T800/5228E复合材料层合板动态冲击力学响应  

Dynamic Impact Mechanical Response on T800/5228E Composite Laminate

作　　者：刘立朋[1] 张明[1] 安学锋[1] 唐邦铭[1] 益小苏[1] 

机构地区：[1]北京航空材料研究院先进复合材料国家重点实验室,北京100095

出　　处：《宇航材料工艺》2011年第6期77-80,共4页Aerospace Materials & Technology

基　　金：国家973计划(2010CB631100)

摘　　要：研究了宽冲击能量范围(12.8、25.5、34.2、42.3与51J)内T800/5228E复合材料层合板动态冲击力学响应历程。结果表明,复合材料层合板损伤历程依次为裂纹引发→分层扩展→最大损伤→二次损伤等,冲击能量基本不会对其发展演化历程产生影响;力学损伤参数研究发现,赫兹失效载荷Fh与冲击能量成线性关系,而最大作用载荷Fmax与冲击能量为特定指数函数关系。不可逆能量LW与能量吸收率η研究表明,两者均与冲击能量保持单调递增关系,反映复合材料板的损伤程度在加重,但损伤面积基本趋于稳定,纤维断裂等二次损伤可能成为新型能量吸收方式。Dynamic mechanical impact response of T800/5228E composite laminates was studied in a wide range of impacting energy. A whole scaling of crack initial→delamination→laminate failure→second damage was observed with 51 impacted energy, as iust a part of this dynamic impact mechanical response curve in lower impacted energy without consideration of rebouding effection. Fh and f are just linely and natural exponential founction of impacted energy respectively,and both of Lw and η exhibit monotonically increasing relation for impacted energy, showing the pre-penetration action happenness in selected nenergy of this article. Worth the whistle, ultrasonic c--scanning ,a kind of non-destructive technique , probably can not evalucate the exact damage in projected composite laminates fairly in our work.

关 键 词：复合材料层合板 低速冲击 动态冲击力学响应 

分 类 号：TB33[一般工业技术—材料科学与工程]