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Light high-strength folding wing material for hovercar and preparation method thereof

A flying car, folding wing technology, applied in aircraft control, chemical instruments and methods, vehicles that can be converted into aircraft, etc. , Good high temperature thermal stability, weight reduction effect

Inactive Publication Date: 2018-04-17
班伟相
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] Among the above two processes, the former uses magnesium-aluminum alloy + carbon fiber materials for compounding. Although a special process is used in the connection method, it still uses the metal + composite material method. In the case of the same volume, th

Method used

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  • Light high-strength folding wing material for hovercar and preparation method thereof

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Embodiment 1

[0026] A lightweight high-strength folding wing material for flying cars, comprising a composite material layer and a skin layer, the skin layer is arranged on the outside of the composite material layer, and the composite material layer includes N layers of unidirectional carbon fiber layers, 2N layers of orthogonal carbon fibers layer and a honeycomb interlayer, the honeycomb interlayer is laid in the middle of the composite material layer and the two sides of the honeycomb interlayer are respectively two layers of orthogonal fiber layers, and the outer side of the orthogonal fiber layer is laid with the unidirectional fiber layer, wherein, N =6.

[0027] A method for preparing a lightweight and high-strength folding wing material for a flying car, comprising the following steps:

[0028] (1) After the unidirectional carbon fiber layer and the orthogonal fiber layer are surface-treated with a coupling agent, they are immersed in an epoxy resin system for impregnation to obta...

Embodiment 2

[0036] A lightweight high-strength folding wing material for a flying car, comprising a composite material layer and a skin layer, the skin layer is arranged on the outside of the composite material layer, and the composite material layer includes N layers of unidirectional carbon fiber layers and 2N layers of orthogonal carbon fibers layer and a honeycomb interlayer, the honeycomb interlayer is laid in the middle of the composite material layer and the two sides of the honeycomb interlayer are respectively two layers of orthogonal fiber layers, and the outer side of the orthogonal fiber layer is laid with the unidirectional fiber layer, wherein, N =6.

[0037] A method for preparing a lightweight and high-strength folding wing material for a flying car, comprising the following steps:

[0038] (1) After the unidirectional carbon fiber layer and the orthogonal fiber layer are surface-treated with a coupling agent, they are immersed in an epoxy resin system for impregnation to ...

Embodiment 3

[0046] A lightweight high-strength folding wing material for flying cars, comprising a composite material layer and a skin layer, the skin layer is arranged on the outside of the composite material layer, and the composite material layer includes N layers of unidirectional carbon fiber layers, 2N layers of orthogonal carbon fibers layer and a honeycomb interlayer, the honeycomb interlayer is laid in the middle of the composite material layer and the two sides of the honeycomb interlayer are respectively two layers of orthogonal fiber layers, and the outer side of the orthogonal fiber layer is laid with the unidirectional fiber layer, wherein, N =6.

[0047] A method for preparing a lightweight and high-strength folding wing material for a flying car, comprising the following steps:

[0048] (1) After the unidirectional carbon fiber layer and the orthogonal fiber layer are surface-treated with a coupling agent, they are immersed in an epoxy resin system for impregnation to obta...

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Abstract

The invention discloses a preparation method of a light high-strength folding wing material for a hovercar and relates to the field of machinery. The material comprises a composite material layer anda skin layer, the composite material layer comprises N single-way carbon fiber layers, 2*N orthogonal carbon fiber layers and a honeycomb interlayer, the honeycomb interlayer is laid in the middle ofthe composite material layer, the two orthogonal fiber layers are arranged at the two sides of the honeycomb interlayer respectively, and the single-way fiber layers are laid at the outer sides of theorthogonal fiber layers. The invention further discloses the preparation method of the wing material. Multi-way carbon fiber prepreg is adopted for the composite material, the anti-pulling, anti-pressing and anti-shearing capacities of wing components in multiple directions are improved, the balance of the whole performance of the composite material is further improved by adopting a laying sequence which is specifically designed at the same time, and the material which is produced through the preparation method has good high-temperature heat stability, chemical stability, a flame retardant property and the like and further has an excellent mechanical property.

Description

technical field [0001] The invention relates to the technical field of composite materials, in particular to a lightweight and high-strength folding wing material for flying cars and a preparation method for lightweight and high-strength folding wing materials for flying cars. Background technique [0002] A composite material is a multiphase solid material composed of two or more substances with different physical and chemical properties. Although the component materials of composite materials maintain their relative independence, the performance of composite materials is not a simple addition of the properties of the component materials, but an important improvement. In composite materials, usually one phase is continuous phase, called matrix; the other phase is dispersed phase, called reinforcement material. Composite materials used in aircraft structures are mainly fiber-reinforced composite materials. [0003] The matrix of composite materials used in aircraft structu...

Claims

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Application Information

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IPC IPC(8): B32B9/00B32B9/04B32B27/04B32B27/38B32B3/12B60F5/02B64C1/30
CPCB32B5/02B32B3/12B32B5/26B32B2260/023B32B2260/046B32B2262/106B32B2307/3065B32B2307/308B32B2307/50B32B2307/552B32B2307/714B32B2307/72B60F5/02B64C1/30
Inventor 班伟相
Owner 班伟相