Preparation method of high-intensity composite material grid structure

A composite material and grid structure technology, applied in the field of composite material preparation and application, can solve problems such as slow progress, and achieve the effects of strong operability, strong designability, and reliable mechanical properties

Inactive Publication Date: 2011-08-17
SHENYANG AEROSPACE UNIVERSITY +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Although the application of honeycomb structure materials in the aviation and aerospace fields is receiving more and more attention, the progress in the field of honeycomb manufacturing, especially the manufacturing of composite material honeycombs, is slow. Based on this, the present invention proposes a high-strength composite material network Preparation method of lattice structure

Method used

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  • Preparation method of high-intensity composite material grid structure
  • Preparation method of high-intensity composite material grid structure
  • Preparation method of high-intensity composite material grid structure

Examples

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Effect test

Embodiment 1

[0026] According to the 0.15mm thick unidirectional carbon fiber / epoxy resin prepreg, the first layer is 0 degrees / the second layer is 90 degrees / the third layer is 0 degrees / the fourth layer is 90 degrees / the fifth layer is 0 degrees (a total of 5 layers ) arranged in a carbon fiber / epoxy resin prepreg. Using the compression molding process (the cross-section waveform of the mold used is trapezoidal, the angle between the trapezoidal slope and the upper bottom is 120 degrees, the cross-sectional wavelength is 20mm, and the amplitude is 10mm), the composite material prepreg is cured and formed into carbon fiber / epoxy corrugated board. Cut the carbon fiber / epoxy corrugated sheet along the direction parallel to the corrugation extension of the section to make a carbon fiber / epoxy corrugated sheet with a width of 15mm (such as figure 1 shown). The upper and lower sides of the carbon fiber / epoxy corrugated sheet are coated with epoxy resin, and the lower surface of a corrugate...

Embodiment 2

[0028] 0.18mm thick unidirectional glass fiber / unsaturated polyester resin prepreg according to the first layer 0 degree / second layer 90 degree / third layer 0 degree / fourth layer 90 degree / fifth layer 0 degree / The sixth layer of 90 degrees / the seventh layer of 0 degrees (total 7 layers) is arranged to make glass fiber / unsaturated polyester resin prepreg. Using the pultrusion molding process (the cross-section of the die used in the pultrusion molding process is rectangular, that is, the angle between the hypotenuse and the upper bottom is 90 degrees, the wavelength of the cross-section is 25mm, and the amplitude is 10mm), the composite material prepreg is processed. Curing and molding to make glass fiber / unsaturated polyester corrugated board. Cut the glass fiber / unsaturated polyester corrugated sheet along the direction parallel to the extension of the section corrugation to make a glass fiber / unsaturated polyester corrugated sheet with a width of 10mm (such as figure 1 show...

Embodiment 3

[0030] According to the 0.15mm thick unidirectional carbon fiber / bismaleimide resin prepreg, the first layer is 0 degrees / the second layer is 90 degrees / the third layer is 0 degrees / the fourth layer is 0 degrees / the fifth layer is 0 degrees / The sixth layer is 90 degrees / the seventh layer is 0 degrees (a total of 7 layers) to make carbon fiber / bismaleimide resin prepreg. Using the pultrusion molding process (the section waveform of the die used in the pultrusion molding process is trapezoidal, the angle between the trapezoidal slope and the upper bottom is 120 degrees, the section wavelength is 20mm, and the amplitude is 12mm), the composite material is prepreg The cloth is cured and formed into a carbon fiber / bismaleimide corrugated board. Cut the carbon fiber / bismaleimide corrugated sheet along the direction parallel to the extension of the cross-sectional corrugation to make a carbon fiber / bismaleimide corrugated sheet with a width of 10mm (such asfigure 1 shown). The uppe...

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Abstract

The invention relates to a preparation method of a high-intensity composite material grid structure, which belongs to the technical field of composite material preparation and application. The method comprises the steps as follows: (1) a one-way fiber prepreg layering is designed; and a composite material prepreg fabric is prepared; (2) an extruding forming technique or a diepressing forming technique is adopted to implement solidifying and forming on the composite material prepreg fabric to prepare composite material corrugated plates; (3) the composite material corrugated plate is cut along a direction parallel to the ripple extension direction of a cross section to prepare composite material corrugated sheets; (4) resin is coated on the upper surface and the lower surface of the composite material corrugated sheet, the upper surface of the wave crest of the corrugated sheet and the corresponding lower surface of the wave trough of another corrugated sheet are stuck to form a hexagonal or rectangular grid structure, and then the upper surface of the wave peak of the grid structure and the corresponding lower surface of the wave trough of a third corrugated sheet are stuck; in the way, a plurality of corrugated sheets can be stuck to prepare the high-intensity composite material grid structure. The preparation method is simple and practical, and is suitable for high technology fields like aviation, aerospace, etc.

Description

technical field [0001] The invention relates to a method for preparing a grid structure of a high-strength composite material, and belongs to the technical field of preparation and application of composite materials. Background technique [0002] Compared with other structures, the composite honeycomb structure can obtain higher load-bearing capacity with less material. When the honeycomb structure plate is subjected to a load perpendicular to the plate surface, its flexural modulus is equivalent to that of a solid plate of the same material and thickness. The weight can be reduced by 70-90%, and it is not easily deformed and cracked. It has good shock absorption, sound insulation, heat insulation and other advantages, and is widely used in aviation and aerospace fields. [0003] In the field of honeycomb structure design, as early as 1938, the British Dr. NORMAN DEBRUYNE invented the hexagonal aluminum honeycomb structure. During World War II, this structure was successfull...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B3/12B32B27/06B32B27/04B32B27/12
Inventor 陆春陈平沙桂英武大伟秦政琪
Owner SHENYANG AEROSPACE UNIVERSITY
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