火箭弹尾翼结构的Isight／ANSYS优化设计

为减轻火箭弹尾翼在结构性能约束下的质量，对其结构设计参数进行了优化。对尾翼的载荷分布、结构特性进行了分析，并利用ANSYS软件APDL语言建立了有限元分析的参数化模型。选取质量最小为目标函数，翼根厚度、翼梢厚度和安装位置为设计变量，强度和刚度为约束条件，建立了结构优化模型。基于应力准则法及直接搜索策略，通过Isight集成ANSYS软件对尾翼结构进行了优化设计。通过典型实例的仿真表明：尾翼减重效果明显、方法有效。

Structure Optimal Design for Tail Fins of Rockets via Isight/ANSYS

To minimize the structural mass of the tail fins of rocket under the constraints of structural per formance, the structural design parameters are optimized. The load distribution and structural features of the tail fin are analyzed, and the parametric modeling of the tail fin which can be executed the finite ele ment analysis is built via APDL language of ANSYS. To take the minimum mass as objective function, and choose some geometric parameters including fin root thickness, fin tip thickness and installation position as the design variables, meanwhile choose strength and stiffness as the constraints, thus the mathematical model for structural optimization design is established. Based on stress criterion method and direct search strategy and by the way of integrating ANSYS into Isight, the iterations of optimization process can be car ried out. The simulation results of a typical example show that the effect to minimize the structural mass of the tail fins is obvious and the method is effective.