摘要
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 kind of high filled granular composite with visco-elastic behavior so that the experimental researches on its fracture are very difficult. In this paper, two new experimental techniques, penetrating method and digital secondary moire method, are developed and used to detect the damage zones near crack tips in solid propellant. The experimental results indicate that the strong damage zones are “strip-shaped.” It is more reasonable and appropriate to define the strip damage zone as the damage zone of solid propellant than the kidney shape before.Thus, an experimental foundation to predict and control the fracture behavior of the propellant is provided.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
1990年第3期59-63,共5页
Journal of Astronautics
关键词
固体推进剂
裂纹
损伤区
断裂
Solid rocket propellant, Damage zone, Fracture.
