On the development of computer code for aircraft flight dynamics analysis
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...
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| Format: | Thesis |
| Published: |
2014
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| Subjects: | |
| Online Access: | http://eprints.uthm.edu.my/5853/ http://eprints.uthm.edu.my/5853/4/ABDELHADI_MOSBAH_MOKHTAR_EMHEMAD_X.pdf |
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| Summary: | 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. |
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