| 摘要 |
FIELD: rocketry, applicable in armament complexes of telecontrolled missiles. SUBSTANCE: the method for missile control consists in missile launching at an angle to the target sighting line, missile acceleration with the aid of a booster engine, missile direction finding by the engine flame, formation of the program control command on the missile flight trajectory leg with an operating engine and transmission of the program control command to the missile for injection of it to the target sighting line. The novelty in the method is in the fact that the current output signal of the photodetector of the missile direction finder is measured, the obtained signal is compared with the reference signal, and if the photodetector output signal is less than the reference one, the program control command is formed to be equal to the maximum probable control command, and if the photodetector output signal exceeds the reference one, the program control command is corrected inversely proportionally to the value of the current output signal of the photodetector of the missile direction finder. EFFECT: prevented blanketing of the "carrier-missile" optical communication line by the flame smoke plume of the own acceleration engine of the missile due to the use, depending on the arisen real conditions of guidance, of correction of the program control commend at injection of the missile to the target sighting line. 2 dwg |
