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    25 October 2016, Volume 36 Issue 5 Previous Issue    Next Issue
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    DynamiccharacteristicsofgeosynchronousLaplaceorbitforspacesolarpowerstation
    LIU Yu-Liang, WU Shu-Nan, WU Zhi-Gang, HOU Xin-Bin, LIU Yu-Fei
    2016, 36 (5):  1.  doi: 10.16708/j.cnki.1000-758X.2016.0053
    Abstract ( 867 )   PDF (5154KB) ( 1529 )   Save
    Previousstudiesonspacesolarpowerstation(SSPS)havesimpleassumedgeostationaryorbit,whileitisnotthebestorbitforSSPS.Aneworbit,knownasthegeosynchronousLaplaceplanewasputforward,whichwassuperiortogeostationaryorbit.
    Firstly,theorbitaldynamicsandtheperturbationswhichaffecttheorbitalmotionweremodeled,includingEarth′snonsphericalperturbation,LuniSolargravitationalperturbation,solarradiationpressureperturbationandmicrowavebeamingforceperturbation.Secondly,threeevaluationindexes,includingreceivedpower,orbitapplicabilityandspacesecurity,werepresentedtodiscusstheadvantagesoftheproposedLaplaceorbitratherthanthegeostationaryorbit.Finally,thelongtermnumericalsimulationwasprovided.AndtheresultshowsthattheSSPSworkinginthegeosynchronousLaplaceorbitcansave364534kilogramsoffuelwhichisusedfororbitmaintaincomparingtotheSSPSworkinginthegeostationaryorbitwiththesamereceivedpowerandmeetingthedemandofpowersupply.
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    Anoptimalguidancemethodbasedonmultipleterminalconstraints
    LI Chao-Bing, WANG Jin-Lin, LI Hai
    2016, 36 (5):  9.  doi: 10.16708/j.cnki.1000-758X.2016.0052
    Abstract ( 772 )   PDF (2030KB) ( 1235 )   Save
    Sincethethrustamplitudeofthemainengineonspacecraftisunadjustable,amultipleterminalconstrainbasedoptimalguidancemethodwasproposed,consideringthedeficiencyofsmallcorrectionangleassumptionofconventionaliterativeguidanceunderfiveterminalconstrains.Anoptimalcontrolmodelwasestablishedintheorbitinjectionorbitalcoordinateframe.Transversalityequationswaredirectlysolvedbyiterationtoobtaintheguidanceanglecommand.Theswitchonandoffinstantswerethenoptimizedtoreducetheinfluenceofunsatisfiedterminalconstraints.Besides, thefiveequivalentterminalconstraintsinthegeocentricinertialcoordinateframewerederivedandappropriateweightfactorswereadjustedtoimprovetheprecisionofnumericalsolvingofguidanceequations.Simulationsonstandardconditionsdemonstratethattheproposedguidancemethodhasincreasedtheprecisionofunsatisfiedterminalconstraintsby1595355m,comparedwiththeconventionaliterativeguidance.TheMonteCarlosimulationsshowtheadaptabilityoftheproposedmethodtotheinitialbiasofthespacecraftpositionandvelocity.
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    Detectionalgorithmofabnormalsubsequenceinpseudoperiodictimeseriesoftelemetry
    DU Ying, LI Si-Hu, HU Shao-Lin, ZHANG Le, WANG Fei
    2016, 36 (5):  18.  doi: 10.16708/j.cnki.1000-758X.2016.0051
    Abstract ( 987 )   PDF (1230KB) ( 1860 )   Save
    Inordertodetecttheabnormalsubsequenceinthepseudoperiodictimeseriesofspacecrafttelemetry,asubsequencesegmentationalgorithmonthewiderangeofmaximumcyclewindowwasproposedbasedonthetwoconventionalsegmentationmethods.Then,ananomalysubsequencedetectionmethodbasedonanoptimizedsequencemodelwasbuiltbyusingthedoublequantilerangescriteriontosetthethresholdofthedistancedetection.Thesatelliteexperimentalresultsshowthatthemethodcaneffectivelydetecttheabnormalsubsequenceofsatellitetelemetrydata.
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    ThealgorithmandvalidationofBeiDousystem
    WANG Yuan-Xin, CAO Yue-Ling, HU Xiao-Gong, HUANG Yong, TANG Cheng-Pan
    2016, 36 (5):  25.  doi: 10.16708/j.cnki.1000-758X.2016.0054
    Abstract ( 822 )   PDF (909KB) ( 1170 )   Save
    Currently,thedesignofintegrityparametersforthesatellitebasedaugmentationsystemofBDSislackofdegradationparametersforthedifferentialinformation′savailability,andcan′tsatisfytheRTCAprotocol.SothesatellitebasedaugmentationsystemofBDSisnotcompatibletotheotherinternationalsatellitebasedaugmentationsystemofGNSS.TheintegritydegradationparametersofBDSweredesignedaccordingtotheRTCAprotocol,andtheeffectontheuserpositioningwasanalyzedbyusingtheBDSmeasureddata.Basedonthese,theeffectivenessofthisalgorithmwasdemonstrated.Theresultsshowthat,thelocationprecisionoftheaugmentationsystemforBDSreaches113m.However,iftheuserfailedtoreceivesomedifferentialcorrection,thepositioningprecisionreaches144m,decreasesby274%approximately.Inthissituation,byoptimizingpositionmatrixwiththeintegrityparameterstothepastdifferentialmessage,thepositioningprecisionwillincreaseto117m,sotheauthorizedservicewillrecover.
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    Researchonregistrationalgorithmofmultipleviewpointcloudfornoncooperativespacecraft
    GUO Rui-Ke, WANG Li, ZHU Fei-Hu, WU Yun
    2016, 36 (5):  32.  doi: 10.16708/j.cnki.1000-758X.2016.0055
    Abstract ( 1082 )   PDF (7080KB) ( 1012 )   Save
    Thepointclouddataregistrationisoneofthekeytechnicalaspectsofthreedimensionalreconstructionfornoncooperativespacecraft.Tosolvethepairwiseregistrationissueofsparsepointcloud,andalignthemultipleviewpointcloudaccurately,anoptimizationregistrationmethodwaspresented.AnovelpointcloudsimplificationalgorithmusinguniformsamplingwasproposedbasedonKDTreeandtheuniformrelationofthethresholdparametersinthe4PCS(4PointsCongruentSets)algorithmwasestablishedviathedensityofthepointcloud.Byusingthemisregistrationcorrectionmethodbasedonattitude,themisregistrationproblemofthesymmetrypointcloudwassolved.Theresultsshowthattheproposedalgorithmcaneffectivelyachievegoodalignmentsofthesparsepointcloudofthesatellite,besides,thestabilityandthesuccessrateofthealgorithmisalsoimproved.
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    Studyontakeoffstabilityboundariesoflunardetector
    HU Jian-Guo, SHI Yao-Zu, ZHAO Yi, XU Hong-Bin
    2016, 36 (5):  40.  doi: 10.16708/j.cnki.1000-758X.2016.0056
    Abstract ( 769 )   PDF (3227KB) ( 1548 )   Save
    Thetakeoffstabilityoflunardetectorisanimportantperformanceindexofanascender′stakingofffromthemoon′ssurface.Bychoosingsomemaininfluencefactorsoftakeoffstability,thetakeoffdynamicapproximationmodelofascenderwasestablishedcombiningwithanoptimallatinhypercubeexperimentaldesignmethodandtheRBFneuralnetwork,andthesensitivityofthefactorsfortheangulardisplacementandvelocitywasquantitativelyanalyzed.Basedonthestabilitycriterionthattheangulardisplacementandangularvelocityofascenderswas5°and5(°)/srespectively,theboundaryvaluesofasingleinfluencefactorweregiven.Aprogramformultiplefactorsboundaryanalysisoftheascendertakeoffstabilitywascompiled.Theboundaryexpressionoftheascendertakeoffstabilityisfoundedbythewayofthreedimensionalspace,andthetakeoffstabilityboundariesweredeterminedwithasample.
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    Aerialrelativemeasurementbasedonmonocularreconstructionfornoncooperationtarget
    LI Yong-Fei, WANG Shi-Cheng, YANG Dong-Fang, SUN Da-Wei
    2016, 36 (5):  48.  doi: 10.16708/j.cnki.1000-758X.2016.0057
    Abstract ( 693 )   Save
    Amonocularvisionbasedrelativepositionandattitudemeasurementalgorithmwaspresented,whichcombinedthereconstructionoftargetswiththemeasurementofrelativepositionsandattitudefornoncooperationtargets.Firstly,aseriesofpointsonthetargetswerereconstructedusingtheimagesobtainedintheearliermeasurementwithafastandgloballyconvergentstructureandmotionestimation.Secondly,therelativepositionandattitudewerecalculatedbyusingaKalmanfilterbasedonrecursivedepthparametrization,inwhichnewpointsobservedfromnewimageswererecoveredandaddedtothe3Dpointsettoimprovetheaccuracyandrobustnessofthemeasurement.Experimentresultshowsthattheattitudemeasurementcanachieveanaccuracyhigherthan1°,andthepositionmeasurementcanachieveanaccuracyhigherthan2cm,whichindicatesthehighprecisionoftheproposedalgorithm.
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    Realtimecalibrationmethodforsatellitereceiverchanneldelay
    YU Xue-Hui, LI Ji-Lin, WANG Dun, WU Jia-Peng
    2016, 36 (5):  57.  doi: 10.16708/j.cnki.1000-758X.2016.0058
    Abstract ( 942 )   PDF (6860KB) ( 1180 )   Save
    Inordertoaccomplishaccuratemeasurementofintersatelliteclockerrorandtransferoftimeandfrequency,theequipmentdelayonthegroundareusuallyrequiredtobecalibrated.Withtheagingofequipmentandthechangeofenvironmenttemperature,thedelayofsendreceivesignalwilldeviatethestandardization.Byusingpseudorandomcodecorrelationmeasurement,combiningwiththetimedivisionearlydelaypseudorandomcodephasealternationmodulationtechnologyandenvelopetechnology,aninorbitchanneldelayselfcalibrationmethodwasproposed.Bydesigningaproperclosedloop,thesendreceivechanneldelaycanbecalibratedinrealtimewithoutinfluencingthenormalcommunication.Theresultsindicatethatthedelaymeasurementprecisionofthismethodreachessubnanosecondlevel.
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    Analysisofdesign,simulation&calculationmoduleforMartianatmosphereenvironmentsimulationdevice
    LIU Gao-Tong, SUN Yu, ZHANG Lei
    2016, 36 (5):  65.  doi: 10.16708/j.cnki.1000-758X.2016.0059
    Abstract ( 1058 )   PDF (6530KB) ( 1304 )   Save
    ThecharacteristicsofMartianatmospherewerestudied. AsimulationcalculationmoduleoftheMartianatmospheresimulationenvironmentboxwassetupbychoosingappropriatecalculationmethodcombinedwithFLUENTfluidfiniteelementcalculationsoftware. ThemodulerealizessteadyandunsteadycalculationsimulationofinteriorflowfieldundermultipleworkingconditionsofthecylindricalMartianatmosphereenvironmentsimulationdevices.ThecalculationresultswasanalyzedsoastoprovidetechnicalsupportandreferencefordesignoftheMartianatmosphereenvironmentsimulationdevice.
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    Constraintandstabilityanalysisofnearspaceairshipoutsidehangar
    ZHANG Tai-Hua, JIANG Lu-Hua, ZHANG Dong-Hui, WANG Li-Xiang
    2016, 36 (5):  72.  doi: 10.16708/j.cnki.1000-758X.2016.0060
    Abstract ( 1112 )   PDF (4776KB) ( 1324 )   Save
    Typically,thenearspaceairshipparksinthehangarbeforelaunch.Assoonasnearspaceairshipleavesitshangaritwillbeaffectedbytheweatherandparticularlybythewind,whichnotonlyaffecttherapidityandsecurityoftheairshipoperation,butalsorelatetothesuccessoftheflighttest.Amechanicalmodelwasestablishedwhenanairshipwasoutsideitshangarwithbothsidesrestricted.Thevariationsofairshipyawandropetensionwereanalyzedbyusingdynamicmethod.Theanalyticalsolutionwasobtainedatthebeginningandstablestateofthewind,then,thestabilityandsafetyofanairshipwerealsoevaluated.Theultimatebearingsofforwardwindandcrosswindonanairshipoutsidethehangarwereproposed.Theresultquantifiestheindicatorsofmeteorologicalconditions,andprovidesreferencesofscientificandrationalmethodsforthelaunchtechnologyofnearspaceairshipinthefuture.
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    Spacecraftmultiplepulsehoveringmethodbasedonstatetransitionmatrix
    CHENG Bo, YUAN Jian-Ping, MA Wei-Hua
    2016, 36 (5):  81.  doi: 10.16708/j.cnki.1000-758X.2016.0061
    Abstract ( 796 )   PDF (824KB) ( 1162 )   Save
    Basedonastatetransitionmatrix,amethodforspacecraftmultiplepulsehoveringwaspresented.Therelativemotiondynamicsmodelandthestatetransitionmatrixwereintroducedtodescribetherelativemotionoftwospacecraftincircular,ellipticalandhyperbolicreferenceorbits.Amethodofachievingtheorbittransfervelocityincrementforhoveringwasdeducedusingthestatetransitionmatrix.Thenumericalsimulationshowsthattheproposedmethodcanachievespacecraftrelativehoveringeffectively.Withtheincreasingofimpulsenumber,theprecisionofrelativehoveringispromoted.Moreover,theprecisionofrelativehoveringisinfluencedbytheeccentricityofreferenceorbit.
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