Aeroelastic vibrations control system of an unmanned aircraft

A control system that allows reducing the amplitude and time of aeroelastic oscillations of the wing of an unmanned aircraft by actively changing its shape is proposed. The shape change is achieved by the wing control surfaces. The control system contains a corrective link, which is synthesized by one of the known methods, in particular, logarithmic frequency characteristics. Semi-real-life modeling was carried out in applied mathematical and design software packages. Using the example of wing ailerons and a corrective link in the form of a PID controller, the effectiveness of the aeroelasticity control system was assessed. It is shown that by selecting the proportional and integral coefficients of the corrective link in the control system, it is possible to increase the critical flutter speed of the wing of an unmanned aircraft.