Aircraft actuating system with mechanical aligning function

Abstract

Belonging to the technical field of aircraft actuating system, the invention discloses an aircraft actuating system with mechanical aligning function. The system comprises an actuator controller (1), an actuator (2) with a mechanical aligning mechanism, a mechanical aligning rod (3) and a support (4). The actuator is mounted on a vertical tail back beam, one end of the mechanical aligning rod (3) is connected to the actuator, and the other end is connected to the support (4), and the support (4) is mounted on a rudder. Under a telex mode, the actuator controller (1) receives instruction from a flight control computer, converts the instruction into an output instruction and sends it to the actuator, the actuator responds to the instruction of the actuator controller (1) and makes movement to drive the rudder to deflect, at the moment a mechanical aligning mechanism on the actuator is in a suspension state, and does not respond to the instruction of the actuator. After conversion from a telex control mode to a mechanical aligning mode, the mechanical aligning mechanism on the actuator starts to work, through the feedback of the mechanical aligning rod to the rudder position, the rudder is driven to return to a neutral position.

Description

technical field [0001] The invention belongs to the technical field of aircraft actuation systems, and in particular relates to an aircraft actuation system with a mechanical centering function. Background technique [0002] When the aircraft is flying in any normal trim position, the pitch, roll, and yaw should all show true centering, especially after the control system corresponding to a certain rudder surface fails. In order to minimize the impact of the system failure, generally Both require the rudder surface to be centered. The realization of the centering of the rudder surface is closely related to the functional configuration of the aircraft actuation system. In the prior art, the general centering of the rudder surface is realized by the fly-by-wire mechanism. However, after the fly-by-wire control fails, it will affect the mechanical centering. Contents of the invention [0003] The present invention proposes an aircraft actuation system with a mechanical cent...

AI Technical Summary

Problems solved by technology

In the prior art, the general centering of the rudder surface is realized by the fly-by-wire mechanism. However, after the fly-by-wire control fails, it will affect the mechanical centering

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