航天器发动机羽流对敏感器热效应仿真研究

Simulation of Plume Thermal Effect on Spacecraft Sensitive Devices

采用差分求解N-S方程与DSMC方法相结合的方法,研究了航天器单台发动机连续工作情况下真空羽流对航天器敏感器的热效应。首先通过求解N-S方程,获得发动机喷管的内流场,然后应用DSMC方法对喷管出口外轴对称羽流场进行计算,最后将轴对称羽流场计算结果作为模拟粒子入口边界条件,在并行计算机平台上进行三维羽流场和热效应计算得到航天器单发动机连续工作情况下羽流场对敏感器的热效应。以两个敏感器为例,对仿真结果进行了分析和比较,并得出了相应结论。

In this paper, the finite difference method for solving NS equations and the Direct Simulation Monte Carlo （DSMC） method are integrated to calculate the plume thermal effect on the sensitive devices of spacecraft when a single engine is working continuously. Firstly, the innerflow field of the nozzle is simulated by solving NS equations. Secondly, the DSMC method is used to simulate the axisymmetric plume field in the outfield of the nozzle. Then, by using the previous results as entrance boundary condition, the plume field and its thermal effect on sensitive devices in three-dimensional space are calculated with the parallel computers. Finally,results of the two cases are compared and analyzed.