Method for forming frame, stringer and covering of composite material component through integrated co-curing

Abstract

The invention belongs to the technical field of composite material forming, and relates to a method for forming a frame, a stringer and a covering of composite material through integrated co-curing. The method adopts advanced temperature-resistant pressure-resistant foams to fill the inner part of the stringer, so that the stringer and the covering can be completed through one-step paving and pasting; a positioning and curing tooling for the frame is adopted, and special sharpening processing is performed on the positioning and curing tooling, so that the pressurizing problem on a joint face of the frame and the stringer can be solved, and the integrated co-curing forming of the frame, the covering and the stringer can be achieved; in addition, a rubber lining film technology is adopted, so that the pressure uniformity of the inner complicated structure and the quality of the inner surface can be ensured. The method for forming the frame, the stringer and the covering of a composite material component through integrated co-curing solves the problem of cementing interfacial effect on the joint face of the frame, the stringer and the covering in the traditional secondary cementing forming, improves the product quality, and satisfies the strength requirement of large load of the structure.

Description

technical field [0001] The invention belongs to the technical field of composite material molding, and relates to a composite material frame, stringer and skin integral co-curing molding method. Background technique [0002] Some composite parts require bulk co-curing to meet strength requirements. For example, the tail beam of a certain type of helicopter is an all-composite material structure, which bears relatively large tail rotor loads and vibration loads, and is the main force-bearing component of the whole machine. . If the traditional frame, stringer and skin are cured separately, and then the secondary bonding is performed, interface effects are likely to occur at the bonding surface, and it is easy to cause degumming when subjected to a large load, and even affect flight safety. Contents of the invention [0003] The purpose of the present invention is to provide a composite material component frame, stringer and skin integral co-curing molding method to elimin...

AI Technical Summary

Problems solved by technology

If the traditional frame, stringer and skin are cured separately, and then the secondary bonding is performed, interface effects are likely to occur at the bonding surface, and it is easy to cause debonding when subjected to a large load, and even affect flight safety.

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