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Automatic Flight Control System Design for a Jet Aircraft
Krasňanský, Milan ; Vlk, Jan (oponent) ; Chudý, Peter (vedoucí práce)
This bachelor's thesis deals with the modelling of flight characteristics of a jet airplane and subsequent design and implementation of an automatic flight control system. Its goal was to implement a model of a jet airplane based on publicly available aerodynamic data of F-16 aircraft and use this model as a platform for the design and implementation of an automatic flight control system based on the non-linear dynamic inversion with a focus on controlling the pitch angle of an airplane by setting a desired value of the angle of attack. Conducted tests of the created system proved the ability of the control system to reach and maintain the desired angle of attack.
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Graphical Interface for Flight Displays
Tabášek, Michal ; Vlk, Jan (oponent) ; Chudý, Peter (vedoucí práce)
This bachelor thesis deals with the flight data visualization. It contains a description of the airplane mathematics and physics model, instruments used for flight data visualization and process of creating a primary flight display for flight simulator. The display is created using C++ language and OpenGL graphics library.
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Graphical Interface for Flight Displays
Tabášek, Michal ; Vlk, Jan (oponent) ; Chudý, Peter (vedoucí práce)
This bachelor thesis deals with the flight data visualization. It contains a description of the airplane mathematics and physics model, instruments used for flight data visualization and process of creating a primary flight display for flight simulator. The display is created using C++ language and OpenGL graphics library.
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Automatic Flight Control System Design for a Jet Aircraft
Krasňanský, Milan ; Vlk, Jan (oponent) ; Chudý, Peter (vedoucí práce)
This bachelor's thesis deals with the modelling of flight characteristics of a jet airplane and subsequent design and implementation of an automatic flight control system. Its goal was to implement a model of a jet airplane based on publicly available aerodynamic data of F-16 aircraft and use this model as a platform for the design and implementation of an automatic flight control system based on the non-linear dynamic inversion with a focus on controlling the pitch angle of an airplane by setting a desired value of the angle of attack. Conducted tests of the created system proved the ability of the control system to reach and maintain the desired angle of attack.
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