本文论述了固体火箭发动机燃烧室一维两相常滞后流动。
In this paper, one-dimensional two-phase constant lag flow in combustion chamber of solid propellant rocket motors is described.
介绍一种固体火箭发动机燃烧室壳体纤维缠绕芯模的设计。
This article introduces a designing means of mold of the fibre winding solid rocket motor combustion chamber shell.
认识到建立固体火箭发动机燃烧室X射线探伤像质计标准势在必行。
It was considered that the establishment of radiographic IQI standard for solid rocket motor chamber was necessary.
凝聚相微粒尺寸分布对固体火箭发动机燃烧室效率和喷管效率有影响。
The condensed phase particle size distribution affects the combustion chamber and nozzle efficiency of solid rocket motors to some extent.
该项研究为长时间工作固体火箭发动机燃烧室热防护层设计提供了有效的分析手段。
This research can offer an effective analytical method for long-time working solid rocket motors.
为了分析液体推进剂火箭发动机燃烧室中存在的非稳态环境，必须很好地了解稳态状态。
To appreciate the unsteady environment existing in liquid propellant rocket chambers it is necessary that the steady state be well understood.
采用SIMPL E算法的可压缩形式求解固体火箭发动机燃烧室喷管内的全速度统一流场；
United flow field at all flow speeds in the chamber and nozzle of SRM is solved by using the compressible form of the SIMPLE algorithm.
本文从燃烧室压力、系统工作循环方式以及最大推力三个方面叙述了世界各国液体火箭发动机的技术水平。
This paper presents the development of the liquid propellant rocket engine technology from the viewpoint of combustion chamber pressure, thrust level and power cycle.
爆震波多管点火技术适合用于多燃烧室液体火箭发动机的同步点火。
The detonation wave ignition technique is suitable to synchronization ignition of multi-chamber liquid rocket engine.
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。
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.
对某锥柱形装药固体火箭发动机(SRM)燃烧室和喷管的内流场进行了三维两相一体化计算。
This paper makes a 3-d two-phase flow united calculation of the inner flow field of chamber and nozzle in certain SRM.
对某锥柱形装药固体火箭发动机(SRM)燃烧室和喷管的内流场进行了三维两相一体化计算。
This paper makes a 3-d two-phase flow united calculation of the inner flow field of chamber and nozzle in certain SRM.
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