Advanced guidance control system design for homing missiles with bearings-only measurements

Author

Hassoun, George E. ; Lim, Cheng Chew

Author_Institution

Dept. of Electr. & Electron. Eng., Adelaide Univ., SA, Australia

fYear

1994

fDate

5-9 Dec 1994

Firstpage

250

Lastpage

254

Abstract

A guidance control law for homing missiles with bearings-only measurements is presented. The law is chosen to be a proportional navigation one, but with an additional term in the control law to induce observability. The design preserves the simplicity of proportional navigation, and offers the ability to enhance the performance of a Kalman filter which is an integral part of the control. The closed form solutions of the differential equations describing the relative motion of missile-target systems under this guidance law are derived. Monte-Carlo simulations to study the system performance are performed

Keywords

Monte Carlo methods; control system synthesis; differential equations; missile guidance; observability; stochastic systems; Kalman filter; Monte-Carlo simulations; advanced guidance control system; bearings-only measurements; closed form solutions; differential equations; homing missiles; observability; proportional navigation; relative motion; Control systems; Electric variables measurement; Filters; Missiles; Navigation; Observability; Optimal control; Proportional control; State estimation; Virtual manufacturing;

fLanguage

English

Publisher

ieee

Conference_Titel

Industrial Technology, 1994., Proceedings of the IEEE International Conference on

Conference_Location

Guangzhou

Print_ISBN

0-7803-1978-8

Type

conf

DOI

10.1109/ICIT.1994.467119

Filename

467119