Eigenstructure invariance for an anticipated flight control surface failure

Author

Belkharraz, Abderrazak I. ; Sobel, Kenneth

Author_Institution

Dept. of Electr. Eng., City Univ. of New York, NY, USA

Volume

3

fYear

2001

fDate

2001

Firstpage

1833

Abstract

Consider an LTI plant which is augmented with first order actuator dynamics. Suppose we know which control surface is most likely to fail. We seek a constant gain output feedback controller such that the dominant eigenstructure is invariant under this failure. We show mathematically that the solution is that the surface which will fail should not be used. That is, if the j^th control surface will fail, then the j^th row of the constant output feedback gain matrix will be zero. We apply our results to the design of a stability augmentation system for the linearized lateral dynamics of the F/A-18 aircraft

Keywords

aircraft control; eigenvalues and eigenfunctions; fault tolerance; feedback; linear systems; matrix algebra; military aircraft; stability; F/A-18 aircraft; LTI plant; anticipated flight control surface failure; constant output feedback gain matrix; eigenstructure invariance; feedback; first-order actuator dynamics; invariant dominant eigenstructure; linearized lateral dynamics; stability augmentation system design; Actuators; Aerospace control; Aircraft; Cities and towns; Educational institutions; Eigenvalues and eigenfunctions; Filters; NASA; Output feedback; Stability;

fLanguage

English

Publisher

ieee

Conference_Titel

American Control Conference, 2001. Proceedings of the 2001

Conference_Location

Arlington, VA

ISSN

0743-1619

Print_ISBN

0-7803-6495-3

Type

conf

DOI

10.1109/ACC.2001.946002

Filename

946002