ROTATING SELF-GUIDED ROCKET Russian patent published in 2003 - IPC

FIELD: rocket engineering, portable shoulder-launched antiaircraft rockets, antiaircraft installations ensuring salvo firing against air targets. SUBSTANCE: rotating self-guided rocket includes motor, collapsible tail stabilizer with aerodynamic planes installed at angle with reference to incoming flow, equipment compartment housing single-channel power drive with aerodynamic and gas dynamic control elements and optical self-guidance head which incorporates corrected gyro with bearing and correction coils initially oriented at specified angle of bearing, former of commands for rocket turn at initial phase of flight and transmitter of rocket descent. Power drive comes in the form of servo drive, outputs of first and second adders are correspondingly connected to controlled input of phase detector and to input of servo drive through limiters of linearity zone. Former of commands for rocket turn comes in the form of first series branch comprising first and second controlled keys, third adder connected to second input of first adder and second series branch comprising amplitude detector, low frequency filter, comparator with preset threshold value and bistable element with specified initial state connected to bearing coil. Third controlled key which output is connected to second input of third adder and which controlling input is coupled to output of bistable element is connected to output of first key. Output of comparator is connected to controlling input of second controlled key, time relay which input is linked to transmitter of rocket descent is connected to controlling input of first controlled key. EFFECT: raised guidance precision, prolonged flight range, widened zones of launch and destruction. 1 cl, 3 dwg