Optimization of processes of management of the spatial movement of the aircraft on the basis of the equations of nonlinear dynamics

The article considers the technique of the synthesis of non-linear aircraft control systems by flight optimization using inverse dynamics problems. To synthetize control algorithms a non-linear model of aircraft flight and trajectory movement is used. The authors define method stages of flight level synthesis which include: selection of aircraft reference movements in accordance with three degrees of freedom, structuring the control algorithms and their parameters, defining the proximity of current and reference movements by means of a quadratic functional and further extremum-minimum movement organization by the gradient method. Through the optimized parameters of flight level the direct dynamics problem of trajectory level control of the aircraft spatial movement is solved. The basis for calculating the aircraft trajectory parameters is a non-linear model of the trajectory movement for which flight level output parameters serve as input data. The trajectory level output parameters are defined by numerical integration of input signals allowing for aircraft dynamic blow coefficients. The structure diagram of aircraft spatial movement control organization is developed. The flight contour functioning is researched by numerical modelling with MathCad and Paskal programs. Reference parameters were determined by Paskal simulation modelling according to the reaction of a non-linear aircraft model to the “bounces” of aerodynamical flight controls. It is shown that the spatial control problem is optimal in terms of input control realization. Besides, in comparison with [9] it is possible to state that due to energy reversibility of rotational and progressive movements only the content of direct and inversed problems of dynamics changes.