Design and validation of a variable camber wing structure  

作　　者：Xiasheng SUN Jingfeng XUE Jin ZHOU Zhigang WANG Wenjuan WANG Mengjie ZHANG 

机构地区：[1]Chinese Aeronautical Establishment,Beijing 100012,China [2]School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China [3]Aircraft Strength Research Institute of China,Xi’an 710065,China [4]Graduate School of Chinese Aeronautical Establishment,Yangzhou 225002,China

出　　处：《Chinese Journal of Aeronautics》2024年第2期1-11,共11页中国航空学报（英文版）

基　　金：supported by the National Research Project“Variable Camber Wing Technology(VCAN)”,China。

摘　　要：Variable camber wing technology is one of the important development trends of green aviation at present.Through smooth,seamless,continuous and adaptive change of wing camber,the aerodynamic performance is improved in achieving increase in lift and reduction in resistance and noise.Based on the aerodynamic validation model CAE-AVM,Chinese Aeronautical Establishment(CAE)has carried out the design and validation of a variable camber wing,proposed an aerodynamic deformation matrix for the leading and trailing edges of aircraft wings in takeoff,landing and cruise conditions.Various structures and driving schemes are compared,and several key technology problems of leading and trailing edge deformation are solved.A full-size leading edge wind tunnel test piece with a span of 2.7 m and a trailing edge ground function test piece are developed.The deformation and shape maintenance capabilities of the leading edge is verified under real wind load conditions,and the load bearing and deformation capabilities of the trailing edge is verified under simulated follow-on load.The results indicate that the leading and trailing edges of the variable camber wing can achieve the required deformation angle and have a certain load-bearing capacity.Our study can provide some insights into the application of variable camber wing technology for civil aircraft.

关 键 词：Variable camber wing Leading edge Trailing edge STRUCTURE Measurement and control TEST 

分 类 号：V224[航空宇航科学与技术—飞行器设计]