一种非线性末制导系统模型的精确线性化

针对未来高机动目标的拦截 ,运用非线性系统几何理论中的精确线性化方法 ,设计了一种空空导弹非线性末制导系统加速度指令。假设目标做逃逸机动 ,弹体 -自动驾驶仪响应用一个二阶环节描述 ,建立了导弹目标三维相对运动方程。根据终端约束直接选取系统输出阵 ,经动态反馈线性化 ,将非线性系统模型转化为线性方程 ,求得了目标任意机动时的非线性末制导系统的加速度指令。以纵向平面为例进行了仿真计算 ,结果表明该方法是行之有效的 ,得到的解可以用来改进导弹大离轴发射角时的进攻能力。

The feedback linearization of a nonlinear terminal guidance system model

To guarantee capture of an engagement in terminal phase, the nonlinear systems geometry theory are used to design command accelerations of a nonlinear terminal guidance system model for an air to air missile attacking evasive target. The model accommodates the nonlinear intercept kinematics and body autopilot dynamics.Instead of solving partial deferential equations according to standard method, the out put vector is chosen directly from the terminal guidance requirements and via dynamic feedback the nonlinear equations are linearized.The command accelerations are obtained. Quantity analyses are presented demonstrating that the algorithm can be used to improve the capture capability with high off boresight angles.