直升机旋翼载荷中的非线性强迫振动方程迭代算法  

ITERATIVE COMPUTATION METHOD FOR NONLINEAR FORCED VIBRATION EQUATION ON HELICOPTER MAIN ROTORLOAD

作　　者：刘祥件[1] 沈锌康 薛正中 

机构地区：[1]中国直升机设计研究所

出　　处：《航空学报》1994年第8期904-909,共6页Acta Aeronautica et Astronautica Sinica

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。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.

关 键 词：直升机 载荷 振动效应 旋翼 

分 类 号：V215.34[航空宇航科学与技术—航空宇航推进理论与工程]