METHOD FOR CORRECTION OF COMMAND SIGNAL ON SPIN-STABILIZED MISSILE AND MISSILE GUIDANCE SYSTEM Russian patent published in 2006 - IPC F42B15/01 

FIELD: armament, in particular, rocketry, spin-stabilized missiles, applicable in missile complexes, for example, in antitank ones with carriers on the ground, in which, for example, the beam guidance systems are used.

SUBSTANCE: in the claimed method for correction of the command signal on a spin-stabilized missile the electromagnetic radiation from the control center is transformed to the command signal components in heading and pitching, and a command signal is produced from the corrected command signal component in pitching and non-corrected component in heading. A roll signal is formed on the missile in the form of electric pulses, whose lengths are determined by angular intervals equal in values that are formed at missile roll rotation, the lengths of the electric pulses are transformed to binary numbers, and the value of variation of the flight speed is computed as a ratio of two numbers, the first of which corresponds to the pulse length taken as the beginning of the count, and the second one - as the length of each subsequent pulse, beginning from the pulse taken as the beginning of the count, and the value of this ratio is used for correction of the command signal component in pitching.

EFFECT: enhanced efficiency of correction of the command signal on the missile, thus reducing the probability of the missile fall in flight at a low altitude.

3 cl, 2 dwg, 1 ex