A composite material main load-bearing wing surface using a dovetail structure and a preparation method thereof

By using dovetail structure in the main bearing airfoil of composite material, the problem of insufficient tensile strength and coordinated deformation ability at the connection in the prior art is solved, and a higher tensile resistance is achieved Strength and better coordinated deformation ability improve the overall performance of composite materials.

CN115743518BActive Publication Date: 2025-01-10AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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Patent Information

Application Number
CN202211267357.7
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2022-10-17
Publication Date
2025-01-10
Estimated Expiration
2042-10-17

AI Technical Summary

Technical Problem

The tensile strength and coordinated deformation capability of the main bearing wing surface of the existing composite material are insufficient at the joints of sandwich foam and metal joints inside the wing surface, which affects the structural performance of the aircraft.

Method used

The dovetail structure is used to prefabricate the sandwich foam to the metal joint. The prefabricated tenon/month and metal joint are used to improve the tensile strength and coordinate deformation ability at the connection, and the thickness design and multi-closed chamber structure are used. Enhance bending and torsional resistance.

Benefits of technology

It significantly improves the tensile strength and coordinated deformation ability at the inner joints of the airfoil, enhances the overall performance of the composite material, reduces the stiffness step, and improves assembly reliability.

✦ Generated by Eureka AI based on patent content.

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Abstract

The present invention relates to a composite main load-bearing wing surface using a dovetail structure and a preparation method thereof. The main load-bearing wing surface comprises a sandwich foam, a metal joint and a skin; the sandwich foam is connected to a prefabricated dovetail tenon on the metal joint through a prefabricated dovetail tenon tenon, or the sandwich foam is connected to a prefabricated dovetail tenon on the metal joint through a prefabricated dovetail tenon tenon; the sandwich foam and the outer part of the metal joint are covered with the skin. The sandwich foam and the skins above and below the sandwich foam, i.e., the composite panels, can be designed with variable thickness to meet the trend of the load gradually decreasing from the root to the wing tip during the operation of the main load-bearing wing surface. In the present invention, the sandwich foam inside the wing surface is connected by a prefabricated tenon / mortise and a prefabricated mortise / mortise of the metal joint, thereby improving the tensile strength and the ability to coordinate deformation at the connection.
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Citation Information

Patent Citations

  • Preparation method of mortise and tenon joint carbon fiber composite laminate plate

    CN111070725A

  • All-composite empennage structure and forming method thereof

    CN113602477A

  • Bionic composite airfoil and manufacturing method thereof

    CN114770975A

  • Block type wing structure with wingtip conformal antenna

    CN216154016U