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A kind of co-curable lightweight high-rigidity core material for composite material sandwich structure and its preparation method and application

A composite material and sandwich structure technology, which is applied in the field of co-curable lightweight high-rigidity core material and its preparation, can solve the problems of co-curing molding, not meeting the requirements of molding process, increasing the weight of structural parts, etc., and achieve excellent moisture and heat resistance , good rigidity, and the effect of reducing the cost of the manufacturing process

Active Publication Date: 2019-10-08
INST OF PETROCHEM HEILONGJIANG ACADEMY OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The above sandwich structures cannot be co-cured with prepregs. For complex shaped parts, they do not meet the molding process requirements. In addition, these structures do not meet the design requirements for the parts where the strength of the sandwich structure needs to be increased. Therefore, prepregs are used in these areas. The way of laying up the parts is completed, and the molding process and strength meet the requirements of the structural parts, but this method increases the weight of the structural parts

Method used

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  • A kind of co-curable lightweight high-rigidity core material for composite material sandwich structure and its preparation method and application
  • A kind of co-curable lightweight high-rigidity core material for composite material sandwich structure and its preparation method and application
  • A kind of co-curable lightweight high-rigidity core material for composite material sandwich structure and its preparation method and application

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specific Embodiment approach 1

[0018] Specific embodiment 1: A co-curable lightweight high-rigidity core material according to this embodiment, it is composed of 70-100 parts by mass of main resin, 10-30 parts of toughening material, 20-50 parts of Made of lightweight materials, 10-33 parts of curing agent, 2-15 parts of filler and 1-3 parts of silane coupling agent;

[0019] Among them, the main resin is a mixture of epoxy resin with high glass transition temperature, common type epoxy resin and epoxy diluent in any ratio, and the epoxy resin with high glass transition temperature is composed of 1,1,1-Triphenylethane glycidyl ether, 2,2'-[(1,1-cyclohexyl(4,1-diphenyl)dioxy)bismethyl]dioxirane, 8,8'-bis(2,3-epoxypropoxy)-1,1'-binaphthyl, N,N,N,N-tetraglycidyl-4,4'-diaminodiphenylmethane and One or more of N,N,O-triglycidyl p-aminophenols are composed in any ratio; common epoxy resins include bisphenol A type epoxy resin, bisphenol F type epoxy resin, novolac epoxy resin One or more of the resins are compo...

specific Embodiment approach 2

[0025] Specific embodiment 2: The difference between this embodiment and specific embodiment 1 is that the co-curable lightweight high-rigidity core material is composed of 80-90 parts by mass of main resin, 15-20 parts of toughening agent, 30 parts by mass. 40 parts of lightweight material, 10 to 33 parts of curing agent, 5 to 12 parts of inorganic filler and 1 to 3 parts of silane coupling agent. Other steps and parameters are the same as those in Embodiment 1.

specific Embodiment approach 3

[0026] Embodiment 3: The difference between this embodiment and Embodiment 1 or 2 is that the co-curable lightweight high-rigidity core material consists of 90 parts by mass of main resin, 20 parts of toughening agent, and 40 parts of Made of lightweight materials, 25 parts of curing agent, 5 parts of filler and 2 parts of silane coupling agent. Other steps and parameters are the same as those in Embodiment 1 or Embodiment 2.

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Abstract

The invention provides a light-weight high-rigidity core material capable of realizing co-curing for a composite material sandwich structure, and a preparation method and application thereof, and relates to a light-weight high-rigidity core material capable of realizing co-curing, and a preparation method and application thereof. In order to solve the problems that the forming process of a complicated shape thin-wall composite material sandwich structure is difficult, and the thickness of the sandwich structure edge needs to be increased, the invention provides the light-weight high-rigidity core material capable of realizing co-curing, and meanwhile, the use of adhesives between a composite material panel and the core material is avoided. The core material is prepared from main body resin, a toughening agent, a light-weight material, a curing agent and filler. The preparation method comprises the steps that the main body resin, the toughening agent, the light-weight material, the curing agent and the filler are uniformly mixed to obtain a glue material; the glue material is preheated in a drying box; then, the glue material is subjected to hot pressure calendaring to form a film by a carrier on a glue film calendaring machine, i.e., the light-weight core material is obtained. The core material is used for preparing high-temperature-resistant composite material structural components in the aerospace field.

Description

technical field [0001] The invention relates to a co-curable lightweight high-rigidity core material and a preparation method thereof. Background technique [0002] The sandwich structure is widely used in the weight reduction design of structural parts due to its excellent specific strength, good heat resistance, and impact resistance. At present, there are mainly PMI foam sandwich structures and honeycomb sandwich structures such as aluminum honeycomb, paper honeycomb, etc. . However, these structures encounter some problems in application. For example, when there are cracks and gaps in the panels of the honeycomb sandwich structure, water and water vapor will enter the honeycomb cells, destroying the bonding of adjacent honeycomb cells and reducing the performance of the sandwich structure. The above sandwich structures cannot be co-cured with prepregs. For complex shaped parts, they do not meet the molding process requirements. In addition, these structures do not meet ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C08L63/00C08L79/08C08K7/28C08K3/36C08K5/54C08G59/50
Inventor 李洪峰曲春艳王德志张杨宿凯杨海冬刘长威肖万宝王海民杜程
Owner INST OF PETROCHEM HEILONGJIANG ACADEMY OF SCI
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