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Low-density and high-performance composite sandwich structure and preparation method thereof

A composite material, sandwich structure technology, applied in chemical instruments and methods, synthetic resin layered products, lamination and other directions, can solve the problems of small thermal expansion coefficient of aramid honeycomb core material, large variation of profile accuracy, poor thermal conductivity and so on , to achieve strong designability, stable performance and dimensional accuracy, and ensure the effect of surface accuracy

Inactive Publication Date: 2016-04-06
SHANGHAI COMPOSITES SCI & TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Aluminum honeycomb has good thermal conductivity, but its thermal expansion coefficient is large, and the thermal expansion coefficient of the composite skin panel is greatly different. The matching of the two is likely to cause internal stress in the honeycomb structure. In the high-precision honeycomb sandwich structure, the amount of thermal deformation is large, and the surface accuracy changes greatly. , cannot meet the precision requirements of high precision and high stability
Aramid honeycomb core material has a small thermal expansion coefficient, but poor thermal conductivity, and high vacuum outgassing rate in space environment, which cannot meet the application requirements of space environment
Both core materials are formed or stretched into plates and then processed into the desired shape, which is difficult to process and the attainable surface accuracy is not high

Method used

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  • Low-density and high-performance composite sandwich structure and preparation method thereof
  • Low-density and high-performance composite sandwich structure and preparation method thereof

Examples

Experimental program
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Effect test

Embodiment 1

[0040] A sandwich structure formed by round rods is an example, see attached figure 1 a and figure 2 The sandwich structure is composed of an upper skin layer 1, a lower skin layer 3 and a sandwich structure 2, and both the upper skin layer and the lower skin layer are made of composite materials. The sandwich structure 2 is made up of multiple rods arranged side by side, the density of the rods is 60kg / m 3 , Flat compressive strength 3.2Mpa, thermal expansion coefficient 1.7×10 -6 .

[0041] 1) Material design

[0042] The resin matrix and reinforcement materials of the sandwich material are selected according to the requirements of use. Here, T300 / 3K carbon fiber and epoxy resin are selected; the layering method is 0 / +60 / -60.

[0043] 2) Rod forming processing

[0044] Cut a single-layer fiber-reinforced resin matrix composite prepreg with a thickness of 0.03mm into strips, one layer is 0 degrees, one layer is +60 degrees, and one layer is -60 degrees. The three-layer fiber prepreg...

Embodiment 2

[0052] A sandwich structure formed by regular hexagonal rods. As attached figure 1 b. figure 2 As shown, the density of the rod is 68kg / m 3 , Flat compressive strength 4.6Mpa, thermal expansion coefficient 1.1×10 -6 .

[0053] 1) Material design

[0054] Choose the core material resin matrix and reinforcement materials according to the use requirements, here choose M55 / 6K carbon fiber, epoxy resin; the layup method is 0 / 90 / +45 / -45.

[0055] 2) Rod forming processing

[0056] Cut a single-layer fiber-reinforced resin matrix composite prepreg with a thickness of 0.15mm into strips, one layer is 0 degrees, one layer is 90 degrees, one layer is +45 degrees, and one layer is -45 degrees, and the four layers of fiber are prepreg The material is wound on the metal mold according to the direction of 0 / 90 / +45 / -45 through the winding process. After solidification, the composite rod is demolded and machined into a short rod with a length of 60mm.

[0057] 3) Laying of skin and interlayer

[0058...

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Abstract

The invention discloses a low-density and high-performance composite sandwich structure and a preparation method thereof. The sandwich structure comprises a core sandwich structure, an upper skin layer arranged on the upper bottom surface of the core sandwich structure and a lower skin layer arranged on the lower bottom surface of the core sandwich structure, wherein the core sandwich structure is formed by arranging a plurality of rod parts in parallel; each rod part is made of a fiber-reinforced resin-based composite. The rod parts made of the fiber-reinforced resin-based composites are spliced in a bonding or physical fixing manner to form the core sandwich structure, so that the core material has designability in mechanical property and hydrothermal property and has formability of complicated molded surfaces, and the high-precision, high-stability and complicated honeycomb sandwich structure is manufactured.

Description

Technical field [0001] The invention relates to a low-density and high-performance composite material sandwich structure and a preparation method thereof, in particular to a preparation method of a composite material sandwich structure with low density, ultra-light weight, strength, rigidity and functionality that can be designed. Background technique [0002] With the development of deep space exploration technology, the operating environment temperature range of spacecraft is getting wider and wider, and the requirements for weight reduction of platform structure are getting higher and higher. Among them, the stability and reliability of the surface accuracy of composite parts in space environment and the structure Functional integration is an important direction of development. [0003] The composite material honeycomb sandwich material uses a metal plate or a composite material plate as the skin, and now mainly uses metal aluminum honeycomb and aramid honeycomb as the core stru...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B9/00B32B27/04B32B9/04B32B3/20B32B7/12B32B37/02B32B37/12
CPCB32B9/007B32B3/20B32B7/12B32B9/04B32B37/02B32B37/12B32B2260/021B32B2260/046B32B2262/106
Inventor 诸静郝旭峰沈峰田杰王池刚
Owner SHANGHAI COMPOSITES SCI & TECH CO LTD
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