导弹侧向喷流干扰及多喷口耦合效应数值模拟

Numerical investigation on coupling effects of multiple spouts and lateral jet interaction over missile configuration

侧向喷流与外部来流的干扰流场相当复杂,流场内会出现弓形激波、再附激波和分离旋涡等复杂的物理现象。通过数值求解NS方程,对导弹的侧向喷流干扰流场进行了数值模拟研究,重点讨论了采用空气冷喷流进行喷流干扰模拟的相似模拟准则,通过与燃气喷流的对比,验证了喷流干扰模拟准则在导弹侧向喷流干扰数值模拟中的可靠性。利用建立的侧向喷流模拟方法,对某导弹外形的多喷口耦合效应进行了数值模拟研究,分析了侧向多喷口耦合干扰下的放大因子及流场结构,相关结论可为导弹喷流控制系统设计提供参考依据。

Supersonic flow structure with lateral jet is highly complex,since it coshock, separation shock, vortex, and other complicated physical phenomena. The present investigation was conducted on lateral jet interaction over supersonic missile crossflow by solving the Navier-Stokes equations with the software MFlow developed by China Aerodynamics Research and Development Center （CARDC ）. The momentum ratio principle was discussed by comparing a gaseous injection in supersonic flow with an air injection, The comparison indicates that the momentum ratio principle is reliable in the present simulation. Besides, numerical simulation was applied to a missile configuration with multiple spouts. The flow structure around the missile and the amplification factor were analyzed？ and the influence pattern was obtained for different spout arrangements. This investigation is useful in providing basic understanding ondesigning missile with revision control system （R C S）.