Preparation method of composite material thin-walled shell based on discontinuous layup

A technology of thin-walled shells and composite materials, which is applied in the field of composite material structure design and composite material processing technology, can solve the problems of easy deformation of thin-walled shells, and achieve the effects of small deformation, short production cycle and good applicability

Active Publication Date: 2016-07-27
BEIJING AEROSPACE HEZHONG TECH DEV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The purpose of the present invention is to solve the problem that the thin-walled shell of fiber-reinforced resin-based composite material used in space remote sensors is easily deformed, and proposes a method of intermittent lay-up. The thin-walled shell of fiber-reinforced resin-based composite material prepared by this method is not easily deformed and can ensure The surface-to-obstruction ratio, modulation transfer function (MTF) and stray light coefficient of the space remote sensor can simplify the structural design and molding process at the same time

Method used

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  • Preparation method of composite material thin-walled shell based on discontinuous layup
  • Preparation method of composite material thin-walled shell based on discontinuous layup
  • Preparation method of composite material thin-walled shell based on discontinuous layup

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Effect test

Embodiment 1

[0044] The cover body 2 adopts the discontinuous lay-up method, which greatly simplifies the structure of the inner cover, effectively controls its maximum deformation, and saves the reinforcing rib 3 at the far end of the cover body 2 at the same time. The structural representation of the cover body 2 without ribs 3 is as follows: Figure 4 shown.

[0045] The first step is to design and manufacture the forming mold of the cover body 2. The mold is a positive mold, and the mold is made of metal material. The external dimensions of the mold are consistent with the inner cavity of the cover body 2; mold release agent, and dry it; the fluorocarbon release agent can be replaced by other release agents with a temperature resistance not lower than 140°C; if necessary, the mold can be heated to 50-60°C.

[0046] The second step is to prepare Kevlar49 / 8D-1 plain fabric prepreg with a nominal thickness of 0.1mm. The resin content of the prepreg is controlled at 42±5%, and the volatil...

Embodiment 2

[0057] The cover body 2 adopts the discontinuous lay-up method, which greatly simplifies the structure of the inner cover, effectively controls its maximum deformation, and saves the reinforcing rib 3 at the far end of the cover body 2 at the same time. The structural representation of the cover body 2 without reinforcing rib 3 is as follows: Figure 4 shown.

[0058] The first step is to design and manufacture the forming mold of the cover body 2. The mold is a female mold, and the mold is made of metal material. The shape and size of the inner cavity of the mold are consistent with the outer surface of the cover body 2; before use, a layer of fluorine is applied to the working surface of the mold. Carbon compound release agent, and dry it; the fluorocarbon release agent can be replaced by other release agents with a temperature resistance not lower than 140°C; if necessary, the mold can be heated to 50-60°C.

[0059] The second step is to prepare Kevlar49 / 8D-1 plain fabric ...

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Abstract

The invention relates to a composite material thin-wall housing preparation method based on intermittent stacking, and belongs to the technical field of composite material structure design and composite material processing technology. A composite material thin-wall housing prepared by using the preparation method is small in deformation, and has the maximum deformation of 0.5 mm or less under the room temperature condition, and the maximum deformation not exceeding 0.5 mm is of great importance to guarantee surface obstruction ratio, modulation transfer function (MTF) and veiling glare index of a space remote sensing system. The composite material thin-wall housing is simple in structural form, tedious structures such as ribs and the like are saved, and also structure weight is mitigated. The composite material thin-wall housing is high in technology maturity, simple in tools and molds, relatively good in adaptability to curing equipment and short in production period.

Description

technical field [0001] The invention relates to a method for preparing a composite material thin-walled shell based on discontinuous layering, and belongs to the technical fields of composite material structure design and composite material processing technology. Background technique [0002] Advanced composite materials have the advantages of light weight, high specific strength and specific modulus, fatigue resistance, good damping and shock absorption performance, and designable performance. They are gradually replacing the original metal materials and becoming the key materials for space remote sensor structures. In terms of process maturity and practical application range, resin-based composite materials with high-performance fibers as reinforcements have become the preferred materials for space remote sensor structures, while carbon fiber composite materials (CFRP) and aramid fiber composite materials (AFRP) are also occupy a dominant position in it. [0003] Some spa...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/34
CPCB29C70/386B29C70/44B29C70/543
Inventor 章令晖陈萍
Owner BEIJING AEROSPACE HEZHONG TECH DEV
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