Research On Structures And Realization Method Of A Variable-thickness Morphing Wing

The surroundings of supersonics aircraft change intensively during flight, and it is difficult fortraditional aircraft wings to fit the change properly. The morphing wing based on adaptive smartstructure is one of the most effective methods to solve the problem. Morphing wing could change itsown shape according to the changes on flight environment and missions to keep the best flight statusby making use of smart material or other actuators. There are many ways of morphing wing. Comparewith others, changing relative thickness of the airfoil is easy to be realized and controlled, and becomeone of the best choice of the wing deformation.This paper is about some theoretical and practical research on a variable-thickness morphingwing. First, the deformation theory of the variable-thickness wing was introduced. Simulation of themorphing wing structure was finished using ANSYS in order to get the optimal airfoil in diffidentdriving displacements. Compared with the original airfoil, the feasibility of this theory was verified.Then, the bearing structures of the morphing wing were designed in CATIA, and were then processedto physical model. In addition, designing a measurement and control system based on PXI, and usingthe strategies combined with segment control and PID control on the morphing wing. Finally, thecontrolling experiment is accomplished. The results show that a certain variation of thickness isachieved and the degree of accuracy of the controlling is high.