寻的制导系统起伏误差解析模型

目前,对寻的制导系统制导精度的有效计算仅限于数值计算。本文通过对运动学环节的近似处理,得到导弹飞行末端的近似传递函数,该传递函数中不含变化剧烈的导弹、目标相对距离,不仅使系统的阶次降低,而且制导回路开环放大系数变为缓变量Na(导弹有效导航比),可采用系数固化法。据此建立的目标角噪声引起的起伏误差解析模型,具有简单、实用的特点,为寻的制导系统制导精度的计算提供了一种新途径。

ANALYTICAL MODEL OF FLUCTUATION ERROR OF HOMING GUIDANCE SYSTEM

To Calculate efficiently guidance accuracy (such as rms miss distance) of a homing system, the usual method is to draw support from numerical calculations (Monte Carlo method, CADET, etc.). In this paper, through approximate kinematic analysis, we obtain an approximate transfer function which does not contain the relative distance (Varying drastically with time) between missile and target in terminal flight phase of the missile Not only the system order is reduced, but also the gain of the open loop system changes into a slowly varying effective navigation ratio. Thus coefficients of the differnetial equation of the system can be frozen. A simple and practical analytical model of fluctuation error (rms miss distance due to glint noise) of the homing guidance System, is then obtained to calculate guidance accuracy.