卫星的光度数据与卫星的姿态、材质、观测角度等多种因素有关, 仿真计算往往无法获取这些因素, 导致仿真计算结果无法与实测进行对比.针对仿真结果无法通过实测进行验证的问题, 结合卫星工具箱中卫星运动场景, 分别通过实验测量与仿真计算获取卫星光学散射特性的时序数据.实验测量中, 在实验室内模拟太空光学环境, 实现实验过程中卫星模型姿态与卫星工具箱中卫星姿态的并行分析, 保证了测量的准确性.仿真计算中, 采用基于前期空间目标常用材质双向反射分布函数实测数据拟合出的双向反射分布函数模型, 且考虑卫星表面材料褶皱对空间目标光学散射特性的影响, 提高仿真精度.此外, 设计了一个轨道参数为：半长轴a=7 716.14 km, 偏心率e=0.001, 轨道倾角i=58°, 近日点幅角ω=36°, 升交点赤经Ω=345°, 平近点角M=231.1°, 相位角变化范围为38°～98°的三轴稳定卫星运动场景, 通过实验测量与仿真计算获取该场景下卫星的光度数据, 发现二者趋势相同, 幅值相近, 相关系数为0.69.

Photometric data of satellites are related to many factors, such as satellite attitude, material and observation angle. The simulation calculation is often unable to obtain these factors, so that the simulation results cannot be compared with the measured results. Aiming at the problem that simulation results cannot be verified by measurement, the photometric data of the satellite in Satellite Tool Kit motion scene are obtained by experimental measurement and simulation calculation. In laboratory measurement, not only the space optical environment is simulated, but also the parallel analysis of satellite model attitude and satellite attitude in Satellite Tool Kit can be realized, which ensure the measurement accuracy. In simulation calculation, the bidirectional reflectance distribution function model based on the bidirectional reflectance distribution function data of the common space target material is used, and the influence of the wrinkled surface is taken into account, which improves the accuracy of the simulation. In addition, a three-axis stable satellite motion scene with phase angle variation range of 38°-98° is designed, the orbital parameters of the satellite are: semi major axis a=7 716.14 km, eccentricity e=0.001, orbit inclination i=58°, argument of perihelion ω=36°, longitude of ascending node Ω=345°, mean anomaly M=231.1°. When compare the photometric data obtained by experiment and simulation, the results show that two trends are same and the correlation coefficient is 0.69.