拦截高速机动目标的非线性自抗扰制导律

Nonlinear active disturbance rejection guidance law for highly maneuvering targets

中文关键词  拦截制导  非线性自抗扰控制  扩张状态观测器

英文关键词  interception guidance  nonlinear active disturbance rejection control  extended state observer

中文摘要

      为实现导弹对目标的高精度拦截, 本文提出了基于加权齐次函数的非线性自抗扰拦截制导设计方法. 首先, 提出了基于加权齐次函数的非线性扩张状态观测器在线估计视线角速率和由目标加速度等内外不确定性因素构成的总扰动. 其次, 设计了基于非线性扩张状态观测器的非线性自抗扰三维制导律对总扰动进行补偿, 该制导律克服了高阶非线性项与强耦合项等不利因素的影响, 提高了拦截制导精度. 本文通过分析误差系统的动力学行为证明了闭环制导系统的稳定性和收敛性. 本文提出的方法在拦截精度等方面优于已有的基于线性扩张状态观测器和基于fal函数的扩张状态观测器的自抗扰制导方法. 仿真结果验证了本文所提出方法的有效性和优越性.

英文摘要

      To improve the precision of missiles interception, this paper proposes a weighted-homogeneous-function based nonlinear active disturbance rejection interception guidance design method. Firstly, a weighted-homogeneous-function-based extended state observer is proposed to online estimate the line-of-sight angular rate and the total disturbances. The total disturbances are composed of internal and external uncertainties including the acceleration of the target missile. Secondly, a nonlinear active disturbance rejection three-dimensional guidance law is designed by using the estimated value from the extended state observer, where the total disturbances are compensated by their estimated values. The proposed guidance law improves the interception accuracy despite high-order nonlinearities and coupling factors of the interception system. The stability and convergence of the closed-loop system are proved by analyzing the dynamic behavior of the error system. It is shown that the proposed method possesses the merit of high-accurate interception compared to existing linear-ESO-based and fal-ESO-based active disturbance rejection guidance methods. Numerical simulations validate the effectiveness and the merits of the proposed method.