Forming process of sandwich structure carbon fiber composite material stringer

Abstract

The invention discloses a forming process of a sandwich structure carbon fiber composite material stringer. The forming process comprises the following steps: step I, overlaying a first prepreg grouponto the surface of a sandwich core material, and pre-compacting; step II, paving and pasting a second prepreg group onto a stringer pre-formed body mold; step III, placing the sandwich core materialcovered with a first prepreg group in a specified mold cavity in the stringer pre-formed body mold; step IV, placing a stringer pre-formed body onto a platform, laying an auxiliary material for pre-compaction, pre-compacting, vacuuming, and enabling the first prepreg group and the second prepreg group to be sufficiently laminated, thereby obtaining a stringer pre-formed body; and step V, paving and pasting a third prepreg group onto a main body mold, and jointly fixing the stringer pre-formed body and the stringer pre-formed body mold onto the main body forming mold. Therefore, by adopting theforming process of the sandwich structure carbon fiber composite material stringer, the surface quality and internal quality of the formed product are reliable, and the quality is stable.

Description

technical field [0001] The invention relates to the field of carbon fiber composite materials, in particular to a molding process of a carbon fiber composite long stringer with a sandwich structure. Background technique [0002] In recent years, drones have developed in a blowout manner. In addition to military drones used for military reconnaissance and attack, various civilian drones have also developed rapidly. In the UAV design process, stiffness and weight are two very key indicators, which are a pair of contradictions. Improving stiffness will inevitably sacrifice weight, which is a pair of contradictions. Among the numerous aircraft components, the long truss is a typical structure with light weight and high rigidity, and it is mainly used in thin skin parts such as the fuselage and power cabin of the aircraft. The fuselage and power cabin of carbon fiber composite drones are often designed as thin skin structures in order to reduce weight, but the equipment is insta...

AI Technical Summary

Problems solved by technology

[0004] During the molding process, often due to various factors such as the operating space, the size of the sandwich core material, the positioning between the sandwich core material and the forming mold, and the bag-making skills, after the carbon fiber composite long truss of the sandwich structure is formed, the clamping occurs. Various defects such as core material deviation, rich resin at the R corner, poor glue at the R corner, fiber bridging at the R corner, etc., make the product unusable

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