Yang Zhenze, Ren Yongfeng, Shi Qiang, Cui Dapeng, Liu Jieqing
State Key Laboratory of Electronic Test Technology, North University of China, Taiyuan 030051, China.
Sensors (Basel). 2024 Aug 28;24(17):5567. doi: 10.3390/s24175567.
Carbon fiber-reinforced polymers (CFRPs) are widely used in the fabrication of solid rocket motor casings due to their exceptional performance. However, the bonding interface between CFRP and viscoelastic materials (rubber) is prone to debonding damage during service and storage under complex environmental conditions, which poses a significant threat to the structural integrity and reliability of the engine. Existing nondestructive testing (NDT) methods, such as X-ray imaging, infrared thermography, and ultrasonic testing, although somewhat effective, exhibit significant limitations in detecting interfacial defects in deep or multilayered composite materials, particularly under the challenging conditions of service and storage. This study proposes an innovative method based on active Lamb wave energy analysis and introduces the Damage Evolution Factor (DEF), specifically designed to detect and evaluate interfacial debonding defects in CFRP-rubber bonded structures within solid rocket motors during service and storage. Through numerical simulations and experimental validation, we selected the A0 mode Lamb wave, which is more sensitive to interfacial damage, as the incident wave and excited it on the surface of the structure. Displacement time-history response signals at observation points under different damage models were extracted and analyzed, and DEF values were calculated. The results show that DEF values increase with the size of the interfacial debonding damage. Similar trends were observed in experimental studies, further validating the effectiveness of this method and demonstrating that DEF can be used for the quantitative evaluation of interfacial debonding defects in CFRP-rubber bilayer bonded structures.
碳纤维增强聚合物（CFRP）因其卓越性能而广泛应用于固体火箭发动机壳体的制造。然而，在复杂环境条件下服役和储存期间，CFRP与粘弹性材料（橡胶）之间的粘结界面容易出现脱粘损伤，这对发动机的结构完整性和可靠性构成了重大威胁。现有的无损检测（NDT）方法，如X射线成像、红外热成像和超声检测，虽然有一定效果，但在检测深层或多层复合材料中的界面缺陷时存在显著局限性，尤其是在服役和储存的挑战性条件下。本研究提出了一种基于主动兰姆波能量分析的创新方法，并引入了损伤演化因子（DEF），专门用于检测和评估固体火箭发动机在服役和储存期间CFRP-橡胶粘结结构中的界面脱粘缺陷。通过数值模拟和实验验证，我们选择了对界面损伤更敏感的A0模式兰姆波作为入射波，并在结构表面激发它。提取并分析了不同损伤模型下观测点的位移时程响应信号，并计算了DEF值。结果表明，DEF值随着界面脱粘损伤尺寸的增大而增大。在实验研究中也观察到了类似趋势，进一步验证了该方法的有效性，并表明DEF可用于定量评估CFRP-橡胶双层粘结结构中的界面脱粘缺陷。
