Aircraft stabilisation: a suitable choice of feedback gain

Author

Djeddi, Mounir ; Hariche, Kamel ; Aissou, Abdallah

Author_Institution

Lab. des signaux et systemes, CNRS-SUPELEC, Gif sur Yvette, France

Volume

2

fYear

2003

fDate

14-17 Dec. 2003

Firstpage

671

Abstract

The dynamics of an aircraft are a perfect example of a multi-input multi-output system; it is known from control theory that the state feedback gain achieving a set of desired closed loop poles is not unique in this case. The objective of this paper is to synthesize the most suitable gain for a given set of desired closed loop poles meeting the best possible closed loop system time response characteristics (small transient, small steady state error, Percentage Over Shoot...), A small system feedback gain to minimize the control energy, and prevent saturation of the controller elements and noise amplification. A simulation study is conducted in order to test the controller for different perturbation models.

Keywords

MIMO systems; aircraft control; closed loop systems; controllability; eigenvalues and eigenfunctions; perturbation techniques; pole assignment; state feedback; step response; aircraft dynamics; aircraft stabilisation; closed loop poles; control energy; controllability; feedback gain; linearized aircraft model; multi-input multi-output system; multivariable control systems; percentage over shoot; perturbation models; pole assignment; small steady state error; small transient; state feedback gain; state-variable description; time response characteristics; Aerospace control; Aircraft; Closed loop systems; Control system synthesis; Control theory; Error correction; Feedback loop; State feedback; Steady-state; Time factors;

fLanguage

English

Publisher

ieee

Conference_Titel

Electronics, Circuits and Systems, 2003. ICECS 2003. Proceedings of the 2003 10th IEEE International Conference on

Print_ISBN

0-7803-8163-7

Type

conf

DOI

10.1109/ICECS.2003.1301874

Filename

1301874