Impact damage tolerance of laminated composite helicopter blades
Impact damage tolerance of laminated composite helicopter blades
复制标题
层压复合材料直升机桨叶的冲击损伤容限
DOI：
10.1016/j.compstruct.2003.09.034
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发表时间：
2003
影响因子：
6.3
通讯作者：
E. Evseev
中科院分区：
文献类型：
--
作者：
E. Morozov;S. A. Sylantiev;E. Evseev
本文研究了复合材料直升机桨叶在冲击载荷作用下的抗损伤性能。采用理论和实验相结合的方法，确定了复合材料层合板和分离层的动态应力强度因子。研究了弹丸尺寸对复合材料叶片损伤容限的影响，并估算了缺陷的容限尺寸。
The paper is concerned with the study of the damage resistance of laminated composite helicopter blades subjected to impact loading. Dynamic stress intensity factors are determined for composite laminate and separate layers using combined theoretical and experimental approach. The effect of the projectile size on the damage tolerance of composite blade is investigated and tolerable sizes of the defects are estimated.