The computation equation and design criterion of real effective navigation ratio of homing control trajectory in PN homing guidance system were given.
给出了PN寻的制导系统的控制弹道实际有效导航比的计算公式及设计准则。
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.
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。
The homing progress can be divided into 6 phases by altitude. Guidance algorithm of every phase and stability of the system are discussed. Finally a conclusion is made in this paper.
文章介绍一种翼伞精确定点着陆归航的方案，按高度将归航过程划分为6个阶段，给出了每个阶段的制导算法，讨论了系统的稳定性并给出结论。
The homing progress can be divided into 6 phases by altitude. Guidance algorithm of every phase and stability of the system are discussed. Finally a conclusion is made in this paper.
文章介绍一种翼伞精确定点着陆归航的方案，按高度将归航过程划分为6个阶段，给出了每个阶段的制导算法，讨论了系统的稳定性并给出结论。
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