Numerical Simulation for Composite Wing Structure Design of an Unmanned Aerial Vehicle

The use of unmanned aerial vehicle (UAV) is getting common as its small size can easily replace bulky aerial vehicle such as helicopters and airplanes in performing surveillance missions. However, spacious room is need to store the UAV.

In this project will be the specific design of a composite wing; structural and aerodynamic numerical analysis interaction, with the help of specialized software (FEA), seeking an aerodynamic increase compared to what exists in the market.

To improve the structure performances of unmanned aerial vehicle (UAV) wing, numerical simulation and optimization design principle was carried out for designing the best composites wing structure. Thus tradeoff can be obtained between the general performance and the weight of the wing. Advanced composite material has its own outstanding features, such as high specific strength, high specific modulus, designable performance and integral forming easily. The application of advanced composite material on the aircraft structure can significantly reduce the weight, and improve the aerodynamic and flight performances. In this project, the parametric finite element model is established using parametric modeling technique for stress and stain analysis. Given any set of geometric parameters, the geometric modeling, meshing, strain and stress analysis can be automatically carried out in sequence