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Composite airfoil sandwich structure and forming method thereof

A sandwich structure and composite material technology, which is applied in other household appliances, household appliances, household components, etc., to achieve the effect of satisfying structural strength design, ensuring consistency, and ensuring compliance

Active Publication Date: 2020-04-10
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] In order to solve the technical problems existing in the application of the existing sandwich sandwich structure to composite airfoil products, the present invention provides a composite airfoil sandwich structure and its forming method

Method used

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  • Composite airfoil sandwich structure and forming method thereof
  • Composite airfoil sandwich structure and forming method thereof
  • Composite airfoil sandwich structure and forming method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0058] Forming a composite material wing "sandwich" weight-reducing structure includes the following steps:

[0059] ①Set the density to 110kg / m 3 The Degussa PMI foam is tested for compressive strength, and the compressive strength of the foam is required to be not less than 1.9MPa at 130°C, and it can be used only after passing the test.

[0060] ②Machining the qualified foam figure 1 shape.

[0061] ③Put the foam in wing root zone Ⅰ according to figure 2 The shape of the foam is pre-cut into three pieces; after drying the machine-added foam in an oven at 130°C±5°C for 3 hours, use a hair dryer to clean the surface debris.

[0062] ④Apply a layer of J-47B glue evenly on the surface of the foam, let it dry for 20-30 minutes, and stick a layer of J-47A glue film.

[0063] ⑤Wrap each of the three pieces of pre-cut foam in wing root area Ⅰ with 4 layers of carbon fiber prepreg (T700 / 9368 prepreg), lay up [90 / 90 / 0 / 90], and then combine the three pieces of foam with Ⅱ ~ The ...

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Abstract

The invention relates to a composite airfoil sandwich structure and a forming method thereof. The method comprises the following steps of machining a foam core material into I, II, III and IV area foam core materials with the thicknesses gradually increased from a wing root to a wing tip; conducting foam surface bonding preparation; coating each piece of foam pre-cut in the area I with four layersof prepregs, conducting paving [90 / 90 / 0 / 90], and conducting combining with the foam core materials in the areas II to IV into a whole; wholly wrapping the I and II area foam with 4 layers of prepregs, conducting paving [90 / 0 / 90 / 90], wholly wrapping the I, II and III areas with 4 layers of prepregs, conducting paving [90 / 0 / 90 / 90], and finally wholly wrapping the I, II, III and IV areas with 4 layers of prepregs, and conducting paving [90 / 90 / 0 / 90]; and conducting foam-reinforced cure molding. By means of the composite airfoil sandwich structure and the forming method, panels on the two sides ofthe wing root are the thickest, panels on the two sides of the wing tip are the thinnest, the compressive deformation resistance of the core materials can be improved, the weight reduction function is achieved, and the structural strength design requirement is met.

Description

technical field [0001] The invention belongs to the technical field of composite material forming, and in particular relates to a composite material airfoil-like sandwich structure and a forming method thereof. Background technique [0002] The composite material of the fuselage can greatly reduce the weight, increase the fuel capacity of the aircraft, and effectively improve the performance of the flight range and fuel economy. It has become the development direction of advanced structural materials for aerospace. [0003] The structural configuration design of composite materials is flexible and changeable, and the sandwich structure is also an important weight-reducing structural method. The sandwich structure is to attach thin panels with sufficient rigidity on both sides of a relatively thick core material. When this structure is subjected to a bending load, there is a certain distance between the upper and lower panels, and a larger proportion of the structure can be o...

Claims

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Application Information

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IPC IPC(8): B29C70/22B29C70/34B29C70/46B29C70/54B29L31/30
CPCB29C70/228B29C70/345B29C70/462B29C70/54B29L2031/3085
Inventor 韩蕾龚文化袁一博卢山李丽英王国勇柳晓辉
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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