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Method for preparing rigid three-dimensional crystal whisker interlayer modified continuous fiber composite material

A continuous fiber and composite material technology, applied in the field of composite material preparation, can solve problems such as difficulties

Active Publication Date: 2009-05-06
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, it is difficult to overcome the complex polymer-polymer multi-phase or multi-phase systems, the material chemical limitations of the phase transition of multi-phase materials, precise control of thermal reaction-induced destabilization phase separation kinetics, and selection of polymer-polymer pairings.

Method used

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  • Method for preparing rigid three-dimensional crystal whisker interlayer modified continuous fiber composite material
  • Method for preparing rigid three-dimensional crystal whisker interlayer modified continuous fiber composite material

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0026] The four needle-shaped zinc oxide whiskers that were vacuum-dried at 100°C for 2 hours were deposited on the surface of high-strength alkali-free glass fiber fabric SW280 through a 60-mesh mechanical vibrating sieve, according to [(0 / 90)] 8 The method is anisotropic layering, and the zinc oxide whisker content between the two layers of fibers is guaranteed to be 5g / m 2 , Clamping. Press the typical aviation epoxy resin system E into the closed mold with a pressure of 0.1MPa to complete the mold filling.

[0027] After the mold filling process is completed, the mold is kept closed, and heating initiates the curing reaction of the epoxy resin of the closed mold. Curing conditions: at a heating rate of 2°C / min, the temperature was raised from room temperature to 180°C under normal pressure, kept at a temperature of 2h, and at the same time kept at a pressure of 0.20Mpa for 2h. Then, raise the temperature from 180°C to 200°C at the same rate, and increase the pressure fro...

Embodiment 2

[0033] The tetraacicular zinc oxide whiskers, which were vacuum-dried at 100°C for 2 hours, were deposited on the surface of continuous glass fiber fabric SW280 through a 60-mesh mechanical vibrating sieve, according to [(0 / 90)] 8 The method is anisotropic layering, and the zinc oxide whisker content between the two layers of fibers is guaranteed to be 5g / m 2 , Clamping. Press the typical aerospace epoxy resin system 3xxx into the closed mold with a pressure of 0.1MPa to complete the mold filling.

[0034] After the mold filling process is completed, the mold is kept closed, and heating initiates the curing reaction of the epoxy resin of the closed mold. Curing conditions: at a heating rate of 2°C / min, the temperature is raised from room temperature to 80°C under normal pressure, kept for 4 hours, and at the same time, the pressure is kept at 0.20Mpa for 2 hours. Then, raise the temperature from 80°C to 120°C at the same rate, and increase the pressure from 0.20MPa to 0.40MP...

Embodiment 3

[0040] The tetraacicular zinc oxide whiskers, which were vacuum-dried at 100°C for 2 hours, were deposited on the surface of the continuous carbon fiber fabric U-3160 through a 60-mesh mechanical vibrating sieve, according to [0] 12 The method is anisotropic layering, and the zinc oxide whisker content between the two layers of fibers is guaranteed to be 5g / m 2 , Clamping. The typical aviation RTM molding process bismaleimide (BMI) resin is pressed into the closed mold with a pressure of 0.1MPa to complete the mold filling.

[0041] After the mold filling process is completed, the mold is kept closed, and the curing reaction of the resin in the closed mold is initiated by heating. Curing conditions: at a heating rate of 2°C / min, the temperature is raised from room temperature to 130°C under normal pressure, kept at a temperature of 1h, and at the same time, the pressure is kept at 0.20MPa for one hour. Then, raise the temperature from 130°C to 190°C at the same rate, and inc...

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Abstract

The invention belongs to a technology for preparing composite materials and relates to a method for preparing rigid three-dimensional crystal whisker interlaminar modified continuous fiber composite materials. The interlaminar modified thermosetting resin composite materials are prepared by the following method by adoption of a micron-scale heteropical rigid micro 3-3 structure and adoption of a four-pin zinc oxide crystal whisker as an interlaminar reinforcement: firstly, the four-pin zinc oxide crystal whisker which is subjected to vacuum drying for 2 hours at a temperature of 100 DEG C is deposited on the surface of fabrics by means of a mechanical vibrating screen or electrostatic adherence or deposition through a fluidized bed or powdering through a drum-type silk screen, and modified fabrics are obtained; and secondly, after the modified fabrics are laid as required, the resin transfer molding technology or the resin membrane permeation technology is utilized for preparing the composite materials by the prior matrix resin solidifying technology. The method can improve the strong interlaminar toughening performance of the composite materials, obtain high surge impedance and high damaged tolerance, and cover the temperature range of structural application of typical aerospace composite materials and particularly cover the high temperature range of more than 300 DEG C.

Description

technical field [0001] The invention belongs to the preparation technology of composite materials, and relates to a preparation method of a rigid three-dimensional whisker interlayer modified continuous fiber composite material. 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. H...

Claims

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Application Information

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IPC IPC(8): C08J5/06C08L63/00C08L79/08C08L61/06C08L79/02C08L79/04C08L67/06C08K9/02B29C70/34
Inventor 益小苏刘刚马宏毅张代军安学锋
Owner BEIJING AVIATION MATERIAL INST NO 1 GRP CORP CHINA AVIATION IND
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