Virtual manufacturing of composite aerostructures
Virtual manufacturing of composite aerostructures
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DOI：
10.1017/aer.2015.19
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发表时间：
2016-01-01
影响因子：
1.4
通讯作者：
Waas, A. M.
中科院分区：
文献类型：
--
作者：
D'Mello, R. J.;Maiaru, M.;Waas, A. M.
过去的一个世纪见证了飞行器的兴起和成熟，从莱特兄弟的飞行员到今天的现代客机和战斗机。本世纪初，随着波音787飞机的推出，飞行器技术又取得了另一项成就，按重量计算，波音787飞机中有相当大一部分是聚合物基纤维复合材料。因此，本文研究了纤维增强聚合物基复合材料的制造工艺对力学性能的影响。计算采用微尺度的有限元(FE)方法，其中代表性体积单元(RVEs)采用周期边界条件(PBCs)分析。考虑了直纤维预浸料基复合材料和纺织复合材料。使用商用程序ABAQUS作为有限元方程的求解器，并辅之以用户编写的子程序。通过使用保持网格客观性的Bazant-oh裂隙带模型，实现了从连续介质到损伤/破坏的转变。给出了首先进行固化，然后进行机械加载的RVE的结果。通过考虑纤维体积分数保持不变但纤维随机堆积的多纤维RVE，考察了纤维堆积随机性对微观结构的影响。平纹织物复合材料也是先硫化，然后施加机械载荷。在整个分析过程中都考虑了故障的可能性，甚至在施加使用中的机械载荷之前，固化过程中也可能发生故障。分析表明，在考虑和没有考虑固化损伤的情况下，固化后的RVE强度和刚度都存在差异。
The past century has witnessed the rise and maturity of the flying machine, starting with the Wright brothers flyer to today's modern passenger aircrafts and warfighters. At the start of this century, yet another achievement in flying vehicle technology was seen with the launch of the Boeing 787 aircraft, which has a significant portion by weight of polymer matrix fibre composites. This paper, therefore, addresses the effects of the manufacturing process of fibre reinforced polymer matrix composites on mechanical performance. Computations are carried out using the Finite Element (FE) method at the microscale where Representative Volume Elements (RVEs) are analysed with Periodic Boundary Conditions (PBCs). Straight fibre prepreg-based composites and textile composites are considered. The commercial code ABAQUS is used as the solver for the FE equations, supplemented by user-written subroutines. The transition from a continuum to damage/failure is effected by using the Bazant-Oh crack band model, which preserves mesh objectivity. Results are presented for RVEs that are first subjected to curing and subsequently to mechanical loading. The effect of the fibre packing randomness on the microstructure is examined by considering multifibre RVEs where fibre volume fraction is held constant but with random packing of fibres. Plain weave textile composites are also cured first and then subjected to mechanical loads. The possibility of failure is accommodated throughout the analysis failure can take place during the curing process even prior to the application of in-service mechanical loads. The analysis shows the differences in both the cured RVE strength and stiffness, when cure-induced damage has and has not been taken into account.