摘要
基于CFD计算所得的固体火箭尾焰流场,建立了尾焰等离子体特征参数模型,编程计算分析研究了入射电磁波频率对尾焰电磁波衰减系数的影响,获得了不同工况下尾焰电磁波衰减系数分布云图。分析结果表明,入射电磁波频率以及来流马赫数的增加可有效降低尾焰对电磁波的衰减作用;推进剂中铝粉含量的增加可显著增强尾焰对电磁波的衰减作用;火箭飞行高度的增加可后移尾焰电磁波干扰区域。
Based on the CFD calculation of the solid rocket exhaust plume flow field,the characteristic parameter model of the exhaust plume plasma was established.The influence of the incident electromagnetic wave frequency on the attenuation coefficient was studied by programming calculation.The distribution of the attenuation coefficient of the exhaust plume under different working conditions was obtained.The analysis results show that the incident electromagnetic wave frequency and the increase of the Mach number can effectively reduce the attenuation of the electromagnetic wave by the exhaust plume;the increase of the aluminum powder content in the propellant can significantly enhance the attenuation of the electromagnetic wave by the exhaust plume;the increase of the rocket flight height can cause the exhaust plume electromagnetic wave interference area to move backward.
作者
孙行
聂万胜
石天一
郑体凯
SUN Xing;NIE Wansheng;SHI Tianyi;ZHENG Tikai(Space Engineering University of PLA,Beijing 101416,China)
出处
《兵器装备工程学报》
CAS
北大核心
2019年第8期65-68,89,共5页
Journal of Ordnance Equipment Engineering
基金
国家自然科学基金项目(51876219)
关键词
电磁波
固体火箭发动机
尾焰
衰减特性
数值计算
electromagnetic wave
solid propellant rocket motor
exhaust plume
attenuation characteristic
numerical calculation
