Firstly, the pulse rocket engine test system has been built and provides hardware constitute plan and test every aspect of the application of the test.
本文首先对脉冲火箭发动机的测试系统进行组建，提出了测试系统的硬件组成方案，并对测试系统的各个应用环节加以论证。
A prototype of pulse detonation rocket engine (PDRE) is introduced to solenoid valves for the control of oxygen, kerosene and isolation gas; thus continuous combustion is avoided.
简述了脉冲爆震火箭发动机的实验系统，利用电磁阀控制煤油，氧气和隔离气体，避免了连续燃烧。
A pulse detonation rocket engine (PDRE) is a new propulsion system that generates thrust by using high-temperature and high-pressure air produced by pulse detonation waves.
脉冲爆震火箭发动机是一种利用脉冲式爆震波产生高温、高压燃气发出的冲量来产生推力的新型推进系统。
A pulse width sampled-data control system for a variable thrust liquid rocket engine is studied both theoretically and experimentally.
本文对变推力液体火箭发动机的脉宽采样数字控制系统进行了理论分析和实验研究。
In order to achieve a rapid initiation of detonation in a short distance, a flame jet ignition system was applied to the pulse detonation rocket engine (PDRE).
为了实现快速短距起爆，火焰射流点火系统被尝试应用在脉冲爆震火箭发动机上。
In order to achieve a rapid initiation of detonation in a short distance, a flame jet ignition system was applied to the pulse detonation rocket engine (PDRE).
为了实现快速短距起爆，火焰射流点火系统被尝试应用在脉冲爆震火箭发动机上。
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