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    Please use this identifier to cite or link to this item: http://tkuir.lib.tku.edu.tw:8080/dspace/handle/987654321/18449


    Title: Lag-damping of the nonlinear blade-wake coupled system in hover
    Authors: Wang, Yi-Ren;Pong, Hui-Yueng;Chang, Hong-Wen
    Contributors: 淡江大學航空太空工程學系
    Keywords: 延滯阻尼;非線性輪葉尾流耦合系統;特徵值;共振;襟翼延遲扭轉結構動力學;盤旋;轉子尾流耦合系統;Lag Damping;Nonlinear Blade-Wake Coupled System;Eigenvalue;Resonance;Flap-Lag-Torsion Structural Dynamics;Hover;Rotor-Wake Coupled System
    Date: 2001-05
    Issue Date: 2009-09-01 13:36:10 (UTC+8)
    Publisher: 臺南市:成功大學
    Abstract: The lead-lag mode is the most sensitive motion in a helicopter rotoraeroelastic analysis. The stability characteristics of a lag mode in arotor system can be observed through the eigenvalues. The resonancephenomenon can be predicted by eigen-analysis as well. This paper usesanalytic methods to integrate the wake dynamics, blade aerodynamics,and nonlinear composite rotor blade flap-lag-torsion structuraldynamics in the form of a coupled system. Only the homogeneousisotropic material blade will be studied in this paper in order tomake a preliminary investigation of a wake-rotor interaction and thecompatibility of the composite blade equation. The Galerkin's methodand the Duncan's polynomial are used to resolve the equations. Thecoupled nonlinear system is separated into equilibrium and disturbant(dynamic) states. The equilibrium state is solved by using nonlinearsolves. The system's flap-lag-torsion eigen-equations are formulatedby the combination of the equilibrium coefficients and the disturbantequations. The Floquet's theory is used to derive the systemeigenvalues. The nonlinear phenomenon will be investigated througheigen-analysis, especially for quasi-linear resonance. Various lagfrequencies (stiffness) of the isotropic rotor blades are studied inthis paper. The equilibrium results show that the wake has strongeffects in the blade tip displacements in higher blade pitch angles.The eigen-analysis of the lag damping shows the eigenvalue veeringphenomenon occurs when pitch angle is 8 degrees. All of these may bedue to the wake effects in the rotor-wake coupled system.
    The lead-lag mode is the most sensitive motion in a helicopter rotoraeroelastic analysis. The stability characteristics of a lag mode in arotor system can be observed through the eigenvalues. The resonancephenomenon can be predicted by eigen-analysis as well. This paper usesanalytic methods to integrate the wake dynamics, blade aerodynamics,and nonlinear composite rotor blade flap-lag-torsion structuraldynamics in the form of a coupled system. Only the homogeneousisotropic material blade will be studied in this paper in order tomake a preliminary investigation of a wake-rotor interaction and thecompatibility of the composite blade equation. The Galerkin's methodand the Duncan's polynomial are used to resolve the equations. Thecoupled nonlinear system is separated into equilibrium and disturbant(dynamic) states. The equilibrium state is solved by using nonlinearsolves. The system's flap-lag-torsion eigen-equations are formulatedby the combination of the equilibrium coefficients and the disturbantequations. The Floquet's theory is used to derive the systemeigenvalues. The nonlinear phenomenon will be investigated througheigen-analysis, especially for quasi-linear resonance. Various lagfrequencies (stiffness) of the isotropic rotor blades are studied inthis paper. The equilibrium results show that the wake has strongeffects in the blade tip displacements in higher blade pitch angles.The eigen-analysis of the lag damping shows the eigenvalue veeringphenomenon occurs when pitch angle is 8 degrees. All of these may bedue to the wake effects in the rotor-wake coupled system.
    Relation: Proceedings of The Fourth Pacific International Conference on Aerospace Science and Technology=第四屆太平洋國際航太科技研討會論文集,pp.543-549
    Appears in Collections:[航空太空工程學系暨研究所] 會議論文

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