Edge strip slender composite material airfoil and forming method thereof

A composite material and molding method technology, which is applied to other household appliances, household appliances, household components, etc., can solve the problems of low material utilization, high density, easy deformation during processing, etc., and achieve improved interlayer performance and high fiber volume content , Good molding quality effect

Active Publication Date: 2022-07-29
SHANGHAI COMPOSITES SCI & TECH CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, for the slender wing structure mentioned in this article, the aluminum alloy material is the main material, and the use of this material to manufacture the slender wing surface has the disadvantages of easy deformation during processing, low material utilization rate and high density. and other shortcomings

Method used

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  • Edge strip slender composite material airfoil and forming method thereof
  • Edge strip slender composite material airfoil and forming method thereof
  • Edge strip slender composite material airfoil and forming method thereof

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Embodiment Construction

[0020] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the inventive concept. These all belong to the protection scope of the present invention.

[0021] According to the molding method of the slender composite material airfoil provided by the present invention, the airfoil is subjected to Z-direction stitching and toughening after the carbon fiber UD cloth is laid, and a prefabricated reinforcement is injected with resin based on an autoclave and cured. The autoclave / VARTM combination process molding.

[0022] Preferably, the airfoil is integrally formed by integral lamination, and the thickness and shape of the airfoil are ensured by a mold, and seconda...

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Abstract

The invention provides a side strip slender composite material airfoil and a molding method thereof. The side strip slender composite material airfoil is layered symmetrically in a stepped shape at the center of the cross-section through carbon fiber UD cloth, and Z-direction stitching is performed after the layers are laid for toughening. , using a combined autoclave / VARTM process based on autoclave injection of resin into prefabricated reinforcements and curing. Aiming at the slender composite material airfoil of the edge strip, the invention adopts the integrated molding of the overall layering, the layering is stitched and toughened in the Z direction, and is formed by the autoclave / VARTM process, which makes up for the poor interlayer performance of the products prepared by the traditional layering process. The weak defect improves the interlayer performance, maintains a high fiber volume content and product molding quality, and ensures the comprehensive performance of the composite airfoil.

Description

technical field [0001] The present invention relates to the technical field of composite material forming, in particular, to an airfoil of slender edge strips and a forming method thereof. Background technique [0002] With the development of aerospace technology, the development trend of flying missiles includes characteristics such as long range, fast speed, and good maneuverability, which also determines that the missile must take the road of light weight. Composite materials have high specific modulus and specific strength, and the composite materialization of missile structures is one of the ways to lighten the weight of airborne missiles. As a part of the missile, the lightweight realization of the wing plays a positive role in reducing the weight of the aircraft, increasing the range and payload, and improving the maneuverability of the aircraft system. [0003] At present, relevant personnel have carried out a lot of composite material research on the smaller missil...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/34B29C70/36B29C70/54B29L31/30
CPCB29C70/342B29C70/345B29C70/36B29C70/54B29L2031/3097
Inventor 梁燕民周涛吴鑫锐章宇界史文锋叶周军董斌杨赟左龙彦翟东坤
Owner SHANGHAI COMPOSITES SCI & TECH CO LTD
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