复合材料加筋壁板多点冲击损伤和高周剪切疲劳试验  

Test of multi-impact damage and high-cycle shear fatigue of stiffened composite panels

作　　者：张铁军[1] 李曙林[1] 常飞[1] 尹俊杰[1] 安涛[1] 

机构地区：[1]空军工程大学航空航天工程学院,西安710038

出　　处：《航空动力学报》2017年第12期2872-2879,共8页Journal of Aerospace Power

基　　金：国家自然科学基金青年基金(51201182)

摘　　要：为研究多点冲击损伤和高周剪切疲劳对复合材料加筋壁板损伤演化、屈曲行为及破坏模式的影响,制作了9块相同构型的复合材料加筋壁板,设计了冲击试验、高周剪切疲劳试验和剩余剪切强度试验。在多点冲击和高周剪切疲劳试验过程中,使用超声C扫描系统监测了损伤区域。C扫描图像表明损伤区域的长度和宽度随着循环次数的增加而增加。与无预制损伤试验件相比,多点冲击损伤和高周剪切疲劳试验件的平均破坏载荷下降了约50%。冲击或疲劳形成的初始损伤对破坏模式产生影响,冲击疲劳试验件出现了局部蒙皮屈曲变形,破坏裂纹非常接近冲击点。To study the effect of multi-impact damage and high-cycle shear fatigue on the damage evolution,buckling behavior and failure modes of stiffened composite panels,nine stiffened composite panels were manufactured with similar configurations,and the impact test,high-cycle shear fatigue test and residual shear strength test were designed.During the multi-impact and high-cycle shear fatigue tests,the damaged zones were detected by the ultrasonic C-scan system.C-scan images indicated that the length and width of damaged zones increased with the increasing number of cycles.Compared with initial undamaged specimen,the average failure load of specimens with multi-impact damage and high-cycle shear fatigue declined about 50%.Furthermore,the failure modes of the specimens were also affected by the initial damage caused by impact or fatigue.For the impact and fatigue specimens,the deformation of local buckling skin appeared,and the failure cracks were much near the impact damaged zones.

关 键 词：复合材料加筋壁板 多点冲击损伤 高周剪切疲劳 剩余剪切强度 破坏模式 

分 类 号：V258[一般工业技术—材料科学与工程]