Secondary flow thrust vector control study for fluidic throat nozzle
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摘要: 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.Abstract: The secondary flow vector control concept for the fluidic throat nozzle of solid rocket motor was studied. Through numerical simulation, the work condition of concurrent thrust modulation and vector control was analyzed, in which there exist secondary flow at the throat and expansion part meanwhile. The throat modulation and thrust vector control performance of nine typical secondary flow concepts were compared, and the influence on the secondary flow vector control was discussed for the existence of secondary flow at the throat. The results of concept comparison can provide references for practical design.
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Key words:
- rocket motor /
- fluidic nozzle throat /
- thrust vector control /
- numerical simulation
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[1] 李娟,李江,王毅林,等.喉栓式变推力发动机性能研究[J].固体火箭技术,2007,30(6):505-509
Li Juan,Li Jiang,Wang Yilin,et al.Study on performance of pintle controlled thrust solid rocket motor[J].Tech of Solid Rocket Motors,2007,30(6):505-509(in Chinese)[2] 谢侃,刘宇,王一白.固体火箭发动机气动喉部的两相流数值模拟[J].推进技术,2010,31(1):56-60
Xie Kan,Liu Yu,Wang Yibai.Simulation for the two-phase flow aerodynamic throat of solid rocket motors[J].Journal of Propulsion Power,2010,31(1):56-60(in Chinese)[3] McArdle J G.Internal characteristics and performance of an aerodynamically controlled,variable discharge convergent Nozzle[R].NACA TN4312,1958 [4] McAulay J E.Cold-air investigation of three variable-throat-area convergent-divergent Nozzles[R]. NASA TMX-42,1958 [5] Catt J A,Miller D N,Giuliano V J.A static investigation of fixed-geometry nozzle using fluidic injection for throat-area control[R].AIAA 95-2604 [6] 谢侃,王一白,刘宇.固体火箭发动机气动喉部非定常过程[J].推进技术,2011,32(1):103-108
Xie Kan,Wang Yibai,Liu Yu.Unsteady process of aerodynamic throat for solid rocket motor[J].Journal of Propulsion Power,2011,32(1):103-108(in Chinese)[7] 谢侃.随控流体喉部的数值和实验研究[D].北京:北京航空航天大学宇航学院,2010
Xie Kan.Numerical and experimental study for the fluidic nozzle throat[D].Beijing:School of Astronautics,Beijing University of Aeronautics and Astronautics,2010(in Chinese)[8] 王峥,胡永强.固体火箭发动机[M].北京:宇航出版社,1993
Wang Zheng,Hu Yongqiang.Solid rocket motors[M].Beijing:Astronautics Press,1993(in Chinese)[9] Waithe K A,Deere K A.Experimental and computational investigation of multiple injection ports in a convergent-divergent nozzle for fluidic thrust vectoring[R].AIAA 2003-3802,2003 -
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