飞行器内SFD-转子系统的动力学特性研究

建立了飞行器内SFD-转子系统的运动模型。数值研究表明。飞行器过大的垂直加速度分量或过小的水平加速度分量都可能使原稳定的SFD-转子系统变得不稳定。随着飞行器爬升角的变化。系统响应会出现周期1、周期3、拟周期、混沌等形态，而且会发生倍周期分叉和倒分叉。设计SFD时，必须充分考虑机动飞行的影响。

Study on the Dynamic Characteristics of SFD-Rotor System in Aircrafts

In the previous literatures, the static supports of the rotor system with squeezed film damper (SFD) are considered, which means that the bases of bearings are not movable. When SFD are applied in aircrafts, however, the supports of the rotor system are moving in the space, and the shaft will incline. The influence of the maneuver of aircrafts on the dynamic characteristics of SFD-rotor system in aircrafts was investigated. Numeric study shows that the responses of the rotor system are significantly affected by the aircraft acceleration, especially its vertical component. A vertical component that is too large or the horizontal component that is too small may lead to the instability of system. With the increase of the climbing angle of an aircraft, the responses of rotor-SFD system may alter from a periodic form to a quasi-periodic and then to a chaotic form, or just the reverse. The bifurcation can also be seen from responses. In some cases of system parameters, the style of the response might not change. The response is also influenced greatly by the time it takes for the aircraft to reach the expected value of acceleration. So, when choosing the parameters of SFD for the rotor system of aircrafts, we have to consider the aircraft maneuver.