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Analysis and mitigation of the Center-of-Mass errors for InSAR baseline determination

  • role： First author第一作者
  • Affiliation：

    College of Science, National University of Defense Technology, Changsha 410073, China

  • Email：jucice@126.com
  • Introduction：鞠冰(1986—　)，男，博士研究生，研究方向为卫星精密轨道确定及应用。E-mail：jucice@126.com
JU Bing,  
  • Affiliation：

    College of Science, National University of Defense Technology, Changsha 410073, China

CHANG Xiao,  
  • Affiliation：

    College of Science, National University of Defense Technology, Changsha 410073, China

GU Defeng,  
  • Affiliation：

    College of Science, National University of Defense Technology, Changsha 410073, China

DUAN Xiaojun,  
  • Affiliation：

    College of Science, National University of Defense Technology, Changsha 410073, China

ZHU Jubo,  
  • Affiliation：

    College of Science, National University of Defense Technology, Changsha 410073, China

WANG Zhengming

résumé

High-precision inter-satellite baseline determination is essential for the distributed InSAR system. The reduced dynamic orbit determination method, which employs onboard GNSS measurements and the dynamical constraints, is most extensively used to generate a baseline solution between two formation-fly satellites in low-Earth orbits. However, the reference point of the dynamical model is the center-of-mass (CoM) of the satellite rather than the phase center of the SAR antenna. Owing to the effect of structural deformation and the inevitable formation-keeping maneuvers, the CoM of a satellite in orbit is usually different from the point calibrated on ground. Thus, the effect of CoM errors must be carefully considered in GNSS-based precision baseline determination; otherwise, CoM errors are likely to induce systematic errors in the spatial baseline solution of the InSAR formation. Simulations are carried out in this study to analyze and mitigate the effect of CoM errors on the InSAR baseline determination. First, a constant CoM error of 1 cm is added to the x-, y-, and z-directions of the satellite-fixed frame. Simulation results show that the effect of such 1 cm error in the x- and y-directions are extremely tiny and can be safely neglected. By contrast, the effect of CoM error in the z-direction is significant, and the results in a systematic variation in the baseline product. In view of this, we further propose two independent methods in GNSS-based InSAR baseline determination to mitigate the z-component CoM errors by adding the following: (1) constant empirical acceleration in the radial direction; (2) an offset parameter in the z-direction of the satellite-fixed frame. The first method is based on dynamical modeling and does not need any extra correction for CoM variations. In addition, the first method is suitable for the mitigation of the CoM errors caused by formation-keeping maneuvers. The second method is based on geometric modeling, and an online calibration for the CoM errors is necessary. Moreover, the second method is suitable for the CoM calibration at the beginning of the in-orbit validation phase. Both methods are proven effective according to the numerical experiments. The 3D RMS caused by the simulated 1 cm CoM errors in the satellite-fixed z-direction can be reduced from 8.8 mm to 0.13 mm and 0.09 mm, respectively. Over 98% of the CoM errors can be mitigated. Using our proposed methods, the systematic errors caused by the CoM offset in the baseline solution can be considerably mitigated. Compared with traditional in-orbit CoM calibration, the proposed method not only avoids the complex design for satellite attitude control but also improves the efficiency of the InSAR system. The current research is based on simulations. Further validation of real data will be carried out in future studies.

mots-clés

Center-of-Mass errors;distributed InSAR;inter-satellite baseline determination;spaceborne GNSS;empirical acceleration

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