Anti-bird-strike leading edge of airplane and support body therefor

A support body and support matrix technology, applied in the direction of bird impact prevention equipment, aircraft parts, wings, etc., can solve the problem of reducing the weight of the aircraft's leading edge structure, achieve the effect of small weight cost, easy implementation, and meet the strength requirements

Active Publication Date: 2018-06-29
COMAC +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] However, the anti-bird strike ability of the leading edge of the aircraft needs to be further improved, and at the same time there is a demand for reducing the structural weight of the leading edge of the aircraft

Method used

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  • Anti-bird-strike leading edge of airplane and support body therefor
  • Anti-bird-strike leading edge of airplane and support body therefor
  • Anti-bird-strike leading edge of airplane and support body therefor

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Embodiment Construction

[0051] The present invention will be further described below in conjunction with the accompanying drawings and embodiments, so as to more clearly connect the inventive principle and beneficial technical effects of the present invention.

[0052] Explanation of terms used in this article:

[0053] The extension direction of the anti-bird strike leading edge of the aircraft along the wingspan is called the longitudinal direction;

[0054] The direction perpendicular to the direction of extension of the leading edge is called transverse;

[0055] Along the transverse direction, the side adjacent to the front side of the leading edge is called the front;

[0056] In the transverse direction, the side adjacent to the rear of the leading edge is called the rear.

[0057] Such as figure 1 and 2 As shown, it shows a preferred embodiment according to the present invention. figure 1A perspective view of an anti-bird strike front edge 10 of an aircraft is shown, and the front edge 1...

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Abstract

The invention provides a support body for an anti-bird-strike leading edge of an airplane. The support body includes: an energy absorbing chamber, which is located on the front part of the leading edge and is extended longitudinally, and is filled with an energy absorbing material and includes a front surface side and a rear surface side being opposite thereto; a support base body located on the rear part of the leading edge and extended longitudinally; and a support rib body arranged between the energy absorbing chamber and the support base body and including a front connection end and a rearsupport end being opposite thereto. A rear connection side of the energy absorbing chamber is connected to the front connection end of the support rib body and the rear support end of the support ribbody is fastened with the support base body by a fastener. The invention also provides the anti-bird-strike leading edge of the airplane with the support body. According to the invention, the anti-bird-strike capability of the leading edge is significantly improved.

Description

technical field [0001] The invention relates to an aircraft leading edge and a support body for the aircraft leading edge, in particular to an aircraft anti-bird strike front edge and a support body structure for an aircraft anti-bird strike front edge. Background technique [0002] The anti-bird strike performance of aircraft leading edge is a key factor to measure the success of an aircraft leading edge design. [0003] The front edge structure used in early civil aviation aircraft was mainly made of metal aluminum alloy. In order to improve the anti-bird strike performance, a great weight price was often paid. Such as B737, MD82, MD90 and other aircraft. Therefore, as more and more composite materials are used in civil aircraft, major civil aircraft manufacturing companies are considering the application of new materials to reduce structural weight while improving bird strike resistance. For example, the leading edge of the A320 empennage adopts a sandwich structure of ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/00B64C3/28
CPCB64C3/00B64C3/28B64D2045/0095
Inventor 李娜孔令勇吴志斌王嘉浏宋春艳朱广荣
Owner COMAC
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