Manoeuvring flight control

Author

Pachter, M. ; Chandler, P.R. ; Smith, L.

Author_Institution

Air Force Inst. of Technol., Wright-Patterson AFB, OH, USA

Volume

2

fYear

1997

fDate

4-6 Jun 1997

Firstpage

1111

Abstract

The development of control laws for manoeuvring flight, specifically, a high amplitude velocity vector roll is addressed. The plant model has seventh order nonlinear dynamics with coupled pitch and lateral directional dynamics. Using time scale separation and pointwise linearization, a receding horizon linear quadratic optimal control law with full state feedback is synthesized online. Also online, the pilot inputs are modulated using linear programming to prevent actuator rate saturation over the optimization horizon. The nonlinear control law performance is demonstrated in a fighter aircraft simulation with a rudder failure during a loaded roll manoeuvre

Keywords

aircraft control; control system CAD; dynamics; linear programming; linear quadratic control; linearisation techniques; military aircraft; nonlinear dynamical systems; state feedback; actuator rate saturation; fighter aircraft; full state feedback; high amplitude velocity vector roll; lateral directional dynamics; loaded roll manoeuvre; manoeuvring flight control; nonlinear control law performance; pitch dynamics; pointwise linearization; receding horizon linear quadratic optimal control law; rudder failure; seventh order nonlinear dynamics; time scale separation; Aerospace control; Aircraft; Couplings; Hydraulic actuators; Linear programming; Modulation coding; Optimal control; State feedback; Vectors; Velocity control;

fLanguage

English

Publisher

ieee

Conference_Titel

American Control Conference, 1997. Proceedings of the 1997

Conference_Location

Albuquerque, NM

ISSN

0743-1619

Print_ISBN

0-7803-3832-4

Type

conf

DOI

10.1109/ACC.1997.609705

Filename

609705