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On the development of computer code for aircraft flight dynamics analysis

Mokhtar Emhemad, Abdelhadi Mosbah (2014) On the development of computer code for aircraft flight dynamics analysis. Masters thesis, Universiti Tun Hussein Onn Malaysia.

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Abstract

The behaviour of the airplane is dependent on the forces and moment works on the airplane. The force and moments cames from aerodynamics forces, aircraft weight and engine thrust. These three source of forces are always changed depended on the aircraft flight aptitude, altitude and flight speed. As result the forces and moments works on the airplane may change at any instants time. The behaviour of the aircraft can be obtained by solving the governing equation of flight motion. This governing equation of flight motion is consist of 12 equation which couple each to others. Those 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. Through solving those 12 equations one can obtain the trajectory of the airplane as well as behavior of the airplane at transient time if the governing equation of flight motions are treated in its linearized form. Beside that by imposing some flight conditions, the governing equation of flight motions can also provide the solution trimming the aircraft at a given flight speed and flight altitude. This thesis presents a work on the development of computer code for Aircraft flight dynamics analysis. The computer code develop by use MATLAB computer programming, which for a given aircraft aerodynamics data, mass and the moment of inertia of the airplane combine with the given flight condition and also flight control setting one can estimate the aircraft trim condition and flight behaviour. The flight control setting can be done through operating the elevator, aileron, rudder, and engine thrust setting. The present work had carried out the flight dynamics analysis for a bussines jet aircraft model with and with out flight control setting. Through such kind computer code one can evaluate the flight dynamic behaviour in view how the aircraft speed in three dimensional direction change with respect to time, the flight altitude, the trim ability of the airplane at any given flight condition.

Item Type: Thesis (Masters)
Subjects: T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL500-778 Aeronautics. Aeronautical engineering
Depositing User: Normajihan Abd. Rahman
Date Deposited: 11 Dec 2014 06:56
Last Modified: 11 Dec 2014 06:56
URI: http://eprints.uthm.edu.my/id/eprint/5853
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