The manufacture quality of solid rocket engine is ensured by the constant temperature pushing core model.
恒温插芯可以确保固体火箭发动机的制造质量，远程控制可以避免事故突发带来的人员伤亡。
The paper introduces a new method of measuring combustion time with CAT technique for solid rocket engine.
介绍一种应用CAT技术确定固体火箭发动机燃烧时间的新方法。
The ablative property requirements and the studies on the insulation layer of solid rocket engine in oxidizer rich environment were presented.
介绍了富氧环境下固体火箭发动机对绝热层性能的要求，以及在该特殊条件下对绝热层所开展的研究工作。
The general method and process to analyze the failure reason of solid rocket engine from the engineering research are discussed in this paper.
从工程研制角度出发，探讨了分析固体火箭发动机试验失败原因的一般方法和过程。
Results of subscale engine test show that the insulation (PFDH-2) can be used for heat protection of oxidizer rich solid rocket engine chamber.
试车结果表明，PFDH - 2绝热层可以对富氧环境下工作的发动机燃烧室实施有效热防护。
The fault effects on restrict layer debonding and crack burning were studied by simulated test in order to provide analysis basis of fault diagnostics for solid rocket engine.
用模拟试验研究各种脱粘和裂缝燃烧对发动机造成的故障效应，为故障诊断和失效分析提供依据。
But although the road-mobile launcher has some off-road capability, it requires solid ground when launching to prevent damage from debris kicked up by the rocket engine.
然而，虽然道路机动发射装置有一定的越野能力，但在发射时也需要有坚实的地面，以防止火箭发动机激起的碎片造成破坏。
The paper presents the composition, functions, technical performance and research of the solid rocket ramjet engine ground test equipment and measurement control system in detail.
介绍了固体火箭冲压发动机地面实验装置及测控系统组成、功能、技术指标和可以开展的研究工作。
The plume temperature is an important parameter, for solid propellant rocket engines and it is useful for determining the combustion process of the engine.
推进剂的羽焰温度是固体推进剂火箭发动机的重要参数，对于研究发动机内的燃烧过程具有重要价值。
Finite element software of ANSYS has been used for making a finite element analysis of a certain type of ball-socket nozzle's pendulous socket in solid-rocket engine.
本文应用an SY S有限元分析软件，完成了对某型号固体火箭发动机珠承喷管摆动接头的有限元分析。
The temperature of a high temperature, high pressure plume solid propellant rocket engine is difficult to measure but is useful for determining the combustion status of the engine.
对于固体火箭发动机羽焰温度的测量是困难的，了解其温度分布对于研究发动机内燃烧流场的特性有重要价值。
As the air-breathing engine, the performance of solid rocket ramjet is determined not only by structure of engine and the performance of propellant, but also by flight condition.
作为吸气式发动机，其性能不仅取决于发动机本身结构和推进剂性能，与飞行状态也有密切的联系。
As the air-breathing engine, the performance of solid rocket ramjet is determined not only by structure of engine and the performance of propellant, but also by flight condition.
作为吸气式发动机，其性能不仅取决于发动机本身结构和推进剂性能，与飞行状态也有密切的联系。
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