Nowadays, researchers are developing technologies in the aviation industry related to the electrification of aircraft functional systems. The braking system has a direct impact on the safety, stability and functionality of the aircraft. Therefore, the motivation for replacing the hydraulic system is accompanied by the results of comprehensive studies of the architectures of electric braking systems, including the possibility of improving the quality of such systems through the introduction of effective control. The work is devoted to the methodology of analytical synthesis of the control algorithm for the electric braking system of the aircraft landing gear, as a multiconnected control object, based on the theory of embedded systems. The mathematical model contains a description of the electrical, mechanical and thermal processes of the system. The require ments for the quality of transients in terms of the angular velocity of the wheel and the temperature on the surface of the frictional disc are set in the form of restrictions on the settling time and overshoot and then transformed into the form of a reference model. The results of computer simulation of the dynamics of the initial and linearized systems, as well as a system with a synthesized regulator by the full vector of states are shown. The discussion about the robustness of the resulting solution are presented and the results of computer simulation of a system with a "simplified" regulator are shown.
