采用实验和数值计算方法研究了固体火箭发动机高空模拟引射器的启动特性。实验和数值计算结果显示引射器在启动过程中出现启动迟滞现象。引射器启动特性与其内部的流动形态(激波位置)变化直接相关,而流动形态变化的驱动力由引射器进口总压提供。根据流动形态分析结果,采用正激波理论计算引射器启动过程中的最小启动压力和最小工作压力,正激波理论分析结果及实验值与数值计算结果接近,表明正激波理论可用于计算引射器的启动特性。

The starting characteristics of the high altitude simulation ejector of solid rocket engine was studied by using the experimental and numerical methods. The results of experiments and simulation showed that the startup hysteresis appeared in the startup process of ejector. The start-up characteristics of ejector were directly related to the change of internal flow pattern (shock position), while the driving force of the change of flow pattern was provided by the total inlet pressure of ejector. According to the analysis of the flow pattern, the normal shock theory was used to calculate the minimum starting pressure and minimum working pressure in the startup process. The results of normal shock theoretical analysis were close to the experimental and numerical results, which indicated that the normal shock theory could be used to calculate the starting characteristics of the ejector.