对脉冲爆震发动机的混合室进行了实验研究。
The experimental study on the mixing chamber of pulse detonation engine prototype is performed.
有效的触发爆震波是脉冲爆震发动机正常工作的关键所在。
Efficient initiation of detonation waves is the key to the pulse detonation engine AB.
脉冲爆震发动机具有众多优点，近来受到广泛的关注和研究。
Pulse detonation engine has received much attention of late because of its several advantages compared to existent engines.
建立了脉冲爆震发动机工作过程、热力参数及其性能分析方法。
A method for analyzing working process, thermal parameters and Performances of PDE have been developed.
脉冲爆震发动机的平均推力随着工作频率的提高接近线性增大。
The averaged thrust of PDE increases almost linearly with the operation frequency.
对脉冲爆震发动机的热力循环过程应用特征线法作了一维流场的数值模拟。
Numerical simulation in one-dimensional unsteady flow of thermal dynamic cycle process in PDE is presented by the characteristic method.
阐述了脉冲爆震发动机工作原理，对脉冲爆震发动机热效率、循环过程及性能进行了初步分析。
This paper describes the principles of pulsed detonation engines (PDE) a preliminary analysis on thermal efficiency, cycle process and Performance of pulsed detonation engines has been made.
分析了两相多循环脉冲爆震发动机工作过程中爆震室内、外壁换热特性，建立了爆震室壁温分布计算模型。
The heat transfer characteristics of the detonation chambers outer and inner wall were analyzed when the pulse detonation engine model was operated in the multi-cycle mode.
本文的研究成果对于脉冲爆震发动机的起爆提供了丰富的经验，对今后爆震发动机的研制具有一定参考价值。
The conclusions of this paper offers abundant experience for the research of the detonation initiated by PDE. It has some reference value for development of the PDE in the future.
在直管脉冲爆震发动机上安装不同类型的喷管，利用推力传感器测量了不同频率下发动机的瞬态推力和平均推力。
Test results from an experimental investigation of the effect of nozzle on the thrust of a straight tube pulse detonation engine are presented.
针对两相无阀脉冲爆震发动机（PDE），研究了点火能量、工作频率、发动机直径、进气方式和燃料种类等对PDE点火-起爆性能的影响。
The ignition-detonation performance of two-phase valveless pulse detonation engines(PDEs) with the inner diameters of 50 mm and 120 mm in different operation cases was investigated.
最后将算例的计算结果与常规液体火箭发动机及固体火箭发动机的相关参数作了对比，脉冲爆震发动机具有更优越的整体性能，因此，有必要对它进行更进一步的研究。
When calculations are compared with the performance parameters of solid engine and liquid engine, it is concluded that PDE has very superior performance. It is necessary to continue research on PDE.
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 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.
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).
因此实际调节脉冲爆震爆震发动机应尽量采用组合的调节方式。
Therefore, combined control method should be used for controlling pulse detonation engines.
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 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.
在涡扇发动机基础上，以脉冲爆震燃烧室代替普通加力燃烧室构成涡扇-脉冲爆震组合发动机。
Based on a turbofan engine, the afterburner is replaced with pulse detonation combustor to form a turbofan-pulse detonation hybrid engine.
所以对于脉冲爆震爆震发动机应采用调节爆震频率和燃气填充相结合的控制策略。
Therefore, a cooperation method of the frequency and fuel flow should be used for pulse detonation engine control.
所以对于脉冲爆震爆震发动机应采用调节爆震频率和燃气填充相结合的控制策略。
Therefore, a cooperation method of the frequency and fuel flow should be used for pulse detonation engine control.
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