弹性高超声速飞行器振动抑制的自适应控制方法

An adaptive control approach for vibration suppression of a flexible hypersonic vehicle

为抑制弹性高超声速飞行器的结构弹性振动,提出了一种基于自适应结构陷波器的自适应控制方法。该方法利用输入指令和传感器输出的采样信号,采用滚动时域最小二乘方法在线估计振动频率,并用于实时更新滤波器的中心频率,以抑制气动弹性对控制的不利影响,保证控制系统稳定。仿真结果表明,相较最小二乘法,滚动时域最小二乘法的估计更准确且收敛更快,自适应控制方法能够稳定地跟踪控制指令,避免了不稳定现象的发生。

In order to suppress the elastic vibration of a flexible hypersonic glide vehicle, an adaptive control approach based on moving horizon least square method is proposed in this paper. In this method, the moving horizon least square method is used to estimate the vibration frequency that is adopted by notch filter as the central frequency according to the input and the output signal sampled by gyroscopes. Simulation results show that the moving horizon least square method is more accurate than the traditional least square method, and applying this adaptive control approach to the flexible hypersonic glide vehicle results in a stable attitude control system, which is unstable without adaptation scheme.