On the development of computer code for aircraft flight dynamics analysis

The stability analysis of the aircraft can be evaluated in two flight modes: longitudinal stability analysis and the lateral – directional stability analysis. The present work focused on the second mode of flight. The stability analysis carried out by evaluates the behavior of three flight par...

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Main Author:	Mohamed Alazomui, Outman
Format:	Thesis
Language:	English English
Published:	2014
Subjects:	TL Motor vehicles Aeronautics Astronautics
Online Access:	http://eprints.uthm.edu.my/1630/1/24p%20OUTMAN%20MOHAMED%20ALAZOMUI.pdf http://eprints.uthm.edu.my/1630/2/OUTMAN%20MOHAMED%20ALAZOMUI%20WATERMARK.pdf
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id	my-uthm-ep.1630
record_format	uketd_dc
spelling	my-uthm-ep.16302021-10-04T01:21:48Z On the development of computer code for aircraft flight dynamics analysis 2014-12 Mohamed Alazomui, Outman TL Motor vehicles. Aeronautics. Astronautics TL500-777 Aeronautics. Aeronautical engineering The stability analysis of the aircraft can be evaluated in two flight modes: longitudinal stability analysis and the lateral – directional stability analysis. The present work focused on the second mode of flight. The stability analysis carried out by evaluates the behavior of three flight parameters if their aircraft control surfaces operated. These three flight parameters are the side slip angle β, the roll angle  and the yaw angle . These three parameters describe the aptitude of the aircraft which can be obtained through solving the governing equation of flight motion. In this respect, the governing equation of flight motion is the Lateral-Directional Flight Equation. To solve this equation, the present work use a Matlab programming language which allow to solution of the governing equation of flight motion carried out by use of a Laplace transformation. The stability analysis of the aircraft carried out over four type aircraft. The first two type of aircraft belong to class of a propeller driven aircraft, while the rests are the turbojet aircraft type of aircraft. The developed computer code provide 2 option how the aileron are deflected, they are namely (1) a single double impulse aileron and (2) a multiple doublet impulse aileron. While from the point of view rudder is also having two type of deflection, namely (1) a single double impulse rudder and (2) a multiple double impulse rudder. These types of control surfaces deflection applied to case of Cessna – 182, Beech – 99, Lear Jet – M24 and The Lockheed F104. The results indicate that each of aircraft has different response in anticipating with the deflection of aileron as well as rudder. 2014-12 Thesis http://eprints.uthm.edu.my/1630/ http://eprints.uthm.edu.my/1630/1/24p%20OUTMAN%20MOHAMED%20ALAZOMUI.pdf text en public http://eprints.uthm.edu.my/1630/2/OUTMAN%20MOHAMED%20ALAZOMUI%20WATERMARK.pdf text en validuser mphil masters Universiti Tun Hussein Onn Malaysia Fakulti Kejuruteraan Mekanikal dan Pembuatan
institution	Universiti Tun Hussein Onn Malaysia
collection	UTHM Institutional Repository
language	English English
topic	TL Motor vehicles Aeronautics Astronautics TL Motor vehicles Aeronautics Astronautics
spellingShingle	TL Motor vehicles Aeronautics Astronautics TL Motor vehicles Aeronautics Astronautics Mohamed Alazomui, Outman On the development of computer code for aircraft flight dynamics analysis
description	The stability analysis of the aircraft can be evaluated in two flight modes: longitudinal stability analysis and the lateral – directional stability analysis. The present work focused on the second mode of flight. The stability analysis carried out by evaluates the behavior of three flight parameters if their aircraft control surfaces operated. These three flight parameters are the side slip angle β, the roll angle  and the yaw angle . These three parameters describe the aptitude of the aircraft which can be obtained through solving the governing equation of flight motion. In this respect, the governing equation of flight motion is the Lateral-Directional Flight Equation. To solve this equation, the present work use a Matlab programming language which allow to solution of the governing equation of flight motion carried out by use of a Laplace transformation. The stability analysis of the aircraft carried out over four type aircraft. The first two type of aircraft belong to class of a propeller driven aircraft, while the rests are the turbojet aircraft type of aircraft. The developed computer code provide 2 option how the aileron are deflected, they are namely (1) a single double impulse aileron and (2) a multiple doublet impulse aileron. While from the point of view rudder is also having two type of deflection, namely (1) a single double impulse rudder and (2) a multiple double impulse rudder. These types of control surfaces deflection applied to case of Cessna – 182, Beech – 99, Lear Jet – M24 and The Lockheed F104. The results indicate that each of aircraft has different response in anticipating with the deflection of aileron as well as rudder.
format	Thesis
qualification_name	Master of Philosophy (M.Phil.)
qualification_level	Master's degree
author	Mohamed Alazomui, Outman
author_facet	Mohamed Alazomui, Outman
author_sort	Mohamed Alazomui, Outman
title	On the development of computer code for aircraft flight dynamics analysis
title_short	On the development of computer code for aircraft flight dynamics analysis
title_full	On the development of computer code for aircraft flight dynamics analysis
title_fullStr	On the development of computer code for aircraft flight dynamics analysis
title_full_unstemmed	On the development of computer code for aircraft flight dynamics analysis
title_sort	on the development of computer code for aircraft flight dynamics analysis
granting_institution	Universiti Tun Hussein Onn Malaysia
granting_department	Fakulti Kejuruteraan Mekanikal dan Pembuatan
publishDate	2014
url	http://eprints.uthm.edu.my/1630/1/24p%20OUTMAN%20MOHAMED%20ALAZOMUI.pdf http://eprints.uthm.edu.my/1630/2/OUTMAN%20MOHAMED%20ALAZOMUI%20WATERMARK.pdf
_version_	1747830833142562816

On the development of computer code for aircraft flight dynamics analysis

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