METHOD AND SYSTEM OF SPINNING MISSILE HOMING Russian patent published in 2010 - IPC F42B15/01 F41G7/24 

FIELD: weapons and ammunition.

SUBSTANCE: substance of proposed invention consists in the fact that additional control is used by angular deviation of missile axis at initial section of flight together with control by linear deviation and its derivative along the whole section of flight. In proposed method angular deviation of missile longitudinal axis is measured relative to position at the start, signal is generated, which is proportional to this deviation and is additionally summed from the moment of missile start to the moment of time t_c with summary control signal. Besides time moment t_c is established by dependence t_c=(0.5…0.7)T_m, where T_m - period of missile own oscillations. Homing system comprises serially connected shaper of signal of mismatch between missile and axis of beam, summing amplifier, modulator and steering drive, and also serially connected sensor of signal that is periodical by angle of list, metre of period and link with controlled delay time. System also comprises serially connected sensor of angular deviation of missile longitudinal axis and shaper of angular deviation signal, outlet of which is connected to the third inlet of summing amplifier.

EFFECT: increased accuracy of homing of missiles spinning by list angle at initial stage of flight.

2 cl, 5 dwg