The pulse firing mode of bipropellant thrusters is crucial for the precise attitude control of spacecraft. This research explains how to simultaneously measure the chamber pressure and observe the combustion dynamics in the consecutive pulse firing of the monomethylhydrazine and the mixture of nitrogen tetroxide with approximately 3% nitric oxide bipropellant thruster. This study investigated transient behaviors in the ignition and cutoff of the pulse firing mode of the thruster. There was a delay in measuring the chamber pressure for two reasons: the time needed for the propellant to fill the manifold, and the delay in the response time of the pressure-sensing system. The time needed to fill the manifold depends on the pulse number, whereas the response time of the system factor is constant. This paper also demonstrates that a fuel-rich injection in the pulse firing mode leading to explosive ignition can be realized by prompt evaporation of the oxidizer from the manifold.

双推进推进器的脉冲发射模式对于精确控制航天器至关重要。这项研究解释了如何在单甲基肼和四氧化氮与约3％一氧化二氮推进剂推进剂的混合物的连续脉冲点火中如何同时测量腔室压力并观察燃烧动力学。这项研究调查了推进器脉冲点火模式的点火和截止过程中的瞬态行为。测量腔室压力存在延迟，这有两个原因：推进剂填充歧管所需的时间，以及压力传感系统响应时间的延迟。填充歧管所需的时间取决于脉冲数，而系统系数的响应时间是恒定的。