Optimal guidance laws with impact point and impact angle for the missile

摘要：

　　In order to study the multiple terminal guidance problems, a guidance model based on lag-free and first-order lag systems is established.Considering the multiple terminal constraint conditions of impact point and impact angle, the general solution of multiple terminal guidance problems is deduced from optimal control theory.It is shown that the two kinds of optimal guidance laws are both satisfied with the require of miss distance and large impact angle whatever in theoretical analysis results or simulation results.The influences of wind and measurement error on guidance precision are studied by Monte-Carlo method.

关键词： Optimal guidance law Multiple terminal constraints Impact point Impact angle Monte-Carlo method

作者: Lei HUANG Wen-jun YI Jun GUAN Dan-dan YUAN Lei SUN

作者单位: National Key Laboratory of Transient Physics, Nanjing University of Science and Technology, Nanjing, Jiangsu, China

会议类型: 国际会议

会议名称: 2018 International Conference on Defence Technology (2018国际防务技术会议)

会议地点: 北京

会议语种:英文

页码: 30-34

在线出版日期: 2018-10-21（万方平台首次上网日期，不代表论文的发表时间）