基于内聚单元的复合材料层合板低速冲击损伤的数值模拟  

Numerical Simulation of Low-velocity Impact Damage in Laminated Com-posites by Using Cohesive Element

作　　者：刘洪权[1] 谭申刚[1] 薛应举[1] 

机构地区：[1]中航工业第一飞机设计研究院,西安710089

出　　处：《机械科学与技术》2016年第9期1455-1460,共6页Mechanical Science and Technology for Aerospace Engineering

摘　　要：建立了一套有限元模型来预测复合材料正交层合板由低速冲击载荷引起的层间应力及损伤。采用连续壳单元模拟层合板的各个单层,在复合材料层合板的可能损伤区域设置内聚单元模拟面内基体裂纹和层间分层损伤的起始和扩展。引入层间摩擦力模型模拟层间压缩应力对分层损伤的抑制作用。对于正交层合板,有限元模型准确的模拟了低速冲击载荷引起的分层损伤的面积和形状。数值模拟结果也表明面内基体裂纹与层间分层存在着相互作用关系,基体裂纹影响着分层损伤预测的准确性。有限元模拟结果和试验结果的对比表明,基于内聚单元的有限元模型可以用在复合材料正交层合板低速冲击损伤的数值模拟中。A numerical model for predicting low-velocity impact induced force and damage in laminated composites is developed. The stacked continuum shell elements are employed to model the laminate plies with discrete cohesive elements being placed in pre-determined potential damage zones to model the initiation and propagation of in-plane matrix cracks and interlaminar delamination. The contact friction is introduced between two adjacent plies,and the friction shear stress at the delamination crack wake will inhibit / reduce delamination growth. For a clustered crossply laminate,the model accurately calculated the impact load and damage area. It is shown that matrix cracks should be included in the model in order to simulate the delamination in adjacent interface. The practical outcome of this research is a validated finite element modelling approach that can be further improved for predicting low-velocity impact damage.

关 键 词：低速冲击 内聚单元 基体裂纹 分层损伤 正交层合板 

分 类 号：V215.2[航空宇航科学与技术—航空宇航推进理论与工程]