Composite material wing leading edge skin with inner interlayer core material and preparation method thereof
A composite material and wing leading edge technology, applied in the direction of wings, chemical instruments and methods, fuselage, etc., can solve problems such as insufficient impact resistance, achieve excellent anti-collision performance, protect safety, and improve impact capability Effect
Inactive Publication Date: 2017-12-22
ZHONGBEI UNIV
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Problems solved by technology
[0004] In order to solve the technical problem that the impact resistance of the leading edge of the current aircraft wing is not good enough, the invention provides a composite structure wing shell with a sandwich core material and a preparation method thereof
Method used
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Embodiment Construction
[0039] The invention provides a wing leading edge skin composed of three parts: an aluminum alloy / basalt fiber metal laminate, an Ω-shaped interlayer core material and an aluminum alloy thin plate.
[0040] A composite wing leading edge skin with an inner pad interlayer core material, comprising an outer skin, an inner skin and an interlayer core material; the inner skin is riveted with the outer skin by its edge to form a skin with a cavity Structure; the sandwich core material is located in the cavity and fixed on the inner surface of the inner skin, and there is a gap between the top of the sandwich core material and the inner surface of the outer skin.
[0041] The outer skin adopts 3 / 2 structural fiber metal laminates, which are sequentially laminated by five layers of metal sheets, fiber cloth, metal sheets, fiber cloth, and metal sheets; the inner skin adopts the same metal sheet as the outer skin Made of the same material.
[0042] The sandwich core material is M-shap...
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Abstract
The present invention relates to a wing leading edge skin, more particularly to a composite structure wing shell with an interlayer core material and a preparation method thereof, and solves the technical problems that the impact resistance of the wing leading edge in the prior art is not good enough. The composite material wing leading edge skin with the inner interlayer core material comprises a fiber metal layer plate composite material outer skin, a metal thin plate inner skin and the interlayer core material, a skin structure with a cavity is formed by riveting of the edge of the metal thin plate inner skin with an outer skin rivet, the interlayer core material is located in the cavity and fixed on the inner surface of the inner skin, and a gap is provided between the top of the interlayer core material and the inner surface of the outer skin. The composite structure wing shell adopts a multi-layer protection design to absorb dissipation energy layer by layer so as to improve the bird collision power of the wing leading edge skin; the inner light and weak core material transmits shear load in the thickness direction, a large amount of bird impact energy is absorbed by local crushing, and the interlayer core material is a second defense line against bird collisions.
Description
technical field [0001] The invention relates to a wing leading edge skin, in particular to a composite structure wing shell with a sandwich core material and a preparation method thereof. Background technique [0002] The bird strike accident of the aircraft is a kind of sudden and frequent flight accident, ranging from damage to the aircraft, to the death of the aircraft in severe cases. From 1974 to 1998, the U.S. Air Force had 22,423 bird strikes, an average of more than 1,600 per year, causing many accidents that endangered flight safety. As a key component on the aircraft, the leading edge of the wing is the most vulnerable part of the aircraft to be struck by birds. The interior of the wing of modern military aircraft is usually equipped with important equipment such as oil system, so it is necessary to strictly control the displacement and deformation of the leading edge of the wing during the bird impact process, let alone penetrating damage. [0003] In order to e...
Claims
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Patent Timeline
Login to View More IPC IPC(8): B64C3/26B64F5/10B32B15/14B32B15/04B32B9/00B32B37/12B32B37/10B32B37/02
CPCB32B5/02B32B15/04B32B15/043B32B15/14B32B37/02B32B37/10B32B37/12B32B2250/40B32B2262/108B32B2307/558B32B2605/18B64C3/26B64C2001/0072B64C2003/146B64F5/10
Inventor 原梅妮李盼辛乐李瑶赵兴成姚磊斌李立州
Owner ZHONGBEI UNIV