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针对结合了二次流矢量控制的固体火箭发动机流体喉部喷管进行了研究.通过数值模拟着重分析了同时存在推力大小调节和方向改变的工况,即喷管喉部和扩张段上同时存在二次流时的情况.比较了典型的9种二次流喷射方案喉部控制性能和推力矢量性能,并讨论了喉部存在二次流时对下游二次流矢量控制的影响.方案的比较结果为实际设计、方案选型提供了参考.
Aiming at the throat nozzle of a solid rocket motor combined with the secondary flow vector control, the condition of concurrent thrust force adjustment and direction change is analyzed emphatically through the numerical simulation, that is, the throat of the nozzle and the expansion segment coexist The situation of secondary flow is compared.The throat control performance and thrust vector performance of typical nine kinds of secondary flow injection schemes are compared and the influence of downstream secondary flow vector control when there is secondary flow in throat is discussed. The results provide the reference for the actual design and program selection.