摘要
对基于真空气压浸渗法制备的三维五向、三维正交、叠层穿刺和2.5D浅交直联4种不同编织结构Cf/Al复合材料,分别在350℃和400℃下进行压缩试验,分析其高温压缩性能以及温度对复合材料压缩性能的影响,并进一步利用SEM观察叠层穿刺结构的断口形貌,探讨其压缩失效机理。结果表明,不同编织结构的复合材料在高温环境下压缩性能差异较大,三维正交结构的压缩强度最高,在350℃和400℃下分别为351.4MPa和288.6MPa,2.5D浅交直联结构的压缩强度最低,分别为87.3MPa和52.2MPa。同时不同编织结构的Cf/Al复合材料高温稳定性也存在较大差异,当温度由350℃升高到400℃时,2.5D浅交直联结构的压缩强度下降幅度较大,约为40.2%,其高温压缩稳定性较差,叠层穿刺结构的压缩强度下降幅度较小,约为4.0%,其高温压缩稳定性较好。叠层穿刺结构复合材料的高温压缩失效过程根据切线模量特征可分为两个阶段:第一阶段基体合金承受主要载荷,第二阶段基体与增强纤维共同承受载荷。
The compressive properties of Cf/Al composites with four different braided structures prepared by vacuum pressure infiltration method,i.e.3D five direction,3D orthogonal,laminated puncture and 2.5D shallow-straight joint woven,are tested at 350℃and 400℃,respectively.The high-temperature compressive properties of Cf/Al composites with different braided structures and the influence of temperature on the compressive properties are discussed,the fracture morphology of laminated puncture structures is further observed by SEM and the compressive failure mechanism is analyzed.The results show different compressive properties of composites with different braided structures at high temperature.The compressive strength of the 3D orthogonal structure is higher,which are 351.4 MPa and 288.6 MPa at 350℃and 400℃,respectively,while that of the 2.5D shallow orthogonal structure is lower,which are 87.3 MPa and 52.2 MPa,respectively.Meanwhile,a large difference exists in high temperature stability.When the temperature rises from 350℃to 400℃,the compressive strength of the 2.5D shallow-straight joint woven decreases by about 40.2%with poor high-temperature compressive stability.The compressive strength of the laminated puncture decreases by about 4.0%,with good high-temperature compressive stability.The high temperature compressive failure process of the laminated puncture structure composite materials can be divided into two stages according to the characteristics of tangent modulus:the first stage is when the base alloy bears the main load,and the second stage is when the base alloy and the reinforced fiber bear the load together.
作者
兰泽宇
余欢
徐志锋
帅亮
胡银生
LAN Zeyu;YU Huan;XU Zhifeng;SHUAI Liang;HU Yinsheng(Key Discipline Laboratory of Light Alloy Processing Science and Technology,Nanchang Hangkong University University.Nanchang 330063.China)
出处
《航空学报》
EI
CAS
CSCD
北大核心
2021年第9期551-561,共11页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(51765045)
航空科学基金(2019ZF056013)。
关键词
碳纤维
编织结构
复合材料
高温
压缩性能
失效机理
carbon fiber
braided structure
composite
high temperature
compressive property
failure mechanism
