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: | |
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| Format: | Thesis |
| Language: | English English |
| Published: |
2014
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| Subjects: | |
| 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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| Summary: | 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. |
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