New insight also was offered on chinese solid rocket motor technology work , important for both missile and space launch applications 研究还提供了对于导弹和航天发射都具有重要影响的固体火箭发动机技术工作。
Hence , it is very significant to analyze the mechanism and extend law of interface debond of solid rocket motor 因此,研究固体火箭发动机界面脱粘的机理和扩展规律,是固体火箭发动机结构完整性分析的重要课题。
In this paper , the finite element method ( fem ) is used in the analysis of the static and dynamic strength of solid rocket engine 本论文运用i - deasmasterseries8 0对固体火箭发动机的动静态强度进行较为系统的分析。
D r greatrix . acceleration - base combustion augmentation modelling for non - cylindrical grain solid rocket motors r . aiaa 95 2876 曹泰岳，常显奇，等.固体火箭发动机燃烧过程理论基础m .长沙：国防科技大学出版社
It is important to develop experiment techniques to simulate flow field in the study of solid rocket motor with high acceleration 本文以高过载固体火箭发动机研制需求为背景，围绕高过载发动机内流场的地面模拟试验技术展开研究。
Numerical simulations for different grain models show that the high frequency longitudinal acoustic oscillations could he generated at the moment of pressure filling 摘要固体火箭发动机中声波振荡是引起不稳定燃烧的一个重要原因。
Based on the progress of nondestructive testing technology of solid rocket motor , the prospect of developing technology in the area was pointed out 在回顾固体火箭发动机无损检测技术发展的基础上，展望了该研究领域未来的发展趋势。
Interface debond between propellant and liner is a key form of failure of the structure integrity in the analysis of solid rocket motor 在固体火箭发动机结构完整性分析中,衬层/推进剂药柱粘接界面的脱粘是完整性被破坏的关键形式之一。
Owing to the dissimilar combustion mode , their working process is different form that of solid rocket motors and the liquid rocket engines 由于氧化剂和燃料的燃烧方式不同,固液火箭发动机工作过程与液体及固体火箭发动机有很大的区别。
