摘要
分析了复合材料剩余强度随加载次数增加而单调衰减的疲劳损伤机理,得出复合材料剩余强度衰减率在其疲劳寿命全程内呈"快→缓→快"演化过程,并提出一个剩余强度衰减模型来描述这一过程。该模型从材料的疲劳破坏机制上分析了铺层形式对复合材料剩余强度衰减的影响,并综合考虑了材料抗疲劳性能、受载水平等影响因素。6种复合材料的系列试验数据验证了该模型。结果表明,该模型合理描述了复合材料剩余强度的衰减规律。
The change rule of residual strength of the laminate is monotonously decreased with the increase of loading cycles and its fatigue mechanism is analyzed. It is concluded that the degradation rate of the residual strength is from quick to slow and to quick again in the whole period of the fatigue life. Then, a residual strength degradation model is presented to describe the failure mechanism. The effects of the stacking sequence, the fatigue-resistant property and the fatigue loading level on strength degradation in the laminate are analyzed in the model. Several sets of experimental data of six type laminates are tested to verify the residual strength degradation model. Results show that the model can describe the degradation rule of the laminate.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2008年第4期517-520,共4页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
复合材料
层舍板
剩余强度
衰减
疲劳损伤
composite materials
laminates
residual strength
degradation
fatigue damage
