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.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1994年第8期904-909,共6页
Acta Aeronautica et Astronautica Sinica
关键词
直升机
载荷
振动效应
旋翼
rotary wings,vibration effects, loads(forces),iterative solution
