The erosive property and principle of copper-infiltrated graphite as solid rocket motor(SRM) throat insert and tailpipe nozzle bushing are presented.
介绍了石墨渗铜材料作为固体火箭发动机（SRM）喉衬与长尾管衬套的烧蚀特性和机理。
Taking system optimization design of SRM as the example, physical programming of was proven to be efficient in modelling of decision-making uncertainty during the solid rocket motor design.
以固体火箭发动机总体方案优化设计为例，证明了物理规划方法作为固体火箭发动机设计决策不确定性建模方法的有效性。
The ignition of the solid rocket motor (SRM) is a very complex physical and chemistry process, which is composed of three component phases: ignition delay, flame spreading and chamber filling.
固体火箭发动机的点火是一个十分复杂的物理化学过程，包括三个阶段：点火延迟、火焰传播和燃烧室气体充填。
High overload yields great influence on the grain combustion of SRM (solid rocket motor) in working process.
大过载会对固体火箭发动机装药燃烧产生很大的影响。
The effect of radial vibration of the chamber structure composed of propellant grain and case on the internal ballistic property of solid rocket motor (SRM) was investigated.
研究了由推进剂药柱和壳体组成的燃烧室结构径向振动对发动机内弹道性能的影响。
This paper deals with the study of the external thermal insulation coating for a solid rocket motor (SRM) case.
介绍某固体发动机壳体外防热涂层的研究情况。
The location of centroid is the one of important parameter of Solid Rocket Motor (SRM). It has important influence for the flexibleness of body, stability of running, safe of running and so on.
固体火箭发动机的质心位置是发动机的重要参数之一，对发动机的机动性、运行稳定性、运行安全性等都有着重要影响。
Structural integrity analysis and storage life prediction of grain is a critical problem for the designers, manufacturers and users of Solid Rocket Motor (SRM).
固体火箭发动机药柱结构完整性分析及贮存寿命预估是设计、生产和使用部门非常关注的关键问题。
Structural integrity analysis and storage life prediction of grain is a critical problem for the designers, manufacturers and users of Solid Rocket Motor (SRM).
固体火箭发动机药柱结构完整性分析及贮存寿命预估是设计、生产和使用部门非常关注的关键问题。
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