Flight Tests for Aircraft in Simulink-FlightGear Environments and Comparison of Aerodynamic Effects on Stability/Frame Axes

A multi-disciplinary work process is required for aircraft design and production processes. Therefore, the collaboration of different disciplines in the design process of the aircraft is critical for the management of time and financial resources. Especially, flight simulations provide very serious facilities for performance tests and optimization of flight parameters, depending on the design requirements of aircraft, before the production phase. Within the scope of this study, orientation outputs were obtained from the mathematical model created in the Matlab/Simulink environment depending on the flight dynamics of a civil aircraft (Research Civil Aircraft Model). These outputs were used as input parameters for FlightGear flight simulator and simulation tests were carried out. FlightGear simulator was chosen for easier interpretation and visualization of flight data obtained in the Simulink environment. In addition, the joystick control orientation signals were transferred to the MATLAB environment in order to use the model input reference parameters in real time. Aerodynamic and structural parameters, engine and actuator dynamics have been added to the nonlinear mathematical model of the aircraft. The aerodynamic forces obtained as a result of this modeling were compared in aircraft stability and fuselage axis. In addition, aerodynamic moments occurring at the center of gravity and aerodynamics were also compared. As a result of these comparisons, the relationships between stability and body axes, aerodynamics and centers of gravity were examined. Depending on the design limits of the aircraft and international aviation standards, control surfaces and thrust limits are represented in the actuator dynamics.