FIELD: aviation instrument engineering, in particular, information means of aiming and group pilotage of flight vehicles. SUBSTANCE: the guide cosines of the used transition matrices are calculated by the method of integration of differential adiabatic equations and inertial navigation, the values of motion parameters of the observed object are formed in the interval of observation by the combination method - continuous and discrete. Introduced are operations of combined processing of several sources of information about one and the same parameter for an additional improvement of the precision of its estimation. The complex system realizing the combination method has an on-board radar or/and an electronic-optical system, computer of the on-board radar or/and electronic-optical system, three units of matrix transducers, aerometric angle- of-attack and slip-angle sensors of the flight vehicle, transducer of true air speed of the flight vehicle, four algebraic adders, units of transducers of absolute velocities and linear accelerations of the flight vehicle, gyro- inertial navigation system, four units of filters of identical parameters, integrator matrix transducer, the first computer of the discrete values of the vectors of velocity and acceleration of the observed object, the second computer of the discrete values of the vector of acceleration of the observed object, complex integrator matric transducer. The mentioned units are interconnected in a proper way. EFFECT: enhanced speed of response and precision of forming of the flight vehicle and object observed from the board motion parameters in the stabilized coordinate system. 2 cl, 4 dwg
