固体火箭发动机尾焰流场特性研究  

Study on characteristics of flow field in exhaust plume for SRM

作　　者：张光喜[1] 周为民[1] 张钢锤[1] 南宝江[1] 

机构地区：[1]中国航天科技集团公司第四研究院,西安710025

出　　处：《固体火箭技术》2008年第1期19-23,共5页Journal of Solid Rocket Technology

基　　金：国防科技重点实验室基金项目(9140C5201020701)

摘　　要：针对某固体火箭发动机,对二维轴对称尾焰流场进行数值模拟,并考虑复燃化学反应和Al2O3颗粒运动的影响。计算得到了尾焰射流的温度场和组分分布图,将计算结果和地面实验结果进行对比,对尾焰流场主要特点进行分析。结果表明复燃化学反应主要发生在燃气空气混合区域,化学反应使复燃区域温度升高约250 K。该计算方法能反映出尾焰复燃流场的主要特点,可为固体火箭发动机尾焰红外特性的计算提供流场基本数据。2D-dimensional axisymmetric flow field in exhaust plume of some SRM was numerically simulated, and after-combustion chemical reaction and motion of Al2O3 particle were taken into account. Temperature field and ingredient distribution curves of the exhaust plume were calculated, and the calculation results were compared with the groud test results. The main characteristics of flow field in exhaust plume were analyzed. The results show that after-combustion chemical reaction mainly appears in the mixing zone, and chemical reaction causes the temperature in the mixing zone increase about 250 K. The calculation method can reflect main characteristics of flow field in exhaust plume and provide flow field basic data for calculation of infrared characteristics of SRM plume.

关 键 词：固体火箭发动机 燃气射流 复燃 数值模拟 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]