Preparation method of foldable self-resilience composite material pipe type hinge

A composite material tube and composite material technology, which is applied in the field of preparation of foldable self-rebound composite material tube hinges, can solve the problems of poor mechanical designability, low strength of fabric reinforced composite materials, and difficulty in achieving single layer thickness of fabric below 0.05mm and other problems, to achieve the effect of improving stiffness and large degree of freedom in mechanical design

Inactive Publication Date: 2016-02-10
AVIC COMPOSITES
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] At present, most of the reinforcements used in composite material hinges prepared abroad are fabrics, and the thickness of a single layer of fabric is difficult to reach less than 0.05mm. The failure strain of the prepared composite material hinges cannot meet some small-sized hinges (such as diameters less than 20mm). The manufacture, with greater use limitations
At the same time, compared with continuous fiber-reinforced composites, fabric-reinforced composites have lower strength and less mechanical designability

Method used

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  • Preparation method of foldable self-resilience composite material pipe type hinge
  • Preparation method of foldable self-resilience composite material pipe type hinge

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preparation example Construction

[0019] The present invention proposes a method for preparing a foldable self-resilient composite tubular hinge, the preparation steps of which are as follows:

[0020] Step 1, preparing a thin-walled composite material circular tube, the specific method is as follows:

[0021] (1) For thermosetting resin prepregs, according to the part size, mechanical design and layup requirements, lay the ultra-thin prepreg sheets with corresponding sizes and layup angles outside the mold by hand or using a coiler The surface is pressurized, heated and cured by vacuum bag method, heat shrinkable film pressing method, molding method or autoclave method. Or manually lay the material on the cylindrical airbag, place it in the female mold, and use the airbag pressing method to form it.

[0022] (2) For thermoplastic resin prepregs, according to the part size, mechanical design and layup requirements, lay the ultra-thin prepreg sheets with corresponding sizes and layup angles outside the mold in...

Embodiment 1

[0027] Select the pre-expanded T300 (3k) carbon fiber tow, use the medium-temperature epoxy resin to form a semi-solid adhesive film with a glue machine, and then heat and press the resin film and fiber tow through the prepreg equipment to prepare unidirectional carbon fiber Ultra-thin prepreg, the fiber volume fraction is 50%, and the prepreg single layer thickness is 0.04mm. Lay the prepreg manually on the cylindrical mold, the diameter of the mold is 30mm, the layering method is [45 / -45 / 0 / -45 / 45], and the thin-walled composite tube is obtained by vacuum bag curing. The processing method is to symmetrically open holes on both sides of the pipe wall, the opening method is scheme 2, the opening width is 12mm, and the opening length is 150mm to obtain a composite material tubular hinge.

Embodiment 2

[0029] Pre-expanded aramid kevlar-29 (200tex) fiber tow is selected, and the resin is selected from cyanate resin system. The fiber tow is pre-impregnated with resin through a wet prepreg machine to obtain a unidirectional ultra-thin prepreg, single-layer Thickness 0.05mm. The prepreg is laid on the cylindrical mold with a tube coiler, the diameter of the mold is 23mm, and the layering method is [45 / -45 / 0 / 0 / -45 / 45], and the thin-wall composite is obtained by curing in an autoclave The material round pipe is symmetrically opened on both sides of the pipe wall by mechanical processing method. The opening method is scheme 2, the opening width is 12mm, and the opening length is 90mm to obtain a composite material tubular hinge.

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Abstract

The invention belongs to the technical field of hinges, and relates to a preparation method of a foldable self-resilience composite material pipe type hinge. The composite material pipe type hinge is prepared by an ultrathin resin base composite material prepreg, and adopts a structural form of a thin-wall composite material round pipe symmetrically perforated in middle. The thickness of the ultrathin prepreg is generally 15-30% of the thickness of a conventional prepreg; and the ultrathin prepreg is suitable for preparing a thin-wall composite material part, and is high in mechanical design degree of freedom. The ultrathin prepreg can realize high performance of a light composite material structure; and on the basis of satisfying a folding function of the composite material hinge, such mechanical performances as rigidity and bending moment of the structure are improved. The foldable self-resilience composite material pipe type hinge, prepared by the method, can be applied to the aerospace field having higher requirements on weight reduction, specific strength and specific rigidity.

Description

technical field [0001] The invention belongs to the technical field of hinges, and relates to a preparation method of a foldable self-rebound composite material tubular hinge. Background technique [0002] In aerospace and other industrial fields, some mechanical structures need to realize the foldable self-deployment function through hinges. In the aerospace field, due to space constraints, expandable solar panels, expandable antennas, expandable trusses and other space expandable structures It must be folded before launching, and it can be unfolded controllably after launching into the working orbit. At present, metal hinge structures are mostly used to realize these functions. With the increasing demand for light weight, high specific strength and specific stiffness of materials in the aerospace field, traditional metal hinges can no longer meet the needs of current technological development. [0003] Fiber-reinforced resin-based composite materials have outstanding adva...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/34B29C70/54B29L31/22
Inventor 邓华高军鹏包建文
Owner AVIC COMPOSITES
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