Abstract
Layered piezo-composite unimorph actuators have been studied by many research teams to provide active vibration control of thin-walled aerospace structures, control the shapes of aircraft wing airfoils, and control the fins of small missiles, because they require less space and provide better frequency responses than conventional electro-magnetic motor actuator systems. However, due to the limited actuation strains of conventional piezo-composite unimorph actuators with poly-crystalline piezoelectric ceramic layers, they have not been implemented effectively as actuators for small aerospace vehicles. In this study, a lightweight piezo-composite unimorph actuator (LIPCA-S2) was manufactured and analyzed to predict its flexural actuation displacement. It was found that the actuated tip displacement of a piezo-composite cantilever could be predicted accurately using the proposed prediction model based on the nonlinear properties of the piezoelectric strain coefficient and elastic modulus of a piezoelectric single crystal.
Highlights
Over the past two decades, research on piezo-composite actuators has been actively performed as a response to strong demands for light, compact actuators to replace conventional electro-magnetic motor actuators in micro robots, small flying drones, and compact missile systems.Layered piezo-composite actuators have become an attractive option for small aerospace structures because they are relatively simple and compact compared with conventional actuators using electro-magnetic motors
A device for measuring the tip displacement of As a unimorph cantilever constructed characterize the performance of lightweight piezo-composite actuator (LIPCA)-S2 and LIPCA-C3
One can see that the cpua values of the LIPCA-S2 are 780% greater than those of the LIPCA-C3, indicating that greater actuation displacement can be obtained from an actuator with a greater cpua value
Summary
Over the past two decades, research on piezo-composite actuators has been actively performed as a response to strong demands for light, compact actuators to replace conventional electro-magnetic motor actuators in micro robots, small flying drones, and compact missile systems. Due to the limited actuation strain of conventional piezo-composite actuators using poly-crystal piezoelectric ceramic layers, the LIPCA has not been implemented effectively for small aerospace vehicles. Yoon et al [13] designed control fins for a small flying vehicle using piezo-composite unimorph actuators and proposed a linear cantilever tip displacement prediction model [14] for the compression stress variations in a PMN-29PT single-crystal layer considering changes in the piezoelectric strain coefficient and elastic modulus. One of the actuator types that was designed to provide excellent flexural displacement performance is the piezo-composite unimorph. These actuators incorporate a piezoelectric single-crystal actuation material layer embedded in a composite laminate. In the LIPCA, the material stacking sequence is designed such that the actuation layer is separated from the flexural neutral surface of the piezo-composite actuator to produce a greater actuating bending moment
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