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

A technology of carbon nanotubes and composite materials, which is applied in the field of preparation of carbon nanotube non-woven interlayer modified continuous fiber composite materials, which can solve the problems of reducing the modification effect of carbon nanotubes and the destruction of carbon nanotube structures

Inactive Publication Date: 2014-05-14
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 on severe chemical reactions and strong mechanical dispersion methods will cause damage to the carbon nanotubes themselves. The structure causes a certain degree of damage, thereby reducing the modification effect of carbon nanotubes

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

[0029] First prepare the low-toughness epoxy resin composite material as the matrix material: T300 / epoxy resin prepreg is prepared by wet method with TB-1 type winding prepreg (the epoxy resin composition is E-54:AG-80:DDS= 40:60:40), according to [45 / 0 / -45 / 90] 4S way of quasi-isotropic layup. Curing and molding in an autoclave, molding process: vacuumize the whole process to 0.095MPa, heat up from room temperature to 130°C, keep warm for 0.5h, pressurize to 0.55MPa~0.6MPa, then heat up to 180°C for 2h, then heat up to 200 ℃ for 2 hours, and finally cooled naturally to below 60 ℃. The heating rate is 1.0°C / min~2.0°C / min.

[0030] Prepare the same prepreg as the low toughness composite material, also according to [45 / 0 / -45 / 90] 4S way of quasi-isotropic layup. During the paving process, the carbon nanotube non-woven fabric is directly pasted on the surface of the epoxy prepreg, and a layer of carbon nanotube non-woven fabric is ensured between the two layers of prepreg. It ...

Embodiment 2

[0033]First prepare the low-toughness bismaleimide composite material as the matrix material: T700 / bismaleimide prepreg is prepared by wet method with TB-1 winding prepreg machine, according to [45 / 0 / -45 / 90] 4S The method is quasi-isotropic layering, autoclave curing molding, molding process: from room temperature to 180°C, when the temperature rises to 120°C, pressurize to 0.4MPa, when the temperature rises to 160°C, pressurize to 0.7MPa; Keep warm for 3 hours at 180°C, continue to heat up to 200°C for 5 hours, vacuumize the whole process, and finally cool naturally below 60°C to open the mold. The heating rate is 1.5°C / min to 2.0°C / min.

[0034] Prepare the same prepreg as the low toughness composite material, also according to [45 / 0 / -45 / 90] 4S way of quasi-isotropic layup. During the laying process, the carbon nanotube non-woven fabric is directly pasted on the surface of the Shuangma prepreg, and a layer of carbon nanotube non-woven fabric is ensured between the two lay...

Embodiment 3

[0037] First prepare the low-toughness polyimide composite material as the matrix material: use the TB-1 type winding prepreg machine to prepare T300 / polyimide prepreg by wet method, according to [45 / 0 / -45 / 90] 4S The method is quasi-isotropic layering, molded and solidified on a hot press, molding process: from room temperature to 205 ° C ~ 210 ° C, after 2 hours of heat preservation, the temperature is raised to 240 ° C ~ 250 ° C for 1 hour, pressurized to 1.5 MPa ~ 2 MPa , then raise the temperature to 300°C for 2 hours, then raise the temperature to 325°C for 1 hour, and finally cool naturally to below 60°C to open the mold. The heating rate is 1.0°C / min~2.0°C / min.

[0038] Prepare the same prepreg as the low toughness composite material, also according to [45 / 0 / -45 / 90] 4S way of quasi-isotropic layup. During the laying process, the carbon nanotube non-woven fabric is directly pasted on the surface of the polyimide prepreg, and a layer of carbon nanotube non-woven fabric ...

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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 preparation method of carbon nanotube non-woven interlayer modified continuous fiber composite materials. Background technique [0002] In the new generation of aerospace vehicles, the proportion of fiber-reinforced resin-based composite materials in the structural weight has increased significantly, and the use of parts has become more extensive, so the requirements for material toughness have become increasingly prominent. Especially for the problem of insufficient interlayer toughness and limited impact damage resistance of composite materials, it has been a research hotspot for a long time. To solve this problem, a variety of improvement measures have been proposed. The most widely used toughening method is to add rubber or thermoplastic resin to the thermosetting resin to form a phase-separated structure through reaction-induced phase separation. However,...

Claims

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Application Information

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Patent Type & Authority Patents(China)
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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