GUIDED MISSILE GUIDANCE SYSTEM AND GYRO INSTRUMENT Russian patent published in 2003 - IPC

FIELD: armament, in particular, artillery guided missiles with laser homing head. SUBSTANCE: the guided missile guidance system has a control actuator, inertial gyroscope with a pick-off and a homing head, whose "Compensation" input is connected to the output of the ABD gate, whose second input is connected to the "Lock-on" output of the homing head, 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", "+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 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 unit of the on-board equipment. The output of the inertial gyroscope is connected to the first input of the AND gate, inserted are the pulse length selector, initial setting circuit, the first and second flip-flops, the S-inputs of these flip- flops are connected to the output of the initial setting circuit, whose input is connected to the power unit of the on-board equipment, the output of the inertial gyroscope is connected to the input of the pulse length selector and to the C-input of the second flip-flop, whose output is connected to the third input of the AND gate. The R-input of the first flip-flop is connected to the output of the pulse length selector, and its output is connected to the D-input of the second flip-flop. The pick-up of the inertial gyroscope is made optron, the output of the second pulse stretcher is connected to the input of the second power amplifier. The gyroscopic instrument has a body, rotor in a suspension and a photooptic attitude sensor consisting of a photodiode and a light-emitting diode, has a blind fastened on the outer frame of the gimbal suspension providing for interruption of the luminous flux of the light-emitting diode. The angular dimension of blind Qθ_bl is selected smaller than the angle of hardover θ_ho by the value of the missile overhoot angle at a controlled flight with reserve factor KK_res. EFFECT: enhanced accuracy of guidance. 3 cl, 3 dwg