Aeronautical composite material box molding tooling

Abstract

The invention discloses an aeronautical composite material box molding tooling, which includes a left die, a right die and a fastening bolt. The left die and the right die are connected by the fastening bolt to achieve die clamping and fixation. The die clamping surface of the left die and the right die is provided with grooves with corresponding positions and consistent shape at the fastening bolt joints respectively. A detachable silicon rubber ring is placed in the groove cavity formed after die clamping of the corresponding grooves, and the size of the groove cavity is slightly larger than the size of the silicon rubber ring. The grooves can be in the shape of a circle, oval, rectangle, square or any one of other closed figures. The silicon rubber ring and the grooves have a consistent shape. According to the invention, during curing, the silicon rubber ring effectively blocks overspill of the composite material's resin matrix, thus avoiding consolidation of the composite material's resin matrix at the fastening bolt joints. The molded parts can realize convenient demolding, thus avoiding scrapping. The fastening bolt and the silicon rubber ring are easy to clean, the labor cost is reduced, the production efficiency is enhanced, and the quality of subsequent products is ensured.

Description

technical field [0001] The invention relates to the technical field of structural forming of composite material parts, in particular to an aviation composite material box forming tooling. Background technique [0002] Composite materials, metal materials, inorganic non-metal materials, and polymer materials are listed as four major material systems. Advanced composite materials refer to the composite materials used to process the main load-bearing structure and secondary load-bearing structure, whose stiffness and strength properties are equivalent to or exceed aluminum alloys, and have light weight, high specific strength, specific modulus, and better Ductility, corrosion resistance, heat insulation, sound insulation, shock absorption, high (low) temperature resistance, etc. [0003] Advanced composite materials such as resin-based fiber-reinforced composite materials have been widely used in the aerospace industry. The structure of the existing aviation resin-based compos...

AI Technical Summary

Problems solved by technology

There are following defects in the above-mentioned forming tooling structure: the first, as attached figure 1 As shown, during the mold clamping and curing process, the resin base will flow along the mold clamping seam 4a, and be consolidated at the fastening bolt connection 5a. Too much resin base solidification makes it difficult to remove the fastening bolt 3a from the tooling. As a result, it is difficult to demould the parts, and even lead to the scrapping of the parts; secondly, even if the fastening bolts 3a are removed during demoulding, the resin base will solidify on the threads and form glue spots, which need to be passed through with tools such as non-metallic wedges and hammers. Cleaning by manual beating is often difficult and the effect is not ideal, which increases the labor cost

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