A design of honeycomb sandwich based on Piezoelectric Fiber Composites

Recently Piezoelectric Fiber Composites has been given more attentions in a variety of aerospace researches because of its good application value, such as the active deformation control of structure and aircraft, noise reduction and structural health monitoring because it has several advantages: larger Piezoelectric coefficient, plane driver response, different anisotropy performances on-demand, strong anti-destruction capability and its easy application to curved surface. This paper will design a new kind of honeycomb sandwich actuators for active deformation control of structure, which is using a novel macro-fiber composites as the driver materials based on Piezoelectric fiber and interdigitated electrodes, and the honeycomb material as core. The specific method will be demonstrated as following: firstly getting MFC materials adhere to panel of plane is used as an actuator, to control the deformation of structure. And then, parameters of honeycomb structure should be optimized based on the theory analysis of sandwich structure, to meet the demand that the honeycomb structure is not only light, but also has lager actuating function and good bearing capability. The results show that the proposed method for designation and optimization of actuator using MFC is feasible, which can be applied in the rudder of small and micro aircraft as well as medium-sized aircraft active control of the flow field.