Kondratiev Andrii, Píštěk Václav, Gajdachuk Vitaliy, Kharchenko Maksym, Nabokina Tetyana, Kučera Pavel, Kučera Ondřej
Department of Materials Science and Engineering of Composite Structures, O.M. Beketov National University of Urban Economy in Kharkiv, Marshal Bazhanov Str. 17, 61002 Kharkiv, Ukraine.
Institute of Automotive Engineering, Brno University of Technology, Technická 2896/2, 616 69 Brno, Czech Republic.
Polymers (Basel). 2023 May 29;15(11):2503. doi: 10.3390/polym15112503.
Carbon fibres used as a honeycomb core material (subject to a proper in-depth analysis of their reinforcement patterns) allows solving the thermo-dimensional stability problem of the units for space systems. Based on the results of numerical simulations with the support of finite element analysis, the paper provides an evaluation of the accuracy of analytical dependencies for the determination of the moduli of elasticity of a carbon fibre honeycomb core in tension/compression and shear. It is shown that a carbon fibre honeycomb reinforcement pattern has a significant impact on the mechanical performance of the carbon fibre honeycomb core. For example, for honeycombs measuring 10 mm in height, the maximum shear modulus values corresponding to the reinforcement pattern of ±45° exceed the minimum values for a reinforcement pattern of 0° and 90° by more than 5 times in the XOZ plane and 4 times for the shear modulus in the YOZ plane. The maximum modulus of the elasticity of the honeycomb core in the transverse tension, corresponding to a reinforcement pattern of ±75°, exceeds the minimum modulus for the reinforcement pattern of ±15° more than 3 times. We observe a decrease in the values of the mechanical performance of the carbon fibre honeycomb core depending on its height. With a honeycomb reinforcement pattern of ±45°, the decrease in the shear modulus is 10% in the XOZ plane and 15% in the YOZ plane. The reduction in the modulus of elasticity in the transverse tension for the reinforcement pattern does not exceed 5%. It is shown that in order to ensure high-level moduli of elasticity with respect to tension/compression and shear at the same time, it is necessary to focus on a reinforcement pattern of ±64°. The paper covers the development of the experimental prototype technology that produces carbon fibre honeycomb cores and structures for aerospace applications. It is shown by experiments that the use of a larger number of thin layers of unidirectional carbon fibres provides more than a 2-time reduction in honeycomb density while maintaining high values of strength and stiffness. Our findings can permit a significant expansion of the area of application relative to this class of honeycomb cores in aerospace engineering.
用作蜂窝芯材料的碳纤维（需对其增强模式进行适当深入分析）能够解决空间系统单元的热尺寸稳定性问题。基于有限元分析支持下的数值模拟结果，本文对用于确定碳纤维蜂窝芯在拉伸/压缩和剪切时弹性模量的解析相关性的准确性进行了评估。结果表明，碳纤维增强模式对碳纤维蜂窝芯的力学性能有显著影响。例如，对于高度为10毫米的蜂窝，在XOZ平面中，对应于±45°增强模式的最大剪切模量值比0°和90°增强模式的最小值高出5倍以上，在YOZ平面中，剪切模量高出4倍。对应于±75°增强模式的蜂窝芯横向拉伸时的最大弹性模量比±15°增强模式的最小模量高出3倍以上。我们观察到碳纤维蜂窝芯的力学性能值会因其高度而降低。对于±45°的蜂窝增强模式，XOZ平面中剪切模量降低10%，YOZ平面中降低15%。该增强模式下横向拉伸时弹性模量的降低不超过5%。结果表明，为了同时确保在拉伸/压缩和剪切方面具有高水平的弹性模量，有必要关注±64°的增强模式。本文涵盖了用于航空航天应用的生产碳纤维蜂窝芯和结构的实验原型技术的开发。实验表明，使用大量单向碳纤维薄层可使蜂窝密度降低两倍以上，同时保持高强度和高刚度值。我们的研究结果能够显著扩大这类蜂窝芯在航空航天工程中的应用领域。
