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A kind of preparation method of high temperature resistant composite cabin section

A composite material, high temperature resistant technology, used in other household appliances, coatings, household appliances, etc., can solve the problems of reducing porosity, high volatile content, and difficult molding.

Active Publication Date: 2021-10-01
长春长光宇航复合材料有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The invention provides a method for preparing a high-temperature-resistant composite material cabin section. After laying a certain number of layers of prepreg, the solvent is removed, and after the laying is completed, the autoclave-vacuum bag technology is used for curing. The purpose of the present invention is to solve the problem of high volatile matter and difficult molding in the molding process of polyimide composite materials, and can reduce the void ratio of the product and realize the application of the composite cabin section at high temperature

Method used

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  • A kind of preparation method of high temperature resistant composite cabin section
  • A kind of preparation method of high temperature resistant composite cabin section
  • A kind of preparation method of high temperature resistant composite cabin section

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preparation example Construction

[0030] The invention provides a method for preparing a high-temperature-resistant composite cabin section, comprising the following steps:

[0031] (1) Make composite material cabin forming molds. The forming mold includes a split valve with a reinforced area and an end frame, a core mold, and upper and lower cover plates.

[0032] (2) Preparation of prepreg.

[0033] Prepare carbon fiber / polyimide composite material, use carbon fiber / polyimide composite material as raw material, prepare with DMAc as solvent prepreg, use DMAc as solvent to enhance the wettability of resin to fiber; the carbon fiber / polyimide In the imine composite material, the volume content of carbon fiber is 57% to 63%.

[0034] The prepreg adopts unidirectional fiber reinforced prepreg or fiber fabric reinforced prepreg.

[0035] (3) laying prepreg. Use prepreg to lay the thickened area, end frame and skin, and remove the solvent once every 8 layers are laid, and then use the porous isolation film, suc...

Embodiment

[0045] Composite material compartment is prepared according to the method provided in the present invention, and specific implementation method is as follows:

[0046] (1) Make composite material cabin forming molds, such as figure 1 As shown, the composite cabin section includes a mold mandrel 110 and a mold split 120;

[0047] (2) Prepare carbon fiber / polyimide composite material, DMAc is used as a solvent, and the volume content of carbon fiber is 57%-63%.

[0048] (3) laying prepreg. Use prepreg to lay the thickening area, end frame and skin, and remove the solvent once every 8 layers are laid, and then use the porous isolation film, suction felt, air guide felt and vacuum bag to cover the product and vacuumize. Rise to 200°C at a constant temperature for 1 hour at a rate of 0.02°C / min; wherein, the vacuum degree in the vacuum bag is ≥0.9.

[0049] (4) Removal of residual solvent. Use porous isolation film, suction felt, air guide felt and vacuum bag to cover the produ...

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Abstract

The invention discloses a method for preparing a high-temperature-resistant composite material compartment, comprising: step 1, preparing a prepreg; step 2, using the prepreg to lay a thickening area, an end frame and a skin; wherein, in During the prepreg laying process, the solvent is removed once after laying the set number of layers; step 3, after the laying is completed, place the product in an autoclave to remove the remaining solvent; step 4, use vacuum material products After coating the product, curing is carried out; Step 5, after demoulding, high-temperature treatment is carried out in a curing furnace to obtain the high-temperature-resistant composite cabin section; wherein, the temperature of the high-temperature treatment is 400-420°C. The preparation method of the high-temperature-resistant composite cabin section provided by the present invention, after laying a certain number of layers of prepreg, removes the solvent, and after the laying is completed, uses the autoclave-vacuum bag technology to cure; can Reduce the void ratio of the product and realize the application of the composite cabin section under high temperature conditions.

Description

technical field [0001] The invention belongs to the technical field of composite material compartment forming technology, and in particular relates to a preparation method of a high-temperature-resistant composite material compartment. Background technique [0002] Fiber-reinforced composite materials have been more and more widely used in the aviation field, and the application scenarios are becoming more and more diverse, and the requirements for the heat resistance of the cabin body are also increasing. Fiber-reinforced thermosetting polyimide resin composite materials have the advantages of high strength, light weight, high temperature resistance, low temperature resistance, and corrosion resistance. In order to meet the needs of lightweight cabins and high heat resistance, polyimide resin composite materials application will be more extensive. [0003] As a temperature-resistant 400°C polyimide composite cabin section with end frame structure and thickened area, the pr...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/44B29B15/12B29K79/00B29L31/30B29K105/10
CPCB29B15/125B29C70/443B29C70/446B29K2079/08B29K2105/0881B29L2031/3097
Inventor 刘永琪丛非李玉龙王泽亮林再文
Owner 长春长光宇航复合材料有限公司