摘要
介绍了在T形燃烧器中用脉冲/变燃面法测定含铝推进剂的响应函数和Al_2O_3微粒平均直径的试验方法和试验原理.并介绍了试验测试系统和试验结果.该试验可为固体火箭发动机燃烧不稳定性预估提供原始数据.
The test method and principle for measurement of response functions and average Al_2O_3 Particle diameters of aluminized propellants using a pulsed-variable area T-burner method are described. Also the measurement system for testing and test results are presented This test can provide original data for estimation of combustion instability in solid rocket motors.
出处
《固体火箭技术》
EI
CAS
CSCD
1993年第2期41-45,共5页
Journal of Solid Rocket Technology
关键词
火箭发动机
固体推进剂
振荡燃烧
Solid rocked engine Solid rocket propellant Oscillatory combustion Burner.
