Please use this identifier to cite or link to this item: https://hdl.handle.net/20.500.13087/913
Title: Output feedback sliding mode control of a fixed-wing UAV under rudder loss
Authors: Güneş, U.
Sel, A.
Kasnakoğlu, C.
Kaynak, Ünver
Issue Date: 2019
Publisher: American Institute of Aeronautics and Astronautics Inc, AIAA
Abstract: The purpose of this study is to design a Dynamic discrete output feedback SMC for fixed wing aircraft under rudder loss operation. Recently, UAVs have been utilized in many commercial and military applications. However, due to environmental factors and unforeseeable mechanical failures, complete loss of control may occur. To deal with this type of malfunctions fault detection and fault tolerant control is developed. Being one of the most prevalent failure, the rudder loss which is caused by mechanical or electronic factors is studied in this paper, and an ODSMC controller design is presented for this scenario. To derive the linearized model around the operation point, the small disturbance theory is used. Based on this derived linear model for the rudder loss operation ODSMC which is a one type of robust control strategy is employed. Owing to its output feedback nature, the process of designing a state estimator is also eliminated. The rudder loss scenario for Apprentice S model aircraft was simulated in MATLAB/Simulink environment and the satisfactory results were achieved. © 2019 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
Description: AIAA Scitech Forum, 2019 -- 7 January 2019 through 11 January 2019 -- -- 225819
URI: https://doi.org/10.2514/6.2019-0911
https://hdl.handle.net/20.500.13087/913
ISBN: 9.78E+12
Appears in Collections:İnşaat Mühendisliği Bölümü Koleksiyonu
Scopus İndeksli Yayınlar Koleksiyonu

Show full item record

CORE Recommender

Page view(s)

6
checked on Oct 3, 2022

Google ScholarTM

Check

Altmetric


Items in GCRIS Repository are protected by copyright, with all rights reserved, unless otherwise indicated.