Preliminary design of sliding mode controller for angular positional tracking of an aircraft

Sliding mode controllers are known to be robust to parameter changes and capable of rejecting disturbances. Most sliding mode controllers were implemented on aircraft models that were derived based on the aircraft's body axes. The aircraft model in this paper are derived from an energy based...

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Main Authors:	Jones, Lim Jen Nee, Tan, Chee Pin, Man, zhihong, Akmeliawati, Rini
Format:	Conference or Workshop Item
Language:	English
Published:	2009
Subjects:	TJ212 Control engineering
Online Access:	http://irep.iium.edu.my/14158/ http://irep.iium.edu.my/14158/1/ascc2009_jn.pdf

id	iium-14158
recordtype	eprints
spelling	iium-141582012-01-09T03:17:43Z http://irep.iium.edu.my/14158/ Preliminary design of sliding mode controller for angular positional tracking of an aircraft Jones, Lim Jen Nee Tan, Chee Pin Man, zhihong Akmeliawati, Rini TJ212 Control engineering Sliding mode controllers are known to be robust to parameter changes and capable of rejecting disturbances. Most sliding mode controllers were implemented on aircraft models that were derived based on the aircraft's body axes. The aircraft model in this paper are derived from an energy based modeling technique where the aircraft dynamics can be defined by Euler-Lagrangian equations that makes decoupling of aircraft dynamics simple and straightforward. It is possible to do so since these equations can be derived from the inertial axes of the aircraft instead of the aircraft's body axes. The nature of these equations makes it easy to implement the sliding mode controller on all the angular positions of the aircraft for the purpose of tracking a reference trajectory. Parameter changes and disturbances were also introduced as part of the evaluation procedure in few sets of simulations to prove how well these angular positions can be tracked. The controller designed to achieve angular positional tracking includes a nominal feedback controller and a sliding mode compensator. The performance of the controller presented are measured using root-mean-square error values and maximum errors for roll, pitch and yaw. Results presented shows good tracking performances throughout entire flight trajectory that includes a one-sided engine failure, a 90 degree turn and rotations in the pitch angle. 2009 Conference or Workshop Item PeerReviewed application/pdf en http://irep.iium.edu.my/14158/1/ascc2009_jn.pdf Jones, Lim Jen Nee and Tan, Chee Pin and Man, zhihong and Akmeliawati, Rini (2009) Preliminary design of sliding mode controller for angular positional tracking of an aircraft. In: the 7th Asian Control Conference (ASCC 2009), 27-29 Aug 2009, Hong Kong.
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English
topic	TJ212 Control engineering
spellingShingle	TJ212 Control engineering Jones, Lim Jen Nee Tan, Chee Pin Man, zhihong Akmeliawati, Rini Preliminary design of sliding mode controller for angular positional tracking of an aircraft
description	Sliding mode controllers are known to be robust to parameter changes and capable of rejecting disturbances. Most sliding mode controllers were implemented on aircraft models that were derived based on the aircraft's body axes. The aircraft model in this paper are derived from an energy based modeling technique where the aircraft dynamics can be defined by Euler-Lagrangian equations that makes decoupling of aircraft dynamics simple and straightforward. It is possible to do so since these equations can be derived from the inertial axes of the aircraft instead of the aircraft's body axes. The nature of these equations makes it easy to implement the sliding mode controller on all the angular positions of the aircraft for the purpose of tracking a reference trajectory. Parameter changes and disturbances were also introduced as part of the evaluation procedure in few sets of simulations to prove how well these angular positions can be tracked. The controller designed to achieve angular positional tracking includes a nominal feedback controller and a sliding mode compensator. The performance of the controller presented are measured using root-mean-square error values and maximum errors for roll, pitch and yaw. Results presented shows good tracking performances throughout entire flight trajectory that includes a one-sided engine failure, a 90 degree turn and rotations in the pitch angle.
format	Conference or Workshop Item
author	Jones, Lim Jen Nee Tan, Chee Pin Man, zhihong Akmeliawati, Rini
author_facet	Jones, Lim Jen Nee Tan, Chee Pin Man, zhihong Akmeliawati, Rini
author_sort	Jones, Lim Jen Nee
title	Preliminary design of sliding mode controller for angular positional tracking of an aircraft
title_short	Preliminary design of sliding mode controller for angular positional tracking of an aircraft
title_full	Preliminary design of sliding mode controller for angular positional tracking of an aircraft
title_fullStr	Preliminary design of sliding mode controller for angular positional tracking of an aircraft
title_full_unstemmed	Preliminary design of sliding mode controller for angular positional tracking of an aircraft
title_sort	preliminary design of sliding mode controller for angular positional tracking of an aircraft
publishDate	2009
url	http://irep.iium.edu.my/14158/ http://irep.iium.edu.my/14158/1/ascc2009_jn.pdf
first_indexed	2023-09-18T20:23:20Z
last_indexed	2023-09-18T20:23:20Z
_version_	1777408252348203008

Preliminary design of sliding mode controller for angular positional tracking of an aircraft

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