MISSILE GUIDANCE SYSTEM Russian patent published in 2003 - IPC

FIELD: armament, or particular, artillery guided missiles with a laser homing head. SUBSTANCE: the guidance system has a control actuator, inertial gyroscope and a homing head, whose "compensation" input is connected to the AND gate output, OR gate, whose first input is connected to the output of the first pulse stretcher, its second input is connected to the output of the AND gate, and the output - to the input of the first power amplifier. The "-y", "+y", "+z" and "-z" outputs of the homing head are connected to the inputs of the first, second, third and fourth pulse stretchers, the outputs of the third and fourth pulse stretchers are connected to the inputs of the third and fourth power amplifiers respectively, the outputs of the first, second, third and fourth power amplifiers are connected to the first inputs of the first, second, third and fourth control windings of the control actuator, whose second inputs and the input of the inertial gyroscope are connected to the power source of the missile-borne equipment. The output of the gyroscope is connected to the first inputs of the AND gate. Use is made of a flip-flop, whose D-input is connected to the "Lock ON" output of the homing head, the clock input - to the output of the inertial gyroscope, and its output is connected to the second input of the AND gate. A shutter is installed in the gyroscope, light-emitting diode and a photodiode with formation of an optron coupling between them. The shutter is made for rotation at the speed of the missile spinning. The photodiode is connected to the output of the gyroscope. EFFECT: enhanced accuracy of guidance. 1 dwg