收稿：2016-09-09，
录用：2016-12-5，
纸质出版：2017-05
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高精度星间基线确定是分布式InSAR干涉测量中的关键技术。针对卫星在轨运行期间的质心与地面标校结果不一致问题，仿真分析了星体系x、y、z不同方向1 cm质心误差对InSAR星间基线确定的影响。结果表明：x、y方向的质心误差对基线解算影响很小；z方向的质心误差对基线解算影响显著，使得InSAR基线产品中含有明显的系统误差。提出了两种消除卫星质心误差影响的方法：一是在星载GNSS定轨过程中增加轨道径向的经验加速度予以补偿；二是增加星体系z方向的质心偏差估计。实验结果表明，经两种方法处理后得到的InSAR基线3维误差由8.8 mm分别降至0.13 mm和0.09 mm，98%以上的卫星质心误差影响被消除。
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.
Allende-Alba G and Montenbruck O. 2016. Robust and precise baseline determination of distributed spacecraft in LEO. Advances in Space Research, 57(1): 46–63
Antony J W, Gonzalez J H, Schwerdt M, Bachmann M, Krieger G and Zink M. 2013. Results of the TanDEM-X baseline calibration. IEEE Journal of Selected Topics in Applied Earth Observations and Remote Sensing, 6(3): 1495–1501
Bergman E V, Walker B K and Levy D R. 1987. Mass property estimation for control of asymmetrical satellites. Journal of Guidance, Control, and Dynamics, 10(5): 483–491
Beutler G, Jäggi A, Hugentobler U and Mervart L. 2006. Efficient satellite orbit modelling using pseudo-stochastic parameters. Journal of Geodesy, 80(7): 353–372
Gonzalez J H, Bachmann M, Krieger G and Fiedler H. 2010. Development of the TanDEM-X calibration concept: analysis of systematic errors. IEEE Transactions on Geoscience and Remote Sensing, 48(2): 716–726
Gu D F, Lai Y W, Liu J H, Ju B and Tu J. 2016. Spaceborne GPS receiver antenna phase center offset and variation estimation for the Shiyan 3 satellite. Chinese Journal of Aeronautics, 29(5): 1335–1344
Jäggi A, Montenbruck O, Moon Y, Wermuth M, König R, Michalak G, Bock H and Bodenmann D. 2012. Inter-agency comparison of TanDEM-X baseline solutions. Advances in Space Research, 50(2): 260–271
Ju B, Gu D F, Herring T A, Allende-Alba G, Montenbruck O and Wang Z M. 2017. Precise orbit and baseline determination for maneuvering low earth orbiters. GPS Solutions, 21(1): 53–64
Krieger G, Fiedler H, Hajnsek I, Eineder M, Werner M and Moreira A. 2005. TanDEM-X: mission concept and performance analysis//Proceedings of 2005 IEEE International Geoscience and Remote Sensing Symposium. Seoul, Korea: IEEE: 4890–4893 [DOI: 10.1109/IGARSS.2005.1526770]
Krieger G, Moreira A, Fiedler H, Hajnsek I, Werner M, Younis M and Zink M. 2007. TanDEM-X: A Satellite Formation for High-Resolution SAR Interferometry. IEEE Transactions on Geoscience and Remote Sensing, 45(11): 3317–3341
Krieger G, Zink M, Bachmann M, Bräutigam B, Schulze D, Martone M, Rizzoli P, Steinbrecher U, Walter Antony J, De Zan F, Hajnsek I, Papathanassiou K, Kugler F, Rodriguez Cassola M, Younis M, Baumgartner S, López-Dekker P, Prats P and Moreira A. 2013. TanDEM-X: a radar interferometer with two formation-flying satellites. Acta Astronautica, 89: 83–98
Kroes R, Montenbruck O, Bertiger W and Visser P. 2005. Precise GRACE baseline determination using GPS. GPS Solutions, 9(1): 21–31
Liu J H, Gu D F, Ju B, Lai Y W and Yi D Y. 2015. Relative clock estimation method between two LEO satellites with a double-difference solution constraint. Acta Astronautica, 109: 34–41
Liu J H, Gu D F, Ju B, Yao J, Duan X J and Yi D Y. 2014. Basic performance of BeiDou-2 navigation satellite system used in LEO satellites precise orbit determination. Chinese Journal of Aeronautics, 27(5): 1251–1258
Montenbruck O, Wermuth M and Kahle R. 2011. GPS based relative navigation for the TanDEM-X mission-first flight results. Navigation, 58(4): 293–304
Moon Y, Koenig R and Wermuth M. 2012. Operational precise baseline determination for TanDEM-X DEM processing//Proceedings of IEEE International Geoscience and Remote Sensing Symposium. Munich: IEEE: 1633–1636 [DOI: 10.1109/IGARSS.2012.6351215]
Richfield R F, Walker B K and Bergmann E V. 1988. Input selection for a second-order mass property estimator. Journal of Guidance, Control, and Dynamics, 11(3): 207–212
Tanygin S and Williams T. 1997. Mass property estimation using coasting maneuvers. Journal of Guidance, Control, and Dynamics, 20(4): 625–632
Tu J, Gu D F, Wu Y and Yi D Y. 2012. Error modeling and analysis for InSAR spatial baseline determination of satellite formation flying. Mathematical Problems in Engineering, 2012: Article ID 140301 [DOI: 10.1155/2012/140301]
王本利, 廖鹤, 韩毅. 2010. 基于MME/EKF算法的卫星质心在轨标定. 宇航学报, 31(9): 2150–2156
Wang B L, Liao H and Han Y. 2010. On-Orbit calibration of satellite center of mass based on MME/EKF algorithm. Journal of Astronautics, 31(9): 2150–2156
汪丙南, 向茂生. 2009. TanDEM-X系统相对测高性能分析. 遥感学报, 13(1): 49–53
Wang B N and Xiang M S. 2009. Relative height accuracy analysis of TanDEM-X system. Journal of Remote Sensing, 13(1): 49–53
Wang F R, Bettadpur S V, Save H and Kruizinga G. 2010. Determination of Center-of-Mass of gravity recovery and climate experiment satellites. Journal of Spacecraft and Rockets, 47(2): 371–379
王青松, 瞿继双, 黄海风, 余安喜, 董臻. 2012. 联合实、复相关函数的干涉SAR图像配准方法. 测绘学报, 41(4): 563–569
Wang Q S, Qu J S, Huang H F, Yu A X and Dong Z. 2012. A method based on integrating real and complex correlation function for InSAR image coregistration. Acta Geodaetica et Cartographica Sinica, 41(4): 563–569
Wermuth M, Montenbruck O and Wendleder A. 2011. Relative navigation for the TanDEM-X mission and evaluation with DEM calibration results. Journal of Aerospace Engineering, Sciences and Applications, 3(2): 28–38
Wu S C, Yunck T P and Thornton C L. 1991. Reduced-dynamic technique for precise orbit determination of low earth satellites. Journal of Guidance, Control, and Dynamics, 14(1): 24–30
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