Thermal diaphragm preforming method suitable for Z-shaped structure composite material

Abstract

The invention provides a thermal diaphragm preforming method suitable for a Z-shaped structure composite material. The method comprises the following steps of firstly, finishing primary forming through a primary preforming tool, and then finishing secondary forming by inverting a first main body tool and butting with a secondary preforming tool to obtain a preform. By means of a primary preformingtool and a secondary preforming tool, laying of prepregs is not limited by the size of a laying head or a fiber laying head any more, stable laying of the prepregs is achieved, controllable transferof uncured prepreg laminated blank pieces can be achieved, the risk of prepreg profile instability caused by tool conversion of two times of thermal diaphragm preforming is avoided, and accurate forming of the Z-shaped structure is guaranteed.

Description

technical field [0001] The invention relates to the processing field of composite materials, in particular to a thermal diaphragm preforming method suitable for Z-shaped structural composite materials. Background technique [0002] The special application environment of aerospace determines its continuous pursuit of lightweight structural materials. Resin matrix composites have become the preferred material option in aerospace structures due to their outstanding specific strength and specific modulus advantages. The characteristics of integrated structural design of composite materials enable composite materials to further exert the mechanical properties of high-performance fibers by designing different reinforcement forms in addition to their own light weight and high strength. For example, using different forms of long strings to reinforce skin structures, Among them, the Z-shaped stringer is a typical stringer form. In the composite material structure, the Z-shaped stru...

AI Technical Summary

Problems solved by technology

[0003] Traditionally, Z-shaped trusses are preformed by manual laying. Due to the concave and convex shape of the laying process, the laying efficiency and quality stability are relatively low, which is difficult to meet the further expansion and application of composite material structures.

However, due to the special structural form of the Z-shaped structure, the automatic forming methods that have been widely used at present, including the automatic tape laying process and the automatic silk laying process, are limited by the size of the tape laying head and the silk laying head, and it is difficult to achieve 90% of the structure. ° and 45° plies for stable placement

For the Z-shaped structure, if the traditional thermal diaphragm preforming method is used, it is difficult to achieve effective and accurate positioning and fixing measures between the blank and the tooling, and cannot meet the precise forming quality assurance

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