基于MDNastran的多工况复合材料T尾优化研究

T尾是典型的民用飞机或运输机气动布局形式之一，寻求满足刚度、强度、稳定性约束条件下的结构轻重量是结构方案设计阶段的主要工作任务。利用复合材料弹性优化剪裁技术，运用Nastran软件系统，在细致建立有限元数值分析模型基础上，将梁和杆面积、板壳厚度以及复合材料铺层厚度作为优化变量，进行了结构优化，结果表明：结构各部件重量有所降低。为了考察给定的典型复合材料铺层角布置的合理性，引入复合材料的单元材料方向作为优化变量进行再次优化。优化结果表明：虽然增加材料方向作为优化变量能够使结构重量较初次优化有所降低，但是考虑到制造工艺要求，典型复合材料铺层布置也是合理的。

Design Optimization for Composites T-tail under Multi-cases Based on MD Nastran

T-tail is one of typical aerodynamic configuration for civil aircraft and military transporter. In the phase of structure design it is the main task to search for the minimum weight satisfying the request of stiffness, strength, and stability. Composite elastic tailoring technique is adopted in the optimization using MD Nastran. On the base of finely built finite element model, the area of beam and rod, the thickness of shell and the thickness of layer for the composite are selected as the optimization variables, the results show that the weight of each component is reduced. To check the rationality of typical arrangement for the ply orientations of composite material, the material orientation is brought in as optimization variable. The optimized data demonstrates that the weight of the T-tail may decrease compared with the first optimization when the material orientation is added as optimization variable. But considering technical requirements the typical arrangement for the ply orientations of composite material is reasonable.