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A fuselage enclosure for use in areas adjacent to where aircraft engines are installed

An aircraft engine and installation location technology, applied in the direction of fuselage, aircraft parts, transportation and packaging, etc., can solve problems such as difficult to resist broken blades, and achieve the effect of low density and excellent impact resistance

Active Publication Date: 2015-12-02
LIYANG TECH DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The current aircraft fuselage skin is usually made of lightweight metal aluminum magnesium titanium or their alloys, and some aircraft use composite materials, but the current fuselage skin is still difficult to withstand the high impact of the broken blade or is the other hit

Method used

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Effect test

Embodiment Construction

[0011] The aircraft fuselage shell in the present invention has a sandwich structure, which is made of metal, fiber and ceramic layered composite materials, and has a sandwich structure composed of at least one metal layer / fiber layer / ceramic layer. The metal layer is made of aluminum, magnesium, titanium or corresponding alloy materials, the fiber layer is made of glass fiber, kevlar fiber, carbon fiber, silicon nitride, silicon carbide or zirconia fiber, and the ceramic material is a kind of high toughness oxide Zirconium ceramics.

[0012] The zirconia ceramic material uses zirconia as a matrix and adopts a niobium / titanium / nickel phase as a toughening phase. Specifically, first select niobium powder, titanium powder and nickel powder with a purity greater than 99.5% and mix them in a ratio of 4:3:2 by weight, and perform ball milling under nitrogen protection for 100 hours to obtain a toughening phase powder; then, take The zirconia powder and the toughening phase powder ...

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PUM

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Abstract

The invention provides a fuselage shell for an airplane. The fuselage shell comprises a sandwich structure which is made of laminar composite materials including metal, fiber and ceramic. The sandwich structure is composed of at least one metal layer, at least one fiber layer and at least one ceramic layer. The sandwich structure is characterized in that the at least one metal layer is made of aluminum materials, magnesium materials, titanium materials or corresponding alloy materials, the at least one fiber layer is made of glass fiber materials, Kevlar fiber materials, carbon fiber materials, silicon nitride materials, silicon carbide materials or zirconium dioxide materials, and the at least one ceramic layer comprises zirconium oxide and a niobium / titanium / nickel toughening phase. The fuselage shell of the fuselage with the sandwich structure is high in hardness, good in toughness, light in mass and good in anti-impact property.

Description

technical field [0001] The invention relates to a fuselage with a sandwich structure, in particular to a fuselage shell with a sandwich structure. Background technique [0002] At present, large commercial jet aircraft usually adopt high-thrust turbofan aeroengines. This type of turbofan aeroengines all use large-size fan blades, the largest fan blade diameter can reach 3m, and the tangent line at the tip of the fan blade during operation If the speed exceeds 450m / s, the tangential speed of the turbofan blade tip will be higher with the development of the turbofan aeroengine in the future. Blades running at high speed are affected by impact damage from foreign objects or high-frequency vibration fatigue, and blade fracture failures will inevitably occur. A broken blade has high energy, and if the blade penetrates the nacelle, it can cause damage to the fuselage skin near where the engine is mounted, endangering the safety of aircraft passengers. The current aircraft fusela...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C1/00C04B35/48B32B18/00
Inventor 狄春保朱琪美张和平张俊
Owner LIYANG TECH DEV CENT