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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,景德镇,333001 |
| 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 |
| 收稿时间： | 1991-03-22 |
| 修稿时间： | 1993-09-30 |
ITERATIVE COMPUTATION METHOD FOR NONLINEAR FORCED VIBRATION EQUATION ON HELICOPTER MAIN ROTORLOAD |
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| 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 |
| Affiliation: | 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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