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对固体火箭发动机气体二次流控制的环缝式气动喉部方案进行了数值模拟.研究了二次流不同喷射位置、角度、流率及喷嘴几何参数对气动喉部调节性能的影响规律.计算得到了气动喉部的流场特征,即气动喉部的声速线起点在二次流喷口的下游,并得到了气动喉部特征存在的喷注范围.结果还表明使二次流的喷入位置越靠近喉部、增大二次流流量或减小喷射角度都能明显增加气动喉部调节性能.
Numerical simulation was made on the annular pneumatic laryngeal scheme of secondary rocket gas control of solid rocket motor.The effects of different injection positions, angles, flow rates and nozzle geometrical parameters on the aerodynamic throat performance were studied. The characteristics of the flow field of the pneumatic throat are obtained, that is, the starting point of the sound velocity line of the pneumatic throat is downstream of the secondary flow orifice, and the injection range of the pneumatic throat feature is obtained.The results also show that the secondary flow injection position Closer to the throat, increase the secondary flow or reduce the injection angle can significantly increase the aerodynamic throat conditioning performance.