针对超声速飞行条件下尾流对轴对称导弹后弹体的影响,采用CFD流场仿真方法,对后弹体在不同飞行状态、落压比、喷管扩张半角及后弹体外形情况下的内外流干扰流场进行了数值计算,研究了发动机尾喷流对后弹体附近压强分布的影响规律。结果表明:尾喷流作用范围随发射高度的增大而增大,随发射马赫数的增大而减小;尾喷流作用范围与落压比呈分段线性关系,与喷管扩张半角呈线性增大关系;后弹体外形对尾喷流作用范围的影响很小。
Aiming at the impact of rocket plume on the axisymmetric aft missile under supersonic condition, the interaction flow field between inner and external flow around aft missile was studied comprehensively under different factors, including flight conditions, nozzle pressure ratio, nozzle expansion cone half angle and the shape of aft missile, using CFD method, and the incidence of the rocket plume was investigated performing as the pressure distribution around the aft missile. The results show that:the effective range of plume enlarges and diminishes with the increase of altitude and Ma respectively; the incidence of plume enhances in a piecewise linear way with the raise of NPR; the incidence of plume linearly grows with the rise of nozzle expansion cone half angle; the shape of aft missile hardly affect the incidence of plume.
[an error occurred while processing this directive]
[1] 鞠玉涛, 郑亚. 火箭燃气喷流与弹体超声速绕流干扰流场数值分析[J].推进技术, 1999, 20(3): 17-20.
[2] SAHU J. Computations of supersonic flow over a missile afterbody containing an exhaust Jet[J].Journal of Spacecraft and Rockets, 1985,24(5):403410.
[3] AVITAL G, POMPAN J, MACALES J, et al. Experimental and CFD study of rocket plume effects on missile longitudinal aerodynamic stability: AIAA 2004-5196[R].[S.l.:s.n.],2004.
[4] JUNG Suk Young. Investigation of plume effects on longitudinal aero dynamics of missile at M∞=1.2: AIAA 2004-1110[R].[S.l.:s.n.], 2004.
[5] 孙振华, 吴催生, 徐东来. 导弹尾流对后弹体影响的CFD仿真分析[J].弹箭与制导学报, 2011, 31(3): 157-159.
[6] 曾庆华, 黄琳, 夏智勋. 不同尾翼受发动机羽流作用对弹体飞行性能的影响[J].固体火箭技术, 2002, 25(3): 26-28.
[7] Fetterman D E. Effects of Simulated Rocket Jet Exhaust on Stability and Control of a Research Type Airplane Configuration at Mach No. of 6.86:NASA Memo 4-22-59E[R].[S.l.:s.n.], 1959.
[8] JAMES C R. Aerodynamics of rocket plume interactions at supersonic speeds[C]//AIAA. Proceeding of 7th Atmospheric Flight Meehanics Conference.[S.l.:s.n.], 1959:361369.
[9] 王友进, 张庆兵. 吸气式导弹尾部喷流对底部阻力影响数值研究[J].现代防御技术, 2009, 37(5): 25-29.
[10] 贺旭照, 秦思, 曾辉, 等. 模拟飞行条件下的吸气式高超声速飞行器后体尾喷流干扰问题实验方案研究[J].推进技术, 2014, 35(10): 1310-1316.
[11] LEE Young-Ki, RAGHUNATHAN Srinivasan, BENARD Emmanuel. Passive control of plume interference on slender axisymmetric bodies[J].AIAA Journal, 2005, 43(8): 1653-1662.
[12] 孙振华, 徐东来, 何国强. 飞行参数对导弹发动机羽流的影响[J].固体火箭技术, 2005, 28(3): 188-191.
[13] Bannink W J, Houtman E M, Bakker P G. Base Flow/Under-Expanded Exhaust Plume Interaction in a supersonic External flow: AIAA-98-1598[R].[S.l.:s.n.], 1998.
[14] 郑忠华, 陈伟芳, 吴其芬. 尾喷流底部流场与外流场干扰的拓扑结构数值模拟[J].国防科技大学学报, 1998, 20(3): 18-22.
[15] Calhoon W H. Flow field and radiation analysis of missile exhaust plumes using a turbulent chemistry interaction model: AIAA 2000-3388[R].[S.l.:s.n.], 2000.