高超声速锥-柱-裙外形不同尾裙尺寸对轨控喷流干扰的影响  

Effect of different flare size of hypersonic cone-cylinder-flare configuration on the interaction of trajectory controlled jet

作　　者：孙瑞斌 刘耀峰[1] 张小亮 倪招勇[1] SUN Ruibin;LIU Yaofeng;ZHANG Xiaoliang;NI Zhaoyong(China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《兵器装备工程学报》2023年第11期188-195,共8页Journal of Ordnance Equipment Engineering

摘　　要：通过求解三维RANS方程研究了锥-柱-裙外形尾裙变化对轨控侧向喷流干扰的影响。利用高超声速条件下轨控喷流干扰风洞试验结果验证了数值方法的可靠性,进而数值模拟给出了不同尾裙长度及底部直径外形的轨控侧向喷流的干扰流场,对比了不同尺寸尾裙外形的壁面压力分布、力干扰因子和轨控偏移量结果。研究结果表明:尾裙尺寸对喷流附加干扰效应的影响显著,在相同尾裙长度条件下,随着尾裙底部直径增加,力干扰因子减小,轨控偏移量量值增大;尾裙底部直径对力干扰因子与轨控偏移量的影响随着负攻角增大而变的更加明显,而在正攻角条件下的影响较小;在相同底部直径条件下,尾裙长度对力干扰因子和轨控偏移量的影响在不同攻角条件下的规律不同。The effect of different size flare on lateral interaction of trajectory controlled jet in cone-cylinder-flare configuration is studied by solving three dimensional RANS equation.The numerical methods are compared and verified by the results of the wind tunnel experiment of the trajectory controlled jet interaction in hypersonic flows.The flow field of trajectory controlled jet with different flare length and bottom diameter in hypersonic flow is simulated numerically,and the wall pressure distribution,force interaction factor and the shift of jet force center results under different flare skirt sizes are compared.The results show that the flare size has a significant effect on the jet additional interaction effect.Under the condition of the same flare length,with the increase of the bottom diameter of the flare,the force interference factor decreases and the shift of jet force center increases.The influence of flare bottom diameter on the force interference factor and the shift of jet force center become more obvious with the increase of negative angle of attack,but the influence is small under the condition of positive angle of attack.At the same flare bottom diameter,the change of the force interaction factor and the shift of jet force center with tail skirt angel are affected by the angle of attack.

关 键 词：高超声速流 侧向喷流 轨控 风洞试验 数值模拟 

分 类 号：TJ011[兵器科学与技术—兵器发射理论与技术]