Research On Bidirectional Large-thrust Linear Piezoelectric Actuator For Folding Wing

With the development of variant flight technology,the new folding wing aircraft has been widely used for its flexible deployment and folding of wings.This transformed form of flight allows it to maintain optimal aerodynamic performance to meet the different flight conditions required for multimission flight.The realization of the wing folding function is inseparable from the driving of the actuator,and requires the actuator not only to have a large thrust to overcome the corresponding aerodynamic drag and structural resistance in flight,but also to realize a large stroke motion to satisfy the folding angle.Therefore,a bi-directional linear piezoelectric actuator with high-thrust and largestroke based on the principle of the inchworm motion were proposed by analyzing the requirement of folded wing.The driving mechanism,structural design method and performance test of the actuator were studied.(1)The functional characteristics of the folding wing aircraft and the characteristics of the actuator were summarized.The characteristics and research status of the piezoelectric inchworm actuator were systematically expounded.(2)The folding wing configuration and power transmission mechanism were analyzed.Kinematics and dynamics of folding wing configuration were simulated by ADAMS software.Thus,the requirements of the actuator's output thrust and stroke were put forward.(3)A bi-directional linear piezoelectric inchworm actuator with high-thrust and large-stroke based on the principle of screw clamping was proposed.The working principle of single-stack and doublestack drive under pressure and tension was analyzed.(4)Through the analysis of the characteristic of the main functional components of the actuator,the selection and design of each functional component were realized.The main components were simulated and analyzed by using ANSYS/Workbench software.Thereby,the overall design of the actuator was completed.(5)The prototype of the actuator was fabricated.The output performance of the actuator was tested when the single-stack and double-stack were driven separately and when the double-head screw was replaced.The experimental results show that the actuator can meet the power and stroke requirements of the designed folding wing configuration.