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提出了一种基于拓扑优化的直升机旋翼桨叶剖面设计方法。采用了有限元方法计算直升机旋翼桨叶剖面刚度特性,截面考虑了剪切和翘曲变形,并消除了翘曲位移和刚体位移之间的耦合作用。基于SIMP拓扑优化算法,以旋翼桨叶平均柔度或者剖面刚度为设计目标,桨叶重量为约束函数,建立了旋翼桨叶拓扑优化模型。提出的敏度求解算法具有较高的计算精度,采用序列线性规划算法对旋翼桨叶剖面进行优化设计。结果表明在展长较小并且承受均布升力载荷情况下,Ⅱ型截面梁的柔度最小,而当展长增大时,工字梁截面具有最小的柔度。此外,旋翼桨叶外载荷等对优化结果也有较大的影响。提出的拓扑优化方法适合于概念设计阶段的直升机旋翼桨叶剖面设计。
A helicopter rotor blade profile design method based on topology optimization is proposed. The finite element method was used to calculate the section stiffness characteristics of helicopter rotor blades. The section considered the shear and warpage deformation and eliminated the coupling between warping displacement and rigid body displacement. Based on the SIMP topology optimization algorithm, the rotor blade average flexibility or section stiffness is taken as the design objective, the blade weight is the constraint function, and the rotor blade topological optimization model is established. The proposed algorithm for solving the sensitivity has a high computational accuracy. The serial linear programming algorithm is used to optimize the rotor blade profile. The results show that in the case of smaller extension and under uniform hoisting load, the flexibility of Ⅱ-type cross-section beam is the smallest, and when the elongation increases, the I-beam section has the minimum flexibility. In addition, the outer rotor blade load on the optimization results also have a greater impact. The proposed topology optimization method is suitable for the helicopter rotor blade profile design in conceptual design stage.