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Undercarriage buffering device

A buffer device and landing gear technology, which is applied to landing gear, transportation and packaging, aircraft parts, etc., can solve the problems of short maintenance period, complex structure, high processing precision requirements, etc., and achieve the effect of avoiding occupying too much space

Inactive Publication Date: 2018-05-15
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The existing buffer devices with oil-gas mixture or air spring structure have relatively complex structure, low reliability, short maintenance period, and complicated assembly, especially when it comes to the sealing structure, which is generally large in size and requires high machining accuracy.

Method used

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  • Undercarriage buffering device
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Examples

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Embodiment Construction

[0022] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0023] The landing gear cushioning device of the present invention wi...

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Abstract

The invention provides an undercarriage buffering device which comprises an end cover (1), a lug ring bolt (2), an outer cylinder (3), a piston rod (4), a first lining (5), a second lining (6), a cylindrical helical compression spring (10) and a third lining (15). The end cover (1) is a cylindrical component, a dual-lug structure sleeved with the third lining (15) is arranged on one side of the end face of the end cover (1), one side of a spigot of the end cover (1) is in butt joint with the cylindrical outer cylinder (3), one end of the piston rod (4) in a stair hollow cylindrical shape is inserted in an inner cavity of the outer cylinder (3), the outer wall face of the piston rod (4) is sleeved with the first lining (5) and the second lining (6) so as to be provided with the cylindricalhelical compression spring (10), and the lug ring bolt (2) is inserted in the inner wall face of the exposed end of the piston rod (4). By the adoption of the provided buffering device, a buffering purpose is achieved through the compression spring, and the problems that a sealing component in the buffering device occupies too much space, leakage is likely to happen, and thus reliability is reduced are solved.

Description

technical field [0001] The invention belongs to the field of aircraft structure design, and in particular relates to a landing gear buffer device. Background technique [0002] The buffer device is a device commonly used in various mechanical equipment to prevent damage to parts caused by impact loads. The existing buffer devices with oil-gas mixture or air spring structure have complex structure, low reliability, short maintenance period and complex assembly, especially when it comes to the sealing structure. Contents of the invention [0003] The object of the present invention is to solve the above problems and provide a landing gear buffer device with high reliability, small size, simple assembly and reduced impact force damage to components. [0004] The purpose of the present invention is achieved through the following technical solutions: a landing gear buffer device, including an end cover, an earring bolt, an outer cylinder, a piston rod, a first bush, a second b...

Claims

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Application Information

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IPC IPC(8): B64C25/62
CPCB64C25/62
Inventor 倪艳红李志鹏李福邵帅张传明
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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