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为了计算考虑不同纬度和季节下地球反射率和发射率时的在轨外热流,建立了适用于任意地球轨道和飞行姿态条件下的反向蒙特卡罗(RMC)法计算模型.该模型考虑了卫星表面遮挡与多次反射效应,通过连续坐标变换法确定飞行器在给定轨道参数下任意时刻的姿态,并将假设地球辐射特性为常数时的结果与商业软件的计算结果进行比较,以验证模型和计算程序的正确性.在此基础上,考察了地球辐射特性随纬度变化时,飞行器在轨外热流的变化情况.结果表明,所建立的RMC法模型在飞行器姿态控制以及代码计算中具有一定的可靠性;地球反射率和发射率随纬度的变化对地球红外辐射和地球反射辐射的影响均较大,在所选取的轨道参数和抽查时刻,与反射率和发射率不变的结果的最大相对误差分别为—21.31%和80.05%,且均出现于星下点南纬57°;卫星表面遮挡和多次反射效应明显,天线导致其所在平面的地球反射辐射热流密度从19.2 W/m~2变化到39.5 W/m~2.
In order to calculate the off-orbit heat flow considering the reflectivity and emissivity of the Earth at different latitudes and seasons, an inverse Monte Carlo (RMC) calculation model suitable for any orbit and flight attitude is established. The model takes into account Satellite surface occlusion and multiple reflection effects, the continuous coordinate transformation method to determine the attitude of the aircraft at any moment under a given orbital parameters, and the results of assuming the earth’s radiation characteristics are constant compared with the commercial software to verify the model And calculating the correctness of the program.On the basis of this, we study the change of the orbital heat flow when the radiation characteristics of the earth changes with the latitude.The results show that the established RMC method model has some advantages in attitude control and code calculation . The changes of the earth’s reflectivity and emissivity with latitude have a great influence on the earth’s infrared radiation and the earth’s reflected radiation. At the chosen orbital parameters and sampling time, the maximum of the results with the same reflectivity and emissivity The relative errors are -21.31% and 80.05%, respectively, and all appear in the satellite below the latitude 57 °; satellite surface occlusion and multiple reflection effect , Resulting in an antenna radiation reflected by the earth in which it is the heat flux from the plane of 19.2 W / m ~ 2 is changed to 39.5 W / m ~ 2.