摘要
针对两种不同铺层顺序的,T300/BMP316复合材料层合板,进行了低速冲击后不同应力水平下的等幅拉-拉疲劳试验。结果表明:低速冲击后,材料疲劳寿命的对数与应力水平成线性关系;在低应力水平下,层合板的主要疲劳损伤模式为分层,而在高应力水平下,其主要疲劳损伤模式为纤维断裂;随着疲劳应力水平的降低,层合板内损伤面积增加且刚度退化幅度变大。
Fatigue testing of 3300/BMP316 laminates with two ply stacking sequences is performed in constant amplitude tension-tension loading at various stress levels. The linear relationship between the stress level and fatigue life is obtained for all laminates with impact damage. At lower stress level, the main damage in fatigue failed specimens is delamination, and at higher stress level, the main damage is fiber failure. The damage area and stiffness degradation of specimen are increased with the decrease of stress level.
出处
《宇航材料工艺》
CAS
CSCD
北大核心
2007年第2期73-76,80,共5页
Aerospace Materials & Technology
关键词
疲劳
低速冲击
复合材料层合板
Fatigue, Low velocity impact, Composite laminates
