A. A. Piskovatskiy

In article questions of synthesis of structure and laws of management of the missile, optimum on various modes of flight are considered. A lack of existing control systems of rockets their low adaptability isnfted at switching on various modes of application, and also to changes of parameters of flight. Also a lack of existing control systems of rockets that they are developed under the single-wire scheme in which the contour of angular stabilization, is an internal contour of a contour of an overload. It means that for a control system basis the simplified model of dynamics of flight of the rocket assuming definition of linear accelerations as sizes proportional is accepted to corresponding angular speeds. In work for a synthesis basis the linearized mathematical model of dynamics forward and a missile rotary motion in which changes of aerodynamic testimonials from of change of parameters of flight are considered is taken. The equations of dynamics forward and a rotary motion are closed through the equations of communication of linear and angular speeds. It allows to define block diagrams of the decision of a direct problem of dynamics in the form of the closed contours for definition of reaction of management on height, a direction, a list and longitudinal speed of the missile. In work for synthesis of laws of management of the missile positions of the concept of return problems of dynamics that allows in a ready kind to receive laws of management with the set dynamic properties are used. Thus entrance signals in the received control paths of height and a direction (decisitons of a return problem of dynamics) can be as the set overloads, and angular speeds (acceleration), and as the given signals together, in the combinations which are not contradicting conditions of their interrelation in a working range of work of a control system. It allows to speak about possibility of invariancy of management for height and direction channels. If entry conditions and a problem it is defined correctly being set by criterion of an optimality for the given mode, it is possible to define the unique optimum decision of a deviation of wheels of the rocket for each mode. In work, as an example, synthesis of laws of management of the rocket with optimization by criterion of a minimum of energy of a rotary motion of the missile is resulted. The decision is presented in an analytical kind and in the form of the management block diagram. Thus, the offered method of synthesis of laws of management allows to develop more adaptive linear control system aircraft and to define optimum decisions of management for various modes of application of the maneuverable rocket. Thus synthesized laws of management of the missile on initial conditions provide adaptability of factors of management at change of aerometric corners and angular position of the missile