Study On The Lightweight Optimization Of Composite Materials Unmanned Aerial Vehicles(UAV) Wing Structure

The wing is a necessary force transferring and load-bearing components on the Unmanned Aerial Vehicles(UAV), having an impact on its overall performance. Study on structural quality about weight loss is also a major problem. The application of composite on UAV wing structure not only can achieve significantly structural weight loss, but also effectively improve the overall performance of UAV wing.The structure of the wing was optimized by the single goal-driven multivariate method. The overlay structure was optimized by composite wing parts were optimized by overlay structure using multiple-step method. The goal of weight loss and improving overall performance of the wing structure was achieved. The main research work and production are as follows:(1) The overall layout of wing structure was carried out, wing airfoil was confirmed and initial design parameters was established through analyzing design features of composite structure, the forms and external load of wing structure. The model of NACA2412 airfoils, thin skin and twin-spar wing multi-ribbed slab structure were established.(2) Wing structure was optimized using goal-driven optimization method in ANSYS Workbench. The influence of various design variables on optimization objectives and wing performance was analyzed. It was found that the initial wing structure was met the design requirements, exiting a big optimization space; the influence of skin thickness, width and thickness of the front and rear wing on the mass and the overall performance of wing structure are great. Comparing with previous design, the mass of wing structure was reduced 64%, structural efficiency was improved 79% after optimization. And a good optimization results was achieved.(3) Overlay structure of carbon fiber wing components was optimized using multiple-step method. The thickness of the sandwich structure upper and lower skin panels and the honeycomb core layer were optimized using single factor analysis method. Ply sequence of spars and ribs laminate structure were optimized using genetic algorithm, then any angle of the ply of spars and ribs was optimized. It was found that the wing was met the design requirements after optimization. Comparing with previous design, the mass of wing structure was reduced 33%; the strength of wing structural was enhanced 28%; the rigidity of wing structural was enhanced 17%; the largest Tsai-Wu failure factor of wing structural was reduced 38%. The overall performance of wing structure was improved.The mass of wing structure was totally reduced up to 76% through the optimization of wing structure and wing components for overlay structure compare to the before optimization of wing structure. Composite wing structure was studied, improving the overall performance of the wing structure. It provides a direction on engineering application.