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A low-cost composite material large cabin integral molding method

A technology of composite materials and molding methods, which is applied in the field of integral molding of large cabins of low-cost composite materials, can solve the problems of high cost of large cabins of composite materials, and achieve the effects of good product strength and rigidity, good durability, and good mechanical properties of the skeleton

Active Publication Date: 2021-09-03
长春长光宇航复合材料有限公司
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Problems solved by technology

[0003] The purpose of the present invention is to solve the high cost problem of the existing composite material large cabin, and provide a low-cost composite material large cabin integral molding method

Method used

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Embodiment Construction

[0020] A low-cost composite material large cabin integral molding method, comprising the following steps:

[0021] S1: Preparation of large metal molds: the outer surface contour of the product is produced by machining the female mold;

[0022] S2: Apply elastic glue on the female mold for sealing treatment. After the elastic glue is cured, lay 3K carbon cloth, and lay the outer skin of room temperature curing epoxy resin prepreg on the carbon cloth. The thickness of the outer skin is 2mm- 3mm;

[0023] S3: Vacuumize the laid outer skin with a vacuum bag or pressurize it in an autoclave, with a pressure of 0.1-0.3MPa;

[0024] S4: Put it into a curing furnace or an autoclave for heating after pressurization, the heating temperature / time is 80°C / 4h, and it is cured and formed;

[0025] S5: Locate the installation position of the metal embedded part on the outer skin according to the drawing line, and bond the metal embedded part to the outer skin, and at the same time locate ...

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Abstract

The invention discloses a low-cost composite material large cabin integral molding method, which belongs to the field of composite material large cabins, and adopts the following methods: large metal mold preparation; mold sealing treatment; outer skin molding, vacuum curing; , vacuum curing; inner skin forming, vacuum curing; product demoulding and trimming. It overcomes the defects of the method of splicing into one piece after segmental molding or the traditional metal skeleton type shelter, which has complicated structural procedures and weak mechanical properties at the splicing point. Using rigid polyurethane foam as a filling material has better thermal insulation performance and stronger functionality, and can better meet the higher performance requirements of large cabins for both military and civilian purposes.

Description

technical field [0001] The invention relates to the field of large-scale cabins made of composite materials, in particular to an integrated molding method for large-scale cabins made of composite materials at low cost. Background technique [0002] The large compartment made of composite materials is mainly used in the process of vehicle parking and motor transportation; it is used to load on-board instruments and equipment, and provides necessary environmental conditions for the instruments and equipment; it provides environmental protection and survival protection during use. There are high requirements for the appearance quality, watertightness and driving test of the thermal insulation cabin. Composite large-scale cabins can be stored for a long time in an environment with an ambient temperature of 0°C to +40°C and a relative humidity of no more than 98% (25°C). The cumulative number of days allowed for abnormal storage conditions per year shall not exceed 30 days. Due ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/68B29C70/44B29C70/54B29C35/02
CPCB29C35/02B29C70/44B29C70/54B29C70/68B29C70/681
Inventor 邹志伟迟贺曹延君秦闯林再文
Owner 长春长光宇航复合材料有限公司
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