Carbon beam composite material wing structure
Through the carbon beam composite wing structure, plug-in and adhesive connection, combined with high-mode carbon fiber and high-strength carbon fiber unidirectional prediction, the weight and load-bearing problems of glider wings are solved, and lightweight and high-strength flight performance, stability and safety are achieved.
CN223237917UActive Publication Date: 2025-08-19JIANGSU CHANGZHUO TECH CO LTD
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Patent Information
- Application Number
- CN202422712973.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-07
- Publication Date
- 2025-08-19
- Estimated Expiration
- 2034-11-07
AI Technical Summary
Technical Problem
The existing glider wing structure cannot meet the load-bearing requirements while meeting the weight requirements, affecting flight performance, stability and safety.
Method used
The carbon beam composite wing structure is adopted, including the main beam of the wing surface, foam layer and skin, and is fastened by plug-in, adhesive and bolts, combined with the one-way preview of high-mode carbon fiber and high-strength carbon fiber, and designed a non-load-bearing area weight reduction structure.
Benefits of technology
The wing weight is controlled below 4.5kg, the bearing capacity is effectively transmitted, the deformation is controlled within 150mm, and the mode is not less than 21HZ, which improves flight performance, stability and safety.
✦ Generated by Eureka AI based on patent content.
Abstract
The utility model relates to the technical field of gliders, in particular to a carbon beam composite material wing structure. The airfoil comprises an airfoil main beam and foam layers located at the two ends of the airfoil main beam, the airfoil is of a structure which is thick in the middle and thin at the two ends on the whole, the airfoil main beam and the foam layers are wrapped with a layer of airfoil skin, and the airfoil main beam and the airfoil handle are connected in an inserted mode and fastened through a binder and a bolt; a weight reduction structure is designed in a non-bearing area of the wing handle, so that the overall weight of the structure is reduced; the modulus of the high-modulus carbon fiber main beam can reach 200Gpa, so that the deformation in a bearing state is effectively controlled, and the structural modal of the airfoil is improved; the high-modulus carbon beams and the wing handles are connected in an inserted mode, bonded through epoxy glue and connected in a fastened mode through bolts, and the bearing force of the wing surfaces is effectively transmitted to wing handle connecting points; the outer skin of the airfoil is made of high-strength carbon fiber one-way material, the laying direction and number of fibers are designed according to calculated stress, the 0-degree fiber direction, the 90-degree fiber direction and the + / -45-degree fiber direction are configured, and the torsional strength of the airfoil is improved on the premise that the bearing requirement is met.
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