飛機(jī)垂直尾翼的分布式振動(dòng)主動(dòng)控制研究.pdf

1、南京航空航天大學(xué)碩士學(xué)位論文飛機(jī)垂直尾翼的分布式振動(dòng)主動(dòng)控制研究姓名：俞茂學(xué)申請(qǐng)學(xué)位級(jí)別：碩士專業(yè)：測試計(jì)量技術(shù)及儀器指導(dǎo)教師：徐志偉20060101飛機(jī)垂直尾翼的分布式振動(dòng)主動(dòng)控制研究IIAbstractTheactivevibrationcontrolaimedataircraftempennagehashugepracticalvaluesintheaspectsofaddingthefatiguelifeofverticalta

2、ilincreasingthecapabilityavailabilityoftheaircraftreducingthethroughlifesupptcostssoon.Thispaperaimsatmodelofverticaltailbasedoncertaintypeaircraft.ThemethodofdistributedactivelyvibrationcontrolbasedonmultiDSPhasbeencarr

3、iedonthismodel.AdistributedactivelyvibrationcontrolsystembasedonDSPsisdesignedtorealtimelycontrolthestructuralvibrationoftwomodes.Furthermerelatedtheiesexperimentsareoutspreaded.Themaincontentofthispaperareasfollowing1.T

4、hematerialacteristicprincipleofpiezoelectricmaterial(PZT)MacroFiberComposite(MFC)isanalyzed.CadaXstructuraldynamicsanalyticsoftwareisusedtocarryontheexperimentalmodelingmodeanalysisoftheverticaltail.Consequentlythedispos

5、alschemeofsensactuatisconfirmed.2.Theadaptivefiltercontrolarithmeticissystemicallyanalyzed.ASimplifiedFXLMS(SFXLMS)adaptivearithmeticisproposed.Finallythisalgithmisderivedindetail.3.Thehardwaresoftwaredesignofvibrationco

6、ntrolsystemisachieved.Theachievementflowofsoftwaredesignisemphasizedindetailed.4.theexperimentofdistributedactivelyvibrationcontrolisachieved.Theidealexperimentalresultsareobtained.Thevalidityfeasibilityofthissystemisval