The Russian Global Navigation Satellite System (GLONASS) satellites have a stretched body shape and take a specific attitude mode inside the eclipse. Based on previous studies, the new Empirical CODE orbit model (ECOM2) performs better than the classical ECOM model if a satellite has elongated shape or does not maintain yaw-steering mode, and the use of an a priori box-wing (BW) model improves the orbits significantly when employing the ECOM model. However, we find that the ECOM model performs better than the ECOM2 model for GLONASS satellites outside eclipse seasons, while it performs two times worse in eclipse seasons. The use of the conventional box-wing model results in very little improvement. By assessing the ECOM Y0\documentclass[12pt]{minimal} \usepackage{amsmath} \usepackage{wasysym} \usepackage{amsfonts} \usepackage{amssymb} \usepackage{amsbsy} \usepackage{mathrsfs} \usepackage{upgreek} \setlength{\oddsidemargin}{-69pt} \begin{document}$$Y _{0}$$\end{document} estimates, we conclude that there are potential radiators on the -x\documentclass[12pt]{minimal} \usepackage{amsmath} \usepackage{wasysym} \usepackage{amsfonts} \usepackage{amssymb} \usepackage{amsbsy} \usepackage{mathrsfs} \usepackage{upgreek} \setlength{\oddsidemargin}{-69pt} \begin{document}$$-x$$\end{document} surface of GLONASS satellites causing orbit perturbations also inside the eclipse. The higher-order Fourier terms of the ECOM2 model can compensate for such effects better than the ECOM model. Based on this finding, we first confirm that GLONASS-K satellites take a similar attitude mode as GLONASS-M satellites inside the eclipse. Then, we adjust optical parameters of GLONASS satellites as part of precise orbit determination (POD) considering the potential radiator and thermal radiation effects. Finally, the adjusted parameters are introduced into a new box-wing model and jointly used with the ECOM and ECOM2 model, respectively. Results show that the amplitude and the dependency of the empirical parameters on the β\documentclass[12pt]{minimal} \usepackage{amsmath} \usepackage{wasysym} \usepackage{amsfonts} \usepackage{amssymb} \usepackage{amsbsy} \usepackage{mathrsfs} \usepackage{upgreek} \setlength{\oddsidemargin}{-69pt} \begin{document}$$\beta $$\end{document} angle are greatly reduced for both ECOM and ECOM2 models. Rather than the conventional box-wing model, the new box-wing model reduces the orbit misclosure between two consecutive arcs for both GLONASS-M and GLONASS-K satellites. In particular, the improvement in GLONASS-M satellites is more than 30% for the ECOM model during eclipse seasons. Further evaluation from 24-h predicted orbits demonstrates that the improvement during eclipse seasons is mainly in along- and cross-track directions. Finally, we validate GLONASS satellite orbits using Satellite Laser Ranging (SLR) observations. The use of the new box-wing model reduces the spurious pattern of the SLR residuals as a function of β\documentclass[12pt]{minimal} \usepackage{amsmath} \usepackage{wasysym} \usepackage{amsfonts} \usepackage{amssymb} \usepackage{amsbsy} \usepackage{mathrsfs} \usepackage{upgreek} \setlength{\oddsidemargin}{-69pt} \begin{document}$$\beta $$\end{document} and Δu\documentclass[12pt]{minimal} \usepackage{amsmath} \usepackage{wasysym} \usepackage{amsfonts} \usepackage{amssymb} \usepackage{amsbsy} \usepackage{mathrsfs} \usepackage{upgreek} \setlength{\oddsidemargin}{-69pt} \begin{document}$$\Delta u$$\end{document} significantly, and the linear dependency of the SLR residuals on the elongation drops from as large as -0.760\documentclass[12pt]{minimal} \usepackage{amsmath} \usepackage{wasysym} \usepackage{amsfonts} \usepackage{amssymb} \usepackage{amsbsy} \usepackage{mathrsfs} \usepackage{upgreek} \setlength{\oddsidemargin}{-69pt} \begin{document}$$-0.760$$\end{document} mm/deg to almost zero for both ECOM and ECOM2 models. In general, GLONASS-M satellites benefit more from the new a priori box-wing model and the BW+ECOM model results in the best SLR residuals, with an improvement of about 50% and 20%, respectively, for the mean and standard deviation (STD) values with respect to the orbit products without a priori model.

中文翻译：

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改进 GLONASS 卫星的太阳辐射压力建模

俄罗斯全球导航卫星系统 (GLONASS) 卫星具有拉伸的机身形状，并在日食内部采用特定的姿态模式。根据以往的研究，如果卫星具有拉长的形状或不保持偏航转向模式，并且使用先验箱翼（BW）模型，则新的经验 CODE 轨道模型（ECOM2）的性能优于经典的 ECOM 模型使用 ECOM 模型时显着改善了轨道。然而，我们发现对于 GLONASS 卫星，ECOM 模型在日食季节之外的表现优于 ECOM2 模型，而在日食季节的表现则差两倍。使用传统的箱翼模型几乎没有改进。通过评估 ECOM Y0\documentclass[12pt]{minimal} \usepackage{amsmath} \usepackage{wasysym} \usepackage{amsfonts} \usepackage{amssymb} \usepackage{amsbsy} \usepackage{mathrsfs} \usepackage{upgreek} \setlength {\oddsidemargin}{-69pt} \begin{document}$$Y _{0}$$\end{document} 估计，我们得出结论，-x\documentclass[12pt]{minimal} \usepackage 上存在潜在的辐射器{amsmath} \usepackage{wasysym} \usepackage{amsfonts} \usepackage{amssymb} \usepackage{amsbsy} \usepackage{mathrsfs} \usepackage{upgreek} \setlength{\oddsidemargin}{-69pt} \begin{document}$$ -x$$\end{document} GLONASS 卫星的表面也在日食内部引起轨道扰动。ECOM2 模型的高阶傅立叶项可以比 ECOM 模型更好地补偿这种影响。基于这一发现，我们首先确认 GLONASS-K 卫星在日食内部采用与 GLONASS-M 卫星类似的姿态模式。然后，考虑到潜在的辐射体和热辐射效应，我们调整 GLONASS 卫星的光学参数作为精确定轨 (POD) 的一部分。最后，将调整后的参数引入一个新的盒翼模型，并分别与 ECOM 和 ECOM2 模型共同使用。结果表明，β\documentclass[12pt]{minimal} \usepackage{amsmath} \usepackage{wasysym} \usepackage{amsfonts} \usepackage{amssymb} \usepackage{amsbsy} \usepackage 上的幅度和经验参数的依赖性{mathrsfs} \usepackage{upgreek} \setlength{\oddsidemargin}{-69pt} \begin{document}$$\beta $$\end{document} 角度对于 ECOM 和 ECOM2 模型都大大减少了。与传统的箱翼模型不同，新的箱翼模型减少了 GLONASS-M 和 GLONASS-K 卫星的两个连续弧之间的轨道错位。特别是 GLONASS-M 卫星的 ECOM 模型在日食季节的改进超过 30%。对 24 小时预测轨道的进一步评估表明，日食季节的改善主要是在沿轨道和交叉轨道方向。最后，我们使用卫星激光测距 (SLR) 观测来验证 GLONASS 卫星轨道。760\documentclass[12pt]{minimal} \usepackage{amsmath} \usepackage{wasysym} \usepackage{amsfonts} \usepackage{amssymb} \usepackage{amsbsy} \usepackage{mathrsfs} \usepackage{upgreek} \setlength{\oddsidemargin} {-69pt} \begin{document}$$-0.760$$\end{document} mm/deg 对于 ECOM 和 ECOM2 模型几乎为零。总的来说，GLONASS-M卫星从新的先验箱翼模型中获益更多，BW+ECOM模型产生了最好的SLR残差，均值和标准差分别提高了约50%和20% (STD) 值相对于没有先验模型的轨道产品。