摘要
对含单个分层损伤国产碳纤维CCF300与T300碳纤维复合材料层合板进行压缩试验,通过对同种中等厚度含不同分层大小、不同分层位置的层合板压缩失效后的宏微形貌及超声波C扫描检测结果的分析,研究了分层大小及分层位置对于国产碳纤维及T300纤维复合材料层合板失效模式造成的影响,比较了两种纤维复合材料失效模式的异同.结果表明,预制分层在压缩过程中都发生了扩展,而分层位置是影响其压缩失效模式较为重要的因素.对于分层位置较深的层合板,其失效模式往往为首先发生分层扩展,进而子层板剪切屈曲失效.总的分析表明,国产碳纤维复合材料与T300纤维复合材料含分层损伤层合板的压缩失效模式基本相同.
The compression test was conducted on the homemade and T300 carbon fiber composite laminate with one delamination.According to the macro-shape and the ultrasonic C-scan result of post-failure specimens which contain different sizes and different positions of delaminations but the same thickness,an investigation has been conducted by this study on the effects of delmaination sizes and positions on the failure mechanism of homemade and T300 carbon fiber composite laminates.Also the differences of failure mode have been analyzed between these two kinds of composites.The final result shows that the imbedded delaminations have all propagated,and the position of delamination proposed to be the most important factors affecting the compressive failure mode.To the laminates with deep delamination the failure mode presented to be the first propagation of delamination and second shear buckling failure of sub-laminate.Based on these analyses we find that the failure mode of homemade carbon fiber composite is same with the T300 carbon fiber composite generally.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2011年第11期2416-2421,共6页
Journal of Aerospace Power
基金
国家自然科学基金(10472006)
北京市教育委员会共建项目(XK100060418)
