摘要
通过拉伸、压缩实验,从宏观上研究了平纹编织C/SiC复合材料在简单载荷作用下模量、残余应变及泊松比的变化。通过断口观察,分析了材料在面内拉、压载荷作用下的损伤与失效模式。实验结果表明,拉伸载荷作用下,材料在低应力就开始损伤。0°纤维束表面基体开裂和层间裂纹是主要损伤形式。损伤后,随着应力增加,拉伸卸载模量、泊松比线性减小,残余应变增加;压缩应力-应变基本呈直线关系,模量、泊松比基本不变。拉伸破坏表现为韧性断裂,断裂机理为分层后0°纤维束的断裂、携带90°纤维束拔出;压缩破坏形成一个与加载方向成13°的断裂平面,破坏机理为层间裂纹、0°/90°纤维束之间裂纹和90°纤维束内裂纹的产生和迅速扩展、最后0°纤维束剪切断裂。
The macro mechanical behavior of 215woven C/SiC composiles produced wilh CVI technique was investigated by loading and unloadittg uniaxial tensile and compress tests, The changes in elastic modulus, residual strain, and Poisson ratio were studied for further characterization of mechanical properlies of lhe CMCs in complex stress states. Failure mode and damage mechanisms were analyzed by SEM and optical microscope. The tensile tests show thai damage begins at a very low tensile stress level of about 40 MPa. and that the unloading modules and Poisson ratio decrease linearly as the tensile stress increases, while the residual strain increases. Fractography analysis shows that matrix cracks around the 0° fiber bundles and interlaminar cracks are the main damage mechanisms.The compress behavior is almnst linear to failure. The compress modulus and Poisson ratio remain constant. The tnsile specimens break in a duetile manner, because of delamination, longitudinal bundles failure and pull out. The global compress failure in a plane orients about 13° to the loading direction, and because of cracks between bundles and within the 90° bundles, lhe 0° bundles are sheared to failure.
出处
《复合材料学报》
EI
CAS
CSCD
北大核心
2005年第4期81-85,共5页
Acta Materiae Compositae Sinica
基金
高等学校博士点基金(20030699040)
国家自然科学基金项目(90405015)
关键词
陶瓷基复合材料
力学性能
拉伸
压缩
平纹编织
ceramic matrix composite （CMC）
mechanical property
tension
compression
plain woven
