本文从燃烧室压力、系统工作循环方式以及最大推力三个方面叙述了世界各国液体火箭发动机的技术水平。
This paper presents the development of the liquid propellant rocket engine technology from the viewpoint of combustion chamber pressure, thrust level and power cycle.
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。
Results show that pintle could change the nozzle throat area and thus the motor pressure and thrust, which provided the capability for thrust control.
该项研究主要测量了发动机的推力和燃烧室压力。
The combustion chamber pressure and propulsive force were tested.
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