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Inflation and deflation connector for undercarriage buffer strut

A buffer strut, inflation and deflation technology, applied in the direction of pipes/pipe joints/fittings, branch lines, connections with fluid cut-off devices, etc. problems, to achieve the effect of simple operation, convenient use and accurate gas measurement

Pending Publication Date: 2022-02-11
CHINA HELICOPTER RES & DEV INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] At present, the detection methods for the filling state of the landing gear buffer strut are very poor, and the tooling used is complicated, complicated, time-consuming and labor-intensive, and has a long cycle.

Method used

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  • Inflation and deflation connector for undercarriage buffer strut
  • Inflation and deflation connector for undercarriage buffer strut
  • Inflation and deflation connector for undercarriage buffer strut

Examples

Experimental program
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Embodiment Construction

[0020] see Figure 1-3 , the present invention provides a landing gear buffer strut inflation and deflation joint, including a pin 1, a push rod 2, a housing 3, an air nozzle connection nut 7, a surface connection nut 20, etc. Fast inflation and deflation and detection of gas pressure.

[0021] In the embodiment of the present application, the landing gear buffer strut rapid inflation and deflation joint ejector pin 2 is composed of five parts, the first stage ejector rod 13, the fourth stage ejector rod 14, the third stage ejector rod 15, the second stage ejector rod 16, the tail stage ejector rod Ejector 17. There is a through hole 11 on the first-stage ejector rod 13 for the insertion of the pin 1. The roughness requirements of the third-stage ejector rod 15 are very high, and it mainly cooperates with the O-ring to play a sealing role.

[0022] In the embodiment of the present application, the ejector pin 2 is processed from a heat-treated metal material, and the fourth-...

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Abstract

The invention provides an inflation and deflation connector for an undercarriage buffer strut. The inflation and deflation connector comprises an ejector rod, a pin and a shell, wherein the pin is inserted into the ejector rod; gas enters or flows out from a conical nozzle of the shell, and the undercarriage buffer strut is inflated and deflated through the ejector rod; a pressure gauge is also arranged on the shell and is used for measuring the pressure in the joint; the inflation and deflation connector for the undercarriage buffer strut is small, exquisite, flexible, convenient to use, easy to operate, stable and reliable in performance and capable of achieving rapid inflation and deflation and accurate gas measurement; meanwhile, inflation and deflation conversion of buffer struts of various large-size helicopters can be achieved, the gas pressure of the buffer struts can be accurately measured, nodes of novel-size development tasks are guaranteed, and the test efficiency is greatly improved.

Description

technical field [0001] The invention belongs to the technical field of helicopter dynamics tests, and in particular relates to an inflation and deflation joint of a landing gear buffer strut. Background technique [0002] The landing gear is an important component of the helicopter, and it is the only means to ensure the safe take-off, landing and landing of the helicopter. At present, the overwhelming majority of helicopter landing gears in my country adopt inflatable cushioning pillars. The landing gear drop test mainly verifies its ability to absorb the designed landing power and power reserve of the helicopter, and provides a theoretical basis for modifying the inflation parameters of the buffer strut, which is related to the landing of the helicopter and the safety of the ship. [0003] In each working condition of the landing gear drop test, it is necessary to ensure the filling state of the buffer strut (mainly the gas volume and pressure of each air cavity and other...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16L29/00F16L41/00F16F9/43G01L19/00B64F5/60
CPCF16L29/00F16L41/008F16F9/43G01L19/0007B64F5/60
Inventor 章剑翟泉星邓先来
Owner CHINA HELICOPTER RES & DEV INST