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Composite material joint and preparation method thereof

A composite material and metal insert technology, applied in the aerospace field, can solve problems such as failure and underutilization of composite material designability, and achieve the effects of improving bearing capacity, improving connection reliability, and uniform force

Active Publication Date: 2021-03-30
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Chinese patents CN108332051A and CN109203510A both disclose the preparation method of composite material joints. Carbon fiber laminates are used to replace metal materials. Although the effect of weight reduction is achieved, the designability of composite materials is not fully utilized. The shear strength is much smaller than its tensile and bending strengths. However, due to the complexity of the composite material joints under load, they tend to fail first in the interlayer. Therefore, the bearing capacity of the composite material joints still has a large room for improvement.

Method used

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  • Composite material joint and preparation method thereof
  • Composite material joint and preparation method thereof

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preparation example Construction

[0046] The method for preparing the above-mentioned composite material joint provided by the present invention comprises the following steps:

[0047] (1) Lay the material required for the skin 1 31 on the surface of the forming female mold of the composite material joint, pressurize; then lay the material required for the matrix 4, pressurize; finally lay the material required for the skin 2 32 piece, install the molded male mold for pre-compression;

[0048] (2) Disassemble the male and female molds, take out the pre-pressed composite material joint, and implant the micro-rod 5 into the first skin 31 and the second skin 32 respectively;

[0049] (3) Hoist the male and female molds to the hot press platform after closing the molds, arrange thermocouples and insulation layers around the molds, and pressurize and solidify;

[0050] (4) After the mold cools down and the pressure is relieved to a predetermined value, disassemble the mold, take out the prefabricated composite mat...

Embodiment 1

[0055] The invention provides a preparation method for a composite material joint, comprising the following steps:

[0056] (1) Mold preparation: Assemble the female and male molds for forming composite material joints, paste the release cloth, apply the release agent, and set aside.

[0057] (2) Lay-up material preparation: According to the composite material joint structure and division area, plan the ply material, then cut, number and reserve.

[0058] (3) Sheet laying and pre-pressing: Lay the prepared sheet in the female mold for composite joint forming, first lay the sheet required for the skin 1 31 on the surface of the female mold, and lay it with the busbar as the reference direction Then arrange a vacuum bag in the female mold to evacuate or install a pre-molded male mold to pressurize; then lay the required material or chopped premix for the matrix 4 on the skin one 31 and the surface of the female mold, the material or The short-cut premix is ​​laid with the busba...

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Abstract

The invention relates to a composite material joint and a preparation method thereof. The composite material joint comprises a metal insert and a joint body, wherein the metal insert is a table body of a non-axisymmetric structure, a mounting mechanism is arranged at the small end of the metal insert and is used for being connected with an external mechanism, the joint body comprises a base body and an outer panel skin laid on the surface of the base body, the base body coats the periphery of the metal insert and exposes the mounting mechanism, the base body is formed by alternately laying chopped fiber mold pressing layers and carbon fiber prepreg laying layers, and the chopped fiber mold pressing layers and the carbon fiber prepreg laying layers are all perpendicular to the axis of the metal insert, the outer panel skin is composed of the carbon fiber prepreg laying layers and micro rods, and the micro rods are perpendicular to the outer panel skin. According to the composite material joint and the preparation method thereof, by means of metal insert structure optimization, base body laying layer structure optimization and outer panel skin laying layer interlayer reinforcement, the composite material joint is prevented from losing efficacy in advance between layers when being loaded, and the bearing capacity of the composite material joint can be greatly improved, so that thepassive mass of the composite material joint can be further reduced through structure optimization.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a composite material joint for a solid rocket motor casing and a preparation method thereof. Background technique [0002] The light weight of solid rocket motors is one of the important indicators to reflect its advanced nature. The front and rear joints of the engine composite shell are necessary for the shell fiber winding, and are important stress and connection parts during the working process of the engine. , the traditional composite shell joints adopt metal structure, which accounts for about 15% of the total mass of the shell. The front and rear joints of the casing are made of composite materials, and the composite material scheme is adopted, so that the casing can significantly reduce the negative mass of the engine. Chinese patents CN108332051A and CN109203510A both disclose the preparation method of composite material joints. Carbon fiber laminates are used to re...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/34B29C70/54B29C65/48B29C69/00B29L31/24
CPCB29C70/345B29C70/545B29C65/48B29C69/00B29L2031/24Y02T50/40
Inventor 赵飞周睿刘冬青司学龙余明敏钟志文郑磊
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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