GUIDED MISSILE GUIDANCE SYSTEM Russian patent published in 2002 - IPC

FIELD: armament, in particular, artillery guided missiles with a laser homing head. SUBSTANCE: the guided missile guidance system has a homing head, inertial gyroscope, control actuator, the first, second, third and fourth pulse stretchers, inverter, the first and second AND gates, the first and second OR gates, the first, second, third and fourth power amplifiers, and the first, second third and fourth control windings. The "Lock-on" output of the homing head is connected to the first input of the first AND gate, and via the inverter - to the first input of the second AND gate, whose second inputs are connected to the second and third outputs of the inertial gyroscope respectively, the output of the first AND gate is connected to the "Compensation" input of the homing head and to the third input of the first OR gate, whose output is connected to the input of the first power amplifier. The output of the second AND gate is connected to the second input of the second OR gate, whose output is connected to the input of the second power amplifier, the "-y", "+y", "+z", "-z" outputs of the homing head are connected respectively to the inputs of the first, second, third and fourth pulse stretchers, the outputs of the first and second pulse stretchers are connected respectively to the first input of the first and second OR gates. The outputs of the third and fourth pulse stretchers are connected respectively to the inputs of the third and fourth power amplifiers, the outputs of the first, second, third and fourth power amplifiers are connected respectively to the first inputs of the first, second, third and fourth control windings, whose second inputs are connected to the fourth output of the inertial gyroscope and the power source of the on-board equipment. Introduced are the firing mode selector unit and the third AND gate, the output of the selector unit is connected to the third inputs of the first and second AND gates and the second input of the third AND gate, whose first input is connected to the first output of the inertial gyroscope, and its output is connected to the second input of the first OR gate. EFFECT: enhanced accuracy of guidance. 1 dwg