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为掌握卫星姿控推进器尾焰的吸收特性,研究了尾焰对太阳红外辐射的吸收问题。在直角坐标系下,建立了尾焰对太阳红外辐射的吸收模型,并采用混合有限体积/有限元法计算太阳光线经过尾焰吸收后的光谱辐射亮度。该方法使用有限元法进行角度离散,有限体积法进行空间离散;对每一个控制体,可同时耦合求出所有角度方向的辐射亮度。通过求解,得到了受到尾焰吸收后的太阳光谱辐射亮度和尾焰的光谱吸收率。以传递方程积分法的计算结果作为基准解,对比分析了有限体积法和混合有限体积/有限元法产生射线效应的强弱程度。通过分析可知:在某些波段上,太阳辐射受到尾焰的吸收程度较强;与有限体积法的计算结果相比,混合有限体积/有限元法的计算结果与基准解之间的差异相对较小。以上结果表明:混合有限体积/有限元法的计算精度较高,并能够较好地降低射线效应。
In order to grasp the absorption characteristics of the tail flame of the satellite attitude control thruster, the absorption problem of the tail flame to the solar infrared radiation was studied. Under Cartesian coordinate system, the absorption model of the tail flame to the solar infrared radiation was established and the spectral radiance of the solar beam after the tail flame was absorbed was calculated by the mixed finite volume / finite element method. The method uses the finite element method to discretize the angle and the finite volume method to disperse the space. For each control body, the radiance of all angles can be obtained by coupling at the same time. Through the solution, the solar spectral radiance and the spectral absorptance of the tail flame are obtained after the tail flame is absorbed. By using the result of integral equation transfer method as the reference solution, the degree of ray effect produced by finite volume method and mixed finite volume / finite element method is comparatively analyzed. It can be seen from the analysis that the solar radiation is strongly absorbed by the tail flame in some wavebands. Compared with the results of the finite volume method, the difference between the results of the mixed finite volume / finite element method and the baseline solution is relatively small. The above results show that the mixed finite volume / finite element method has higher calculation precision and can reduce the radiation effect better.