摘要
进行了复合材料层合板低速冲击和冲击后压-压疲劳试验。在疲劳试验过程中详细测量了损伤扩展情况,获得了损伤扩展规律。将冲击损伤等效为一圆形开孔,应用含椭圆形夹杂的杂交应力单元分析含圆孔有限大板的应力分布,采用特征曲线和点应力判据相结合的方式并通过引入损伤扩展规律建立了含低速冲击损伤复合材料层板压-压疲劳寿命预测模型。通过与试验数据的对比,证明了该模型的有效性。同时,该模型还可预报在疲劳载荷下含冲击损伤层板的剩余压缩强度。
Low velocity impact and post-impacted compression-compression fatigue tests of composite laminates were performed. After measuring the damage area in detail, the paper proposed the rule of damage propagation in compression-compression fatigue tests. The impact damage was considered as a circle hole, and a special finite element including an elliptic inclusion was adopted to analyze the stress distribution. Base on the damage propagation rule, characteristic length and point stress criterion were used for predicting the compression-compression fatigue life of post-impacted laminates. A good agreement is observed between the computational and experimental results. In addition, this model can also be applied to predict the residual compressive strength of damaged laminates under fatigue loads.
出处
《工程力学》
EI
CSCD
北大核心
2013年第3期410-416,423,共8页
Engineering Mechanics
基金
国家自然科学基金项目(11102082)
关键词
复合材料层合板
低速冲击
疲劳
损伤扩展
剩余强度
composite laminates
low velocity impact
fatigue
damage propagation
residual strength
