卫星姿控发动机混合物羽流场分区耦合计算研究  

Coupled simulation of mixture plume for attitude-control satellite thruster

作　　者：李志辉[1,2] 李中华[1] 杨东升[3] 毕林[1,2] 张顺玉[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000 [2]国家计算流体力学实验室,北京100191 [3]北京卫星环境工程研究所,北京100094

出　　处：《空气动力学学报》2012年第4期483-491,518,共10页Acta Aerodynamica Sinica

基　　金：国防基础科研项目(51313030104);国家自然科学基金项目(91016027)

摘　　要：研究求解喷管内流场N-S方程数值计算方法,发展基于N-S方程物面边界滑移流理论计算技术。提出求解羽流核心区轴对称DSMC模拟方法与远场三维DSMC仿真方案,发展多组元混合物羽流DSMC仿真方法。研究求解卫星姿控发动机内外近场、远场、倒流区和物面相互作用影响区多流域流场分区耦合计算技术,建立了一套用于求解混合物燃气羽流及对太阳电池帆板与卫星体表面撞击污染影响数值模拟方法。通过对分别安装于某在轨卫星不同位置两个典型姿控发动机燃气五组元混合物羽流计算研究及相关结果对比分析,证实本文数值方法可靠性。Abstract：The numerical method for the steady Navier-Stokes equations is studied to solve the inner flow field of the nozzle. The N-S computing technique with the slip-boundary theory is developed for the near-continuum slip flow near the nozzle exit. The DSMC method for the flow of axial symmetry is studied to simu-late the core plume, the DSMC scheme for the simulation of three-dimensional far-field plume flow is devel- oped, and the DSMC method is studied for multi-species mixture plume. Then, the multiregion decomposing and coupling technique is developed to solve the inside and outside flow of the thruster including the near- field, far-field, backflow and gas-surface infected regions. As a result, the numerical simulation method has been presented to compute the gas-fired mixture plume from the attitude-control thruster of the satellite and the impinging contamination on the surface of the solar array panel and satellite. To study the contamination effects produced by the five-species mixture plume from two representative attitude-control thrusters installed in different locations of the satellite in orbit, the present method is adopted to simulate the nozzle inflow, tremendous plume flowfield of five-species mixture including the impinging contamination of the particles from the gas-fired plume. The flowfield properties of the gas-fired plume from the attitude-control thrusters are obtained, the related computed results are compared and analyzed with the experimental measurement and other theoretical calculation, which validates the reliability of the present numerical method.

关 键 词：姿控发动机 混合物羽流 N—S解算器 DSMC方法 数值仿真 羽流污染 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]