固体火箭推进剂是一种粘弹性高聚物,同时又是颗粒基复合材料。其断裂实验难度较大。本文用两种新方法:数字二次云纹法和渗透探伤法,进行裂纹端部损伤区的实验研究。结果说明裂纹端部的强烈损伤区是“窄带形”的,定义此窄带形损伤区为固体推进剂裂纹端部损伤区比以往的“腰子形”损伤区更为合理。为研究预测、控制固体推进剂的断裂性质提供了实验依据。 Solid rocket propellant is a viscoelastic polymer, but also a particle-based composite material. Its fracture experiment is more difficult. In this paper, two new methods, the digital secondary moiré method and the penetrant flaw detection method, were used to carry out the experimental study of the crack tip damage area. The results show that the zone of intense damage at the crack tip is “narrow-band”. It is more reasonable to define this zone as the damage zone of the solid propellant at the crack tip than the previous “kidney-shaped” zone. In order to study the prediction, experimental evidence is provided to control the fracture properties of solid propellants.