Finite Element Analysis Of UAV Wing Based On ABAQUS And Local Design

Wing as the main force transmission components of UAV, Prone to fatigue failure, the deformation will also have a huge impact on flight performance. Therefore, structural analysis of the wing is particularly important. In addition, the layout of materials and the connection forms among components has an effect on structural performance. Reasonable optimization of the structure can not only saved material, but also improved the structural efficiency and reduced the weight.In this paper, nonlinear finite element analysis software ABAQUS was used to analysis the structural strength and stiffness of the wing which under variety of conditions and materials. The new design project have gotten. The main contributions of this dissertation are as follows:First of all, the finite element model of the wing is built and simplified. The paper discussed the issues of meshing techniques, algorithm and the selection of unit types. In the modeling process, the principle is reduced the calculation and improve the accuracy, appropriate techniques and algorithms was used. The aerodynamic loads on the wing were calculated under different attack angle, at the same time according to the actual situation the total loads on the wing have been simplified, we got loads of three flight conditions.Secondly, According to the design requirements, the structural strength and stiffness of the wing which under three conditions were analysis, the design load and the danger zone of structure were determined. We also conducted a comparative analysis of different materials wing and different wing. The results show that the composite materials used in the wing not only to reach the structural strength and stiffness requirements, but also reduced weight, however , poor process performance of skin will effect lift which the wing obtained.Finally, According to analysis result of the wing under design load, the paper discussed the efficiency of the wing, the materials of structure and the thickness of skin is selected, then the new solution have been determined. From the simulation result of the new solution wing, the new wing not only ensured the reliability and safety of structure, but also made 66.5% weight reduction compared with design wing.