直升机惯性交感对稳定性、操纵性和离散突风响应的影响

The Influence of the Inertia Coupling on the Stability and Control of the Helicopter and the Response of Helicopter to Gust

本文研究直升机惯性交感对稳定性和操纵性的影响,亦研究了对直升机在离散突风中响应的影响。旋翼动力学模型采用水平铰外伸量和桨叶根部有弹性约束的结构模型。诱导速度在桨盘处的分布采用广义涡流理论所导的公式。离散突风模型为规范所要求的正弦平方型。 本文以某典型直升机为算例,比较了计及惯性交感与否的稳操特性和突风响应。

The influence of the inertia coupling on the stability and control of the helicopter and the response of helicopter to dispersed gust are investigated. An articulated rotor with a blade hinge offset and with an elastic restraint about the flap hinge is used as the rotary wing dynamic model. The nonuniform distribution of induced velocity on the rotor disk derived from the generalized vortex theory is taken into account. The model of the dispersed gust is a sine-squared one according to the demand of the specification.A sample calculation of a typical helicopter has been made. Having compared the states whether the inertia coupling is considered or not, the detailed calculation and analysis of the stability, control and the response of helicopter to dispersed gust are given.