Time-to-go estimation algorithm for the proportional navigation guidance law with a large lead angle

被引：0
作者：
Zhang, Youan [1 ]
Ma, Guoxin [1 ,2 ]
机构：
[1] Department of Control Engineering, Naval Aeronautical and Astronautical University
[2] Unit 93132, PLA
来源：
Zhang, Y. (zhangya63@sina.com) | 1600年 / Editorial Board of Journal of Harbin Engineering卷 / 34期
关键词：
Anti-ship missiles; Impact time control; Lead angle; Proportional navigation guidance; Time-to-go estimation;
D O I：
10.3969/j.issn.1006-7043.201209052
中图分类号：
学科分类号：
摘要：
The traditional time-to-go estimation approaches often suffer from poor precision when the lead angle of the missile is large in the guidance. To cope with this, a time-to-go estimation algorithm for the proportional navigation guidance law with a large lead angle is proposed by using piecewise linear approximation. Firstly, the first-order nonlinear differential equations of range-to-go and flight time with respect to the lead angle are derived by transforming the closed-form system equations. Then, the interval of the lead angle is divided into small pieces and the increment of the lead angle in each piece is guaranteed to be a small angle. The differential equations in each piece are solved by using first-order Taylor expansion. Finally, the time-to-go estimation for the large lead angle is obtained by piecewise iterations. Simulation results show that, the time-to-go estimation precision is enhanced from 1.2 s to 0.1 s by the algorithm for the large lead angle in the representative scenario.
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页码：1409 / 1414
页数：5
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