Aircraft landing gear frame stabilization buffer device and control method thereof

Abstract

The invention discloses an aircraft landing gear vehicle frame stabilizing buffer device and control method thereof. The aircraft landing gear vehicle frame stabilizing buffer device comprises an actuator cylinder assembly and a hydraulic control valve assembly, wherein the actuator cylinder assembly connects a landing gear buffer supporting column with a vehicle frame, and a piston rod of the actuator cylinder assembly is sleeved with an outer cylinder; core bars are sleeved with inner cavities of a cylinder cover and the piston rod so as to divide an inner cavity of the outer cylinder into acavity I which is served as an air cavity, a cavity II and a cavity III, wherein the cavity II and the cavity III are served as oil cavities; an cavity of the hydraulic control valve assembly is divided into a first cavity and a second cavity which are symmetrically arranged by a hydraulic control piston, and stepped faces and first and second one-way throttle valves are correspondingly disposedin the first and second cavities; a cavity I of the actuator cylinder assembly is filled with compressed gas, and a cavity II is connected with a cavity III by a three-position four-way solenoid valvewith a Y-type meso-position function; and an aircraft hydraulic oil passage P is connected with an oil inlet of the three-position four-way solenoid valve, and a system outlet oil line T is connectedwith an oil return port of the three-position four-way solenoid valve. The aircraft landing gear vehicle frame stabilizing buffer device and control method thereof realize the retracting and buffering damping of the vehicle frame and has the function of lowering in a backup mode.

Description

technical field [0001] The invention relates to a frame-type landing gear used in large aircraft, in particular to a stable buffer device used for retracting, buffering and damping of a small frame of an aircraft landing gear and a control method thereof. Background technique [0002] At present, the landing gear of large aircraft generally adopts the front three-point layout, and its main landing gear mostly adopts the configuration of a single strut with a multi-wheel frame arranged in the longitudinal direction. In order to reduce the flight resistance, the landing gear is usually designed to be retractable. : After the plane takes off, retract the landing gear into the fuselage or wing, and then lower the landing gear when landing. like figure 1 As shown, the movements of the landing gear retraction mechanism are mostly plane movements in the heading S and vertical H planes. If the landing gear is retracted in the attitude when it leaves the ground, that is, the angle b...

AI Technical Summary

Problems solved by technology

Invention patent CN103032403 introduces a frame position control actuator that can retract and retract the main landing gear frame at a large angle, which can realize the adjustment of the attitude of the frame beam and the follow-up with the ground load, but the failure of the hydraulic system is not considered Under the circumstances that the frame cannot be put down, it will be very dangerous for the aircraft to land with the frame retracted, which will reduce the overall reliability and safety of the aircraft landing gear

Although this type of frame stabilizing buffer device has a simple structure, it only realizes the dynamic buffering and damping function of the frame when the aircraft is sliding on the ground, and cannot realize the active adjustment of the position of the frame beam.

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