Nonlinear vibration control of high-aspect-ratio composite trapezoidal plate wing structure via shape memory alloy: Theoretical formulation and experimental research

Abstract

It is a crucial mission for the engineers to ensure the dynamic stability and safety of the composite wing with high-aspect-ratio, which is the effective component to guarantee aerodynamic efficiency of aircraft. This contribution addresses on a systematic theoretical and experimental investigation on the vibration control of the high-aspect-ratio composite wing of electric aircraft which is simplified to the composite laminated trapezoidal plate (CLTP). The shape memory alloy (SMA), which belongs to the light high-damping material with great energy absorbing characteristics, is imported for the nonlinear vibration control of high-aspect-ratio wing. The governing equation of the trapezoidal plate in the hygrothermal environment is obtained through the coordinate change in frame of the Kirchhoff thin plate theory. On the basis of determining the constitutive equation and the ability of energy dissipation at various temperatures of shape memory alloy via experiment and theory, the dynamic equation of the composite laminated trapezoidal plate with SMA is established via a beam- trapezoidal plate combing structure, in which the SMA is stand by the Euler beam with nonlinear constitutive model. After confirming the accuracy of present formulation, the vibration damping ability of shape memory alloy on CLTP is demonstrated. The influence of temperature, laying mode and external excitation amplitude on the vibration suppression performance of shape memory alloy is revealed. Some novel conclusions are reached, which can provide theoretical and experimental guidance for the dynamic and vibration suppression of the high-aspect-ratio composite wing of electric aircraft.