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    25 February 2015, Volume 35 Issue 1 Previous Issue    Next Issue
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    Research on Non-synchronization During Deployment of Hoop Truss Deployable Antenna
    TAO Cheng, LIU Li-Kun, ZHOU Zhi-Cheng, TIAN Qiang, XING Zhi-Gang
    2015, 35 (1):  1-8.  doi: 10.3780/j.issn.1000-758X.2015.01.001
    Abstract ( 1389 )   PDF (555KB) ( 1951 )   Save
    The non-synchronization phenomenon during the deployment of the hoop truss deployable antenna is obvious in the ground test, which was caused by the damping and other factors. The multi-flexible dynamics system model was established by the absolute nodal coordinate formulation (ANCF). To analyze the non-synchronization phenomenon, the stress and the distortion were obtained during the continuous deployment of the truss. The results show that the non-synchronization is caused by the distortion and friction between the elements of the antenna. The non-synchronization phenomenon is consistent with the stress, which makes the truss endure higher load.
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    ImprovedINS/VNSIntegratedNavigationMeasurementModelforLunarRover
    NING Xiao-Lin, XU Yong-Zhi
    2015, 35 (1):  9-18.  doi: 10.3780/j.issn.1000-758X.2015.01.002
    Abstract ( 1334 )   PDF (564KB) ( 1688 )   Save
    TheINS/VNSintegratednavigationisanimportantautonomousnavigationmethodforlunarrovers.TraditionalINS/VNSintegrated navigationmethodswhichutilizetherelativemotiondifferencesbetweentheinertialandthevisionasmeasurements,usually makeanapproximationbetweentheinertialattitudeerrorsandthemisalignmentangletosimplifytherelativerotation measurementmodel.However,theapproximationerrorcanexceedthemisalignmentanglewhentheheadislarge,which cannotbeignored. Tosolvethisproblem,anewmeasurementerroranalysismethodwaspresentedwhichcanavoidthe approximationintraditionalmethod,andbuildthecorrespondingimprovedmeasurementmodel. Theknowninertialattitudewhichcontainserrorutilizedtogetmoreaccurateerrorexpressionofrelativeinertialrotationquaternion,andreducetheforecasterrorofrelative rotationdifferencebetweentheinertialandthevision.BothoftheMoonbasedsimulationandtheEarth-basedexperiment demonstratethatthepresentedmethodiseffectiveandcanachievehigheraccuraciesofpositionsandattitudesthanthe traditionalone,inwhichthepositionaccuracyhasimproved68%from0.456%to0.143%intheEarth-basedexperiment.
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    NovelFaultDiagnosisAlgorithmfor    ReactionWheelIncompleteData
    HU Di
    2015, 35 (1):  19-26.  doi: 10.3780/j.issn.1000-758X.2015.01.003
    Abstract ( 1900 )   PDF (463KB) ( 1256 )   Save
    AnovelalgorithmcalledKernelfuzzyC-meansimputation(KFCM-I)wasproposedfortheincompletedataofsatellitereactionwheel.ThecentersandradiusoftheknownfaultsampleswereclusteredbytheKFCM,andtheincompletedatapointswerereplacedbythechosendatapointsforkeepingthesampledatacompletely,whichwerechosenfromtheknownfaultdatabythesimilaritycalculationandwerethemostsimilartotheincompletedatapoint.Thenthesimilaritywasadoptedtodiagnosethetestsampledata.Twoscenarioswereconsidered,onewasthatallthefeaturedatamissedatthesametime,andtheotherwasthateachdatamissedattherandomtime,butthelocationsofallthemissingdatapointswererandom.Comparedwithdirectlyexcludingtheoutlierormissingdatapointsinengineering,whenthemissingdataislessthan13%ofthetotaltestdata,theaccuracyofKFCM-Iishigherthan90%,whilethemissingdataisbetween13%~20%,theaccuracyalsoachievesat80%.TheKFCM-Ialgorithmismoreaccuracyandhaslowcomputation,whichisanusefulreferencetotheengineering.
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    RobustAdaptiveFilterforSmallSatelliteAttitudeEstimation
    XING Yan-Jun, WANG Yong-Fu, LU Ya-Dong
    2015, 35 (1):  27-35.  doi: 10.3780/j.issn.1000-758X.2015.01.004
    Abstract ( 1548 )   PDF (471KB) ( 1535 )   Save
    Theattitudekinematicequationsandmeasurementequationsarethefunctionoftheorbitparameters,sothestandardExtendedKalmanFilter(EKF)can′tgiveoptimalattitudeestimationbecauseoftheorbiterrors,especiallyforamagnetometerbasedsmallsatellite.ArobustadaptiveKalmanfilterwasdesignedtodealwiththedisturbancefromtheorbitestimationerrors.Theprincipleofrobustestimationwasadoptedfortheadaptivefilters,andthecovariancematrixandobservationalnoisewereadjustedtogetproperKalmangains,andthentheapproximatelyoptimalfilteringresultswereobtained.BasedonEKFstabletheory,RAKFwasproveduniformlyandstochasticallystableifthesystemisasymptoticallycontrollableandasymptoticallyobservable.SimulationresultsindicatethatRAKFcanimproveattitudeestimationprecisionfrom0.3°to0.2°,andthefilterisapprovedtobemoreeffectiveandrobustforattitudeestimation.
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    ResourcesSchedulingOptimizationProblemoftheTDRSS
    WANG Zhi-Lin, LI Xin-Ming
    2015, 35 (1):  36-42.  doi: 10.3780/j.issn.1000-758X.2015.01.005
    Abstract ( 1235 )   PDF (449KB) ( 1238 )   Save
    Inordertosimplifythemodel,theexistingTDRSSresourceschedulingresearchassumestheantennapreparingtimeforafixedvalue,makingitthebottleneckforthepromotionofthesystemusage.ThroughreferencingtheVRPTWtheory,theLOPVAPTmodelwasproposed,andtheoptimizationtimeoftheTDRSantennasetoutwasachievedbyoptimizingtheantennascanroute.ThetaskprogramwassimulatedbySTK, andtheANT-CYLEalgorithmontheMatlab,andtheutilizationpercentageoftheTDRSSwasincreasedfromlowerthan80%tomorethan90%.
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    PreliminaryDesignonNear-spaceAerostatforLongDurationandRegionalStationKeepingbyNaturalEnergy
    WANG Chao, YAO Wei, WU Yao, LYU Xiao-Chen , MA Rong
    2015, 35 (1):  43-50.  doi: 10.3780/j.issn.1000-758X.2015.01.006
    Abstract ( 1312 )   PDF (525KB) ( 1942 )   Save
    Thematerialandpowertechnologiesarethekeyproblemsandchallengestothenear-spaceaerostatsduringlongdurationandregionalstationkeeping.Themainreasonsarethesuper-heatandsuper-pressureandmaneuverabilityagainstthewindduringthestationkeeping.Anovelnearspaceaerostatwasproposedwhichmadeuseofthenaturalheatandthenearspacequasi-zerowindlayer.Theworkingprinciple,systemcomponentsandflightstrategyofthenovelaerostatwereintroduced.Byuseofthethermalmodelingandsimulationandtotalparameterdesign,thecouplingrelationshipofboththermalcontrolledparametersofthemaincellandthesuper-heatcapabilitiesduringdayandnightandthesizeofaerostatwereresearched.Theresultsshowthatthesuper-heatcanreachaboveof100Kduringdaytimeand20Katnightthroughthermalparametersoptimizationdesign.Thedesignresultsofthetotalparametersoftheconceptualaerostatweregivenforthesuper-heatrangingfrom20Kto80K.
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    TransferTrajectoriestoL3LibrationPointofSun-EarthSystem
    PAN Xun, PAN Bin-Feng
    2015, 35 (1):  51-57.  doi: 10.3780/j.issn.1000-758X.2015.01.007
    Abstract ( 1377 )   PDF (533KB) ( 1504 )   Save
    AmethodwaspresentedfordesigningthetransfertrajectoriestotheSun-EarthL3periodicorbitsbasedonthepseudomanifoldsinthecircularrestrictedthreebodyproblem.Thedynamicsofthepseudomanifolds,constructedbygivingalargeperturbationtoL1orL2orbits,wereusedtoconstructthetransfers.Threedeterministicmaneuverswererequiredtocompletetheorbittransfer:first,leavethelow  Earth  orbit; second, transferintothepseudomanifold; third, injecttotheL3orbit.Numericalsimulationresultsshowthat, comparedwiththetransfersbasedoninvariantmanifolds,thismethodreducesthetransformationalenergyconsumptionfrom4398m/sto4014m/s, andtheflightdurationisshortenedfrommorethan9yearstolessthan7.3years, thusimprovingtheefficiencyofthespacecraft.
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    MissionProgrammingofPeer-to-PeerRefuelingonNon-CoplanarCircularOrbit
    DU Bing-Xiao, ZHAO Yong, CHEN Li-Hu, YAO Wen
    2015, 35 (1):  58-65.  doi: 10.3780/j.issn.1000-758X.2015.01.008
    Abstract ( 1438 )   PDF (450KB) ( 1379 )   Save
    TheaimoftheoptimalscheduleforthePeer-to-Peerrefuelingstrategyistofindthebestrendezvoustrajectorieswiththeminimumfuelconsumptionduringthewholemission.Firstly,themathematicmodelforthemissionprogrammingwassetup,whichwassummedupasathree-indexmatchproblem,andtheminimumfuelexpenditurewassettobetheobjective.Secondly,thealgorithmflowfortheproblemwasdesigned,andthecombinationofKuhn-Mundresalgorithmandtheintegergeneticalgorithmwereadopted,theconvergencewasacceleratedandtheglobaloptimizationwasguaranteed.Atlast,twoconstellationsinthenon-coplanarcircularorbitwithasmallintersectionanglewasconsideredasanexample,andtheoptimalschedulingandfuelcostfortwoimpulsemaneuverweregottensuccessfully.Andtheresultshowsthattheproposedmodelandalgorithmareefficient.
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    ApplicationofaNewAblationThermalResponseAlgorithminMassEstimation
    WANG Jun, YANG Yang, ZHOU Yi, CHAI Xiu-Li
    2015, 35 (1):  66-74.  doi: 10.3780/j.issn.1000-758X.2015.01.009
    Abstract ( 1276 )   PDF (549KB) ( 1363 )   Save
    Themasslossesofheatshieldsurfacematerialssubjecttotheablationthermalresponseresultingfromaerodynamicheatfluxcanbeefficientlyestimatedinthereentryprocess.Ageometricmodelandablationmassestimationmethodofheatshieldswasstudied.Thethreedegreeoffreedom(3DOF)reentrytrajectorydynamicsequationwasestablished.ThemodifiedNewtonianflowtheory,Detra-Kemp-RiddellandTauber-Suttontheorywereadoptedrespectivelytocalculatetheaerodynamicparameters,stagnationheatfluxandheatradiation.Aone-dimensionalnonlinearheatconductionmodelwasemployedtosimulatetheprocessofcharringmaterialablation. BasedontheNewton-RaphsonandTDMAablationthermalresponsealgorithm, anapproachwaspresentedtoestimatethemasslossesofvehicleheatshields. Theresultsofablationpredictionshowthatthecontinuousdynamicchangeofthesurfacematerialdepthcanberealizedbyanalyzingtheablationthermalresponsealgorithm.Thepresentedapproachcanbeanavailablesurrogateofheatbalanceintegral(HBI)method.Theestimatedablationmasscanhelptooptimizethegeometricmodelofheatshieldsandreentrytrajectory.
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    AnImprovedPseudoliteLocationModelofGPS/PseudoliteIntegratedPositioning
    LIU Chao, LIN Peng, ZHANG Jing-Xia, ZHAO Xing-Wang
    2015, 35 (1):  75-83.  doi: 10.3780/j.issn.1000-758X.2015.01.010
    Abstract ( 3450 )   PDF (706KB) ( 1507 )   Save
    InordertoimprovethegeometrystructureofGPSsatellitesandtheprecisionofGPS/pseudolitesintegratedrelativepositioning,fundamentaltheoriesbetweenGPSandpseudolitewerecompared.Then,thecorrespondingformulaswereillustrated,andthenecessityofthepseudoliteapplicationwasexplained.Afour-dimensionallocationmodelwasproposed,takingthedilutionofprecision(DOP)asthedependentvariableandtheparametersoftime,azimuthandelevationangleastheindependentvariables,andtheconcretestepstotheapplicationofthemodelwasgiven.Inaddition,aonestepadditionmethodofpseudolitewasgiventoimprovethemulti-stepone,andthepositiondilutionofprecision(PDOP)wastakenastheevaluationindex. Theresultsindicatethatthetwoadditionmannerscanrealizetheoptimalpseudolitelocationanddramaticallyimprovethereliabilityandefficiencyofthepseudolitelocation.And,thenewone-stepmethodissuperiortothemulti-stepone,especiallyforthecaseoftwopseudolitesaddition.ThenewmethodcanprovidemoreeffectivelocationschemeswiththePDOPdecreasingbyover1.0insomeunfavourableareas.
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