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为全面了解卫星的红外辐射特性,需掌握卫星姿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的红外辐射亮度的逻辑顺序,较完整地建立了卫星姿控推进器尾焰红外辐射的求解模型;根据该模型计算得到尾焰的辐射亮度,进一步求解获得了1000~4500cm-1内的光谱和波段辐射强度。通过分析可知,光谱辐射强度在波数1525cm-1、1700cm-1、2 155 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天顶角。在波数2 350 cm-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。
In order to fully understand the infrared radiation characteristics of the satellite, it is necessary to know the infrared radiation characteristics of the tail flame of the satellite attitude control thruster. According to the calculation of the flow field of the end flame first and then the absorption coefficient of the end flame, and then calculating the logical order of the infrared radiation brightness of the end flame by using the finite volume method, the model for solving the infrared radiation of the satellite pose control thruster is established more completely According to this model, the radiation brightness of the tail flame was calculated and the spectral and band radiation intensities within 1000 ~ 4500cm-1 were obtained. Through the analysis, we can see that the intensity of spectral radiation is larger in the wave number 1525cm-1, 1700cm-1,2 155 cm-1,2 350 cm-1 and 3 750 cm-1; the vertical distance to the exit of the nozzle is different, The maximum band radiation intensity may correspond to different zenith angles. The spectral irradiance at 2 350 cm-1 and 3 750 cm-1 near the wavenumber is in good agreement with that of the corresponding literature. The results show that this model has high feasibility and accuracy.