MISSILE GUIDANCE SYSTEM Russian patent published in 1999 - IPC

FIELD: armament, in particular, artillery guided missile with a laser homing head. SUBSTANCE: missile guidance system comprises a control actuator, inertial- reference gyroscope and a homing head, whose "Lock-on" output is connected to the first input of the first AND gate, and via an inverter, to the first input of second AND gate, whose second are connected respectively to the second and third outputs of the inertial-reference gyroscope; the output of the first AND gate is connected to the homing head "Compensation" input and to the third input of the first OR gate, whose second input is connected to the first output of the inertial-reference gyroscope, and the output - 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; the output of the second OR gate is connected to the input of the second power amplifier; 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 are connected to the fourth input of the inertial-reference gyroscope and to the power source of the missile-borne equipment. In addition, the system comprises the first, second, third and fourth pulse stretchers; 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, and the outputs of the first and second pulse stretchers are connected to the first inputs of the first and second OR gates respectively, the outputs of the third and fourth pulse stretchers are connected to the inputs of the third and fourth power amplifiers respectively, the duration of pulses shaped by the stretchers is strictly associated with the durations of guidance pulses shaped by the homing head. EFFECT: enhanced accuracy of guidance system. 3 dwg