期刊名称：International Journal of Hybrid Information Technology
印刷版ISSN：1738-9968
出版年度：2015
卷号：8
期号：9
页码：53-62
DOI：10.14257/ijhit.2015.8.9.06
出版社：SERSC
摘要：In missile guidance systems, classical proportional navigation law has been used most widely. But with the increasing of the maneuverability of the targets, the classical proportional navigation guidance law has been unable to meet the requirements of people on the ballistic parameters. So this paper will further study the algorithm error of guidance law. Based on the previous theoretical results and the working principle of aircraft in the homing guidance system, this paper studies a guidance trajectory guidance principle which based on the ratio, and has carried on the analysis and the simulation theory. And simulation accuracy analysis has been carried on with practical examples. The results show that the method is put forward to effectively reduce the guided ballistic calculation method of error.
