Optimal setpoint controller for a generic X-29A aircraft with forebody vortex nozzles

Author

Valasek, John

Author_Institution

Dept. of Mech. & Aeron. Eng., Western Michigan Univ., Kalamazoo, MI, USA

fYear

1996

fDate

15-18 Sep 1996

Firstpage

1

Lastpage

6

Abstract

This paper presents the design, synthesis, and performance of an optimal setpoint high angle-of-attack lateral/directional controller for the X-29A aircraft equipped with forebody vortex flow control nozzles. The closed-loop control law is full state feedback, and is synthesized using a linear time-invariant generic model of the X-29A. Results demonstrate that by proper selection of the weighting elements, the forebody vortex nozzles together with the aerodynamic control effecters can be modulated to improve the closed-loop response compared to a controller design which uses only the aerodynamic control effecters

Keywords

aircraft control; attitude control; bang-bang control; closed loop systems; control system synthesis; military aircraft; optimal control; state feedback; X-29A aircraft; aerodynamic control; bang bang control; closed-loop response; closed-loop system; directional control; forebody vortex nozzles; lateral control; linear time-invariant generic model; optimal setpoint controller; state feedback; Aerodynamics; Aerospace control; Aircraft propulsion; Control systems; Military aircraft; Optimal control; Pressure control; Symmetric matrices; Velocity control; Weapons;

fLanguage

English

Publisher

ieee

Conference_Titel

Control Applications, 1996., Proceedings of the 1996 IEEE International Conference on

Conference_Location

Dearborn, MI

Print_ISBN

0-7803-2975-9

Type

conf

DOI

10.1109/CCA.1996.558583

Filename

558583