虽然连续旋转爆震燃烧室几何构型简单，但由于其内部发生极其复杂的超声速流动与爆震燃烧过程，对这一过程的物理机理认识不足导致当前对旋转爆震的控制手段匮乏，严重制约着连续旋转爆震发动机的工程研制与发展。因此，本文基于自主设计的氢气燃料/空气小型连续旋转爆震燃烧室实验测试平台，对连续旋转爆震燃烧模式与稳定性控制开展实验测试工作，分别针对点火起爆、爆震燃烧模式、稳定传播特征、爆震波稳定性控制等进行了深入研究与分析，揭示了流量和当量比等多种因素对连续旋转爆震波稳定传播的影响规律。本文研究了普通火花塞、高能火花塞以及等离子体点火器等不同点火方式对旋转爆震波点火起爆过程的影响，比较分析了嵌入燃烧室的等离子体发生器放电产生的低温等离子体对旋转爆震波形成与稳定传播等燃烧特性影响。研究发现，高能火花塞能缩短爆燃向爆震的转变时间。低温等离子体点火器放电引燃形成的旋转爆震波压力峰值与相同实验条件下由高能火花塞点火所形成的旋转爆震波强度相近。在相同实验条件下，对于嵌入到燃烧室内的等离子体发生器，产生在环形通道内的低温等离子体能够诱导产生旋转爆震波，其强度高于其它点火方式得到的旋转爆震波强度。低温等离子体电离产生大量活性粒子，能够提高旋转爆震波传播的稳定性。进一步，选用高能火花塞，对贫、富燃以及宽流量工作条件下的燃烧特性进行了实验研究。实验测量了当量比为0.6至1.4，空气质量流量从25 g/s至245 g/s时旋转爆震燃烧室的瞬变压力。根据实验测试所获得的压力信号，建立了连续旋转爆震燃烧室宽当量和宽流量条件下的工作图谱，工作图谱基于不同的燃烧特性划分成五个主要的区域：非稳定纵向快速爆燃区域、稳定纵向快速爆燃区域、稳定快速爆燃区域、不稳定爆震区域、准稳定爆震区域和稳定爆震区域。研究结果表明，非稳定/稳定纵向快速爆燃区域的发生主要取决于燃烧室燃料喷射条件和环形燃烧室的声学特性。快速爆燃和爆震相互交替的现象通常发生在不稳定爆震区域，并且爆震波传播速度的波动率非常高，通常在平均速度的65%到75%之间的范围内变化。在准稳定爆震区域，快速爆燃消失，但出现了单/双爆震波反转的现象。在稳定爆震区域，形成的稳定爆震波不会发生爆震波的反传或分裂。稳定爆震波的速度和压力波动率均小于平均值的15%。本文还研究了氧气体积分数分别为30%和35%的富氧空气作为氧化剂时，氢气/空气连续旋转爆震波传播特性，分析得到了不同质量流量和当量比对燃烧室内燃烧波或连续

The geometric configuration of the combustion chamber for organizing continuous rotating detonation is relatively simple, but the supersonic flow and detonation process inside the combustor is extremely complicated. The poor understanding of the physical mechanism of this process leads to the current lack of control approaches for rotating detonation, which severely restricts development and application of continuous rotating detonation engines. Therefore, based on the independently designed experiment platform of hydrogen/air continuous rotating detonation combustor (CRDC), experimental research has been conducted on the combustion characterization and stability modulation of continuous rotating detonation. The ignition, combustion mode, stable detonation wave propagation characteristics, and stability control of detonation waves, are studied respectively. The effects of mass flow rate and overall chemical equivalence ratio on the steady propagation of continuous rotating detonation waves further discussed.Firstly, different ignition approaches, such as ordinary spark plug, high-energy spark plug, and low temperature plasma igniter are employed to study the ignition process. The influence of the low-temperature plasma, which is generated by the plasma generator embedded in the combustion chamber, on the combustion characteristics and formation of steady propagation waves are examined experimentally. It is found that the high-energy spark plug can shorten the transition time from deflagration to detonation. Under the same experimental conditions, the peak pressure of rotating detonation wave induced by the low-temperature plasma igniter is similar as that subject to the high-energy spark plug. While for the plasma generator embedded in the combustion chamber, the low-temperature plasma discharged in the annular channel can induce stronger rotating detonation waves. Due to the impaction of large number of active particles, the stability of the rotating detonation wave propagation can hence be improved.The high-energy spark plug is selected to investigate the combustion characterization and operating diagram under the lean and rich fuel condition in the hydorgen/air CRDC. Equivalence ratios ranging from 0.6 to 1.4 and air mass flow rates ranging from 25 to 245?g/s are chosen in the experiments. The operating diagram characterized by different combustion properties includes unstable longitudinal pulsed fast deflagration (ULPFD), stable longitudinal pulsed fast deflagration (SLPFD), unstable detonation (UD), quasi-stable detonation, and stable detonation sub-regions. The results indicate that the occurrence of unstable longitudinal pulsed / stable longitudinal pulsed fast deflagration is mainly determined by the fuel-injection condition and the acoustic properties of the annular combustor. The alternating occurrence of FD and detonation is typically observed in the UD region; therefore, the speed fluctuation of the wave propagation is very high, usually changed from 65% to 75% of its mean value. In the quasi-stable detonation region, the FD completely disappears, but the single/double-detonation wave inversion occurs. The statistical probability of the inversion of the single-detonation wave is approximately 10% in 100 test runs conducted in the quasi-stable detonation region. In the stable-detonation region, a stable-detonation wave is formed and propagates stably without the wave inversion or splitting. The speed and peak pressure fluctuations of the stable detonation wave are less than 15% of the mean ones. The enhancement of continuous rotating detonation in the oxygen-enriched air is demonstrated under a diffusive supply of hydrogen and oxidizer. Experimental tests are performed to reveal the effects of oxygen volume fraction, mass flow rate, and equivalence ratio on the propagation of continuous rotating detonation wave (CRDW). For the oxygen volume fraction up to 35%, the difference between the propagation velocity of stable detonation waves and the theoretical Chapman-Jouguet value is less than 5%. Under the chemical stoichiometric ratio condition, the CRDW is stabilized when the air mass flow rate reaches 165 g/s. However, the stabilized CRDW is observed even when the oxygen-enriched air mass flow rate is only 45 g/s under the presence of 30% or 35% oxygen. The increase of the oxygen volume fraction leads to an extension of the rich/lean boundary for generating a stable detonation wave.