摘要
建立了固体火箭发动机(SRM)点火后的尾流场数值模型,分析了高速燃气射流沿SRM轴向和径向的分布规律,并与红外实验图像进行了对比分析。结果表明:高速射流的速度、压强和温度在喷管出口的波动幅度较大;靠近喷管出口处的压强沿径向呈先降低后增加趋势,随着距喷管出口距离的增加,压强呈单调递减趋势;到达射流剪切层边界时,径向速度的衰减梯度增大,在离开喷管出口约2m附近的射流峰值压强较高。
The numerical model for the wake field of a solid rocket motor(SRM)after ignition is established,and the distribution of the high speed gas jet along the axial and radial direction of the SRM are all analyzed and compared with the experimental infrared image.The results demonstrate that the jet velocity,pressure and temperature are fluctuating greatly at the outlet of the nozzle.The pressure near the nozzle along the radial direction was firstly decreased and then increased,and with the increase of distance from the nozzle exit,the pressure is reduced monotonously.At the boundary of the jet shear layer,the attenuation gradient of the radial velocity increases,and the peak pressure is greater near the exit of the nozzle at 2 m.
作者
张俊
田中旭
高天宇
高璞清
覃飞
ZHANG Jun;TIAN Zhongxu;GAO Tianyu;GAO Puqing;Qin Fei(College of Engineering Science & Technology,Shanghai Ocean University,Shanghai 201306,China;The 41st Institute of the 6th Academy,CASIC,Hohhot 010010,China)
出处
《弹箭与制导学报》
CSCD
北大核心
2018年第6期15-18,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
上海市科委2017年“创新行动计划”项目(17050502000)
上海市临港管委会2017年“产学研合作”项目(2017-56)
上海市青年教师培养计划(A1-2061-17-000111)资助
