推力不對(duì)稱(chēng)時(shí)民機(jī)飛行控制律重構(gòu)技術(shù)研究.pdf

1、南京航空航天大學(xué)碩士學(xué)位論文推力不對(duì)稱(chēng)時(shí)民機(jī)飛行控制律重構(gòu)技術(shù)研究姓名：姬猛申請(qǐng)學(xué)位級(jí)別：碩士專(zhuān)業(yè)：模式識(shí)別與智能系統(tǒng)指導(dǎo)教師：江駒201103推力不對(duì)稱(chēng)時(shí)民機(jī)飛行控制律重構(gòu)技術(shù)研究IIABSTRACTEngineOutisthemainreasoncausingcivilaircraftaccidentsespeciallyinthephasesofapproachingling.Thrustasymmetrycausedbytheo

2、utboardengineinonesideoutofwkresultsinabnmalattitudetheaircraftdeviatesfromtheidealdirection.Todealwiththedynamicacteristicschangingoftheaircraftwithengineinoperativecontrollawreconfigurationisaneffectivemethodfsafefligh

3、t.Thetechnologyofcontrollawconfigurationfflightcontrolsystemoftheaircraftwithasymmetricthrustismainlystudiedinthisthesis.ThelongitudinallateralmathematicmodelsofA300inthephasesofapproachlingareestablishedfirstly.Baseoncl

4、assiccontroltheynmalcontrollawsincludingpitchattitudecontrollawaltitudecontrollawairspeedkeepingcontrollawrollattitudecontrollawheadingcontrollawlateralbiascontrollawaredesigned.Numericalsimulationresultsshowthatthecontr

5、ollawsdesignedwkeffectivelyinnmalflightcondition.Then，thedynamicacteristicsofaircraftwithasymmetricthrustareanalyzedtheetically.Thefeasibilitythatconstantdisturbancefcesmomentscanbeintroducedtosimulatethethrustasymmetryi

6、sdemonstratedbynumericalsimulation.Thecontrollabilityconditionsbalancedflightattitudeinthecaseofthrustasymmetryarestudiedbasedonflightdynamics.Simulationresultsindicatethatnmalcontrollawsperfmbadlyduetostaticerrinthethru

7、stasymmetryflightconditionflightattitudeoftheaircraftisunsuitablefling.Finallyinthecaseofasymmetricthrustreconfiguredcontrollawsaredesigned.Numericalsimulationresultsdemonstratethatthereconfiguredcontrollawshavegoodcontr

8、oleffect.Themethodtosuppresstransientwhichcanensurethesmoothswitchingfromnmalcontrollawstoreconfiguredcontrollawsisstudiedprovedeffectivebysimulation.KeyWds:flightcontrolthrustasymmetrycontrollawconfigurationcivilaircraf