论文部分内容阅读
为了研究外界环境变化以及二次燃烧现象对固体火箭发动机喷管射流流场结构的影响,采用四阶Runge-Kutta时间推进法及三阶MUSCL空间离散格式,建立了二维轴对称固体火箭发动机喷管燃气射流数值模型。在与文献结果对比验证的基础上,分析了不同海拔高度与马赫数以及二次燃烧现象对固体火箭发动机喷管自由射流结构的影响,获得了燃气射流马赫数场、温度场、组分云图分布以及轴线温度变化曲线。数值结果表明:随着海拔高度的升高,射流对外界的扰动区域变大,最大马赫数升高;随着外界气流马赫数的增加,燃气射流波节数减少,对外界环境的作用范围减小;另外,二次燃烧的发生会使得射流核心区域温度显著增加,激波与喷管轴线的交点位置向后推移。
In order to study the influence of external environment changes and secondary combustion on the jet flow field structure of solid rocket motor nozzle, a four-order Runge-Kutta time-based method and a third-order MUSCL spatial discrete format were used to establish a two-dimensional axisymmetric solid rocket motor jet Tube gas jet numerical model. Based on the comparison with the literature results, the influence of different altitude, Mach number and secondary combustion on the structure of free jet of solid rocket motor nozzle was analyzed. Mach gas field, temperature field and component cloud distribution of gas jet were obtained As well as the axis temperature curve. Numerical results show that as the altitude increases, the jets of the jet become larger and the maximum Mach number increases. With the increase of the Mach number of the jet, the jets number of the jets decreases and the range of effect on the environment decreases In addition, the occurrence of secondary combustion will make the jet core temperature significantly increased, shock and nozzle axis of the intersection point of the backward shift.