nozzle throat

The changes of the pressure in puffer chamber and nozzle throat under different base pressure are compared, which shows that base pressure has an influence on the pressure in gas chamber.

分析了压力变化与开断时间的关系，比较了不同基压下压气缸与喷口喉部气体压力特性的变化，说明了基压对断路器灭弧室内压力的影响。

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The nozzle throat diameter was 35 mm, and the inlet stagnation temperature and pressure were 800 K and 274 4 kPa, respectively.

主喷管喉道直径为35mm，进口总温和总压分别为800K及274.4kPa。

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Hot-jet is divided into two streams when the aspect ratio at nozzle throat section ( ARt) becomes 2.

在收扩喷管喉道宽高比（ARt）为2时，热射流被分成两股。

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The scheme to control launch power is introduced for changeable depth launch of missile. It is to change the aeration area at the nozzle throat of high pressure chamber in launcher.

该文针对导弹变深度发射提出通过改变发射装置高压室喷管喉部的通气面积来实现发射动力可调。

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The Calculation and Prediction of Transient Value of Nozzle Throat Radius

固体火箭发动机喷管喉径瞬变值的计算和预示

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The technical difficulty is accurately controlling the low-pressure rotor speed through adjusting nozzle throat area.

技术难点在于通过调节喷管喉道面积,精确控制发动机低压转子转速.

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Results show that pintle could change the nozzle throat area and thus the motor pressure and thrust, which provided the capability for thrust control.

结果显示喉栓能够有效改变发动机燃烧室压力和推力，满足发动机推力控制要求。

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The thrust coefficient has direct relationship with the area ratio of nozzle and is independent of the area of nozzle throat.

矢量状态下，推力系数与面积比呈正比关系，而对喉道面积的变化不敏感。

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Condensed Phase Aluminium Oxide Particles Deposit on the Nozzle Throat and Its Theoretical Analysis

三氧化二铝粒子在喷管喉部沉积变化规律的理论分析

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The influence of fuel grain length and port diameter, oxidizer mass flux and nozzle throat diameter on the combustion efficiency and propulsion performance was then analyzed in further tests to optimize these parameters.

利用试验数据分析了燃料药柱几何尺寸、氧化剂质量速度和发动机喷嘴喉径对燃烧效率及推进性能的影响，探讨了这种发动机的优化设计范围。

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The characteristic velocity, area of nozzle throat and other parameters are calculated by using the static test results of solid rocket motor ( SRM) and introducing generalized pressure coefficient and thrust coefficient.

利用发动机地面试验结果，引入广义的压强系数和推力系数，计算了发动机的特征速度、喷管喉部面积等参数。

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Based on the interior trajectory calculation model of the launch system, the parameters of missile movement and interior trajectory performance are numerated and analyzed for the influence of gas generator nozzle throat area on launch power.

根据发射系统内弹道计算模型，针对燃气发生器喷喉面积对导弹发射动力的影响进行导弹运动参数、内弹道性能的计算与分析。

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