计及诱速不均匀挥扭耦合的直升机侧风稳操特性

本文研究了无铰旋翼直升机在侧风下的稳定性和操纵件。旋翼动力学模型采取挥舞-变距(包括操纵系统的弹性变形)-扭转耦合的模型,桨盘诱速模型采用广义涡流理论所导出的诱速分布。推出的表达式除适用于研究侧风的影响外,还可以进一步研究剖面质心、气动力中心,弹性轴位置、操纵系统刚度和桨叶剖面扭转刚度对直升机稳定性和操纵性的影响。 本文以某典型直升机为例,详细考虑了诱速分布、挥扭耦合和侧风对直升机稳定性和操纵性的影响,计算结果和试飞数据有较好的一致。

Stability and Controllability of Holicopters under Lateral Gust with Uneven Induced Velocity and Flap-Pitch-Torsion Coupling

A method is given for the calculation of the stability and the control of a helicopter with hingeless rotor under lateral gust. The first harmonic variation of nonuniform induced velocity distribution derived from the generalized vortex theory is employed. The rotory wing dynan.ic model considered is a nodel of flap-pitch (including the elastic deforn-atioa of the control system)-torsion coupling. The influence of C.G-A. C-E.C offset, blade control system stiffness and blade torsional stiffness on the stability and the control of the helicopter are also considered in all expressions of this study.A sample calculation of a typical helicopter has been made. All the derivatives calculation by the method of the numerical derivation. The influence of induced velocity distribution, flap-pitch-torsion coupling and lateral gust on the stability and control of helicopter are taken into account in detail. And, SOme useful conclusions are given. It is found that the calculated results are in a good agreea.ent with the flight test data.