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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 ( 1083 )   PDF (5154KB) ( 1941 )   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. Related Articles | Metrics

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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 ( 929 )   PDF (2030KB) ( 1722 )   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. Related Articles | Metrics

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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 ( 1167 )   PDF (1230KB) ( 2415 )   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. Related Articles | Metrics

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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 ( 1142 )   PDF (909KB) ( 1415 )   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. Related Articles | Metrics

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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 ( 1373 )   PDF (7080KB) ( 1183 )   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. Related Articles | Metrics

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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 ( 1121 )   PDF (3227KB) ( 1782 )   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. Related Articles | Metrics

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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 ( 907 )   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. Related Articles | Metrics

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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 ( 1299 )   PDF (6860KB) ( 1384 )   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. Related Articles | Metrics

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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 ( 1324 )   PDF (6530KB) ( 1997 )   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. Related Articles | Metrics

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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 ( 1301 )   PDF (4776KB) ( 1571 )   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. Related Articles | Metrics

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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 ( 940 )   PDF (824KB) ( 1537 )   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. Related Articles | Metrics