在环缝 -喷孔对撞式喷射的连续旋转爆震模型发动机上，以 H2/Air为工质，对连续旋转爆震波以单波模态稳定自持的典型波形特征和时域、频域特征进行了研究。直接测量了模型发动机工作在该模态下产生的一维推力，讨论了比冲等推进性能。试验结果表明:出口背压为大气压时，在空气流量 253 g·s-1，氢气流量 6.15 g·s-1，当量比为 0.834的工况下，模型发动机以平均传播频率 5.5563 kHz、平均传播速度 1658.3 m·s-1的单波模态稳定工作 360 ms。产生可靠的有效推力约为 183.7 N。以火箭模式计算，有效排气速度为 708.9 m·s-1总比冲为 72.34 s；以冲压模式计算，有效排气速度(氢气消耗率)为 29870 m·s-1，燃料比冲为 3048 s，消耗的氢，气的单位面积质量流率为 4122 g·m-2·s-1，单位推力为 726 m·s-1。推力曲线的面积积分表明旋转爆震模型发动机所提供的推力比较稳定；微观来看，推力波形与爆震波高频压力波形耦合，围绕推力平均值振荡。

A model continuously rotating detonation engine(CRDE)，in which H2/Air mixture via slit-orifice collision was injected，was used to study the typical waveform characteristics and the time/frequency-domaincharacteristics of the self-sustained single rotating detonation wave. Simultaneously，one dimensional thrust sup. plied by this model engine working in single wave mode was directly measured，and propulsive performance，such as specific impulse，was explained. Results show that supplying the operating condition of 1 atmosphere backpres.sure and 0.834 equivalent ratio，that is，air injected 253 g·s-1 and H2 injected 6.15 g·s-1，the model engine steadi. ly works in single wave mode for 360 ms，which has an average frequency of 5.5563 kHz and an average velocity of 1658.3 m·s-1. Therefore this model engine generates a reliable effective thrust of 183.7 N. Calculated in rocket mode，the effective exhaust velocity is 708.9 m·s-1，and total specific impulse is 72.34 s. Calculated in ramjet mode，the effective exhaust velocity(hydrogen consumption rate)is 29870 m·s-1，fuel specific impulse is 3048 s， the consumption of hydrogen mass flow rate per unit area is 4122 g·m-2·s-1，and the unit thrust is 726 m·s-1. The area integral of thrust curves indicates thrust provided by the rotating detonation model engine is relatively stable.In microscopic perspective，the thrust wave and the high frequency continuously rotating detonation wave couple and resonate，vibrating around the approximately average thrust.

V435.12

国家自然科学基金资助项目( NSFC51306202；NSFC51206182)。