Aircraft Lateral-Directional Stability in Critical Cases via Lyapunov Exponent Criterion

Based on Lyapunov exponent criterion, the aircraft lateral-directional stability during critical flight cases is presented. A periodic motion or limit cycle oscillation isdisplayed. A candidate mechanism for the wing rock limit cycle is the inertia coupling between an unstable lateral-directional (D...

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Autores principales:	Emad N.Abdulwahab, Qasim A.Atiyah, Ali Talib Abd Alzahra
Formato:	article
Lenguaje:	EN
Publicado:	Al-Khwarizmi College of Engineering – University of Baghdad 2013
Materias:	wing rock; nonlinear dynamic system; limit cycle oscillation. Chemical engineering TP155-156 Engineering (General). Civil engineering (General) TA1-2040
Acceso en línea:	https://doaj.org/article/9bcf868c1cdc4702832117853668e7ad
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id	oai:doaj.org-article:9bcf868c1cdc4702832117853668e7ad
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spelling	oai:doaj.org-article:9bcf868c1cdc4702832117853668e7ad2021-12-02T06:41:03ZAircraft Lateral-Directional Stability in Critical Cases via Lyapunov Exponent Criterion1818-1171https://doaj.org/article/9bcf868c1cdc4702832117853668e7ad2013-01-01T00:00:00Zhttp://www.iasj.net/iasj?func=fulltext&aId=69962https://doaj.org/toc/1818-1171Based on Lyapunov exponent criterion, the aircraft lateral-directional stability during critical flight cases is presented. A periodic motion or limit cycle oscillation isdisplayed. A candidate mechanism for the wing rock limit cycle is the inertia coupling between an unstable lateral-directional (Dutch roll) mode with stable longitudinal (short period) mode. The coupling mechanism is provided by the nonlinear interaction of motion related terms in the complete set equations of motion. To analyze the state variables of the system, the complete set of nonlinear equations of motion at different high angles of attack are solved. A novel analysis including the variation of roll angle as a function of angle of attack is proposed. Furthermore the variation of Lyapunov exponent parameter as function of time is introduced. The numerical result indicated that the system became lightly damped at high angle of attack with increasing the amplitude of aircraft state variables limit cycle. A good agreement between the numerical result and published work is obtained for the onset of limit cycle oscillation, almost at(?=?20?^°-?23?^° ).Emad N.AbdulwahabQasim A.AtiyahAli Talib Abd AlzahraAl-Khwarizmi College of Engineering – University of Baghdadarticlewing rock; nonlinear dynamic system; limit cycle oscillation.Chemical engineeringTP155-156Engineering (General). Civil engineering (General)TA1-2040ENAl-Khawarizmi Engineering Journal, Vol 9, Iss 1, Pp 29-38 (2013)
institution	DOAJ
collection	DOAJ
language	EN
topic	wing rock; nonlinear dynamic system; limit cycle oscillation. Chemical engineering TP155-156 Engineering (General). Civil engineering (General) TA1-2040
spellingShingle	wing rock; nonlinear dynamic system; limit cycle oscillation. Chemical engineering TP155-156 Engineering (General). Civil engineering (General) TA1-2040 Emad N.Abdulwahab Qasim A.Atiyah Ali Talib Abd Alzahra Aircraft Lateral-Directional Stability in Critical Cases via Lyapunov Exponent Criterion
description	Based on Lyapunov exponent criterion, the aircraft lateral-directional stability during critical flight cases is presented. A periodic motion or limit cycle oscillation isdisplayed. A candidate mechanism for the wing rock limit cycle is the inertia coupling between an unstable lateral-directional (Dutch roll) mode with stable longitudinal (short period) mode. The coupling mechanism is provided by the nonlinear interaction of motion related terms in the complete set equations of motion. To analyze the state variables of the system, the complete set of nonlinear equations of motion at different high angles of attack are solved. A novel analysis including the variation of roll angle as a function of angle of attack is proposed. Furthermore the variation of Lyapunov exponent parameter as function of time is introduced. The numerical result indicated that the system became lightly damped at high angle of attack with increasing the amplitude of aircraft state variables limit cycle. A good agreement between the numerical result and published work is obtained for the onset of limit cycle oscillation, almost at(?=?20?^°-?23?^° ).
format	article
author	Emad N.Abdulwahab Qasim A.Atiyah Ali Talib Abd Alzahra
author_facet	Emad N.Abdulwahab Qasim A.Atiyah Ali Talib Abd Alzahra
author_sort	Emad N.Abdulwahab
title	Aircraft Lateral-Directional Stability in Critical Cases via Lyapunov Exponent Criterion
title_short	Aircraft Lateral-Directional Stability in Critical Cases via Lyapunov Exponent Criterion
title_full	Aircraft Lateral-Directional Stability in Critical Cases via Lyapunov Exponent Criterion
title_fullStr	Aircraft Lateral-Directional Stability in Critical Cases via Lyapunov Exponent Criterion
title_full_unstemmed	Aircraft Lateral-Directional Stability in Critical Cases via Lyapunov Exponent Criterion
title_sort	aircraft lateral-directional stability in critical cases via lyapunov exponent criterion
publisher	Al-Khwarizmi College of Engineering – University of Baghdad
publishDate	2013
url	https://doaj.org/article/9bcf868c1cdc4702832117853668e7ad
work_keys_str_mv	AT emadnabdulwahab aircraftlateraldirectionalstabilityincriticalcasesvialyapunovexponentcriterion AT qasimaatiyah aircraftlateraldirectionalstabilityincriticalcasesvialyapunovexponentcriterion AT alitalibabdalzahra aircraftlateraldirectionalstabilityincriticalcasesvialyapunovexponentcriterion
_version_	1718399767464116224

Aircraft Lateral-Directional Stability in Critical Cases via Lyapunov Exponent Criterion

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