METHOD OF PROPORTIONAL CONTROL OF ROCKET AIR-DYNAMIC CONTROL ACTUATOR AND DEVICE FOR ITS IMPLEMENTATION Russian patent published in 2017 - IPC F42B15/01 

FIELD: aviation.

SUBSTANCE: in control loop of air-dynamic control actuator (ADCA) with pulse width modulation (PWM), the error signal is passed through a variable-factor unit whose control input, after sequentially extracting the absolute value and a constant component, is supplied with a linearized signal proportional to the speed of control actuator movement. The value of variable-factor unit coefficient is varied depending on linearized signal of the wheels movement rate from the condition of ensuring constant values of the stability reserves of the actuator control loop in phase and amplitude on the entire rocket flight path. The generation of forced oscillations in actuator control loop is performed by an internal controlled oscillator formed by introducing a positive feedback of the relay element, due to which the rectangular pulse signal at the output of the relay element is converted into a triangular signal, and their difference signal is summed with the output signal of the variable-factor unit.

EFFECT: increase of the dynamic characteristics of the air-dynamic control actuator when implementing proportional control in the mode of pulse width modulation in a wide range of rocket flight speed changes due to the correction of the open actuator control loop transmission coefficient, depending on wheels movement rate, while maintaining constant reserves in the control loop in phase and amplitude over the entire range of rocket flight speed changes.

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