We performed experimental studies of the ejector driven by a pulse detonation rocket engine using gasoline as fuel and air as oxidant in order to investigate the thrust augmentation performance of unsteady pulsejet coupling with complex shock wave and detonation combustion wave. Theinner diameters of the detonation engine and the ejector with a convergent inlet were 60mm and 120mm respectively. The thrust augmentation was measured at e-leven different positions at four operating frequencies of 15Hz, 20Hz, 25z and 30Hz. The experimental results indicated that the ejector was very effective in increasing the thrust of the system. The engine-ejector had a larger thrust augmentation when the ejector was located at the upstream of the engine exit. Peak thrust augmentation level was recorded to be approximately 158% at upstream position. The results also showed preliminarily that the thrust augmentation was increased with increasing operating frequency.%为了研究脉冲爆震燃烧这种耦合有复杂激波结构的非稳态脉动气流的引射增推性能,采用汽油为燃料、空气为氧化剂,对基于爆震燃烧的脉冲爆震发动机在加引射器前后的推力进行了实验测试.实验采用在技术比较成熟的内径60mm脉冲爆震火箭发动机上安装内径120 mm的引射器,分别测试了15 Hz、20Hz、25 Hz、30Hz4种不同频率下,引射器与发动机11种不同相对轴向位置处的推力增益.实验发现脉冲爆震发动机引射器能很好地提高发动机推力,当引射器入口位于发动机出口上游位置比处于其下游时推力增益较好,最大推力增益可达158％；并且发动机高频比低频产生的推力增益大.
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