摘要
用两种经高温处理的碳纤维织物 ,以酚醛树脂作为基体先驱体 ,制备了二维C/C复合材料。通过扫描电镜 (SEM)、X—射线光电子能谱 (XPS)研究了两种碳纤维 (TCF和JCF)的表面状态 ,测试了C/C复合材料 (TCC和JCC)的层间剪切强度、拉伸性能。SEM观察表明 ,TCF及JCF表面都有沟槽 ,但TCF横断面呈腰子形非圆形 ;XPS分析表明TCF表面含氧官能团数量多。力学测试结果为 :TCC层间剪切强度 (ILSS)高于JCC ,达到 16 .1MPa ;TCC拉伸强度、模量均高于JCC ,而JCC断裂延伸率达 1.1% ,是TCC的 3倍。拉伸断口SEM分析表明 ,TCC断口平整 ,无纤维拨出 ,呈脆断 ;JCC断口有纤维拨出 。
Two types of heating treated carbon fabrics reinforced two dimensional C/C composites(TCC and JCC) are fabricated with phenolic resin as matrix precursor. The surface states of TCF and JCF are analyzed by means of scanning electronic microscope(SEM) and X ray photoelectron spectroscopy(XPS). The interlaminar shear strength(ILSS) and tensile properties of C/C are tested. It is observed by SEM that there are slits on both TCF and JCF's surfaces,and cross section of TCF is kidney rather than round.It is found by XPS that there are more oxygen contained functional groups in TCF's surface than that of JCF.Mechanical test results show that TCC has higher ILSS,up to 16.1 MPa, and higher tensile strength and modulus, while JCC's fracture elongation is as high as 1.1%,which is three times of TCC's. The SEM observation shows that there are no fibers pulled out in TCC fracture section which is flat and exhibits typical brittle fracture,but there are fibers pulled out in JCC fracture section which presents a kind of fiber dominated multi layer matrix crack.
出处
《宇航材料工艺》
CAS
CSCD
北大核心
2000年第3期25-29,共5页
Aerospace Materials & Technology
