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Processing method for large-thickness composite skirt

A processing method and composite material technology, which are applied in the field of resin-based fiber reinforced composite material prepreg autoclave molding, can solve problems such as poor quality stability, and achieve the goal of improving quality, compacting tightness, and improving interlayer bonding quality. Effect

Inactive Publication Date: 2019-06-07
成都联科航空技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a simple process that can improve the compaction degree between the prepreg layers of the large-thickness composite skirt product in order to solve the problem of poor quality stability of the large-thickness composite skirt product in the prior art. , reduce the internal porosity and delamination defects of the product, effectively ensure the surface quality of the product, and prevent the mechanical properties from decreasing due to internal fiber folds

Method used

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  • Processing method for large-thickness composite skirt
  • Processing method for large-thickness composite skirt
  • Processing method for large-thickness composite skirt

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0028] see Figure 1-7 . The embodiment of the present invention provides a method for processing a large-thickness composite material skirt 1 . The processing method of this composite material skirt 1 comprises the following steps:

[0029] S1. Prepare materials: thaw the composite material sheet, and cut the composite material sheet.

[0030] S2. Preparation of the mold 2: cleaning the mold 2, and applying a release agent on the mold 2. After the processing is completed, the demoulding process can be conveniently carried out.

[0031] S3. Laying: the steps of laying include:

[0032] S31. Design a lay-up scheme;

[0033] S32. Laying the composite material on the mold 2 according to the laying plan.

[0034] specific:

[0035] S31. Design the lay-up plan: first establish the three-dimensional model of the composite material skirt 1 through three-dimensional modeling software, then analyze the structural characteristics and load conditions of the composite material skir...

Embodiment 2

[0050] The embodiment of the present invention provides a processing method for a large-thickness composite skirt 1, which is basically the same as the processing method provided in Embodiment 1, the difference is that in the embodiment of the present invention, in the laying process , the composite skirt 1 is pre-compacted by hot-pressing pre-compacting method.

[0051] Specifically, the processing method of the composite skirt 1 provided in the embodiment of the present invention includes:

[0052] S1. Prepare materials: thaw the composite material sheet, and cut the composite material sheet.

[0053] S2. Preparation of the mold 2: cleaning the mold 2, and applying a release agent on the mold 2. After the processing is completed, the demoulding process can be conveniently carried out.

[0054] S3. Laying: the steps of laying include:

[0055] S31. Design a lay-up scheme;

[0056] S32. Laying the composite material on the mold 2 according to the laying plan.

[0057] In ...

Embodiment 3

[0065] This embodiment provides a processing method for a large-thickness composite skirt 1, which is basically the same as the processing method provided in Embodiment 1, the difference being that in the embodiment of the present invention, during the lay-up process, The pre-compaction of the composite skirt 1 is carried out by two methods of normal temperature pre-compaction and hot-press pre-compaction.

[0066] Specifically, the processing method of the composite skirt 1 provided in the embodiment of the present invention includes:

[0067] S1. Prepare materials: thaw the composite material sheet, and cut the composite material sheet.

[0068] S2. Preparation of the mold 2: cleaning the mold 2, and applying a release agent on the mold 2. After the processing is completed, the demoulding process can be conveniently carried out.

[0069] S3. Laying: the steps of laying include:

[0070] S31. Design a lay-up scheme;

[0071] S32. Laying the composite material on the mold ...

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Abstract

The invention relates to the technical field of pre-immersed hot-pressing tank molding of resin-based fiber-reinforced composite materials, in particular to a processing method for a large-thickness composite skirt. The processing method comprises the following steps of the material preparation; the mold preparation; the stacking; the assembly and bag sealing; the curing; and the demoulding and ischaracterized in that in the stacking process, after stacking the composite material with the pre-set thickness, the composite material and the whole mold are pre-compacted. By means of the processing method, in the stacking process, the composite material is pre-compacted, the bubbles between the composite layers can be effectively eliminated, the bonding quality between the layers is improved,and the compacting of the composite billet is more tight, and the quality of the composite skirt is improved accordingly.

Description

technical field [0001] The invention relates to the technical field of autoclave molding of resin-based fiber-reinforced composite material prepregs, in particular to a processing method for a large-thickness composite skirt. Background technique [0002] The rocket / missile engine casing must be connected to the interstage or to other components by relying on the casing interstage composite material skirt to effectively realize the interstage thrust transmission. The composite material skirt bears various loads such as axial tension, axial compression, hoop tension, bending, shearing, etc., and the load conditions are complex; the composite material has low density, high specific strength, high specific modulus, and corrosion resistance Good and other advantages, are widely used in the aerospace field. The autoclave method is the main method for preparing high-performance aerospace composite materials; this method has been successfully applied to the molding of rocket / missi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/34
Inventor 李书军陈剑尹军华杨自燕周才超石小平谷雨
Owner 成都联科航空技术有限公司
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