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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 ( 2076 )   PDF (414KB) ( 1478 )   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. Related Articles | Metrics

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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 ( 2337 )   PDF (418KB) ( 909 )   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. Related Articles | Metrics

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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 ( 1902 )   PDF (404KB) ( 1035 )   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. Related Articles | Metrics

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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 ( 1579 )   PDF (483KB) ( 1419 )   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. Related Articles | Metrics

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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 ( 1791 )   PDF (427KB) ( 1427 )   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. Related Articles | Metrics

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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 ( 1840 )   PDF (479KB) ( 1370 )   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. Related Articles | Metrics

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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 ( 1806 )   PDF (354KB) ( 1145 )   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. Related Articles | Metrics

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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 ( 1586 )   PDF (321KB) ( 1544 )   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. Related Articles | Metrics

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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 ( 1570 )   PDF (473KB) ( 979 )   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. Related Articles | Metrics

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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 ( 1864 )   PDF (472KB) ( 1483 )   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. Related Articles | Metrics

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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 ( 1755 )   PDF (365KB) ( 1553 )   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. Related Articles | Metrics

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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 ( 1663 )   PDF (433KB) ( 1826 )   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. Related Articles | Metrics