METHOD OF GUIDANCE OF REMOTE-CONTROLLED ROCKET AND GUIDANCE SYSTEM FOR ITS REALIZATION Russian patent published in 2002 - IPC

FIELD: rocket engineering, weapon complexes of remote-controlled rockets. SUBSTANCE: method of guidance of remote-controlled rocket includes formation of wide and narrow control fields, launch of rocket at angle to target sight line, rocket boost with the aid of engine in the course of time interval t_b, rocket guidance in wide control field in the course of time interval t_b with formation of control command proportional to angular mismatch between flame of rocket engine and target sight line, rocket guidance in narrow control field with formation of control command proportional to angular mismatch between radiation source on rocket and target sight line. With rocket guidance in wide control field reference signal is formed, present angular velocity of rocket relative to target sight line is measured, signal proportional to angular position of longitudinal axis of plum of flame of rocket engine with respect to its sight line is formed on its basis, generated signal is compared with reference signal. If signal proportional to angular position of longitudinal axis of plume of flame of rocket engine relative to its sight line is less than reference one then correction control command proportional to present angular velocity of rocket with reference to target sight line is formed and rocket is guided with allowance for this correction command. Guidance system of remote-controlled rocket includes target direction finder and rocket control circuit each pitching and course channel of which has rocket direction finder with narrow control field, rocket direction finder with wide control field, controlled switch which second input is connected to first output and which information input is connected to second output of rocket direction finder with narrow control field and former of control command proportional to angular mismatch between rocket and target sight line which second input is connected to corresponding output of target direction finder connected in series. Circuit is inserted with former of reference signal proportional to angular position of longitudinal axis of plume of flame of rocket engine relative to its sight line which input is connected to second output of rocket direction finder with wide control field, with comparator which second input is connected to output of former of reference signal, with controlled key which input is connected to second output of rocket direction finder with wide control field and which information input is connected to output of comparator, with former of correction control command and with adder which second input is connected to output of former of control command proportional to angular mismatch between rocket and target sight line and which output is connected to input of transmitter of control commands. EFFECT: increased noise immunity of optical communication line CARRIER-ROCKET and efficiency of weapon complexes of remote-controlled rockets. 2 cl, 2 dwg