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    Please use this identifier to cite or link to this item: https://tkuir.lib.tku.edu.tw/dspace/handle/987654321/18461

    Title: 三維尾流及非線性旋翼葉片耦合模式之葉片弦向阻尼分析
    Other Titles: The Lead-Lag Damping Analysis of a Nonlinear Rotor-Wake Coupled System
    Authors: 王怡仁;彭暉元;唐鵬駿
    Contributors: 淡江大學航空太空工程學系
    Keywords: 旋翼葉片;尾流動力學;拍撲延遲扭轉;直昇機;阻尼;Rotor Blade;Wake Dynamics;Flap Lag Torsion;Helicopter;Damping
    Date: 1999-12
    Issue Date: 2009-09-01 13:36:42 (UTC+8)
    Abstract: 本論文利用解析的方法將尾流運動方程、葉片空氣動力學及一個非線性的複材葉片的Flap-lag-torsion結構運動方程整合成一耦合的系統。該系統為一極複雜之非線性積分---偏微分方程式,本論文將利用Galerkin及Duncan多項式將其展開,求得平衡項(Equilibrium term)係數,再與擾動項(Disturbant term)合併且線性化之後,利用Floquet理論求解該系統之Flap-lag-torsion阻尼值。由結果得知,本文之Lead-lag阻尼值的預估在低仰角時與前人的實驗結果相比誤差較大,然而整體誤差較前人之數值分析結果為小。此外,本文所建立的數學模式包含尾流及複材葉片之因素且為時域內之方程式,對於旋翼葉片之 Flap-lag-torsion的Damping及穩定性的分析將又邁出一大步。
    In this research, a new three-dimensional wake and nonlinear composite rotor blade flap-lag torsion coupled model is developed. The generalized dynamic wake model employed is based on an induced undetermined time dependent coefficients as aerodynamic states. The nonlinear composite beam theory governs the equations of motion of an extensional-flexure-flexure-torsional vibrations of a slewing or rotating beam. The nonlinear equilibrium states results are employed as the coefficients of the linearized disturbant equation. The Floquet Theory is used to find the system dampings. Results show that the error of lag damping for different pitch angles has been reduced from 40.7%~92.1% to 10.2%~34.2%. The present model thus proves to be successful.
    Relation: 一九九九中華民國「航太學會/燃燒學會/民航學會」航太學術聯合會議論文集=Proceedings of the 1999 AASRC/ CIROC/ CSCA Aerospace Joint Conference,頁455-462
    Appears in Collections:[Graduate Institute & Department of Aerospace Engineering] Proceeding

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