METHOD FOR CONTROL OF MISSILE AND MISSILE GUIDANCE SYSTEM FOR ITS REALIZATION Russian patent published in 2004 - IPC

FIELD: armament, in particular rocketry, applicable in development of missile complexes, for example, with carriers on the ground, in which beam teleguidance systems are used.

SUBSTANCE: electromagnetic radiation from the control point is transformed to electric signals of the missile heading and pitch co-ordinates, missile heading and pitch control commands are formed, the heading control command is formed from the heading co-ordinate electric signal, at which the first additional command proportional to the value of missile sagging is program-produced, the second additional command is produced integrating the electric signal of the pitch co-ordinate, and then the first and second additional commands are the pitch co-ordinate electric signal are summed up, and the missile pitch control command is formed from the summary value. Described is the missile guidance system based on this method, it has an adder, compensation unit, integrator and an integrator switching unit connected to the integrator control input, the integrator signal output is connected to the output of the pitch co-ordinate discrimination unit, connected to the first input of the adder, whose second input is connected to the integrator output, and the third one - to the compensation units, the adder output is connected to the second input of the autopilot.

EFFECT: enhanced accuracy of guidance due to correction of the value of the control command in the pitch channel on board the missile.

1 cl, 1 dwg