陶瓷基复合材料（Ceramic Matrix Composite, CMC）以其耐高温、低密度、高比刚度、高比强度的特点，已成为航空航天领域重要的结构材料，并逐步应用于航空航天热结构部件，而CMC与金属零部件的连接结构设计与性能考核是CMC实现广泛应用的关键。为研究CMC-金属柔性支承结构的高温回弹性能，根据支承结构的典型特征设计了CMC-金属柔性支承结构试验模拟件，对其在高温条件下开展压缩疲劳试验，并采用DIC方法对支承结构的疲劳变形行为和金属支承弹片的回弹性能进行了原位在线观测和量化分析。结果表明：内支承与外支承金属弹片的回弹率受结构循环硬化和非弹性变形累积的影响，循环硬化提高弹性变形比例进而提高回弹率，而非弹性变形的变速累积弹片使回弹率不断下降。疲劳载荷水平越高，支承结构变形幅度越大，非弹性变形在弹片高变形区域的累积越显著，支承结构从而表现出越低的回弹率。高温疲劳结束后，外支承结构弹片回弹率在35%以下，内支承结构弹片回弹率在40%-60%。

Ceramic Matrix Composite (CMC) has emerged as a crucial structural material in the aerospace industry, distinguished by its excep-tional resistance to high temperatures, low density, high specific stiffness, and high specific strength. It is increasingly being utilized in aerospace thermal structural components. Therefore, the design of connecting structures and the performance assessment of CMC and metal parts are pivotal in enabling the widespread application of CMC. In order to study the high-temperature springback proper-ties of the CMC-metal flexible support structure, a test simulator of the CMC-metal flexible support structure was designed accord-ing to the typical characteristics of the support structure, and compression fatigue tests were carried out under high-temperature con-ditions. The fatigue deformation behavior of the support structure and the springback properties of the metal spring plate specimen were observed and quantitatively analyzed in-situ online using the DIC method. The results show that the springback ratios of the inner and outer support metal spring plate specimens are affected by the cyclic hardening and the accumulation of inelastic defor-mation of the structure. Cyclic hardening increases the proportion of elastic deformation and thus the springback ratio, while the variable-speed accumulation of inelastic deformation of the spring plate specimens leads to decreasing springback ratio. The higher the fatigue load level, the larger the deformation amplitude of the support structure, the more significant the accumulation of inelastic deformation in the high deformation region of the spring plate specimens, and the support structure thus exhibits a lower springback ratio. At the end of fatigue, the springback ratios of the outer support structure spring plate specimens are below 35%, and the inner support structure spring plate specimens are in the range of 40%-60%.