Investigation Of The Trailing Edge Of Morphing Wing Based On The Multi-functional Skin

Morphing wing can significantly enhance flight control ability, reduce the aerodynamic drag,reduce structural weight, improve the wing flutter characteristics and resist the ability of sudden wind,as well as improve the plane motor performance. Deflection of leading and trailing edge of morphingwing, which can lead to an increased aerodynamic efficiency, has become the focus of currentresearch project.The main contents in this thesis are listed as below:First of all, MSC.NASTRAN software is used to optimize the structure radius, layer thicknessU-type flexible wing skin and the number of layers, and analyze the inherent characteristics of thisskin, a better comprehensive mechanical properties structure size is obtained. After finite elementsimulation about the inherent characteristics of the flexible wing skin, the first four inherent frequencyare got as belows,4.99Hz,18.48Hz,28.74Hz and40.37Hz, which provided the basis for vibrationfrequency of the further experiment.Then, specimen made of glass fiber enhanced composite materials is tested to verify thecorrection of simulation, the size are number of ten, thickness of1.2mm and radius of4mm, bearingcapacity of the skin is enhanced while the extension ability is not affected with filled colloid. What’smore, impact of vibration experiment of the skin was done to prove the correction of the formersimulation, the first inherent frequency of the skin attached to the trailing edge of morphing wing is13.08Hz, which verified the reliability of finite element simulation (error between0.2%-7.4%).Finally, vibration exciter is used to excite the trailing edge of a wing to simulate environmentinterference noise, dynamic strain signal is obtained under different vibration frequency. Butterworthband pass filter is designed to analyze the dynamic strain signal, and data which can reflect thedeflection of trailing edge of morphing wing is finally obtained. The results showed that the dataextracted from dynamic strain signal can go well with the given stain signal, which can reflect thedeflection of trailing edge of the morphing wing.This study is mainly used for the structure and inherent characteristics of U-type flexible skinattached to the trailing edge of morphing wing, as well as relevant strain experiment tests, which canprovide useful reference, experimental basis and data support for the further study of morphing wing.