DocumentCode
3186458
Title
Sliding mode control scheme for aircraft
Author
Zhan-shan, Zhao ; Jing, Zhang ; Lian-kun, Sun ; Gang, Ding
Author_Institution
Comput. Sci. & Software Instn., Tianjin Polytech. Univ., Tianjin, China
fYear
2010
fDate
3-5 Dec. 2010
Firstpage
278
Lastpage
281
Abstract
An Integral sliding mode based on the finite time stabilization control scheme for the longitudinal dynamics of aircraft is proposed in this paper. The Input/Output Linearization technique is applied for control design to linearize the dynamics of aircraft with respect to air speed V and altitude h. Simulation studies demonstrate that the proposed controller is robust with respect to the perturbation.
Keywords
aircraft control; control system synthesis; stability; variable structure systems; aircraft; control design; finite time stabilization control; input/output linearization technique; integral sliding mode; longitudinal dynamics; sliding mode control; Aerospace control; Aircraft; Atmospheric modeling; Mathematical model; Robustness; Vehicle dynamics; Vehicles; Aircraft; Linearization technique; Sliding Mode Control; insert; styling;
fLanguage
English
Publisher
ieee
Conference_Titel
Computer and Information Application (ICCIA), 2010 International Conference on
Conference_Location
Tianjin
Print_ISBN
978-1-4244-8597-0
Type
conf
DOI
10.1109/ICCIA.2010.6141591
Filename
6141591
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