1、南京航空航天大學(xué)碩士學(xué)位論文重型直升機尾槳動力學(xué)特性與動響應(yīng)分析姓名：思燦勇申請學(xué)位級別：碩士專業(yè)：飛行器設(shè)計指導(dǎo)教師：夏品奇201012重型直升機尾槳動力學(xué)特性與動響應(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