused.WhenSGCMGsapproachingtoorlockedinthesingularpoints,thefeedforwardwasconstructedtohelpthemavoidordetourroundthesingularpoints.Comparedwiththeconventionaldynamicsteeringlaws,thehybridonehasmuchmoresuperiorperformancesinsingularityavoidanceandescape.Meanwhile,thealgorithmhaslittlecalculationamountandiseasytoimplementsinceitonlyneedsthetransposeratherthanthepseudoinverseoftheJacobianmatrix.Extensivesimulationresultsdemonstratetheeffectivenessofthealgorithm.
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    HybridControlMethodforLarge-angleAttitudeManeuverofSingle-axisAirBearingTable
    TANG Sheng-Yong, HU Min, WU Jin-Jie, ZHANG Yu-Lin
    2013, 33 (3):  8-14.  doi: 10.3780/j.issn.1000-758X.2013.03.002
    Abstract ( 2023 )   PDF (418KB) ( 800 )   Save
    Tovalidatethelargeangleattitudemaneuvercontrolandprecisionstabilizationofasmallsatellite,ahybridcontrolmethodforasingle-axisairbearingtable(SABT)wasproposed,usingfourthrustersandaflywheeltoperformthescheme.Thephaseplaneapproachandfinitetimecontroltheoremwasusedtodesignthecontroller.Inthiscontrolscheme,thefourthrusterswerefirstlyactuatedtoachieveafastslewmaneuverwithoutovershoot,andtheflywheelwasthenactuatedtoperformthehighprecisionstabilizationinlimitedtime.Themethoddefinedanintelligentswitchbetweenthetwoactuatorsinrealtime.PhysicalsimulationresultsshowthatthemethodcanachievethelargeanglemaneuveroftheSABTinlimitedtime,andcaneffectivelyavoidtheovershootofthemaneuver,thechatteringofthethrustersandthesaturationoftheflywheel.
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    ImpulseControlforSpacecraftNearAsteroid
    GONG Sheng-Ping, LI Jun-Feng, BAOYIN He-Xi
    2013, 33 (3):  15-21.  doi: 10.3780/j.issn.1000-758X.2013.03.003
    Abstract ( 1739 )   PDF (404KB) ( 875 )   Save
    Animpulsecontrolmethodwasproposedforthepositionkeepingofaspacecraftnearasteroid.ConsideringthegravityoftheSunandasteroid,therelativeequationofmotionofthespacecraftwithrespecttotheasteroidwasderived.Thestatetransitionmatrixwasusedtodescribethemotioninthevicinityoftheasteroid.Athresholdcontrolmethodwasusedtoachievethepositionkeeping.Theimpulsecontrollerwastriggeredwhenthepositionerrorwaslargerthanaspecifiedvalue.Theresultsshowthatthismethodperformswellforthepositionkeeping,andthecontrolperiodislongandpropellantconsumptionislow.
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    DynamicModelingandCharacteristicsAnalysisforManipulatorTransformationSystemoftheSpaceStation
    ZHAO Zhi-Gang, ZHAO Yang, GE Wei-Ping, LIU Tun
    2013, 33 (3):  22-29.  doi: 10.3780/j.issn.1000-758X.2013.03.004
    Abstract ( 1402 )   PDF (483KB) ( 1242 )   Save
    Tostudythedynamiccharacteristicsofthespacestationtransformationviamanipulatorsystem,avectormechanicsmethodwasadoptedtodeducethedynamicequations.Thedynamicmodelingconsideringtheeccentricitywasestablished.Theelasticdeformationoftheflexiblemanipulatorwasdepictedbythefiniteelement(FE)method.ThedynamicmodelrepresentingtheattitudemotionwasestablishedwiththeNewtonEulermethod.ThevibrationsoftheflexiblemanipulatorcanbeobtainedbytheLagrangeapproach.Theloadangularvelocitycausedbythetipofelasticdeformationofthemanipulatorwasseparatedfromtheabsoluteanglevelocityoftheload.Toreducethedimensionsofthedynamicequations,aconstrainedmodeexpansionmethodwasusedfortheflexiblemanipulatorwithaheavyload.Themodelreductionmatrixfromspacetoplaneofthespacestationtransformationviamanipulatorwasproposed.Thesimulationresultsshowthattheoverallmomentofinertiarelativetothecenterofmasschangesgreatlyinthetranslocationprocessofthespacestation.Thescopeoftheeccentricityisbeyondthescopeofthegeometryofthecoremodule.Theresultscanbethetheoreticalreferencefordesigningcontrolsystemofspacestation.
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    PreciseModelingandApplicationofFluidicRingActuator
    GUAN Hong, XU Shi-Jie
    2013, 33 (3):  30-36.  doi: 10.3780/j.issn.1000-758X.2013.03.005
    Abstract ( 1651 )   PDF (427KB) ( 1269 )   Save
    Aprecisedynamicmodelofanovelattitudecontrolactuator——thefluidicringactuator(FRA)wasderived.Basedonthepracticalfactorsoftheflowinflowfield,thevariationofvelocitycausedbyviscouswasanalyzed.Theequivalentangularmomentumofthisnovelactuatorwasdeducedbyintegratingthevelocityoneverycrosssectionundertheconsiderationoffluidproperties.Then,theattitudedynamicsofthespacecraftwiththreeorthogonalFRAswasestablished.AnattitudecontrollawwasdesignedaccordingtotheattitudedynamicsofthespacecraftFRAssystem.Finally,simulationresultsdemonstratethattheoutputtorquehassuchadvantagesasfastreactionrateandsmallerrorbyusingtheprecisemodelofFRA.TheapplicationoftheprecisemodelofFRAmakestheattitudecontrolofaspacecraftmoreefficientandaccurate.
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    PeriodicSolutiontoEllipticalOrbitNonlinearRelativeMotionModelandtheApplication
    CAO Jing, YUAN Jian-Ping, LUO Jian-Jun
    2013, 33 (3):  37-45.  doi: 10.3780/j.issn.1000-758X.2013.03.006
    Abstract ( 1688 )   PDF (479KB) ( 1207 )   Save
    Traditionalformationkeepingorbitdesignisbasedonlinearrelativemotionmodelwhichwillleadtomorefuelconsumptionduringlongtermspacecraftformationflying.Firstly,theperiodicconditionandperiodicsolutionwereobtainedbysolvingtheellipticalorbitrelativemotionmodelconsideringthesecondordernonlineartermswithperturbationapproach.TheperiodicsolutionobtainedwasthenusedasthereferenceorbitofaPDcontrollawforformationkeepingbasedontheLyapunovstabilitytheory.Simulationresultsshowthattheperiodicsolutionbasedonthenonlinearrelativemotionmodelofellipticalorbitismoreaccuratethanthatbasedonlinearrelativemotionmodelofellipticalorbit.Andtheformationmaintaincontrollawwithperiodicreferenceorbitbasedonnonlinearmodelcansavemuchmorefuelcomparedwiththatbasedonthelinearmodel.
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    FittingParametersDesignforGEOBroadcastEphemeris
    DU Lan, ZHANG Zhong-Kai, LIU Li, HE Feng, HUANG Hua
    2013, 33 (3):  46-51.  doi: 10.3780/j.issn.1000-758X.2013.03.007
    Abstract ( 1632 )   PDF (354KB) ( 964 )   Save
    Thefirstclassofnosingularityvariablesasfittingparameters,alongwiththeorbitalinclinationof5°rotation,caneasilykeepthebroadcastephemerisofGEOconsistentwiththatofMEOandIGSO.However,thesingularityproblemcausedbyorbitalelementsstillexiststosomeextent.A16parameterfittingsetwaspresentedspecificallyforGEOephemerisfitting.Firstly,GEOelementswereintroducedtodescribethemotionofGEO′ssubsatellitepoint.Secondly,thelongitudedriftduetotesseralharmonictermsofgeopotentialwasconsideredinthedesignofperturbedparameters.Fitsimulationsshowthattherootofmeansquaresofuserrangeerrorwith2hdatasetisbetterthan0.01m.
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    ReliabilityAssessmentMethodforSolarArrayDeploymentofSpacecraft
    LIU Zhi-Quan, WU Yue-Min, PU Hai-Ling, YANG Qiao-Long
    2013, 33 (3):  52-56.  doi: 10.3780/j.issn.1000-758X.2013.03.008
    Abstract ( 1474 )   PDF (321KB) ( 1388 )   Save
    Aselectricpowersupplydevicesofspacecraft,solararrayshaveplayedanimportantroleinassuringsuccessfulspaceflight.Basedontheanalysisofsomecharacteristicparametersofsolararraydeploymentprocess,theequivalentdrivingmomentobtainedfromeveryhingedrivingmomentmeasurementvaluewasselectedasreliabilitycharacteristicparameterofsolararraydeployment.Bystressstrengthinterferencetheory,areliabilityassessmentmethodwasputforwardwhichapplinghingemeasurementdataofbothdrivingmomentandresistancemomenttoreliabilityassessmentofthesolararraydeployment.Thismethodprovidesatechnicalapproachtovalidatethereliabilityofspacecraftsolararraydeployment.
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    AnOnlineDynamicDelayCalibrationMethodforChannelSimulationSystem
    ZHANG Xin, LI Yuan-Ling, XIAO Zhi-Bin, OU Gang
    2013, 33 (3):  57-63.  doi: 10.3780/j.issn.1000-758X.2013.03.009
    Abstract ( 1426 )   PDF (473KB) ( 849 )   Save
    Whenrunningchannelsimulationsystemsforsatellitenavigationsystemsimulation,thezerovaluedriftofenvironmentsimulationchannelswillcausesystemerrorwhichcannotbeeliminated,soit′snecessarytotakeonlinechannelzerovaluecalibrationduringthesimulation.Traditionalzerovaluecalibrationmethodbasedonthedirectsequence spreadspectrum(DSSS)delaycalibrationreceivercannotdistinguishbetweensetting simulatedspacepropagationdelayandthechannelzerovalue,anditcan′tsuppressmultipleaccessinterference.Basedonthechangingmechanismofspacepropagationdelaysimulatedbytheenvironmentsimulationchannel,amethodwhichcandistinguishbetweenthechannelzerovalueandsettingsimulatedspacepropagationdelaywasdescribed.Themultipleaccessinterferenceintensityandthesuppressionmethodswerealsoanalyzed.Thetheoreticalanalysisandsimulationshowthattheprecisionoftheproposedonlinedelaycalibrationmethodislessthannanoseconds.
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    NewINS/CNSIntegratedAlgorithmOnAerospaceVehiclewithDirectlySensingHorizon
    ZHANG Cheng, XIONG Zhi, WANG Rong, LIU Jian-Ye, PENG Hui
    2013, 33 (3):  64-71.  doi: 10.3780/j.issn.1000-758X.2013.03.010
    Abstract ( 1619 )   PDF (472KB) ( 1272 )   Save
    InthetraditionalINS/CNSintegratedalgorithm,thesystemnoiseiscorrelatedwiththemeasurednoisebecausethecelestialobservationoutputcouplesthehorizontalplatformbenchmarkerror.Tofixthisproblem,theprincipleofusingcelestialobservationtomodifygyroscopeexcursionwasanalyzed,andanaerospacevehiclepositioningandnavigationthemebasedondirectlysensinghorizontoachievecelestialanalyticalpositioningandintegratedfilteringwasproposed,thentherelevantintegratedfiltermodelwasbuilt.Inthetheme,aninertiabenchmarkwasbuiltbystarsensorandgyro,thencelestialpositioningbasedoninfraredhorizonsensorwascalculated,andatlasttheINS/CNSintegratedfilteringwasimplemented.Thisthemefullytakestheadvantageoftheaccuratecelestialinformationandsucceedsinmakingthesystemnoiseandthemeasurednoiseindependent.Thesimulationresultsshowthevalidityoftheproposedtheme.
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    ResearchandDesignofAnti-radiationAnalogCMOSIntegratedCircuits
    ZHAO Yuan, XU Li-Xin, ZHAO Qi, JIN Xing
    2013, 33 (3):  72-76.  doi: 10.3780/j.issn.1000-758X.2013.03.011
    Abstract ( 1524 )   PDF (365KB) ( 1288 )   Save
    ThecharacteristicsandeffectsofanalogCMOSintegratedcircuitonspacecraftwereanalyzedintheradiationenvironment.Basedonthegenerationofradiationeffect,themainanti-radiationdesignmethodswereintroducedfortheanalogCMOSintegratedcircuitdesigningandprocessing.Intheouterspace,thresholdvoltagedeviation,transdiodedecreasing,substrateleakagecurrentincreasingandcornernoiseamplitudeincreasingoccurtotheCMOSsemiconductorcomponentsintheanalogCMOSintegratedcircuit.Asaresult,therearethreekindsofmethodsproposedtoprotectagainstradiationoftheanalogintegratedcircuits,includinganti-radiationanalogCMOSintegratedcircuit′,anti-radiationPCB′andsilicononinsulatoranti-radiationprocessing.Accordingly,thedesignedanti-radiationanalogCMOSintegratedcircuitsobtaintheidealeffectinantiradiationfunction.
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    GlobalSatelliteMobileCommunicationConstellationSystemSpace-basedInter-satellite-linkTC&RScheme
    YANG Tong, WU Yu-Xiang, LI Ming-Feng
    2013, 33 (3):  77-82.  doi: 10.3780/j.issn.1000-758X.2013.03.012
    Abstract ( 1507 )   PDF (433KB) ( 1481 )   Save
    Anoveltelemetry,controlandranging  (TC&R)  schemewasproposed,adoptingspace-basedGEOsatellites′inter-satellite-link  (ISL).Aspace-basedTC&Rnetworkwasestablishedbylaunching3GEOsatellites,transmittingandreceivingvarioussignalsthroughISLbetweenLEOandGEOsatellites,andretransmittingsignalstothegroundfacilities.Thelinkperformance,forwardandreturnlinkbudgetcapability,andthecoverageareaanalysiswerestudied.ThesimulationresultsshowthattheGEOspace-basedTC&Rbeam,formedby3GEOsatellites,iscapableofcreatingamuchwidercoverageareathantheordinaryterrestrial-basedone,whichremarkablyextendstheTC&Rcoverageareaby8timesduringa24-hourcomputingperiod,andthetotalTC&Rmissionperformingtimeisalmost10timesincomparisonwiththeordinaryscheme.
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