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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
TL500-777 Aeronautics. Aeronautical engineering
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
http://eprints.uthm.edu.my/1630/
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spelling my.uthm.eprints.16302021-10-04T01:21:48Z http://eprints.uthm.edu.my/1630/ On the development of computer code for aircraft flight dynamics analysis 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 NonPeerReviewed text en http://eprints.uthm.edu.my/1630/1/24p%20OUTMAN%20MOHAMED%20ALAZOMUI.pdf text en http://eprints.uthm.edu.my/1630/2/OUTMAN%20MOHAMED%20ALAZOMUI%20WATERMARK.pdf Mohamed Alazomui, Outman (2014) On the development of computer code for aircraft flight dynamics analysis. Masters thesis, Universiti Tun Hussein Onn Malaysia.
institution Universiti Tun Hussein Onn Malaysia
building UTHM Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Tun Hussein Onn Malaysia
content_source UTHM Institutional Repository
url_provider http://eprints.uthm.edu.my/
language English
English
topic TL Motor vehicles. Aeronautics. Astronautics
TL500-777 Aeronautics. Aeronautical engineering
spellingShingle TL Motor vehicles. Aeronautics. Astronautics
TL500-777 Aeronautics. Aeronautical engineering
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
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
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
http://eprints.uthm.edu.my/1630/
_version_ 1738580884721762304
score 13.211869

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