The design of the next generation of aeronautical vehicles is driven by the vastly increased cost of fuel and the resultant imperative for greater fuel efficiency. Carbon fiber composites have been used in aeronautical structures to lower weight due to their superior stiffness and strength-to-weight properties. However, carbon composite material behavior under dynamic ballistic impact and blast loading conditions is relatively unknown. For aviation safety consideration, a computational constitutive model has been used to characterize the progressive failure behavior of carbon laminated composite plates subjected to ballistic impact and blast loading conditions. Using a meso-mechanics approach, a laminated composite is represented by a collection of selected numbers of representative unidirectional layers with proper layup configurations. The damage progression in a unidirectional layer is assumed to be governed by the strain-rate-dependent layer progressive failure model using the continuum damage mechanics approach. The composite failure model has been successfully implemented within LS-DYNA® as a user-defined material subroutine. In this paper, the ballistic limit velocity (V50) was first established for a series of laminates by ballistic impact testing. Correlation of the predicted and measured V50 values has been conducted to validate the accuracy of the ballistic modeling approach for the selected carbon composite material. A series of close-in shock hole blast tests on carbon composite panels were then tested and simulated using the LS-DYNA® Arbitrary-Lagrangian-Eulerian (ALE) method integrated with the Army Research Laboratory (ARL) progressive failure composite model. The computational constitutive model has been validated to characterize the progressive failure behavior in carbon laminates subjected to close-in blast loading conditions with reasonable accuracy. The availability of this modeling tool will greatly facilitate the development of carbon composite structures with enhanced ballistic impact and blast survivability.

中文翻译：

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碳复合材料弹道和爆炸行为建模与仿真

燃料成本的大幅增加以及由此产生的提高燃料效率的必要性推动了下一代航空器的设计。碳纤维复合材料由于其优异的刚度和强度重量比特性，已被用于航空结构以减轻重量。然而，碳复合材料在动态弹道冲击和爆炸载荷条件下的行为相对未知。出于航空安全考虑，计算本构模型已用于表征碳层压复合板在弹道冲击和爆炸载荷条件下的渐进破坏行为。使用细观力学方法，层压复合材料由具有适当叠层配置的选定数量的代表性单向层的集合表示。假定单向层中的损伤进展由使用连续损伤力学方法的应变率相关层渐进式失效模型控制。复合失效模型已在 LS-DYNA® 中成功实现为用户定义的材料子程序。在本文中，首先通过弹道冲击试验建立了一系列层压板的弹道极限速度 (V50)。已进行预测和测量的 V50 值的相关性，以验证所选碳复合材料的弹道建模方法的准确性。然后，使用与陆军研究实验室 (ARL) 渐进式失效复合模型集成的 LS-DYNA® 任意-拉格朗日-欧拉 (ALE) 方法对碳复合材料面板进行了一系列近距离冲击孔爆炸试验进行测试和模拟。计算本构模型已经过验证，可以以合理的精度表征在近距离爆炸载荷条件下碳层压板的渐进破坏行为。这种建模工具的可用性将极大地促进具有增强弹道冲击和爆炸生存能力的碳复合结构的开发。