以一种平直机翼布局小型无人机模型为研究对象,利用CATIA软件构建机翼结构模型,包括蒙皮、翼肋和翼梁.基于ANSYS WORKBENCH集成软件平台,使用单向流固耦合方法对机翼进行应力和变形数值分析,获得气动载荷作用下机翼上的应力和总变形.利用拓扑优化方法以提高静强度为优化目标,减少模型重量为优化对象,对翼肋结构进行优化设计,对优化后构建的机翼再次进行应力和变形数值分析.结果表明经过拓扑优化设计,模型机翼结构重量减小约31％,承受最大应力减小约6％.拓扑优化得到的最优布局,既能减小机翼结构重量,同时其承载能力也有所增强.%A small UAV with straight wing configuration is used as the prototype, and the wing structure model is built by CATIA, including the structure of skin, wing rib, wing beam and so on. Based on the ANSYS WORKBENCH platform, the stress and deformation numerical analysis of the wing is carried out by unidirectional fluid-solid coupling. The stress and total deformation of the wing are obtained under the aerodynamic load. Topology optimization is used to enhance static strength for optimization purpose, reduce weight as optimization object, and optimize the original rib design. The stress and deformation analysis of the wing after optimization is carried out. The results of the numerical calculation show that the structural weight of the wing is reduced by about 31％, and the strength is enhanced by about 6％ after topology optimization. The optimal layout obtained by topology optimization can not only reduce the weight of wing structure, but also enhance the structure strength.
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