为全面了解卫星的红外辐射特性，需掌握卫星轨控推进器尾焰的红外辐射特性。按照先计算尾焰的流场、再计算尾焰的吸收系数、最后用有限体积法求解尾焰红外辐射亮度的先后顺序，较完整地建立了卫星轨控推进器尾焰红外辐射的求解模型。根据该模型计算得到的尾焰辐射亮度，进一步求解获得了1 000~4 500 cm-1 内的光谱和波段辐射强度。通过分析，光谱辐射强度在1 525 cm-1、1 700 cm-1、2 155 cm-1、2 175 cm-1、2 350 cm-1 和3 750 cm-1附近的数值较大；到喷管出口截面的垂直距离不同，最大的波段辐射强度可能对应不同的方位角。在波数2 350cm-1和3 750 cm-1 附近，光谱辐射强度与同类文献中的计算结果能够相互吻合。此结果表明，该模型具有较高的可行性和精确性。

To totally obtain infrared characteristic of satellites, it was necessary to know the infrared characteristic of satellite orbit-control thruster plume. A complete model for calculating the infrared radiation of satellite orbit-control thruster plume was founded. The model calculated the plume flow field, absorption coefficient and radiative luminance by using Finite Volume Method (FVM) in order. According to the spectral luminance obtained by using the model, the spectral and band radiative intensity at the range of 1 000~4 500 cm-1 were calculated further. Through analysis of the intensity, the spectral intensity values at 1 525 cm-1, 1 700 cm-1, 2 155 cm-1, 2 175 cm-1, 2 350 cm-1 and 3 750 cm-1 are larger than the values at other spectrums; and the largest band intensity may be corresponding to different azimuth angle at different vertical distance to the nozzle exiting plane. The figure of spectral intensity curve at 2 350 cm-1 and 3 750 cm-1 well agrees with the figures in similar papers. The result shows that the calculation model is reliable and accurate.