真空热压制备SiCf/TC17/TB8复合材料板材的界面特性  

Interface Characteristics of SiC_(f)/TC 17/TB 8 Composite Sheet Prepared by Vacuum Hot Pressing

作　　者：高少青 周文龙[1] 王敏涓 付雪松[1] 黄浩 陈国清[1] Gao Shaoqing;Zhou Wenlong;Wang Minjuan;Fu Xuesong;Huang Hao;Chen Guoqing(School of Materials Science and Engineering,Dalian University of Technology,Dalian 116024;Titanium Alloy Research Institute,AECC Beijing Institute of Aeronautical Materials,Beijing 100095)

机构地区：[1]大连理工大学材料科学与工程学院,大连116024 [2]中国航发北京航空材料研究院钛合金研究所,北京100095

出　　处：《航天制造技术》2025年第2期41-49,共9页Aerospace Manufacturing Technology

摘　　要：碳化硅纤维增强钛基复合材料板材具有优良的性能特征和较强的可设计性,是可应用于翼面蒙皮上的新一代轻质高强复合材料。本文利用真空热压方法制备的SiCf/TC17/TB8复合材料板材,通过扫描电镜和能谱分析板材的界面结构及元素分布,利用顶出实验分析界面结合强度,采用纳米压痕仪测试板材的硬度和等效弹性模量,利用扫描电镜分析板材室温拉伸断口的形貌特征。结果表明:SiCf/TC17/TB8复合材料由碳化硅纤维、碳涂层、界面反应层及基体组成,其界面无缺陷且纤维/基体的界面结合强度为89.10MPa;基体的硬度和等效弹性模量高于TB8包套,分别为5.37GPa、120.23GPa;复合材料拉伸断裂的纤维脱粘发生在反应层及其与碳涂层界面;基体处断裂断口为混合型断口,包套处为韧性断口。Continuous silicon carbide fiber reinforced titanium matrix composite sheet has excellent performance characteristics and strong design ability,which is a new generation of lightweight and high-strength composite materials that can be applied on airfoil skins.In this paper,SiCf/TC17/TB8 composite sheets prepared by vacuum hot pressing method.The interface structure and elemental distribution of the plates were analyzed by scanning electron microscopy(SEM)and energy dispersive spectroscopy(EDS).The interfacial bonding strength was investigated through the push-out experiment.The hardness and equivalent elastic modulus of the plates were measured using a nanoindentation tester.The morphological characteristics of the tensile fracture surfaces at room temperature were analyzed by SEM.The results indicate that the SiCf/TC17/TB8 composite consists of silicon carbide fibers,carbon coatings,an interface reaction layer,and a matrix,with no defects at the interface.The interfacial bonding strength between the fiber and the matrix is 89.10 MPa.The hardness and equivalent elastic modulus of the matrix are higher than those of the TB8 plate,being 5.37 GPa and 120.23 GPa respectively.The fiber debonding during the tensile fracture of the composite occurs at the reaction layer and its interface with the carbon coating.The fracture surface at the matrix is a mixed fracture,while that at the plate is a ductile fracture.

关 键 词：真空热压法 界面成分 界面结合强度 硬度 等效弹性模量 断口形貌 

分 类 号：V257[一般工业技术—材料科学与工程] TB333[航空宇航科学与技术—航空宇航制造工程]