Experimental validation for axial-symmetric plume numerical simulation
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摘要: 针对在轨航天器羽流效应对航天器整体寿命的影响,在"DFH"系列卫星姿控发动机喷管羽流实验研究的基础上,建立喷管的轴对称模型,选取矩形计算区域,设定一定的边界条件和计算条件,采用轴对称单组分直接模拟蒙特卡罗(DSMC,Direct Simulation Monte Carlo)方法对相应实验状态的羽流流场进行数值模拟研究.通过对比数值模拟结果和实验测量结果,表明DSMC数值模拟羽流流场的计算结果符合实际流动规律,实验验证了所编制的轴对称DSMC数值模拟程序的正确性和有效性.Abstract: To solve effect problem of spacecraft lifetime caused by on-orbit spacecraft plume effect, numerical simulation and experimental validation were used. Based on the experiment studies of DFH series satellite attitude control thruster nozzle plume, axial-symmetric nozzle model was established. Rectangle calculation region was chosen, and a certain boundary condition and calculation condition were assumed. The calculations were carried out by axial-symmetric single gas direct simulation Monte Carlo (DSMC) method for plume of corresponding experiment state. By comparing numerical simulation results with experimental results, the calculation results of plume agree well with the experiment flow characteristics. It shows that the program of axial-symmetric single gas DSMC method designed is accurate and effective.
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Key words:
- attitude control thruster /
- plume /
- numerical simulation /
- experimental validation
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