挠性捷联惯导系统机载安装方式误差激励研究

南京航空航天大学硕士学位论文挠性捷联惯导系统机载安装方式误差激励研究姓名：王松申请学位级别：硕士专业：精密仪器及机械指导教师：刘建业20070101IIIABSTRACTAsmodernnavigationequipments,inertialnavigationsystem(INS)hasbeenwidelyusedinbothmilitaryandcivilaircraft,especiallyinthefieldsofmodernmilitaryaeronauticswheretheyholdapivotalposition.Nowithasbecomeoneofcrucialsignsoftechnologicallevelandmilitarystrengthofacountry.Asaresultoftheprinciple,design,manufacturecraft,installment,algorithmandsoon,theinertialmeasurementunit(IMU)inSINSmaycausesnavigationlocalizationerror.Especially,becauseIMUisdirectlyinstalledonthecarrier,thechangeofinstallationwayofwhichcanmakeSINSnottodistinguishandmeasurethecarrier’smovementaccurately.Accordingly,itcaninfluencetheexcitatedationeffectofstrapdowninertialnavigationsystem’s(SINS’s)errormodelparameter,andaffectthenavigationaccuracywithoutanycompensation.Therefore,researchonerrorexcitatedationinflexibleSINScausedbyairborneinstallationwillplayanimportantroleininertialmeasurementsystemerrormodelingandinimprovinghitprecisionofthestrategyandthetacticalweaponrelyingontheinertialsystem.Becauseofallabove,thisthesisstudiessystematicallyanddetailedlyontheerrorexcitatedationinflexibleSINScausedbyairborneinstallation,.Themaincontributionsareasfollowing:Carryonthoroughanalysisandinductionontheinertialmeasurementsystem’serrormodelinflexibleSINS,itcanprovidethebasistohaveafurtherresearchontheerrorexcitatedationcausedbyairborneinstallation.Analyzesystematicallyfromtheoreticalpointofviewingtheinstallationerror,concludethesystem’serrormodelwhenthereisposition-installingerror.OnthebasisofanalyzingIMU’sangle-installingerror,thispaperproposesthesystem’serrormodelinthiscondition.AndthesimulationresultsrepresentthedisadvantagesinSINSstemmingfrominstallationerror.TheresearchcanprovideaneffectivebasisontheinitialalignmentofthegimbaledINSandcompensationtothesystem.AnalyzetheeffectiveexcitatedationoftheflighttrajectoryfortheIIIinertialmeasurementsystem,inthisfoundation,studytheerrormodelexcitatedationcausedbyairborneinstallationway,andvalidatetherelationbetweenthem.Thisresearchisvaluablefordistinguishingtheerrormodelparameterindynamicconditionmakinguseoftheerrormodelexcitatedationcausedbyairborneinstallationway.Onthebasisoftheoryanalysisandsimulationvalidation,thispaperhasdesignedanddevelopedtheinertialmeasurementsystemerrormodelconfirmationsimulationplatform,itcanprovideaneffectiveresearchmethodandenvironmentforstudyingtheerrormodelexcitatedationcausedbyairborneinstallationandvalidatingitsvitalroleintheinertialmeasurementsystemerrormodelverificationtestplan.KeyWordsinertialnavigation,installationway,errorexcitatedation,flighttrajectory,errormode,simulationplatformVI1.1.................................................................11.2G-2000.........................................................31.3TN-1............................................................42.1......................................................82.2..........................................................93.1.............................................263.2.........................................283.3().....................................................303.4().........................................................313.5IMU(1)......................................................343.6IMU(2)......................................................353.7IMU(3)..............................................................353.8IMU(1)..............................................................373.9IMU(2)..............................................................373.10IMU(3)............................................................383.11..........................................................393.12IMU(1)............................................................393.13IMU(2)............................................................403.14IMU(3)............................................................404.1.....................................474.2........................................................484.3.........................................494.4................................................504.5IMU...................................................524.6...............................................................554.7.........................................564.8..................................57VII4.9..................................574.10......................................................584.11..................................................604.12...........................................614.13....................................614.14.................................................................644.15..........................................................644.16DTG(1)...............................................................654.17DTG(2)...............................................................663.1...................................................................413.2.....................................433.31.0e-004................................444.1V