Mode change-over valve used in aircraft front wheel control and shimmy damping system

Abstract

The invention discloses a mode change-over valve used in an aircraft front wheel control and shimmy damping system. The mode change-over valve comprises a stroke detection switch, a valve body, a sleeve, a spring, a valve element, a valve sleeve and a plug, wherein a distance measuring rod of the stroke detection switch is located in the sleeve and connected with one end of the valve element, meanwhile, the stroke detection switch and the sleeve are fixed to the inner side of one end of the valve body, the plug is arranged at the other end of the valve body, and a control oil port and an oil port which are controlled by an electromagnetic valve in the system are formed in the valve body; one end of the spring is fixed in the sleeve, and the other end of the spring is connected with a shaft shoulder at one end of the valve element; the other end of the valve element is connected with the control oil port, and the valve element is installed in the valve sleeve and can move in the valve sleeve; one end of the valve sleeve is connected with the sleeve, and the other end of the valve sleeve is connected with the plug; when the valve element is in the zero position, the system is in the shimmy damping mode, and the system is switched into the control mode through movement of the valve element. According to the mode change-over valve, free conversion between the control mode and the shimmy damping mode of a combination valve can be achieved, and the mode change-over valve has the advantages of being compact in structure, light in weight, high in anti-pollution capacity and high in reliability.

Description

technical field [0001] The invention belongs to the technical field of aircraft front wheel steering systems, and in particular relates to a mode conversion valve used in aircraft front wheel steering and swing reduction systems. Background technique [0002] The aircraft front wheel steering and sway reduction system generally adopts a multi-valve integrated servo hydraulic system to realize the front wheel steering in the aircraft front wheel control mode and the vibration absorption in the sway reduction mode. The core components should have the requirements of high reliability, strong anti-pollution ability, and high control precision. The problem of low precision. Contents of the invention [0003] The purpose of the present invention is to provide a mode conversion valve used in the aircraft front wheel control and swing reduction system, which can realize the free conversion between the control mode and the swing reduction mode of the combined valve, and has the ad...

AI Technical Summary

Problems solved by technology

[0002] The aircraft front wheel control and swing reduction system generally adopts a multi-valve integrated servo hydraulic system to realize the front wheel steering in the front wheel control mode of the aircraft and the swing vibration absorption in the swing reduction mode. The mode switching valve is to realize the mode conversion The core components should have the requirements of high reliability, strong anti-pollution ability, and high control precision. The problem of low precision

Images