Variable structure robust flight control system for the F-14

Author

Singh, Sahjendra N. ; Steinberg, Marc ; DiGirolamo, Robert D.

Author_Institution

Dept. of Electr. & Comput. Eng., Nevada Univ., Las Vegas, NV, USA

Volume

1

fYear

1995

fDate

21-23 Jun 1995

Firstpage

815

Abstract

A flight control law for a simplified F-14 aircraft model is designed, based on variable structure control (VSC) theory. For m-input, q-output linear uncertain systems q<m, a VSC law is derived. For the derivation of the control law, a choice of a sliding surface is made so that the zero dynamics of the system are stable. Application of variable structure system theory to the control of lateral dynamics is presented. A control law is derived for the control of roll angle, lateral velocity and yaw rate. Simulation results are presented to show that in the closed-loop system, precise bank angle trajectory tracking and regulation of lateral velocity and yaw rate can be accomplished in spite of the aerodynamic parameter uncertainty

Keywords

aerodynamics; aircraft control; attitude control; closed loop systems; robust control; uncertain systems; variable structure systems; velocity control; F-14 aircraft model; aerodynamic parameter uncertainty; bank angle trajectory tracking; closed-loop system; flight control law; lateral dynamics control; lateral velocity control; linear uncertain systems; robust flight control system; roll angle control; simulation; sliding surface; stable zero dynamics; variable structure control theory; variable structure system theory; yaw rate control; Aerodynamics; Aerospace control; Aircraft; Control systems; Robust control; Sliding mode control; Trajectory; Uncertain systems; Variable structure systems; Velocity control;

fLanguage

English

Publisher

ieee

Conference_Titel

American Control Conference, Proceedings of the 1995

Conference_Location

Seattle, WA

Print_ISBN

0-7803-2445-5

Type

conf

DOI

10.1109/ACC.1995.529362

Filename

529362