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直升机旋翼载荷中的非线性强迫振动方程迭代算法
引用本文:刘祥件,沈锌康,薛正中.直升机旋翼载荷中的非线性强迫振动方程迭代算法[J].航空学报,1994,15(8):904-909.
作者姓名:刘祥件  沈锌康  薛正中
作者单位:中国直升机设计研究所
摘    要: 介绍用迭代方法求解直升机桨叶气动载荷中的非线性强迫振动方程。计算时,先假定诱导下洗已确定,求出桨叶的初始载荷;再通过非线性强迫振动方程求出弯-弯-扭弹性变形。以某一直升机为例,求出了桨叶的各阶谐波载荷和弹性变形。计算结果与实验数据吻合。

关 键 词:旋翼  振动效应  载荷  迭代解  

ITERATIVE COMPUTATION METHOD FOR NONLINEAR FORCED VIBRATION EQUATION ON HELICOPTER MAIN ROTORLOAD
Liu Xiangjian, Shen Xinkang, Xue Zhengzhong.ITERATIVE COMPUTATION METHOD FOR NONLINEAR FORCED VIBRATION EQUATION ON HELICOPTER MAIN ROTORLOAD[J].Acta Aeronautica et Astronautica Sinica,1994,15(8):904-909.
Authors:Liu Xiangjian  Shen Xinkang  Xue Zhengzhong
Institution:Chinese Helicopter Research and Development Institute, Jindezhen, 333001
Abstract:An iterative computation method for nonlinear forced vibration equation on helicop- ter blade aerodynamic load is given. Initial load of blade is calculated by supposing that downwash flow is determined, and then flapping-swing-torsional elastic defonnation is calcu- lated by nonlinear foreed vibration equation. Harmonic load and elastic defonnation of various orders in blades are calculated in the x-type helicopter computation example;the calculated results coincide with the test data.
Keywords:rotary wings  vibration effects  loads(forces)  iterative solution
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