Design Of A Variable Trailing Edge Camber Wing Based On The Piezoelectric Hydraulic Pump

The higher requirements on vehicle performance have been put forward with the rapid development of aerospace technology, and the traditional plane layout methods make it more and more difficult to satisfy the aircraft to keep better aerodynamic performance and better flying state. Therefore, the new conceptual aircrafts with the self-adaption and self-adjusting structure have been preliminarily researched and explored by global researchers and scholars in recent years. The new conceptual aircraft, also named morphing aircraft, can change their structure to achieve optimal aerodynamic performance and state under different missions and environments. The continuous variable trailing edge aircraft is a mesoscale, variable airfoil aircraft, which can effectively improve aircraft maneuverability and cruise performance. At the same time, it puts forward new requirements to the actuation of driving its deformation.The new challenge traditional hydraulic pump difficultly satisfied the requirements, such as small volume, light weight, large energy density and so on, has been possible to be solved with the rapid development of smart materials in recent years. The actuation of different properties and purposes used smart materials such as piezoelectric material as the power output component have been developed by more and more researchers. Its unique advantages make it has broad application prospects in the aerospace, precision medical, precision instrument and robot, etc.Piezoelectric ceramic material has the advantages of high energy density, high output force and rapid response, and hydraulic transmission has the advantages of stepless speed regulation and reliably drive. In this paper, the actuator developed by utilizing piezo-stack material and the hydraulic drive system built by combining the advantages of both to drive the wing structure continuous variable camber of trailing edge.In this paper, first of all, the working principle of piezoelectric hydraulic pump has been described, and analyzed the output performance of it according to the theory of quasi static. The structure of the actuator has been designed and has carried on comprehensive testing of the output performance. The relations between the driving voltage amplitude, frequency, pre-pressure and the output performance are detailed analyzed respectively. The results show that the voltage amplitude has obvious effects on the output flow rate and the pressure difference, and the frequency mainly effect the output flow rate.Secondly, the wing structure has been designed systematically according to the requirements and the way of variable camber trailing edge has been chosen under the airfoil limitation. The driving mechanism has been designed with the method of skin carried on which utilize the hydraulic push rod through the connecting structure to drive trailing edge deformation. At the same time, the aerodynamic analysis and strength check of the wing structure has also been carried out.Finally, the preliminary flexible simulation analysis to the trailing edge structure model has been carried out by using ADAMS software, and the relation between the velocity of the hydraulic push rod motion and the angular momentum of trailing edge is obtained which can provide a reference for the follow-up flexible dynamics simulation analysis related it. The testing of trailing edge structure deformation was completed.