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Double-cavity buffer

A buffer and air cavity technology, applied in the field of aircraft landing gear buffer design, to achieve the effect of small mass, compact structure and shortened length

Active Publication Date: 2019-02-01
CHINA HELICOPTER RES & DEV INST
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

[0006] The purpose of this application is to provide a double chamber buffer to solve the problem of overcoming or alleviating at least one aspect of the above

Method used

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Embodiment Construction

[0040] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application. 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 application. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application. Embodiments of the present application will be described in detail below in conjunction with th...

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Abstract

The invention belongs to the technical field of aircraft landing gear buffer design, particularly relates to a double-cavity buffer, and provides a double-cavity buffer. The double-cavity buffer comprises an inner cylinder, a first plug cap, a second plug cap, a first floating piston, a second floating piston, an outer cylinder and a spacer sleeve; two independent first oil cavities, a first air cavity and a second air cavity are formed in the inner cylinder; the outer side of the inner cylinder is sleeved with the outer cylinder; a second oil cavity is formed between the outer cylinder and the inner cylinder and communicates with the first oil cavity through a throttling hole; and the second oil cavity, the first air cavity and the second air cavity are arranged in parallel. Compared withthe prior art, the length of the double-cavity buffer can be effectively decreased, the structure is more compact, and the small mass can be obtained.

Description

technical field [0001] The application belongs to the technical field of aircraft landing gear buffer design, in particular to a double-cavity buffer. Background technique [0002] During the landing process, the aircraft always hits the ground at a certain speed, generating impact loads. In order to reduce the impact of such impact loads on the aircraft, the landing gear of modern aircraft is designed to withstand and slow down such impact loads. Wherein, because the landing gear has no effect during the flight of the aircraft, based on this consideration, it is hoped that the quality of the landing gear is as light as possible, and its volume is as small as possible. [0003] The key part of the landing gear to withstand and slow down the impact load is the buffer on it. During the landing process of the aircraft, the buffer absorbs and dissipates the energy carried by the impact load through the compression of the oil and gas in it, so as to reduce the impact load. effec...

Claims

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Application Information

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IPC IPC(8): F16F9/06F16F9/32
CPCF16F9/062F16F9/32F16F2222/12F16F2222/126
Inventor 孙为民苗红涛方建义
Owner CHINA HELICOPTER RES & DEV INST
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