CONTROLLED MISSILE STEERING DRIVE CONTROL METHOD Russian patent published in 2024 - IPC F42B15/01 F42B10/60 

FIELD: rocket science.

SUBSTANCE: invention can be used in rockets with a wide range of speeds and flight altitudes as a proportional control system of a steering drive with relay element linearization by natural harmonic oscillations. In the odd quarters of the oscillation period of the linearizing error signal before the relay element, determining the maximum error value and the time interval of the quarter of the period, calculating the average speed, the magnitude of the absolute value of the maximum error and the absolute value of the average speed are stored during even quarters of the period and reset at the end of the period. By changing the error signal transmitted to the relay element, two advancing switching of the relay element are performed during the passage of even quarters of the period.

EFFECT: improved dynamic characteristics of the steering drive in a wide range of variation of speeds and altitudes of flight due to the implementation of advance switching of the relay element, allowing to reduce the amplitude and increase the frequency of self-oscillations, while providing constant phase and amplitude margins in the control loop on the entire range of variation of speeds and altitudes of flight.

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