摘要
为了准确表征C/C复合材料在热力氧耦合环境下的力学性能,采用高温试验装置,在不同的预应力与温度条件下对带/不带抗氧化涂层2类典型的C/C复合材料拉伸试验件进行测试.试验结果表明,不同应力水平导致C/C复合材料的损伤可分为扩散控制和反应控制2个阶段.在扩散控制阶段,结构各部分承载的均匀性较好;在反应控制阶段,材料拉伸模量显著下降.当高温下外载荷产生的应变小于等于0.2%时,不带抗氧化涂层C/C复合材料的强度约为带抗氧化涂层C/C复合材料强度的50%.不同温度条件下材料的强度性能变化不显著,但随时间增加,其高温强度逐渐下降.研究结果对于C/C复合材料在飞行环境下的强度设计与评估具有重要的参考价值.
In order to characterize the mechanical properties of C/C（carbon/carbon） composite subjected to thermo-mechanical-oxygenic coupling environment,a high-temperature testing device w as employed to test the tensile pieces of tw o kinds of C/C composite（w ith and w ithout antioxidant coating） under different temperatures and pre-stresses.The experimental results show that different levels of stress lead to tw o stages of damaging,diffusion-controlled stage and reaction-controlled stage.In the diffusion-controlled stage,the structural bearing capacity is uniform.In the reactioncontrolled stage,the tensile elasticity modulus descends significantly.At elevated temperature,w hen the strain caused by the external load is no more than 0.2%,and the strength property of C/C composite w ithout antioxidant coating is 50% that of C/C composite w ith antioxidant coating.The change of strength properties presents less temperature-dependent.But the strength properties at elevated temperature degrade w ith the time passing by.The results of this study can be applied to the structural strength design and evaluation of C/C composite in flight environment.
出处
《东南大学学报（自然科学版）》
EI
CAS
CSCD
北大核心
2013年第4期845-848,共4页
Journal of Southeast University：Natural Science Edition
基金
国家自然科学基金资助项目(10902024)
教育部新世纪优秀人才支持计划资助项目(NCET-11-0086)
航空科学基金资助项目(20090869009)
江苏省自然科学基金资助项目(BK2010397)
关键词
热力氧耦合
C
C复合材料
力学性能
损伤模式
thermo-mechanical-oxygenic coupling
C/C（carbon/carbon） composite
mechanical performance
damage modes
