多喷管火箭动力系统尾焰辐射特性可视化研究

Visualization research on plume radiation characteristics of rocket propulsion system with multiple nozzles

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。

To realize the visualization calculation of plume radiation characteristics of the multi-nozzle propulsion system, the 3D N-S equations coupling with Realizable κ-ε model are used to describe the plume flow process. The chemical reaction rate is controlled by means of the turbulent fluctuation mechanism and Arrhenius method. The PISO algorithm is used to solve the plume flow process, and the parameter distribution of plume flow-field is acquired. Based on those parameters, the gas radiation transform equation and SLG model are used to calculate the plume irradiation illuminance accepted on viewing planes at different directions, thus acquire the plume radiation distribution at different directions and make the radiation visualization computation come true. The simulation calculation results indicate that the plume radiation of the boosters is stronger than the core vehicle at high altitude, the plume radiation at the nozzle outlet is strongest and is easiest to be discovered and identified, and the visualization computation of plume radiation can effectively get the structure of the plume flow-field, which can lay a great foundation for research on the infrared tracking and early warning of the plume.