Pull-out failure mechanism of C/SiC composite connection structure
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摘要: 通过C/SiC陶瓷基复合材料连接结构单轴拉伸试验，研究了连接结构拉脱失效过程的力学性能变化规律，结合应变测量、高速摄像、CT检测等测试手段从宏观角度和细观角度探究了连接结构拉脱失效过程中的损伤演化过程，确定了陶瓷基复合材料连接结构拉脱失效机制。结果表明：由于螺纹部位沉积及接触状态的差异，导致不同连接结构的初始刚度不一致；随着位移不断增加，连接部位的刚度趋于一致。加载过程中螺纹孔附近受到挤压产生损伤并发生分层现象；当螺纹孔局部的损伤达到一定程度时，连接结构达到最大承载能力，此时随着位移继续增加螺钉开始拉脱，承载能力开始下降，直至螺钉完全拉脱拔出。Abstract: Through uniaxial tensile test of C/SiC ceramic matrix composite connection structure, the change law of mechanical properties of connection structure during pull-off failure was studied. Combined with strain measurement, high-speed camera, CT detection and other test methods, the damage evolution process of the connection structure during the pull-off failure process was explored from the macro and micro perspectives, and the pull-out failure mechanism of the ceramic matrix composite connection structure was determined. The results show that the initial stiffness of different connection structures is inconsistent due to the difference of the deposition and contact state of the thread. As the displacement increasing, the stiffness of the connecting part tends to be consistent. Damage and delamination occur when the threaded hole is squeezed during loading. When the local damage of the threaded hole reaches a certain degree, the connecting structure reaches the maximum bearing capacity. At this time, as the displacement continues to increase, the screw begins to pull out, and the bearing capacity begins to decline until the screw is completely pulled out.
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Keywords:
- C/SiC composites /
- connection structure /
- pull-out failure /
- damage evolution /
- CT detection
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图 1 H型连接结构试件示意图
Figure 1. Diagram of H-shape connection structure
Φ—Diameter; A—Section view in mechanical drawing
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图 3 C/SiC连接结构试件的载荷-位移曲线
Figure 3. Load-displacement curves of C/SiC connection structure test piece
Fmax—Maximum tensile load of the specimen; T1, T2, T3—Specimen number
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图 4 C/SiC连接结构试件T1的载荷-位移曲线及连接界面变化
Figure 4. Load-displacement curve and change of connection interface of C/SiC connection structure test piece T1
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图 5 C/SiC连接结构试件试验后状态
Figure 5. State of the C/SiC connection structure specimen after test
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目的
热端部件经历严酷的高温环境，常规的金属紧固件无法使用，因此C/SiC复合材料连接结构大量的使用在飞行器热端部件中。本文对C/SiC复合材料连接结构试件进行单轴拉伸试验，获取了拉脱失效过程中载荷及连接状态的变化，分析了连接结构拉脱过程的损伤演化机制。
方法以H型C/SiC复合材料连接结构试件为对象，开展沿螺钉轴向的单轴拉伸试验。采用高速摄像、应变测试等方式监测连接部位的状态及力学特性的变化。采用CT测试的方式，扫描获取试件试验前后连接部位的特征。通过对比分析确定了C/SiC复合材料连接结构试件拉脱失效的机理。
结果连接结构试件拉脱失效的载荷位移曲线分为三个阶段：初始加载阶段、稳定加载阶段、卸载阶段。C/SiC连接结构受到制备工艺、材料初始缺陷以及初始连接状态的影响导致初始加载阶段试件体现出的刚度有所差异；加载过程中伴随着结构的损伤演化会出现不同程度的局部卸载现象。最大拉伸载荷存在着一定的离散性，稳定加载阶段的刚度表明连接结构的拉伸行为规律整体上一致性较好。试件达到最大承载能力后，承载能力随着位移增加逐渐下降，直至螺钉拉脱拔出。CT测试结果表明制备过程中螺纹部位基体沉积不充分。试验后连接部位出现了“鼓起”，螺孔位置出现了分层和局部压溃的现象。螺钉未出现明显的压溃、螺纹破坏等失效现象
结论连接结构制备过程中，二次沉积工艺导致连接界面存在SiC基体，但试验中SiC基体的“粘接”效应并不显著。试件制备过程中螺钉安装、沉积效果差异等原因导致试件初始加载阶段存在刚度不一致及非线性特征，当螺钉完全承载后，连接结构得到刚度趋于一致。拉脱失效的主要原因是连接结构螺纹孔变形挤压导致材料分层，螺纹丧失承载能力。试件达到最大拉伸载荷后，螺钉开始拔出，承载能力逐渐下降，直至螺钉完全拉脱拔出。
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C/SiC陶瓷基复合材料由于具备高强度、高模量、耐高温等特点，广泛应用于飞行器的热防护结构以及热端部件上。由于常规的金属紧固件无法承受热防护结构以及热端部件经历严酷的高温环境，因此C/SiC复合材料连接结构大量的使用在热端部件的紧固和连接中。
本文针对C/SiC复合材料连接结构设计了H型连接结构试件，开展沿螺钉轴向的单轴拉伸试验，采用宏观测试与细观测试相结合的方式研究了陶瓷基C/SiC连接结构的拉脱失效机制。研究结果表明C/SiC连接结构的受到制备工艺、材料初始缺陷以及初始连接状态的影响，导致连接结构初始加载阶段的刚度有所差异、最大拉伸载荷存在着离散性，并且加载过程中存在着非线性现象。CT测试结果表明连接结构螺纹孔变形挤压导致材料分层，螺纹丧失承载能力是引发结构拉脱失效的主要原因。
C/SiC连接结构力学行为规律(a)和细观损伤检测结果分析(b)
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