考虑不确定复合控制系统动态特性的前向拦截三维导引律

为实现高空高速目标的精确拦截,研究了考虑直接力气动力复合控制动态特性及不确定性的前向拦截三维导引律设计方法。对采用复合控制的慢旋导弹的动力学模型进行了线性化处理,在气动舵控制的基础上设计连续直接力,然后对其进行离散化处理,避免复杂的控制分配问题。在三维弹目相对运动模型和不确定导弹动力学线性化模型的基础上,利用时标分离的思想将系统划分为慢变子系统和快变子系统,应用基于李雅普诺夫稳定性理论的鲁棒控制方法对慢变子系统和快变子系统分别进行鲁棒动态逆设计,得到考虑不确定复合控制系统动态特性的前向拦截三维导引律。对单通道控制和双通道控制的情况分别进行了仿真研究,验证了本文方法的正确性和有效性。

Three-dimensional head pursuit guidance law considering dynamic characteristics of uncertain hybrid control system

In order to intercept targets with high speed in high altitude accurately, a three-dimensional head pursuit guidance law considering uncertain dynamic characteristics for missiles with blended lateral jets and aerodynamic control is researched. The dynamics model of rotating missiles with blended lateral jets and aerodynamic control is simplified by linearization, and based on aerodynamic control, continuous lateral jets control is designed, and then it is discretized, which avoids the complicated control allocation problem. According to the kinematic model of three dimensional head pursuit guidance and the dynamics linear model with uncertainties of missiles, the system is separated into a slow subsystem and a fast subsystem using time-scale separation, and the robust dynamic inversion controls of the slow subsystem and the fast subsystem are designed separately by applying the robust control method based on the Lyapunov stability theory. Thus, the three-dimensional head pursuit guidance law considering dynamic characteristics of the uncertain hybrid control system is obtained. The simulation of single channel control and double channels control are done to show the accuracy and effectiveness of the proposed method.