MISSILE GUIDANCE SYSTEM Russian patent published in 2003 - IPC

FIELD: armament, in particular, artillery guided missiles with a laser homing head. SUBSTANCE: the missile guidance system has an inertial gyroscope, control actuator and a homing head, whose "Lock ON" output is connected to the first input of the first AND gate and the input of the NOT gate, whose output is connected to the first input of the second AND gate, whose second input is connected to the third output of the inertial gyroscope, whose second output is connected to the second input of the first AND gate. The output of the first AND gate is connected to the "Compensation" input of the homing head and to the second input of the first OR gate, whose third input is connected to the first output of the inertial gyroscope and to the input of the first power amplifier, whose output is connected to the first output of the electric igniter of the mechanism of deployment of control surfaces of the control actuator, whose second output is connected to the first pole of the power source. The output of the second AND gate is connected to the second input of the second OR gate, the -Y, +Y outputs of the homing head are connected to the first inputs of the first and second OR gates respectively, the outputs of the second, third, fourth and fifth power amplifiers are connected respectively to the first inputs of the first, second, third and fourth control windings of the control actuator. The second inputs of the control windings and the input of the inertial gyroscope are connected to the second pole of the power source, use is made of a delay circuit, RS-flip-flop, reset circuit, the third, fourth, fifth and sixth AND gates, the outputs of these gates are connected to the inputs of the second, third, fourth and fifth power amplifiers respectively, and the second inputs of these AND gates are connected to the output of the RS-flip-flop, whose R-input is connected to the output to the reset circuit, whose input is connected to the second pole of the power source, and the S-input-to the output of the delay circuit, whose input is connected to the first output of the inertial gyroscope. The first inputs of the third, fourth AND gates are connected to the outputs of the first and second OR gates respectively, and the first inputs of the fifth and sixth AND gates are connected to the +Z and Z outputs of the homing head respectively. EFFECT: enhanced accuracy of guidance. 1 dwg