A guidance law design with terminal impact angle constraint based on nonlinear generalized predictive control

Author

Teng Lv ; Chuanjiang Li ; Yanchao Sun ; Guangfu Ma ; Junzi Xiao

Author_Institution

Sch. of Astronaut., Harbin Inst. of Technol. HIT, Harbin, China

fYear

2014

fDate

15-17 Nov. 2014

Firstpage

1

Lastpage

5

Abstract

In this paper, a kind of reference trajectory of line-of-sight (LOS) angle based on the optimal control theory is given. Then, the corresponding nonlinear generalized predictive control law is designed to make the missile´s actual LOS angle track the reference LOS angle. Simulation results show that the proposed nonlinear generalized predictive control law can make the missile hit the ground stationary target accurately and meet the demand for terminal impact angle constraint.

Keywords

missile guidance; nonlinear control systems; optimal control; predictive control; LOS angle; missile guidance law design; nonlinear generalized predictive control; optimal control theory; terminal impact angle constraint; Acceleration; Adaptive systems; Missiles; Navigation; Predictive control; Target tracking; Trajectory; line-of-sight angle tracking; nonlinear generalized predictive control; optimal control; terminal impact angle constraint;

fLanguage

English

Publisher

ieee

Conference_Titel

Systems and Informatics (ICSAI), 2014 2nd International Conference on

Conference_Location

Shanghai

Print_ISBN

978-1-4799-5457-5

Type

conf

DOI

10.1109/ICSAI.2014.7009249

Filename

7009249