应用动态逆和三时标分离的飞航导弹过载控制离散化设计

Discrete-time overload control design for winged missile using dynamic inversion and three time-scale separation

目的是选用普通舵系统来设计一种低成本高性能飞航导弹过载数字控制系统。这种情况下舵系统的动态特性将不能忽略。假设舵系统具有一阶动态特性,导弹的单通道(例如纵向通道)成为一个三阶的被控对象。应用三时标分离的方法将导弹动力学(含舵系统)分离为3个一阶的动力学子系统,这3个子系统分别对应于过载层(慢速子系统)、角速度层(中速子系统)和角加速度层(快速子系统),对这3个子系统分别采用Adams-Bashforth数值方法进行离散化、并进行离散化动态逆控制设计,应用李雅普诺夫综合法,分别设计出期望的慢、中、快离散动力学子系统。给出了各子系统带宽参数的选择方法。仿真结果验证了本文方法的正确性和有效性。

In order to design a low cost high performance digital overload control system for winged missile by common rudder described by first order plant, on the basis of the assumption that the single channel of the missile is a third order plant, the dynamics of the missile were separated into overload subsystem （ low speed subsystem）, angular rate subsystem （middle speed subsystem）, and angular acceleration subsystem （high speed subsystem）. And Adams-Bashforth numerical approach was used to discrete the subsystems for the design of a discrete-time dynamic inversion controller. Desired discrete-time dynamics for the subsystems was obtained by using Lyapunov synthesis method and bandwidth parameter selection method was also given. Simulation results demonstrate the rightness and validity.