The invention relates to an aircraft integrated composite material airfoil structure and a manufacturing method, the airfoil structure comprises a skin, a foam core material and a wing rib, the skin is formed by mixing a carbon fiber unidirectional belt and a carbon fiber fabric, the front edge and the rear edge of the airfoil are respectively thickened to serve as a front beam follow-up body and a rear beam follow-up body, and the skin is filled with the full-height foam core material. The wing rib comprises a tip wing rib and a root wing rib, the tip wing rib is of a laminated board structure with a C-shaped section and is connected with the skin in a glued and solidified mode, the root wing rib is a special-shaped piece of a metal structure, one part of the root wing rib is connected with the skin in a glued and solidified mode, the other part of the root wing rib is mechanically connected with the fuselage, the airfoil structure is integrally manufactured and formed, and the skin, the wing rib and the core material are connected in a co-solidified mode. Extra mechanical connection and assembly procedures are not needed, only one curing process is needed, and the manufacturing cost and the manufacturing time of a composite material workpiece are reduced from the design source.
一种飞行器整体化复合材料翼面结构及制造方法,所述翼面结构包括蒙皮、泡沫芯材、翼肋,蒙皮为碳纤维单向带与碳纤维织物混杂,并在翼面前缘、后缘处分别增厚作为前梁、后梁随形体,蒙皮内部填充全高度泡沫芯材,所述的翼肋包含梢部翼肋和根部翼肋,梢部翼肋为“C”形截面层压板结构,与蒙皮胶接固化连接,根部翼肋为金属结构异形件,一部分与蒙皮胶接固化连接,另一部分与机身机械连接,翼面结构为一体化制造成型,蒙皮、翼肋、芯材之间为共固化连接,无需额外机械连接和装配工序,且仅需要一次固化过程,从设计源头降低了复合材料制件的制造成本和制造时间。
Integrated composite airfoil structure of aircraft and manufacturing method
一种飞行器整体化复合材料翼面结构及制造方法
2024-09-17
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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