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首页> 外文期刊>Chinese journal of aeronautics >DELAMINATION FORMATION AND DELAMINATION PROPAGATION OF COMPOSITE LAMINATES UNDER COMPRESSIVE FATIGUE LOADING
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DELAMINATION FORMATION AND DELAMINATION PROPAGATION OF COMPOSITE LAMINATES UNDER COMPRESSIVE FATIGUE LOADING

机译：复合材料层合板在压缩疲劳载荷下的分层形成和分层传播

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摘要

Fatigue tests of the smooth composite laminates and the notched composite laminates un- der compressive cyclic loading have been carried out. The damage mechanism is discussed and ana- lzyed. Damage evolution is monitored using stiffness decay. From these tests, it is found that the ini- tial delamination occurs at the free boundary of smooth specimens, or the notch boundary of notched specimens, subjected to the compression-composites cyclic load. A point of view in relation to two- phases of compression fatigue delamination of composites is proposed, namely, compression-compres- sion delamination consists of the delamination formation phase and the delamination propagation, and there is a "damage transition point" to separate this two-phase.
机译：在压缩循环载荷下，对光滑复合材料层压板和带缺口复合材料层压板进行了疲劳测试。讨论并分析了损坏机理。使用刚度衰减来监控损伤的演变。从这些测试中发现，初始分层发生在承受压缩复合循环载荷的光滑试样的自由边界或缺口试样的缺口边界处。提出了关于复合材料压缩疲劳分层的两个阶段的观点，即压缩-压缩分层由分层形成阶段和分层传播组成，并且存在一个“损伤转变点”来将其分开。两相。

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