Failure Prediction in Fiber Metal Laminates for Next Generation Aero Materials
Failure Prediction in Fiber Metal Laminates for Next Generation Aero Materials
复制标题
下一代航空材料纤维金属层压板的失效预测
DOI：
10.1088/1757-899x/149/1/012102
复制
发表时间：
2016
期刊：
影响因子：
--
通讯作者：
C. Chandramouli
中科院分区：
文献类型：
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作者：
H. Rao;P. J. Ramulu;M. Vardhan;C. Chandramouli
在航空航天工业中，对低密度、低成本、具有良好机械性能的材料有着巨大的需求。在这种情况下，有许多研究者开发了复合材料方面的新材料。同样，本文也旨在通过数值研究为不同成分的三维编织玻璃纤维金属层压板（FML）材料的成本效益提供一种新的方法。提出了一种基于脱黏元的渐进式分层模拟方法。去粘聚单元被放置在固体单元层之间，这些单元会根据加载情况打开和剪切。在没有事先知道脱层的位置、大小或传播方向的情况下，模拟损伤的发生和脱层的生长。提出了一种适用于任何相互作用准则的混合模式分层软化规律。提出的本构方程采用最大相对位移这一单一变量来跟踪一般加载条件下的界面损伤。定义单元本构方程所需的材料性能是层间断裂韧性、惩罚刚度和强度。
In aerospace industry, there is huge demand for low density and low cost materials with better mechanical properties. In this view, there are many researchers developed new materials interms of composites. Similar manner, the present paper also aimed to produce a new approach for cost effective materials of 3D weaved glass fiber metal laminates (FML) with different compositions using a numerical study. A method for the simulation of progressive delamination based on de-cohesion elements has been presented. De-cohesion elements are placed between layers of solid elements that open and shear in response to the loading situation. The onset of damage and the growth of delamination are simulated without previous knowledge about the location, the size, or the direction of propagation of the de-laminations. A softening law for mixed-mode delamination that can be applied to any interaction criterion is also proposed. The constitutive equation proposed uses a single variable, the maximum relative displacement, to track the damage at the interface under general loading conditions. The material properties required to define the element constitutive equation are the inter-laminar fracture toughness's, the penalty stiffness, and the strengths.