Wire nozzle structure and method of use for wet forming prepreg

A wet forming and prepreg technology, which is applied in the field of composite material forming, can solve the problems of affecting the design of composite material layup structure, reducing the utilization rate of prepreg material, single nozzle structure, etc., so as to improve uniformity and layup. Design flexibility, meet fine manufacturing requirements, and improve the effect of manufacturing efficiency

Active Publication Date: 2019-09-17
SHANGHAI COMPOSITES SCI & TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, at present, the wire nozzle structure of prepreg preparation equipment by wet method is single, and it is difficult to prepare thin prepregs, which seriously affects the design of composite material layup structures, and it is difficult to meet the needs of composite products with complex structures on satellites for prepregs of different thicknesses. In the prepreg preparation process, the large-tow carbon fiber preparation process has a serious yarn spreading problem, and white spots appear in the middle of the prepreg, which reduces the utilization rate of the prepreg

Method used

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  • Wire nozzle structure and method of use for wet forming prepreg
  • Wire nozzle structure and method of use for wet forming prepreg
  • Wire nozzle structure and method of use for wet forming prepreg

Examples

Experimental program
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Effect test

Embodiment 1

[0041] This embodiment provides a wire nozzle structure for wet forming carbon fiber reinforced resin-based composite material prepreg and its use method. The wire nozzle structure is as follows Figure 1-7 As shown, it includes a support module 1, a dipping module 5, a pre-spreading module 3 and a spreading module 4; the support module 1 includes a side plate and a bottom plate; the dipping module 5, a pre-spreading module 3 and a spreading module 4 The side plates are sequentially arranged on the side plates along the horizontal direction of the side plates.

[0042] The pre-spreading module 3 includes two connecting disks 6 and a pre-spreading roller arranged between the two connecting disks 6 .

[0043] The pre-expanding rolls include concave pre-spreading rolls 9, convex pre-spreading rolls 7 and plane pre-spreading rolls 8; set uniformly in the circumferential direction.

[0044] The end surface diameters of the concave pre-spreading roll 9, the convex pre-spreading ro...

Embodiment 2

[0061] This embodiment provides a high modulus carbon fiber / epoxy resin prepreg prepared by adopting the wire nozzle structure described in embodiment 1 for wet forming carbon fiber reinforced resin matrix composite material prepreg, and its molding method includes the following step:

[0062] S1. According to the clear requirements of the process design documents, the theoretical single-layer thickness of the high-modulus carbon fiber prepreg of the composite material is 0.2mm. The linear density of high modulus carbon fiber is 230 (g / km), and the density of carbon fiber is 2.04 (g / cm 3 ), the carbon fiber volume fraction is 60%. The width of the original fiber bundle is 1.8mm. According to the requirements of the yarn sheet width of 0.9mm, a concave pre-spread roller is required.

[0063] In the pre-spreading module, the section curvature of the concave pre-spreading roller is calculated as follows:

[0064]

[0065] Among them, the angle corresponding to the spreading...

Embodiment 3

[0078] This embodiment provides a high modulus carbon fiber / epoxy resin prepreg prepared by adopting the wire nozzle structure described in embodiment 1 for wet forming carbon fiber reinforced resin matrix composite material prepreg, and its molding method includes the following step:

[0079] S1. The theoretical single-layer thickness of the high-modulus carbon fiber prepreg of composite materials prepared according to the clear requirements of the process design documents is 0.18mm. The linear density of high modulus carbon fiber is 230 (g / km), and the density of carbon fiber is 2.04 (g / cm 3 ), the carbon fiber volume fraction is 60%, the original fiber bundle width is 1mm, and the yarn sheet width is 1mm when the fiber bundle is unfolded. The width of the fiber yarn sheet is consistent with the width of the original fiber bundle and does not need to be expanded. Therefore, the radius of curvature of the section of the spreading roller is selected as R=+∞(mm), that is, the...

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Abstract

The invention provides a spinning nozzle structure for a wet molding process of prepreg and a using method thereof. The spinning nozzle structure comprises a support module, an impregnation module, a yarn pre-spreading module and a yarn spreading module. The support module comprises a side plate and a base plate. The impregnation module, the yarn pre-spreading module and the yarn spreading module are sequentially arranged on the side plate in the horizontal direction of the side plate. According to the spinning nozzle structure, due to the design of yarn spreading rollers and pre-spreading rollers, the widths of yarn sheets can be controlled, yarn spreading of the widths of different yarn sheets is achieved under the condition of cross sectional shapes of the different yarn spreading rollers and yarn pre-spreading rollers, and the carbon fiber reinforced resin matrix composite prepreg of different thicknesses is prepared so as to meet the requirement for the thicknesses of the prepreg in the composite product design process. The spinning nozzle structure can be applied to yarn spreading phenomena of different fiber types and fiber bundle sizes, the spinning nozzle structure can adjust the widths of the yarn sheets by adjusting the cross sectional shapes of the yarn spreading rollers so as to achieve the purpose of preparing the carbon fiber prepreg of different thicknesses.

Description

technical field [0001] The invention relates to the technical field of composite material molding, in particular to a wire nozzle mechanism for wet molding prepregs and a method for using the same. Background technique [0002] Due to the high specific modulus and specific strength of composite materials, and the advantages of the integration of structural design and manufacturing, composite materials are widely used in the aerospace field. With the continuous improvement of the reliability and quality requirements of the composite material product structure in the aerospace field, and the continuous improvement of the composite material forming process technology, the requirements for the performance, reliability and stability of the composite material preform in the intermediate link of composite material forming Getting harsher. Especially in the satellite truss structure with prepreg as the intermediate molding material, hand laying, automatic laying, and prepreg windin...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/50B29C70/54
Inventor 董晓阳郭金海史文峰潘江左龙彦师璐宋超
Owner SHANGHAI COMPOSITES SCI & TECH CO LTD
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