Optimal guidance for acceleration constrained missile and maneuvering target

1990 ◽  
Vol 26 (4) ◽  
pp. 618-624 ◽  
Author(s):  
I. Rusnak ◽  
L. Meir
Keyword(s):  
Maneuvering Target ◽  
Optimal Guidance

Three-Dimensional Nonlinear Optimal Guidance against Maneuvering Target with Large Initial Heading Error

2022 ◽  
Author(s):  
Hongyan Li ◽  
Shaoming He ◽  
Jiang Wang ◽  
Hyo-Sang Shin ◽  
Antonios Tsourdos
Keyword(s):  
Three Dimensional ◽  
Maneuvering Target ◽  
Optimal Guidance

Biased optimal guidance law with specified velocity rendezvous angle constraint

2015 ◽  
Vol 119 (1220) ◽  
pp. 1287-1299 ◽  
Author(s):  
X. Xu ◽  
Y. Liang
Keyword(s):  
High Speed ◽  
Terminal Phase ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Terminal Time ◽  
Optimal Guidance ◽  
Simulation Results ◽  
Miss Distance ◽  
Simplified Mathematical Model ◽  
Distance Setting

Abstract In order to increase the effectiveness of interceptor missile, velocity rendezvous angle control is required in the terminal phase. The purpose of this paper is to obtain an optimal guidance law which can achieve specified velocity rendezvous angle as well as zero terminal miss distance. A biased optimal guidance law based on a simplified mathematical model is deduced for interceptors engaging against invasion aircraft. Different from previous literatures on this issue, the presented guidance law suitable for intercepting high-speed maneuvering target. Another advantage is, under centimeter level miss distance setting, the guidance law needs smaller guidance command near the terminal time, which can successfully avoid command saturation. Simulation results demonstrate the effectiveness of the presented guidance law.

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