航天器發(fā)動機羽流對太陽電池板力及熱效應仿真

Simulation of thruster plume impingement on solar arrays of spacecraft and the thermal effects

摘要: 文章將差分求解N-S方程與DSMC方法相結合，研究了航天器單臺發(fā)動機連續(xù)工作時的真空羽流對航天器太陽電池板的力效應和熱效應。通過求解N-S方程，獲得發(fā)動機噴管的內流場；再以內流場計算結果作為模擬粒子入口邊界條件，應用DSMC方法，在并行計算機平臺上進行三維羽流場和力及熱效應計算，得到航天器單發(fā)動機連續(xù)工作情況下羽流場對太陽電池板的力效應和熱效應。文章以太陽電池板處于斜45°狀態(tài)為例，對仿真結果進行了分析。

Abstract: In this paper, the finite difference method for solving NS equations and the Direct Simulation Monte Carlo (DSMC) method are used jointly to calculate the plume impingement on the solar arrays of spacecraft and the thermal effects, on the condition of a single engine working continuously. First, the inner-flow field of the nozzle is simulated by solving NS equations. Then, with the obtained results as the entrance boundary condition, the thruster plume field is calculated on a parallel computer platform and its impingement on solar arrays and the thermal effects are simulated in three-dimensional space. The case of solar arrays with 45 degrees of incline is analyzed in the end.