Forming method of heterogeneous composite grid skin cabin

A composite material and forming method technology, which is applied in the field of special-shaped composite material grid skin compartment forming, can solve the problems of large loss of silicone rubber, poor rib position accuracy, and large product size deviation, etc., to ensure smooth compaction, The effect of reducing the possibility of deformation and improving the overall performance

Active Publication Date: 2018-06-15
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Application Information

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Problems solved by technology

However, due to the high elasticity of silicone rubber, the position accuracy of the ribs is poor, the size deviatio

Method used

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  • Forming method of heterogeneous composite grid skin cabin
  • Forming method of heterogeneous composite grid skin cabin
  • Forming method of heterogeneous composite grid skin cabin

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Embodiment Construction

[0044] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0045] Through the following steps, the present invention realizes one-time integral solidification molding of the carbon fiber prepreg cabin section of the special-shaped composite material grid.

[0046] Step (1), making special-shaped composite material mesh carbon fiber prepreg compartment forming mold

[0047] Such as image 3Shown is a schematic diagram of the special-shaped composite material grid carbon fiber prepreg cabin mold. It can be seen from the figure that the special-shaped composite material grid carbon fiber prepreg cabin molding mold includes a core mold 1, a split male mold 2, an outer female mold 3, and an upper end The frame pressure ring 4 and the lower frame pressure ring 5; wherein, the core mold 1 is located at the center of the forming mold; the split male mold 2 is covered on the outer wall of the core mold 1; the u...

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Abstract

The invention provides a forming method of a heterogeneous composite grid skin cabin, and relates to technical field of a composite forming process. The forming method comprises the following step (1)of making a forming mould of the heterogeneous composite grid carbon fiber prepreg cabin; the step (2) of spreading carbon cloth prepreg at a hoop rib deep-groove area; the step (3) of winding carbonfiber prepreg filaments, and filling the hoop rib deep-groove area; the step (4) of winding the carbon fiber prepreg filaments, and spreading the carbon fiber prepreg; the step (5) of making vacuum suction treatment for first time; the step (6) of spreading the carbon fiber prepreg, and making vacuum suction treatment for second time; the step (7) of winding the carbon fiber prepreg filaments, spreading the carbon fiber prepreg, and making vacuum curing treatment; and the step (8) of removing the mould, and obtaining the heterogeneous grid carbon fiber prepreg cabin. According to the formingmethod provided by the invention, the problems of demoulding of a male die disc, locating and pressurization of a female die disc and so forth are solved, and the internal quality and profile accuracyrequirements of products are ensured.

Description

technical field [0001] The invention relates to the technical field of composite material forming technology, in particular to a method for forming a mesh skin compartment of a special-shaped composite material. Background technique [0002] The grid structure of composite materials is a network rib structure, and the ribs in the grid are wound by unidirectional fiber prepreg filaments. According to the shape of the grid in the ribs, it can be divided into orthogonal grid structure, triangle network Lattice structure and hexagonal grid structure. Its outstanding features are high specific strength / specific modulus, low production cost, high structural efficiency, and outstanding stability. A composite mesh structure is applied in the segment. For example, in 1997, the U.S. Air Force Research Laboratory Space Vehicle Administration and Orbital Technology Corporation jointly developed a composite grid structure fairing, which is 60% lighter than the current aluminum fairing,...

Claims

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Application Information

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IPC IPC(8): B29C70/34
CPCB29C70/342
Inventor 付平俊李健芳郭鸿俊张娅婷冯海东黄智彬陈薇
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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