METHOD AND SYSTEM FOR GUIDANCE OF SPIN-STABILIZED MISSILE Russian patent published in 2006 - IPC F41G7/24 F42B15/01 

FIELD: development of missile guidance systems, applicable in anti-tank and anti-aircraft guided missile complexes.

SUBSTANCE: the method consists in formation of radiation, formation of the error signal between the missile and the beam axis, summation of the error signal and the signal proportional to the difference of the error signal and the error signal shifted by the response time, modulation of the summary signal by a signal periodic in the bank angle and transduction of the obtained signal to deflection of the missile control surfaces. At an appearance or disappearance of radiation during a time equal to the response time read out from the instant of appearance or disappearance of radiation only the error signal is modulated, and on expiration of this time the sum of the error signal and the signal proportional to the difference of the error signal and the error signal shifted by the response time is modulated. In the missile guidance system realizing this method, as compared with the known guidance system, including the conditioner of the error signal between the missile and the beam axis, consisting of series-connected source of modulated radiation, radiation receiver and error signal generation unit, link with a controlled response time, whose first input is connected to the output of the error signal generation unit, summing amplifier, whose first input is connected to the output of the link with a controlled response time, and the second input is connected to the output of the error signal generation unit, modulator whose first input is connected to the output of the summing amplifier, and the second input is connected to the output of the roll-angle pick-off signal, control actuator, whose input is connected to the modulator output, period meter, whose input is connected to the output of the pick-off of periodic in roll-angle signal, and the output is connected to the second input of the response time link with reference to which the control of the response time is effected, a threshold device is introduced, whose input is connected to the output of the radiation receiver, the first logic device between the output of the link with a controlled response time and the first input of the summing amplifier, the second logic device between the output of the error signal generation unit and the third input of the summing amplifier, the second inputs of the first and second logic devices are connected to the output of the threshold device, and their third inputs are connected to the output of the period meter.

EFFECT: enhanced accuracy of fire by beam-guided spin-stabilized missiles in the conditions of appearance and disappearance of radiation.

2 cl, 5 dwg