Buffering device used for controlling movement speed of actuator cylinder

Abstract

The invention discloses a buffering device for controlling the movement speed of an actuator cylinder. The reliability of a locking device mechanism can be improved. The buffering device is achieved through the following technical scheme that an upper locking cavity is communicated with a damping pipe, and an intercepting ring groove is formed in the circumference of a sliding section of the damping pipe; when a piston rod extends downwards, hydraulic oil enters a blind hole cavity of the piston rod along the damping pipe, after the blind hole cavity is filled with the hydraulic oil, the hydraulic oil slowly flows upwards into the upper locking cavity along the intercepting ring groove in the damping pipe, the hydraulic pressure of the upper locking cavity is slowly increased, and the piston rod is pushed to move under the action of the hydraulic pressure; when the piston rod retracts, pressure of the unlocking cavity extrudes the piston rod, the piston rod extrudes the hydraulic oil in the upper locking cavity, the pressure of the upper locking cavity is increased, the hydraulic oil slowly flows into the blind hole cavity of the piston rod from the upper locking cavity along an intercepting annular groove of the damping pipe, the hydraulic oil in the unlocking cavity is reduced, and the piston rod slowly slides along the damping pipe; and liquid flow generates damping force through a gap between the inner wall of a blind hole and the damping pipe, the damping force controls the movement speed of the piston rod, and buffering of the actuator cylinder is achieved.

Description

technical field

[0001] The invention relates to a buffer device applied to control the movement speed of an unlocking actuator for a cabin door uplock. Background technique

[0002] Modern aircraft landing gear retraction systems generally use hydraulic pressure as the power source for normal retraction, and hydraulic pressure, air-conditioning or electricity as backup emergency power sources. Whether the landing gear retractable system can work normally directly affects the safety of the aircraft and passengers. Commonly used typical hydraulic-powered landing gear retraction system is composed of actuator, selection valve, retraction lock, release lock, sequence valve, pipeline and some hydraulic accessories. These accessories can ensure the safety of landing gear and hatch are connected to each other by sequential movement. Since the sequence valve is closed, the pressure oil cannot flow into the hatch actuator at this time, so the hatch cannot be closed. Most of the ac...

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