METHOD OF COMBINED GUIDANCE OF SMALL-SIZED MISSILE WITH SEPARABLE PROPULSION SYSTEM AND GUIDANCE SYSTEM FOR ITS IMPLEMENTATION Russian patent published in 2015 - IPC F41G7/00 

FIELD: weapon and ammunition.

SUBSTANCE: method includes formation of an information field of control, start of the missile at an angle to the line of vising of the target. At the start the angular position of the line of vising of the target in the starting system of coordinates is transmitted to the missile. From the moment of separation of the missile the angular speeds of rotation of the longitudinal axis of the missile and linear accelerations by axes of the system of coordinates related to the missile are measured, the angles of roving, pitch and coordinate of the centre of mass of the missile are calculated. Before enabling the engine the gas-jet control of angular position of the missile is performed by the measured angular speeds of rotation of its longitudinal axis and the calculated angles of roving and pitch. After enabling of the engine the aerodynamic control of the missile is performed by deviations of the calculated coordinates of the centre of mass of the missile with reference to the programmed trajectory of the missile launch to the line of vising of the target.

EFFECT: improvement of noise stability of lines of vising of the target and missile, improvement of accuracy and decrease of near boundary of the hitting zone of the complex.

3 cl, 5 dwg