旋转爆震火箭发动机推进性能分析

In order to analyze the propulsive performance of the rotating detonation engine(RDE), a performance analysis model has been developed and established for the operating characteristics according to the simplified two-dimensional flowfield. The model can describe the flowfield structure in the combustion chamber including the inclined angle of detonation wave, the angle of oblique shock wave and the angle of slip line for the single wave mode, which takes into account the flow angle matching during the expansion process in the combustion chamber. The results of the flowfield structure are consistent with previous studies. Based on the inlet and outlet parameters of the control volume extracted in the flowfield, the propulsive performances of RDE under the ideal expansion state can be obtained directly. The results of the propulsive performance are in good agreement with the estimations of previous models and the deviation to the existing experimental results is 8%. Furthermore, it is confirmed that this model can be used for the multi-wave modes as well. The propulsive performances of the rocket RDE under different equivalence ratios, the inlet total pressures, and total temperatures are estimated utilizing this model. The study shows that the current model is able to reveal the characteristics of the unsteady flowfield in the RDE chamber, which provides an effective way to estimate the RDE propulsive performance quickly and reliably.