月球探测器发动机羽流辐射热流计算  

Simulation of radiant heat flux of rocket engine exhaust plume on lunar detector

作　　者：石良臣[1] 朱定强[1] 徐旭[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《航空动力学报》2010年第1期187-192,共6页Journal of Aerospace Power

摘　　要：火箭发动机羽流的辐射的计算需要求解气体介质的辐射传递方程(RTE).计算模型中基于单线组(SLG)模型考虑气体组分的光谱特性,并采用离散传递法(DTM)求解RTE,对波长积分得到辐射热流密度.通过对圆柱高温CO2气团辐射热流计算来验证计算程序,然后在流场计算的基础上,计算了月球探测器主发动机和姿控发动机羽流对各部位和仪器的辐射热流密度,根据对不同工况计算结果的分析为探测器的设计提供参考.It＇s necessary to solve radiative transfer equation （RTE） of gaseous mediums when simulating the radiation of rocket engine exhaust plume. In the calculation model, spectral parameters of gaseous constituents were given based on single line group （SLG） band model; and RTE was settled by the use of discrete transfer method （DTM）. Radiant heat flux emitted by exhaust plume was then achieved through integral wavelength. The program was then validated by applying to high temperature carbon dioxide gas with geometry of cylinder. Finally, radiant heat flux on different parts and instruments, which was emitted by main and attitude control engines, was calculated according to flow field of plume. The results of heat flux provide a reference for integrated design of the detector.

关 键 词：月球探测器 单线组模型 离散传递法 羽流 辐射热流 

分 类 号：V520.6[航空宇航科学与技术—人机与环境工程]