Preparation method for carbon nanotube non-woven fabric interlayer modified fiber reinforced composite materials

A carbon nanotube and composite material technology is applied in the field of preparation of carbon nanotube non-woven interlayer modified continuous fiber composite materials, which can solve the problems of carbon nanotube structure damage, reduce carbon nanotube modification effect, etc. The effect of improving strength-toughening properties, high damage tolerance, and high impact damage resistance

Inactive Publication Date: 2012-06-27
AVIC BEIJING INST OF AERONAUTICAL MATERIALS +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, no matter what kind of dispersion method and surface modification method of carbon nanotubes are used, the process complexity will be greatly increased, and the modification of the surface of carbon nanotubes by relying...

Method used

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  • Preparation method for carbon nanotube non-woven fabric interlayer modified fiber reinforced composite materials
  • Preparation method for carbon nanotube non-woven fabric interlayer modified fiber reinforced composite materials
  • Preparation method for carbon nanotube non-woven fabric interlayer modified fiber reinforced composite materials

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0030] First prepare low toughness epoxy resin composite material as matrix material: prepare T300 / epoxy resin prepreg (epoxy resin composition is E-54:AG-80:DDS= 40:60:40), as per [45 / 0 / -45 / 90] 4S The method is quasi-isotropic layup. It is cured and formed in an autoclave. The forming process is: vacuuming to 0.095MPa in the whole process, heating from room temperature to 130℃, holding for 0.5h and then pressurizing to 0.55MPa~0.6MPa, then heating to 180℃ for 2 hours, and then heating to 200 ℃ for 2h, and finally cooled to below 60℃. The heating rate is 1.0°C / min to 2.0°C / min.

[0031] Prepare the same prepreg as the low toughness composite, also press [45 / 0 / -45 / 90] 4S The method is quasi-isotropic layup. In the laying process, the carbon nanotube non-woven fabric is directly attached to the surface of the epoxy prepreg, and a layer of carbon nanotube non-woven fabric is ensured between the two layers of prepreg. It is cured and formed in an autoclave according to the pr...

Embodiment 2

[0034] First prepare low toughness bismaleimide composite material as matrix material: prepare T700 / bismaleimide prepreg by wet method with TB-1 winding prepreg machine, according to [45 / 0 / -45 / 90] 4S The method is quasi-isotropic layup, and the autoclave is cured and formed. When it reaches 180 °C, it is kept for 3 hours, and the temperature is continued to rise to 200 °C for 5 hours. The whole process is evacuated, and finally cooled to below 60 °C to open the mold. The heating rate is 1.5 °C / min ~ 2.0 °C / min.

[0035] Prepare the same prepreg as the low toughness composite, also press [45 / 0 / -45 / 90] 4S The method is quasi-isotropic layup. In the laying process, the carbon nanotube non-woven fabric is directly attached to the surface of the Shuangma prepreg, and a layer of carbon nanotube non-woven fabric is ensured between the two layers of prepreg. It is cured and formed in an autoclave according to the process of low toughness composite materials.

[0036] Impact damag...

Embodiment 3

[0038] First prepare low toughness polyimide composite material as matrix material: prepare T300 / polyimide prepreg by wet method with TB-1 winding prepreg machine, according to [45 / 0 / -45 / 90] 4S The method is quasi-isotropic layering, and it is molded and cured on a hot press. The molding process: from room temperature to 205 ℃ ~ 210 ℃, after holding for 2 hours, heating to 240 ℃ ~ 250 ℃ for 1 hour, pressurizing to 1.5 MPa ~ 2 MPa , then heat up to 300 °C for 2 hours, then heat up to 325 °C for 1 hour, and finally cool to below 60 °C to open the mold. The heating rate is 1.0°C / min to 2.0°C / min.

[0039] Prepare the same prepreg as the low toughness composite, also press [45 / 0 / -45 / 90] 4S The method is quasi-isotropic layup. In the laying process, the carbon nanotube non-woven fabric is directly attached to the surface of the polyimide prepreg, and a layer of carbon nanotube non-woven fabric is ensured between the two layers of prepreg. It is cured and formed in an autoclave a...

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Abstract

The invention belongs to the advanced composite material preparing technology and relates to a preparation method for carbon nanotube non-woven fabric interlayer modified fiber reinforced composite materials. The method includes: enabling carbon nanotube non-woven fabric to enter resin rich areas of the layers of fiber reinforced thermosetting resin base composite materials in direct intercalation mode, using an autoclave molding process or a liquid forming process, and preparing interlayer the interlayer modified composite materials according to an original curing process of matrix resin. The carbon nanotube non-woven fabric can enter weak interlayer areas of the composite materials through direct intercalation mode, has no influence on flow of the resin in the curing process and a liquid forming process of the matrix resin, and simultaneously a network structure formed by carbon nanotubes in an interlayer can effectively prevent interlayer microcracks from being formed and extending, thereby improving strengthening-toughening performance of interlayer of the composite materials, obtaining high impact damage resistance and high damage tolerance, and covering a temperature range of typical aerospace composite structure application, in particular to a more than 300 DEG C high temperature range.

Description

Technical field [0001] The invention belongs to the preparation technology of composite materials and relates to a method for preparing modified continuous fiber composite materials between carbon nanotube non-woven fabric layers. Background technique [0002] In the new generation of aerospace vehicles, fiber-reinforced resin-based composite materials account for a significantly larger proportion of the structural weight and are used in a wider range of applications. Therefore, the requirements for material toughness have become increasingly prominent. In particular, the problem of insufficient interlayer toughness and limited impact damage resistance of composite materials has been a hot topic of research for a long time. To solve this problem, a variety of improvement measures have been proposed. Currently, the most widely used toughening method is to add rubber or thermoplastic resin to thermosetting resin to form a phase-separated structure through reaction-induced phas...

Claims

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Application Information

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IPC IPC(8): C08J5/00C08J5/04C08L63/00C08L79/08C08L61/06C08L79/04C08L67/06C08K9/00C08K3/04
Inventor 刘刚张朋陈名海李清文包建文益小苏
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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