Technological method for forming large-thickness honeycomb sandwich structure composite material

A composite material and honeycomb interlayer technology, which is applied in the field of composite material molding, can solve problems such as large curing stress, reducing the temperature rise rate at the leading position of the part temperature, and product deformation, so as to reduce curing stress, improve application value and economic benefits, The effect of improving uniformity

Inactive Publication Date: 2021-11-09
THE RES INST FOR SPECIAL STRUCTURES OF AERONAUTICAL COMPOSITE AVIC
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Problems solved by technology

[0005] The invention aims at the problem of large curing stress and product deformation caused by uneven distribution of the heat field of the large-thickness honeycomb sandwich structure composite material when i

Method used

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Examples

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example 1

[0045] A certain product needs to undergo two curing heat histories. The curing system is 2 hours at 180°C, and the curing pressure is 0.3-0.32MPa. During the curing process, the vacuum value shall not be greater than 0.034kPa.

[0046]When the product is cured for the first time, the number of skin layers is small, and during the heating and curing process, the constant temperature time gap between the temperature leading position and the lagging position is 55-60 minutes. In order to control the constant temperature time difference within 30 minutes and meet the requirements of heat distribution uniformity and heat history during part molding, a combined heat insulation layer consisting of 4 layers of N10 air felt and 1 layer of vulcanized Airpad rubber pad was prepared. First, use a blanking template that matches the shape of the part to cut 4 layers of N10 air felt, and then stack the 4 layers of N10 air felt layer by layer on the operating table to form a multi-layer heat...

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Abstract

The invention belongs to the technical field of composite material forming, and relates to a technological method for forming a large-thickness honeycomb sandwich structure composite material. In order to solve the problems of high curing stress and product deformation caused by non-uniform thermal field distribution of the workpiece when the large-thickness honeycomb sandwich structure composite material workpiece is cured, the temperature rise rate of the temperature leading position of the workpiece is effectively reduced by designing the combination of breathable and non-breathable thermal insulation materials, and therefore, the purpose of uniform distribution of the thermal field in the workpiece curing process is achieved. The uniformity of the workpiece curing thermal field is improved, the workpiece curing stress is reduced, and the product quality is improved. The technological method is successfully applied to manufacturing of test pieces of a certain product. The technological method has good application value and economic benefit in the technical field of aeronautical manufacturing.

Description

technical field [0001] The invention belongs to the technical field of composite material forming, and in particular relates to a process method for forming a large-thickness honeycomb sandwich structure composite material. Background technique [0002] The material molding and structural molding of composite materials are completed at the same time. The control of the manufacturing process affects the quality of the composite material structure. The thermal field distribution of the workpiece during the molding process is a factor that affects the curing quality. The uneven distribution of the thermal field will cause As a result, the curing of each part of the material is not synchronized, resulting in curing deformation and internal stress. With the development of composite materials technology, the application of large-thickness honeycomb sandwich structure composite materials is becoming more and more extensive. Affected by the honeycomb structure and thickness, the un...

Claims

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Application Information

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IPC IPC(8): B29C70/34B29C70/54
CPCB29C70/34B29C70/54
Inventor 卢红龙郝磊陆祥坤
Owner THE RES INST FOR SPECIAL STRUCTURES OF AERONAUTICAL COMPOSITE AVIC
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