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 paper introduces a new method of measuring combustion time with CAT technique for solid rocket engine.
因此，他们需要时间来实现在发动机中燃烧相对较长的数额时，重新启动。
As such, they require a relatively long amount of time to achieve combustion in the engine when it restarts.
本文介绍了一种对研究发动机燃烧过程有着重要应用价值的实验技术一时间分幅全息技术。
This paper presents a time-based multi-frame holographic technique, which has many important applications in the research work of the combustion process of I. C. engines.
高超声速气流在燃烧室的停留时间非常短，使得超燃冲压发动机燃烧室内燃料与气流的混合及其燃烧变得非常困难。
Due to extremely short residence time of supersonic airflow, it is difficult to effectively mix and combust for the fuel and air in scramjet combustor.
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.
压力-时间痕量从kdx- 002静力试验的河童的DX火箭发动机将被用来估计推进剂燃烧率，与结果相比，钢绞线燃烧器的数据 。
The pressure-time trace from the KDX-002 static test of the Kappa-DX rocket motor will be used to estimate the propellant burn rate, with the results compared to Strand Burner data .
压力-时间痕量从kdx- 002静力试验的河童的DX火箭发动机将被用来估计推进剂燃烧率，与结果相比，钢绞线燃烧器的数据 。
The pressure-time trace from the KDX-002 static test of the Kappa-DX rocket motor will be used to estimate the propellant burn rate, with the results compared to Strand Burner data .
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