Forming method of heterogeneous composite grid skin cabin

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,...

AI Technical Summary

Problems solved by technology

However, due to the high elasticity of silicone rubber, the position accuracy of the ribs is poor, the size deviation of the formed product is large, and the loss of silicone rubber in the continuous production process is also large.

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