Comparative Structural Optimization Study of Composite and Aluminum Horizontal Tail Plane of a Helicopter

Bertan Arpacioglu, A. Kayran
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Abstract

This work presents structural optimization studies of aluminum and composite material horizontal tail plane of a helicopter by using MSC. NASTRAN SOL200 optimization capabilities. Structural design process starts from conceptual design phase, and structural layout design is performed by using CATIA. In the preliminary design phase, study focuses on the minimum weight optimization with multiple design variables and similar constraints for both materials. Aerodynamic load calculation is performed using ANSYS and the finite element model of the horizontal tail plane is created by using MSC.PATRAN. According to the characteristics of materials, design variables are chosen. For the aluminum horizontal tail, thickness and flange areas are used as the design variables; and for composite horizontal tail, attention is mainly focused on the ply numbers and ply orientation angles of the laminated composite panels. By considering the manufacturability issues, discrete design variables are used. For three different mesh densities, different initial values of the design variables, and similar design constraints, optimizations are repeated and the results of optimizations are examined and compared with each other. In the optimizations performed, constraints are taken as strength and local buckling constraints. It is shown that the optimization methodology used in this study gives confident results for optimizing structures in the preliminary design phase.
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直升机复合材料与铝制水平尾翼结构优化对比研究
利用MSC对某型直升机的铝及复合材料水平尾翼进行了结构优化研究。NASTRAN SOL200优化能力。结构设计过程从概念设计阶段开始,利用CATIA进行结构布置图设计。在初步设计阶段,研究的重点是两种材料在多设计变量和相似约束条件下的最小重量优化。利用ANSYS软件进行气动载荷计算,利用MSC.PATRAN软件建立水平尾翼的有限元模型。根据材料的特点,选择设计变量。对于铝水平尾翼,采用厚度和法兰面积作为设计变量;而对于复合水平尾板,关注的主要是层合板的层数和层合板的层向角。考虑到可制造性问题,采用离散设计变量。针对三种不同的网格密度、不同的设计变量初始值和相似的设计约束条件,重复优化,并对优化结果进行检验和比较。在优化过程中,约束条件分别为强度约束和局部屈曲约束。结果表明,本文所采用的优化方法对结构的初步设计具有较好的优化效果。
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