On the development computer, code for determinig the root of equation for transient flight analysis

This thesis presents the governing equation of flight motions which can be used to describe the flight behavior of any type flying vehicles consist of 12 equations described 12 state – space variables involving the aircraft position and aircraft aptitude with respect to the inertial coordinate sy...

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التفاصيل البيبلوغرافية
المؤلف الرئيسي:	Khaire Elarosi, Muwfik Faidi
التنسيق:	أطروحة
اللغة:	English English English
منشور في:	2013
الموضوعات:	TL Motor vehicles Aeronautics Astronautics
الوصول للمادة أونلاين:	http://eprints.uthm.edu.my/1991/1/24p%20MUWFIK%20FAIDI%20KHAIRE%20ELAROSI.pdf http://eprints.uthm.edu.my/1991/2/MUWFIK%20FAIDI%20KHAIRE%20ELAROSI%20COPYRIGHT%20DECLARATION.pdf http://eprints.uthm.edu.my/1991/3/MUWFIK%20FAIDI%20KHAIRE%20ELAROSI%20WATERMARK.pdf
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id	my-uthm-ep.1991
record_format	uketd_dc
spelling	my-uthm-ep.19912021-10-14T05:52:54Z On the development computer, code for determinig the root of equation for transient flight analysis 2013-12 Khaire Elarosi, Muwfik Faidi TL Motor vehicles. Aeronautics. Astronautics TL500-777 Aeronautics. Aeronautical engineering This thesis presents the governing equation of flight motions which can be used to describe the flight behavior of any type flying vehicles consist of 12 equations described 12 state – space variables involving the aircraft position and aircraft aptitude with respect to the inertial coordinate system and also with respect to their axis body system had been used. These twelve equations are coupling each to others and in the forms highly non linear equation; the numerical approach is required for solving such system equation. The coefficient of system equation can be said as a result of the combination between aircraft’s mass and inertia, aircraft geometry properties and also their aircraft aerodynamics derivatives. The present work is focused in the development computer code which allows in manner of determining the root of equation of the 12 equations which described the flight behavior for particular airplane. Through determining the root of equation one will able to carry out a non linear transient analysis such as aircraft at landing approaches gust response and pilot initiated maneuvers. 2013-12 Thesis http://eprints.uthm.edu.my/1991/ http://eprints.uthm.edu.my/1991/1/24p%20MUWFIK%20FAIDI%20KHAIRE%20ELAROSI.pdf text en public http://eprints.uthm.edu.my/1991/2/MUWFIK%20FAIDI%20KHAIRE%20ELAROSI%20COPYRIGHT%20DECLARATION.pdf text en staffonly http://eprints.uthm.edu.my/1991/3/MUWFIK%20FAIDI%20KHAIRE%20ELAROSI%20WATERMARK.pdf text en validuser mphil masters Universiti Tun Hussein Malaysia Fakulti Kejuruteraan Mekanikal dan Pembuatan
institution	Universiti Tun Hussein Onn Malaysia
collection	UTHM Institutional Repository
language	English English English
topic	TL Motor vehicles Aeronautics Astronautics TL Motor vehicles Aeronautics Astronautics
spellingShingle	TL Motor vehicles Aeronautics Astronautics TL Motor vehicles Aeronautics Astronautics Khaire Elarosi, Muwfik Faidi On the development computer, code for determinig the root of equation for transient flight analysis
description	This thesis presents the governing equation of flight motions which can be used to describe the flight behavior of any type flying vehicles consist of 12 equations described 12 state – space variables involving the aircraft position and aircraft aptitude with respect to the inertial coordinate system and also with respect to their axis body system had been used. These twelve equations are coupling each to others and in the forms highly non linear equation; the numerical approach is required for solving such system equation. The coefficient of system equation can be said as a result of the combination between aircraft’s mass and inertia, aircraft geometry properties and also their aircraft aerodynamics derivatives. The present work is focused in the development computer code which allows in manner of determining the root of equation of the 12 equations which described the flight behavior for particular airplane. Through determining the root of equation one will able to carry out a non linear transient analysis such as aircraft at landing approaches gust response and pilot initiated maneuvers.
format	Thesis
qualification_name	Master of Philosophy (M.Phil.)
qualification_level	Master's degree
author	Khaire Elarosi, Muwfik Faidi
author_facet	Khaire Elarosi, Muwfik Faidi
author_sort	Khaire Elarosi, Muwfik Faidi
title	On the development computer, code for determinig the root of equation for transient flight analysis
title_short	On the development computer, code for determinig the root of equation for transient flight analysis
title_full	On the development computer, code for determinig the root of equation for transient flight analysis
title_fullStr	On the development computer, code for determinig the root of equation for transient flight analysis
title_full_unstemmed	On the development computer, code for determinig the root of equation for transient flight analysis
title_sort	on the development computer, code for determinig the root of equation for transient flight analysis
granting_institution	Universiti Tun Hussein Malaysia
granting_department	Fakulti Kejuruteraan Mekanikal dan Pembuatan
publishDate	2013
url	http://eprints.uthm.edu.my/1991/1/24p%20MUWFIK%20FAIDI%20KHAIRE%20ELAROSI.pdf http://eprints.uthm.edu.my/1991/2/MUWFIK%20FAIDI%20KHAIRE%20ELAROSI%20COPYRIGHT%20DECLARATION.pdf http://eprints.uthm.edu.my/1991/3/MUWFIK%20FAIDI%20KHAIRE%20ELAROSI%20WATERMARK.pdf
_version_	1747830894621622272

On the development computer, code for determinig the root of equation for transient flight analysis

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