The invention provides a lightweight airfoil structure of an aircraft. The airfoil structure comprises an airfoil framework (1), an airfoil skin (2) and a plurality of airfoil connecting joints (3), the airfoil framework (1) is of a frame structure, the surfaces of the two sides of the airfoil framework (1) are bent surfaces, a plurality of reinforcing ribs which are transversely and longitudinally staggered are arranged in the airfoil framework (1), the plurality of staggered reinforcing ribs divide the airfoil framework into a plurality of small spaces, and the projection shapes of the small spaces on the surfaces of the two sides of the airfoil framework (1) comprise rectangles and triangles; the airfoil skin (2) is paved on two side surfaces of the airfoil framework (1); and a plurality of airfoil connecting joints (3) are arranged on the bottom surface of the framework. On the premise that the structural strength/rigidity performance requirement is met, the mass of the airfoil structure is reduced, and lightweight of the airfoil structure is achieved.
本发明提供了一种飞行器的轻量化翼面结构,该翼面结构包括翼面骨架(1)、翼面蒙皮(2)和多个翼面连接接头(3);翼面骨架(1)为框架结构,翼面骨架(1)的两侧表面为折弯面,翼面骨架(1)内设置有横向和纵向交错的多条加强筋,交错的多条加强筋将翼面骨架分成多个小空间,小空间在翼面骨架(1)两侧表面上的投影形状包括长方形和三角形;翼面蒙皮(2)铺在翼面骨架(1)的两侧面上;多个翼面连接接头(3)设置在骨架底表面上。本发明在满足结构强度/刚度性能要求的前提上,降低了翼面结构质量,实现了翼面结构轻量化。
Lightweight airfoil structure of aircraft
一种飞行器的轻量化翼面结构
2024-08-02
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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