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。
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。
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