摘要
介绍了一种预示固体发动机火箭压强曲线上升段的实用方法。用该方法编制的程序具有结构简单,精度高的优点,能够满足工程需要。
A practical method for predicating the pressure curve at the starting transient of solid rocket motor is presented. The program based on the method is simple in structure and precision. Test data also proved that this method is acceptable for engineering.
出处
《固体火箭技术》
EI
CAS
CSCD
1994年第1期1-7,共7页
Journal of Solid Rocket Technology
关键词
火箭发动机
固体推进剂
点火
性能
Solid rocket engine Solid propellant ignition Performance predication
