METHOD FOR CONTROL OF MISSILE CONTROL ACTUATOR ELECTRO-PNEUMATIC DRIVE AND DEVICE FOR ITS REALIZATION Russian patent published in 2003 - IPC

FIELD: missiles. SUBSTANCE: the method for control of missile control actuator electro-pneumatic drive is based on measurement of control actuator angle (δ) comparison of the measured value with the preset one and formation of a control signal supplied to the drive by passing the error signal of the control actuator control angle (Δδ) via an amplifier and the first relay element, for formation of the control signal to the drive the control error signal from the amplifier output is passed via the series-connected amplifier - limiter and the module separation unit and applied to the first input of the second relay element, whose second input receives a triangle-shaped periodic signal of a fixed frequency from the output of the signal generator, the output signal of the second relay element is applied to the input of the triangle-shaped periodic signal generator of controlled signal, whose signal frequency is changed in accordance with the first mathematic dependence. The output signal of the controlled frequency generator is applied to the second input of the first relay element. The initial frequency of the controlled frequency signal generator is set proceeding from the condition of provision of the allowable preset amplitude of vibrations of the control actuators at action of alternating hinge load on the drive, and the signal amplitude - from the condition determined by the second mathematic dependence. The frequency of the fixed-frequency signal generator is set essentially higher than the initial frequency of the controlled - frequency signal generator proceeding from the condition of provision of the minimum allowable amplitude of ripples of the signal of the controlled-frequency generator, and the signal amplitude equal to the selected one from the condition determined by the first mathematic dependence. The level of limitation of the amplifier-limiter is selected from provision of relation determined by the third mathematic dependence. EFFECT: reduced complitude of vibrations of the control actuators of the missile control actuator electro-pneumatic drive at action of alternating hinge load on control actuators, reduced missile drag without any increase of the mass and dimensions of the power unit, enhanced accuracy of follow-up of control signals and accuracy of retaining of the zero position of the control actuators at an absence of control signals without any increase of the mass and dimensions of the control equipment. 3 cl, 6 dwg