摘要
本文研究了直升机对离散突风的动态响应,文中所用突风模型均按规范要求选取,为分析不同突风模型对响应的影响,本文还讨论了正弦型突风模型和旋翼动力学模型。后者采用水平铰外伸量和桨叶根部有弹性约束的结构模型,其诱导速度在桨盘处的分布采用了由广义涡流理论所得的表达式。文中没有对直升机运动方程进行线化处理。本文以“直九”为算例,所得结果与规范较一致。
The dynamic response of a helicopter to the dispersed gust is investigated in this paper. According to the specifications, a sine-squared gust model is selected. Sine-gust model is also selected in order to investigate the influences of different gust models on response. An articulated rotor with a blade hinge offset from the shaft and with an elastic restrain about the flap hinge is used as the rotary wing dynamic model. The non-uniform distribution of induced velocity on the rotor disk which is derived from Wang's generalized vortex theory is taken into account. The linear partial-differential small-perturbation equation is not used.A sample calculation of the Z-9 helicopter has been made. A detailed calculation is given, of responses which are penetrates gust, steeps gust and withdraws from gust, of helicopter trim and stability roots which are needed in calculation. The influences of distribution of induced velocity and gust model on response are considered.It is found to be in good agreement with the specifications.
关键词
直升机
离散突风
阵风响应
helicopter, gust response, dispersed gust, aerodynamics, rotor dynamics model
