It is known from engineering practice that the actuators of the aircraft control surfaces have physical limits of thrust which are manifested in the nonlinear effects of actuator rate and the level saturation. In turn, the influence of nonlinearities causes a negative phase shift between the actual and control pilot signal, which negatively affects the stability of the aircraft. As a result, nonlinear oscillations of the aircraft's angular motion may arise, which endanger flight safety. To prevent fluctuations various methods have been developed, but there is no general approach to modeling. In this paper, the nonlinear correcting device synthesis methods is proposed. It is illustrated by the example of stabilizing the pitch angle in a piloted aircraft control system. The synthesis is implemented on the base of the optimization of system parameters and uses the Matlab/Simulink dynamic modeling software package. As a result of the study, the algorithm for the synthesis of a nonlinear correcting device is presented on the example of a remotely controlled UAV. The parameters of the pilot model, at which pilot-induced oscillations occur, are obtained. The properties of the optimal system are illustrated and evaluated using frequency response, pitch transients, and flight characteristics.