AIRCRAFT PITCH ANGLE CONTROL SYSTEM Russian patent published in 2012 - IPC G05D1/08 B64C13/18 

FIELD: physics.

SUBSTANCE: invention relates to aircraft on-board automatic control systems. The aircraft pitch angle control system has an angular velocity sensor, a pitch signal selector, an angular position sensor, a comparator unit, an integrator, amplifier units K_ϑ, K_ω and K_∫, an adder, a steering machine amplifier, a steering machine with feedback and an altitude control. The first input of the comparator unit is connected to the output of the angular position sensor, the second input of the comparator unit is connected to the output of the pitch signal selector. The output of the angular position sensor is connected through the amplifier unit K_ϑ to the first input of the adder. The second input of the adder is connected through the amplifier unit K_ω to the output of the angular velocity sensor. The third input of the adder is connected through the amplifier unit K_∫ and the integrator to the output of the comparator unit. The output of the adder is connected through the steering machine amplifier to the input of the steering machine, the output of the steering machine is connected to the input of the altitude control and through the feedback to the fourth input of the adder.

EFFECT: reduced overcontrol in transient processes when processing a given pitch angle command and the resultant reduction in power consumption of the drive of the control device.

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