The invention relates to the technical field of aircraft wing design, in particular to an aircraft morphing wing which comprises a front edge, a wing body and a rear edge which are sequentially connected, the wing body comprises a plurality of unit cell structures, every two adjacent unit cell structures are connected with each other, and each unit cell structure comprises a chiral structure and a zero poisson ratio structure which are connected with each other; all the chiral structures are arranged on the transverse section of the morphing wing, and each chiral structure has a tensile rotation characteristic, so that the morphing wing is bent when subjected to tension and compression loads; all the zero Poisson's ratio structures are arranged on the longitudinal section of the morphing wing, and each zero Poisson's ratio structure has the tensile deformation characteristic, so that the morphing wing is lengthened when subjected to tension and compression loads. According to the scheme, the problems of small adjustable range and discontinuous shape change of the wing in the prior art can be solved.
本发明涉及飞机机翼设计领域技术领域,尤其涉及一种飞机的变体机翼,包括:依次连接的前缘、翼身和后缘,所述翼身包括多个单胞结构,相邻两个所述单胞结构相互连接,每个所述单胞结构均包括相互连接的手性结构和零泊松比结构;所有所述手性结构均设置于所述变体机翼的横向剖面上,每个所述手性结构均具有拉伸旋转特性,以使所述变体机翼在受到拉压载荷时变弯度;所有所述零泊松比结构均设置于所述变体机翼的纵向剖面上,每个所述零泊松比结构均具有拉伸变形特性,以使所述变体机翼在受到拉压载荷时变展长。本方案可以解决相关技术中存在的机翼可调节范围小和形状变化不连续的问题。
Morphing wing of airplane and assembling method thereof
一种飞机的变体机翼及其组装方法
2023-12-08
Patent
Electronic Resource
Chinese