重型直升機(jī)尾槳?jiǎng)恿W(xué)特性與動(dòng)響應(yīng)分析.pdf

1、南京航空航天大學(xué)碩士學(xué)位論文重型直升機(jī)尾槳?jiǎng)恿W(xué)特性與動(dòng)響應(yīng)分析姓名：思燦勇申請(qǐng)學(xué)位級(jí)別：碩士專業(yè)：飛行器設(shè)計(jì)指導(dǎo)教師：夏品奇201012重型直升機(jī)尾槳?jiǎng)恿W(xué)特性與動(dòng)響應(yīng)分析IIAbstractTheanalysisofdynamicpropertiesdynamicalresponsesuchasthenaturalfrequencymodeshapesthefcedvibrationresponseoftailrotbladesun

2、deraerodynamicfceplayanimptantpartintailrotdynamicdesign.InthisthesisthemultibodydynamicssimulationbasedonMSC.ADAMSwasusedtoanalyzethedynamicpropertiesdynamicresponseofheavylifthelicoptertailrots.Firstofalltheequationsof

3、flappingleadlagmotionoftailrotbladeswerefmulatedbyusingNewtonmethodtoanalyzedescribeitsdynamicproperties.Nextfaheavylifthelicopterthenaturalfrequenciesmodeshapesofflappingleadlagmotionofitstailrotbladesunderdifferentrota

4、tingspeedwereobtainedbyusingmultibodydynamicssimulationaCampbelldiagramofflappingleadlagmotionwasmadeaccdingtothenaturalfrequency.TheresultswhichtheCampbelldiagramindicatesareinaccdancewiththetheeticalanalysis.Withrespec

5、ttotheproblemofdynamicresponsefirstofalltherelationshipexpressionofaerodynamicloadswasbuilt.Whiletheinducedvelocityinhoverwascomputedbycombiningmomentumtheybladeelementtheytheinducedvelocityinfwardflightwascomputedbyusin

6、gthelinearinflowmodels.FinallytheaerodynamicloadsweremanipulatedsothattheycanbeappliedtothetailrotbladesinthefmofmodalfceinMSC.ADAMS.Nextthemultibodydynamicsimulationofdynamicresponseoftailrotbladeswasperfmedinadditionto

7、thedisplacementdefmationofbladesinhovertheflappingvelocitydisplacementofbladesinfwardflightwereobtained.Theeticalanalysisindicatesthatalltheseresultsareinaccdancewithpracticalcase.KeyWds:heavylifthelicoptertailrotdynamic