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Composite material laminated board for displaying internal injury on surface

A composite material layer and laminated board technology, applied in the field of composite material manufacturing, can solve problems such as hidden dangers, and achieve the effects of avoiding impact, ensuring safety, and wide adaptability

Active Publication Date: 2009-08-12
BEIJING AVIATION MATERIAL INST NO 1 GRP CORP CHINA AVIATION IND
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, when the composite material is subjected to low-speed impact, when the internal layer of the composite material is delaminated, the matrix is ​​cracked, or the fiber is broken, the surface layer of the composite material has no obvious destructive damage, which will cause hidden dangers.

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0040] Preparation of toughened film: Polyaryletherketone resin (PAEK) was dissolved in tetrahydrofuran (THF) to prepare a 5% solution. On the solution scraping film machine, evenly scrape the PAEK solution onto the release paper, and obtain a toughened film after the solvent evaporates. Adjust the height of the knife edge of the scraping film to control the surface density of the toughened film to 20g / m 2 . Trimmed and rolled to obtain a continuous PAEK film.

[0041] Internal layup: T300 / 5228 epoxy-based prepreg prepared by hot melt prepreg method.

[0042] Surface layup: T300 / 5228 epoxy-based prepreg, a layer of PAEK toughening film is applied on the upper surface of the prepreg, and it is compacted by a hot pressing roller at 80°C to obtain a toughened layup.

[0043] According to [(45 / 0 / -45 / 90) 表面 / (45 / 0 / -45 / 90) 内部，3 ] S Lay-up Laminate. After curing in an autoclave according to the process of 130°C, 30min->180°C, 2h->200°C, 2h, a laminate with the ability to displ...

Embodiment 2

[0046] Preparation of toughened film: Polyaryletherketone resin (PAEK) was dissolved in tetrahydrofuran (THF) to prepare a 5% solution. On the solution scraping film machine, evenly scrape the PAEK solution onto the release paper, and obtain a toughened film after the solvent evaporates. Adjust the height of the knife edge of the scraping film to control the surface density of the toughened film to 20g / m 2 . Trimmed and rolled to obtain a continuous PAEK film.

[0047] Internal layup: T300 / 5228 epoxy-based prepreg prepared by hot melt prepreg method.

[0048] Surface layup: T300 / 5228 epoxy-based prepreg, a layer of PAEK toughening film is applied on the upper surface of the prepreg, and it is compacted by a hot pressing roller at 80°C to obtain a toughened layup.

[0049] According to [(45 / 0 / -45 / 90) 2表面 / (45 / 0 / -45 / 90) 内部，6 ] S Lay-up Laminate. After curing in an autoclave according to the process of 130°C, 30min->180°C, 2h->200°C, 2h, a laminate with the ability to disp...

Embodiment 3

[0052] Preparation of pre-toughened fabric: Add polyethersulfone (PES) resin powder into water dissolved with emulsifier and thickener to prepare a slurry with a viscosity of about 10 000 cPoise and a solid content of about 35%. Coat the slurry on the T700 carbon fiber unidirectional fabric on a slurry point coating machine, and pass through a high-temperature oven at 300°C to melt and bond the PES powder on the surface of the carbon fiber fabric. Control the areal density of the toughening agent to 20g / m through the amount of paste coating 2 . So far, the compounding of the toughening layer is completed.

[0053] Internal laminate reinforcement fabric: T700 unidirectional fabric.

[0054] Press [(45 增韧 / 0 增韧 / -45 增韧 / 90 增韧 ) / (45 / 0 / -45 / 90) 2 ] S Lay up and cut T700 fabrics, lay up and combine them into prefabricated bodies and mold them. Using 6421 bismaleimide as the matrix resin, it is injected into the mold by RTM process, and cured according to the process of 130°...

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Abstract

The invention belongs to the technology of composite material manufacturing, relating to a composite material laminated board displaying internal damage at surface. The laminated board is divided into two parts of internal ply and surface ply, reinforced material at the surface ply and the form of the reinforced material are the same as or different from the reinforced material at internal ply and the form of the reinforced material; when the laminated board is prepared by using resin transfer molding or resin membrane impregnating molding technology, the internal ply and the surface ply are dry reinforced materials, and the surface ply uses resin base body the same as the internal ply; when the laminated board is prepared by using autoclave molding or compression molding or vacuum-bag molding or hand lay-up molding technology, the internal ply and the surface ply are wet reinforced materials, and the surface ply uses resin base body the same as or different from the internal ply. In the invention, internal damage can be displayed at surface in time when the material suffers from low-speed impact and causes internal injury so that ground support staff can find out potential risks in time to guarantee aerocraft safety.

Description

technical field [0001] The invention belongs to composite material manufacturing technology, and relates to a composite material laminate whose surface shows internal damage. Background technique [0002] One of the main weaknesses of continuous fiber reinforced resin matrix composites is their poor resistance to low-velocity impact damage. Impacts such as crushed stones, hail, and falling tools that have a high probability of encountering during service may cause serious breakdown inside the composite. layer damage, resulting in a sharp decrease in the compressive strength of the structure. To make matters worse, this internal delamination damage is imperceptible on the surface of the material, and its compressive strength has been reduced to 40% of its original value when there is barely detectable visual surface damage. In order to ensure flight safety, it is required that the composite material structure at this time can still serve for a short period of time, that is t...

Claims

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Application Information

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IPC IPC(8): B32B27/12B32B33/00B29C70/34
Inventor 安学锋益小苏马宏毅崔海超闫丽
Owner BEIJING AVIATION MATERIAL INST NO 1 GRP CORP CHINA AVIATION IND
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