Comparative study of two lay-up sequence dispositions for flexible skin design of morphing leading edge  

作　　者：Yu YANG Zhigang WANG Shuaishuai LYU 

机构地区：[1]Aircraft Strength Research Institute,Xi’an 710065,China

出　　处：《Chinese Journal of Aeronautics》2021年第7期271-278,共8页中国航空学报（英文版）

摘　　要：Morphing leading edge has great potential for noise abatement and aerodynamic efficiency improvement.The drooping effect is realized by bending of the flexible skin which encloses to form the leading edge.Since the flexible skin is often made of composite laminates of Glass Fiber Reinforced Plastics(GFRP),the lay-up sequences have become the determinant,which affects not only the morphing quality but also the manufacturing complexity.Two optimizing methods of layup sequences are comparatively studied.In the first method,the laminal quantities in 0,±45and 90vary independently,while in the second one,the concept of isotropic laminate unit[0/45/45/90]s is employed and the unit quantity is the unique variable.Final evaluation demonstrates that for both methods there is insignificant impact to the overall morphing quality;however,specific concern is equally necessary for these two methods to the tip of the leading edge where the skin is at its minimum thickness and bears the most severe bending deformation.In terms of computational efficiency and post-processing labor,the second method has better performance.

关 键 词：Composite laminates Flexible skin Glass fiber reinforced plastics Lay-up sequence Leading edge Morphing wing 

分 类 号：V22[航空宇航科学与技术—飞行器设计]