轻质拓扑优化夹芯板的气动弹性分析

Maliheh Najafi, António J. M. Ferreira, Flávio D. Marques
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引用次数: 0

摘要

带有晶格核心的夹层结构是一种新型轻质复合材料结构,在航空航天工业中得到了广泛应用。此外,夹芯板在超音速流动状态下的气动弹性行为仍有待深入研究。本研究对夹芯板进行了拓扑优化,研究了夹芯板的超音速扑动。本文介绍了基于分层理论和一阶活塞理论的夹芯板有限元模型。夹芯板芯材采用拓扑优化方法进行评估,并设置了飘动载荷约束。随后开发了分析均质化方案,以提供拓扑优化面板的等效力学性能。建模方法得到了充分验证,结果表明,与其他传统面板设计相比,夹层面板能够扩大无扑翼作业飞行范围。对拓扑优化的夹层板的临界扑翼条件进行了参数分析。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Aeroelastic analysis of a lightweight topology-optimized sandwich panel
Sandwich structures with lattice cores are novel, lightweight composite structures and are widely used in the aerospace industry. Besides, the aeroelastic behavior of sandwich panels in a supersonic flow regime still needs to be thoroughly studied. This work investigates the supersonic flutter of a sandwich panel whose core is topology-optimized. A finite element model of a sandwich panel based on the layerwise theory, coupled with the first-order piston theory, is presented. The sandwich panel core is assessed using a topology optimization approach with flutter loading constraints. The subsequent analytical homogenization scheme is developed to provide the equivalent mechanical properties of the topology-optimized panel. The modeling approach is fully validated, and the results demonstrate that the sandwich panel is capable of enlarging the flutter-free operational flight range when compared with other conventional panel designs. A parametric analysis of the topology-optimized sandwich panel regarding the critical flutter conditions is performed.
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