Aircraft bird strike leading edge and support body for aircraft bird strike leading edge

A technology of supporting body and supporting base, which is applied in the direction of preventing bird strikes, aircraft parts, wings, etc., can solve the problem of reducing the weight of the aircraft's leading edge structure, and achieve the effect of small weight cost, easy implementation, and low weight cost

Active Publication Date: 2021-04-23
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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  • Aircraft bird strike leading edge and support body for aircraft bird strike leading edge
  • Aircraft bird strike leading edge and support body for aircraft bird strike leading edge
  • Aircraft bird strike leading edge and support body for aircraft bird strike leading edge

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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 supporting body for the anti-bird strike front edge of an aircraft. The supporting body includes: an energy-absorbing cavity located at the front of the leading edge and extending longitudinally, the energy-absorbing cavity is filled with energy-absorbing material and includes a front surface side and the rear connection side opposite to the front surface side; the support base located at the rear of the front edge and extending longitudinally; The rear supporting end opposite to the connecting end; wherein, the rear connecting side of the energy-absorbing cavity is connected to the front connecting end of the supporting rib through a connecting piece; the rear supporting end of the supporting rib is fastened to the supporting base through a fastener. The present invention also provides an anti-bird strike front edge of an aircraft using the above-mentioned supporting body. According to the wing leading edge of the invention, its anti-bird strike performance has been 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 Patents(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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