摘要
简要介绍了一种高压燃速声发射测试方法的原理、测试系统及其技术参数。在3~20MPa下进行了不同燃速的测定,结果表明,该系统测试相对误差小于0.9%.
The principle of a high-pressure burning rate measuring method, measuring system and its main technical parameters are briefly presented. It is used for measuring of the burning rates at 3~20MPa. The measured results show that the relative error of the measuring system is less than 0. 9%.
出处
《固体火箭技术》
EI
CAS
CSCD
1997年第3期74-78,73,共6页
Journal of Solid Rocket Technology
关键词
固体推进剂
声发射
火箭发动机
燃速
燃烧性能
Solid propellant Acoustic emission Burning rate Measuring technique