Internal supercharging method for composite material multi-rib siding structure cementing forming technology

Abstract

The invention discloses an internal supercharging method for a composite material multi-rib siding structure cementing forming technology. A multi-rib siding structure includes an upper skin siding (1), wall bodies (2) and a lower skin siding (3), wherein the wall bodies (2) are cemented with the upper skin siding (1) and the lower skin siding (3) through a double faced gel mold (4) secondary cementing forming technology, and the multi-rib siding structure is characterized in that metal core molds (5) are arranged at the inner cavities of the wall body (2) sides of the multi-rib siding structure; a layer of 3 mm thick silicone rubber plate (6) formed after high temperature sulfuration is laid on each of the lower mold surfaces of the metal core molds (5); a layer of 6 mm thick swelled rubber plate (7) is laid on each of the upper mold surfaces of the metal core molds (5); after all the inner cavities of the wall body (2) sides of the multi-rib siding structure are subjected to the processes, entire heating is performed, when the temperature rises, the swelled rubber plates (7) swell to press flange areas of the wall bodies (2) to enable the wall bodies (2) to be glued to the upper skin siding (1) and the lower skin siding (3) in a clinging manner, and finally demoulding is performed after natural cooling and solidification of gel molds. According to the method, as the pressed assembly is adopted, all the wall body parts are accurately supported, as a result, the outline requirement of the cementing parts is met and the cementing quality is guaranteed.

Description

technical field [0001] The invention relates to a composite material manufacturing technology, in particular to a method for pressurizing the interior of a composite material multi-ribbon wall plate structure bonding forming process. Background technique [0002] The rapid development of composite material forming technology promotes the application of composite materials in the main load-bearing structure of aircraft. At present, most of the wing-shaped structural parts at home and abroad adopt composite material reinforced wall plate structure, and the ribs are mostly "I" and "T" shapes. Co-curing, secondary bonding and other molding methods. A certain type of aircraft composite material part in my country is a multi-rib honeycomb sandwich structure, which is manufactured by double-sided rubber mold secondary bonding molding process, and the ribs are all "I"-shaped walls. After the mold is taken out from the side cavity of the wall, the flange of the wall will shr...

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Problems solved by technology

[0003] Purpose of the invention: the present invention provides a method for internal pressurization of composite material multi-rib wall panel structure adhesive bonding molding process, which solves the defects of the secondary adhesive molding process of the wall and the skin panel using double-sided rubber molds

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