Compression molding method for variable cross-section carbon fiber composite material missile wing
A composite material and compression molding technology, which is applied in the field of carbon fiber composite material wing molding, can solve the problems of debonding of the connecting part and complicated layup process, achieve good specific strength and specific stiffness, improve safety and reliability, and save Effect of Enhanced Features
Active Publication Date: 2021-07-30
绍兴宝旌复合材料有限公司 +1
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Problems solved by technology
There are many types of layup angles and layup sequences used in composite projectile wings, and the layup process is complicated
The connection interface between the embedded aluminum metal parts and the foam is weak, and there is a risk of debonding as a connection part
Method used
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Embodiment 1
[0029] 1) Dip Chem-Trend’s release agent with a clean white cotton cloth, and wipe the entire surface of the mold cavity, and do this 3 to 5 times, each time at an interval of 15 to 20 minutes, and the last time it is left for more than 30 minutes.
[0030] 2) Lay the cut prepreg sheets, and pave the surface layer carbon fiber 3K twill prepreg on the surface of the upper mold and the lower mold, and the laying angle is ±45°. When the first layer of prepreg is laid, depending on the condition of the laying, the mold can be heated to improve the stickiness of the prepreg. The heating process is 80°C*30min. The surface layer requires the texture to be as continuous as possible, and can be properly cut.
[0031] 3) Lay reinforcement strips on the flat mold according to the best layup angle and layup sequence, and cut the laid reinforcement strips into appropriate sizes according to the size of the reinforcement area in the mold and place them on the upper and lower molds of the fo...
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The invention relates to a compression molding method for a variable cross-section carbon fiber composite missile wing. The method comprises the following steps: firstly, respectively paving a surface layer carbon fiber 3K twill prepreg on an upper die and a lower die of a forming die; then, laying reinforcing strips on a flat plate die according to the optimal laying layer angle and laying layer sequence; according to the size of a reinforcing area in the die, cutting the laid reinforcing strips into appropriate sizes and placing them in the upper die and the lower die of the forming die, wherein at the moment, vacuumizing and pre-compaction are required; finally, laying the profile on the lower die of the forming die according to the optimal laying layer angle and laying layer sequence, wherein in the laying process, different layers are laid according to the staggered layer size requirement; after the layering process is completed, putting the upper die and the lower die into a press for molding and curing; and finally, using a numerical control machining mode for machining trimming of the missile wing root and punching of a clamping area. The strength and rigidity of the prepared missile wing meet the requirements, the production efficiency is high, batch production can be achieved, and the quality stability and the size consistency are good.
Description
technical field [0001] The invention relates to the technical field of forming wings of carbon fiber composite materials, in particular to a compression molding method for wings of variable cross-section carbon fiber composite materials. Background technique [0002] As a new type of high-performance material, carbon fiber composites are widely used in high-tech fields such as aerospace, rail transit, and new energy vehicles. At present, the molding processes for preparing carbon fiber composite panels mainly include prepreg-autoclave molding process, compression molding process, hand lay-up molding process, resin transfer molding molding process, vacuum introduction molding process, etc. Compared with other molding processes, compression molding has higher production efficiency and is suitable for mass production. The size of the product is accurate, the surface is smooth, and it can have two refined surfaces. Most products with complex structures can be formed at one time ...
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IPC IPC(8): B29C70/34B29C70/54
CPCB29C70/342B29C70/54
Inventor 张继涛赵丽民高艳
Owner 绍兴宝旌复合材料有限公司