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Light Airplane Flight Parameters Estimation
Dittrich, Petr ; Pačes, Pavel (oponent) ; Fiľakovský, Karol (oponent) ; Chudý, Peter (vedoucí práce)
This thesis is focused on a light airplane flight parameter estimation, specially aimed at the Evektor SportStar RTC. For the purposes of flight parameter estimation the Equation Error Method, Output Error Method and Recursive Least-Squares methods were used. This thesis is focused on the investigation of the characteristics of the flight parameters of longitudinal motion and the verification, that this estimated parameters corresponds to the measured data and thus create a prerecquisite for a sufficiently accurate airplane model. The estimated flight parameters are compared to the a-priori values obtained using the Tornado, AVL and Datcom softwares. The differences between the a-priori values and estimated flight parameters are also compared to the correction factors published for the subsonic flight regime of an F-18 Hornet model.
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Development of Autopilot and Flight Director Modes inside a Simulink Environment
Novák, Jiří ; Matoušek, Radomil (oponent) ; Nechvátal, Luděk (vedoucí práce)
This thesis is focused on the development of a simulation environment in Matlab/Simulink for a selected aircraft. The position and orientation of the aircraft moving in the air is described by six-degrees-of-freedom equations of motion. The system of translational, rotational and kinematic equations forms a set of nine nonlinear first order differential equations. These equations can be linearized around an equilibrium point referred to as a steady--state flight condition. The simulation environment contains a developed flight control system based on PID controllers. A basic autopilot is capable of holding pitch attitude and roll angle. Flight director modes including altitude hold, heading select, vertical speed mode, flight level change mode, altitude capture mode and navigational mode based on a nonlinear guidance law are presented. A Pareto optimality based optimization tuning process is developed to optimally tune the regulators. The simulation is graphically represented in FlightGear open source software.
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Development of Autopilot and Flight Director Modes inside a Simulink Environment
Novák, Jiří ; Matoušek, Radomil (oponent) ; Nechvátal, Luděk (vedoucí práce)
This thesis is focused on the development of a simulation environment in Matlab/Simulink for a selected aircraft. The position and orientation of the aircraft moving in the air is described by six-degrees-of-freedom equations of motion. The system of translational, rotational and kinematic equations forms a set of nine nonlinear first order differential equations. These equations can be linearized around an equilibrium point referred to as a steady--state flight condition. The simulation environment contains a developed flight control system based on PID controllers. A basic autopilot is capable of holding pitch attitude and roll angle. Flight director modes including altitude hold, heading select, vertical speed mode, flight level change mode, altitude capture mode and navigational mode based on a nonlinear guidance law are presented. A Pareto optimality based optimization tuning process is developed to optimally tune the regulators. The simulation is graphically represented in FlightGear open source software.
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Light Airplane Flight Parameters Estimation
Dittrich, Petr ; Pačes, Pavel (oponent) ; Fiľakovský, Karol (oponent) ; Chudý, Peter (vedoucí práce)
This thesis is focused on a light airplane flight parameter estimation, specially aimed at the Evektor SportStar RTC. For the purposes of flight parameter estimation the Equation Error Method, Output Error Method and Recursive Least-Squares methods were used. This thesis is focused on the investigation of the characteristics of the flight parameters of longitudinal motion and the verification, that this estimated parameters corresponds to the measured data and thus create a prerecquisite for a sufficiently accurate airplane model. The estimated flight parameters are compared to the a-priori values obtained using the Tornado, AVL and Datcom softwares. The differences between the a-priori values and estimated flight parameters are also compared to the correction factors published for the subsonic flight regime of an F-18 Hornet model.
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