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The paper is devoted to the structural – parametrical design of the control systems for unmanned aerial vehicles. The structural – parametrical design of control systems was carried out with use of the separation theorem. The optimum law of control with use of Kalman filter and the optimum deterministic regulator was synthesized. The technique of simplification of obtained solution for the purpose of a possibility of its realization in the simple onboard computer is performed. Aforementioned synthesis procedure was applied for design of unmanned aerial vehicles autopilots with limited amount of the navigation sensors in presence of stochastic disturbances. The aerodynamic coefficients that compose the stat space matrices and used for synthesis are obtained via DATCOM software application

Structural-parametric synthesis of the flight control system with the previous design of unmanned aerial vehicle model