Design of a CLOS guidance law via feedback linearization

Author

Ha, In-Joong ; Chong, Song

Author_Institution

Dept. of Control & Instrum. Eng., Seoul Nat. Univ., South Korea

Volume

28

Issue

1

fYear

1992

fDate

1/1/1992 12:00:00 AM

Firstpage

51

Lastpage

63

Abstract

An application of the feedback linearization technique to the design of a new command to line-of-sight (CLOS) guidance law for short-range surface-to-air missiles is described. The key idea lies in converting the three-dimensional CLOS guidance problem to the tracking problem of a time-varying nonlinear system. The result may shed new light on the role of the feedforward acceleration terms used in the conventional CLOS guidance laws. Through computer simulation, the effect of the dynamics of the ground tracker and the autopilot on the guidance performance of the new CLOS guidance law is investigated

Keywords

aerospace control; command and control systems; control system CAD; control system synthesis; digital simulation; feedback; linearisation techniques; military computing; missiles; nonlinear control systems; time-varying systems; tracking; 3D; autopilot; command to line-of-sight guidance law; computer simulation; dynamics; feedback linearization; feedforward acceleration; ground tracker; short-range surface-to-air missiles; time-varying nonlinear system; Acceleration; Aerodynamics; Azimuth; Feedback; Linearization techniques; Missiles; Nonlinear systems; Optimal control; Target tracking; Time varying systems;

fLanguage

English

Journal_Title

Aerospace and Electronic Systems, IEEE Transactions on

Publisher

ieee

ISSN

0018-9251

Type

jour

DOI

10.1109/7.135432

Filename

135432