Methodology of creation of the nonlinear control system to the basis of optimization of the trajectory contour of the aircraft

The article discusses the procedure for the synthesis of non-linear aircraft control systems at the level of a trajectory based on the method of inverse problems of dynamics (UED) and the possibility of combining it with a solution of direct problems of dynamics on a flight level. A block diagram of an aircraft control loop. In comparison to results of work [1] it is shown that application of concepts of the return problems of dynamics in combination with the organization of control contours for the principle of symmetry (the maintenance of the return and direct problem of dynamics is reversible rather synthesizable managements according to power and moment characteristics) allows to solve evidence-based an important technical problem of creation of nonlinear aircraft SAU.