MISSILE REMOTE CONTROL METHOD Russian patent published in 2014 - IPC F41G7/00 

FIELD: physics; control.

SUBSTANCE: invention relates to rocket engineering and can be used in guidance systems of guided missiles. The method includes measuring angular coordinates and ranges of the target and the missile; generating programmed range and programmed missile velocity as a function of the flight time of the missile; generating the reference guidance trajectory of the missile; generating a signal for the linear mismatch between the missile and the reference guidance trajectory; generating the missile control instruction in proportion to the said mismatch signal; generating a dynamic error signal for guiding the missile relative to the said reference trajectory; correcting the missile control instruction with the value of the dynamic error signal for guiding the missile on the reference trajectory. The novelty is that the programmed range and programmed velocity of the missile are generated at the current flight time of the missile using a model of the missile and based on the generated missile control instructions; generating the current signal for the mismatch between the measured missile range and the programmed missile range; correcting, based on the said mismatch, the programmed range and programmed velocity of the missile; and generation of the signal for the linear mismatch between the missile and the reference trajectory and generation of the dynamic error signal for guiding the missile relative to the reference trajectory are carried out based on the corrected programmed range and programmed velocity of the missile; further, using the model of the missile and based on the corrected programmed velocity of the missile, generating the current programmed overload of the missile and the current programmed frequency of natural vibrations of the missile and then successively converting the current missile control instruction in proportion to a transfer constant, which varies inversely proportional to the current value of the current programmed overload of the missile, and with a band-rejection filter, the mid-frequency of the rejection band of which is set equal to the current value of the programmed frequency of the natural vibrations of the missile.

EFFECT: high accuracy and noise-immunity of remote control of a missile.

4 cl, 2 dwg