基于雷达动力学误差的战斗机综合引导方法

Synthesized Guidance Method for a Fighter Plane Based on Radar Dynamics Error

针对战斗机雷达跟踪目标中断导致引导失效的问题,提出一种基于动力学误差的综合引导方法。首先给出雷达测角装置的动力学结构模型,建立了动力学误差传递函数,分析了导致角度跟踪中断的因素;然后建立综合引导法的运动学模型,提出雷达惯性不可逃逸距离的概念和雷达开机时间的计算方法;最后对综合引导法和最佳前置法进行对比仿真,验证了方法的可行性。

For the problem of guiding failure induced by radar＇s target tracking intermittence for a fighter plane,a synthesized guidance method based on radar dynamics error is proposed. First dynamics structure model for radar angle-measuring equipment is presented,dynamics error transfer function is built,and the cause of interrupting angle tracking is analyzed. Then kinematics model of the synthesized guidance is built,the definition of radar’s inertial no-escaped range is given,and the method of computing radar’s startup time is presented. Finally the comparative simulation for synthesized guidance and best lead guidance verifies the feasibility.