A multi-gain sliding mode based controller for the pitch angle control of a civil aircraft

Author

Polas, Mahikshit ; Fekih, Afef

Author_Institution

Dept. of Electr. & Comput. Eng., Univ. of Louisiana at Lafayette, Lafayette, LA, USA

fYear

2010

fDate

7-9 March 2010

Firstpage

96

Lastpage

101

Abstract

A multi-gain sliding mode based controller for the pitch angle control of a civil aircraft is presented in this paper. The proposed controller is based on a novel concept of the sliding mode controllers in which multiple gains are being used to control the pitch angle of an aircraft and make it insensitive to parameter variations while reducing the chattering and guaranteeing the stability of the closed loop system. The proposed approach was implemented on a Delilah aircraft model to control the pitch angle under faulty conditions. Performance comparison between the traditional one gain SMC and the proposed multi-gains SMC are discussed.

Keywords

aircraft control; closed loop systems; position control; stability; variable structure systems; Delilah aircraft model; chattering reduction; civil aircraft; closed loop system stability; faulty condition; multigain sliding mode based controller; pitch angle control; Aerospace control; Aircraft; Control systems; Frequency; Nonlinear control systems; Open loop systems; Robust control; Scheduling; Sliding mode control; Vehicles; aircraft; fault tolerant control; robust control; sliding mode control;

fLanguage

English

Publisher

ieee

Conference_Titel

System Theory (SSST), 2010 42nd Southeastern Symposium on

Conference_Location

Tyler, TX

ISSN

0094-2898

Print_ISBN

978-1-4244-5690-1

Type

conf

DOI

10.1109/SSST.2010.5442854

Filename

5442854