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由于飞行过程中飞行环境与自身特性的大幅度变化,导弹的飞行动力学特性和结构模态参数变化范围很大,难以精确建模,对导弹的气动伺服弹性稳定性带来潜在危险,传统结构滤波器的适用性也难以保证。提出一种自适应结构滤波器的设计方法,利用导弹输入指令和传感器输出的采样信号,建立导弹的自回归滑动平均(ARMA)模型;采用递归最小二乘算法,在线辨识飞行器的结构模态参数并用于实时更新滤波器的中心频率。仿真结果表明:相对于传统设计方法,自适应结构滤波器在较大参数摄动范围内都可明显提高导弹的气动伺服弹性稳定裕度,对于导弹飞行环境和结构特性的变化都有较强的鲁棒性。
Due to the large changes of the flight environment and its own characteristics during the flight, the flight dynamics and structural modal parameters of the missile vary widely and it is difficult to accurately model the missile, posing potential dangers to the elastic stability of the missile’s pneumatic servo. The traditional structure The applicability of the filter is also hard to guarantee. A design method of adaptive structure filter is proposed. The ARMA model of missiles is established by using missile input commands and the sampled signals output by sensors. The recursive least squares algorithm is used to identify the structure modal parameters And used to update the center frequency of the filter in real time. The simulation results show that compared with the traditional design method, the adaptive structure filter can significantly improve the stability margin of the aerodynamic servo elasticity of the missile over a wide range of parameter perturbation, which has a strong change for the missile flight environment and structural characteristics Robustness.