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本文提供了一种近地航天器受照角系数的计算方法。在一定的假设条件下,近地航天器空间外热流的计算,可归结为计算三个辐射角系数。太阳直接辐照角系数、地球红外辐射角系数和地球反照的太阳辐射角系数。计算公式是采用矢量分析和坐标变换的方法推导出来的,并且用航天器的轨道和姿态参数来表示,这些参数可以是已知的或由测量获得。本文提出的方法,不仅可以用于变轨和不变轨的近地航天器的空间外热流的实时计算,而且也可以用于近地空间目标的红外辐射特性的预测。
This article provides a method of calculating the illumination angle of near-spacecraft. Under certain assumptions, the calculation of heat flux outside the spacecraft spacecraft can be attributed to the calculation of three radiation angle coefficients. Direct solar radiation angle coefficient, the earth’s infrared radiation angle coefficient and the Earth’s albedo solar radiation angle coefficient. The formulas are derived using vector analysis and coordinate transformation, and are expressed using the orbital and attitude parameters of the spacecraft, which parameters may be known or obtained from measurements. The proposed method can not only be applied to the real-time calculation of space-based heat fluxes of near-spacecraft in orbit without orbit change, but also can be used to predict the infrared radiation characteristics of near-Earth space targets.