GUIDANCE SYSTEM OF GUIDED MISSILE Russian patent published in 2003 - IPC

FIELD: armament, in particular, artillery guided missiles with a laser homing head. SUBSTANCE: the missile guidance system has a control actuator, inertia gyroscope with a sensor, clock mechanism and a homing head, whose "Lock-on" output is connected to the second input of the AND gate, whose output is connected to the "Compensation" input of the homing head and the first input of the OR gate, whose second input is connected to the "-Y' output of the homing head, and the output is connected to the input of the first power amplifier. The "Z" and "-Z" outputs of the homing head 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 inertia gyroscope feed input are connected to the power source of the carry-on equipment. The input of the inertia gyroscope uncaging mechanism is connected to the output of the clock mechanism, use is made of a phase-shift device, whose first input is connected to the output of the inertia gyroscope, its second input is connected to the output of the clock mechanism. The output of the phase-shift device is connected to the first input of the AND gate, the "+Y" output of the homing head is connected to the input of the second power amplifier. The inertia gyroscope uses an optronic sensor, and the phase-shift device has the first, second and third flip-flops, nullification unit, the first, second, third and fourth pulse counters, reference frequency generator and a permanent storage. EFFECT: enhanced accuracy of guidance. 2 cl, 2 dwg