Servo-Stabilization of Combustion in Rocket Motors
Servo-Stabilization of Combustion in Rocket Motors
复制标题
火箭发动机燃烧的伺服稳定
DOI：
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发表时间：
1952
期刊：
影响因子：
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通讯作者：
H. Tsien
中科院分区：
文献类型：
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作者：
H. Tsien
本文表明，通过从燃烧室压力传感器，经过适当设计的放大器，到推进剂供给线上的控制电容的反馈伺服链路，可以稳定火箭发动机中的燃烧，以对抗燃烧中任何值的时滞。稳定性分析技术基于萨奇图和奈奎斯特图的结合。为了计算简便，只考虑了单组元火箭发动机的低频振荡。然而，伺服稳定的概念和分析方法被认为是普遍适用于其他情况。
This paper shows that the combustion in the rocket motor can be stabilized against any value of time lag in combustion by a feedback servo link from a chamber pressure pickup, through an appropriately designed amplifier, to a control capacitance on the propellant feed line. The technique of stability analysis is based upon a combination of the Satche diagram and the Nyquist diagram. For simplicity of calculation, only low-frequency oscillations in monopropellant rocket motors are considered. However, the concept of servo-stabilization and method of analysis are believed to be generally applicable to other cases.