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为研究高空多喷管火箭动力系统尾焰辐射特性的可视化计算,采用耦合了Realizable k-ε湍流模型的三维N-S方程描述尾焰流动过程,化学反应速率采用湍流脉动机制和Arrhenius机制控制,采用PISO算法对多喷管动力系统尾焰流动过程进行求解,得到了尾焰流场的各项参数分布。在此基础上,运用气体辐射传输方程和SLG模型对不同方向观测面上接收到的尾焰辐射照度进行计算,得到尾焰在不同方向上的辐射特性分布,进而实现尾焰辐射特性的可视化计算。计算结果表明:高空助推器尾焰的辐射特性要明显强于芯级,其中喷管出口处尾焰的辐射特性最强,最容易被发现和识别;尾焰辐射特性的可视化计算可以有效捕捉到尾焰流场的结构,从而为尾焰的红外追踪与预警研究奠定基础。
In order to study the visual calculation of the radiation characteristic of the tail flame of a high-altitude multi-nozzle rocket power system, a three-dimensional NS equation coupled with a Realizable k-ε turbulence model was used to describe the tail flame flow. The chemical reaction rate was controlled by turbulent pulsation and Arrhenius mechanism. The algorithm solves the tail-flame flow in multi-nozzle power system, and obtains the parameters distribution of the tail-flow field. Based on this, the gas radiation emission equation and SLG model are used to calculate the radiation irradiance of tail flame received in different directions, and the radiation characteristic distribution of tail flame in different directions is obtained, and then the visual calculation of tail flame radiation characteristic is achieved . The calculation results show that the radiation characteristic of the tail flame of the high-altitude booster is obviously stronger than that of the core. The tail flame of the nozzle outlet has the strongest radiation characteristic and is most easily found and identified. The visual calculation of the radiation characteristic of the tail flame can effectively capture To the structure of the flame flow field, which laid the foundation for the infrared flame tracking and early warning research.