Initial experimental procedures for modeling and identification of a fixed wing aerial vehicle

Modeling and identification of an aerial vehicle will allow engineers to design and implement guidance and control systems using the mathematical model acquired on flight. Using the mathematical model, several improvements and benefits shall be obtained, such as designing control subsystem using Modern Control Theory; the expected results at the workbench test will correspond more accurately to the real flight data. The model described here is a nonlinear model for fixed wing. This model uses several geometric, inertial and aerodynamic parameters. The procedures used to determine these parameters will be presented along the discourse of this article. To determine these aerodynamic parameters, it is frequently necessary to acquire flight data using embedded electronic systems on the aerial vehicle. Therefore, accuracy is key when acquiring reliable data from these sensors used where several lab and ground tests were performed.