固体火箭发动机环缝式气动喉部研究

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.

Investigation of ring aerodynamic throat for solid rocket motor

A ring aerodynamic throat concept of solid rocket motor controlled by secondary injection was simulated numerically. The influence and rules of secondary flow injection positions, injection angle, secondary flow rate and injector geometry parameters to the performance of aerodynamic throat has been studied. The flow field character of aerodynamic throat is attained by calculation, which is that the starting point of sonic line comes from the downstream of secondary injection outlet. And the scope of injection positions for the existence of aerodynamic throat character is also attained. The results show that the performance of aerodynamic throat can be obviously increased by getting secondary flow injector close to throat, increasing secondary flow rate or decreasing secondary flow injection angle.