CE-5T1 is the pilot probe of China’s lunar exploration project phase 3, which is mainly used to verify CE-5’s orbit and reentry technology. CE-5T1 extended mission is the first of China to fly spacecraft in the Earth-Moon L2 region. It stayed at the L2 region for about 40 d from Nov. 2014 to Jan. 2015. The Shanghai Astronomical Observatory (SHAO) team utilizes the SODP (SHAO Orbit Determination Program), using a batch least squares method, to process range, Doppler and VLBI tracking measurements from ground stations. The orbit characteristics determine that L2 probe needs to use long arc data to improve the orbit accuracy. The effect of VLBI systematic errors on the orbit is bigger than that of range measurement because of the geometry difference between the probe and ground stations. For CE-5T1 in Earth-Moon L2 libration point orbit, the tracking accuracy for range, Doppler, VLBI delay and rate are typically
国家自然科学基金(11473056)
中国科学院关键技术人才项目
探月工程
上海市科学技术委员会(12DZ2273300)
万人计划
CE-5T1工程测控系统和VLBI测轨分系统提供了测量数据, 作者对上海天文台刘庆会、舒逢春、洪晓瑜等老师的帮助表示感谢.
[1] Yan J G, Ping J S, Li F, et al. Chang’E-1 precision orbit determination and lunar gravity field solution. Adv Space Res, 2010, 46: 50-57 CrossRef ADS Google Scholar
[2] Li P J, Hu X G, Huang Y, et al. Orbit determination for Chang’E-2 lunar probe and evaluation of lunar gravity models. Sci China-Phys Mech Astron, 2012, 55: 514-522 CrossRef ADS Google Scholar
[3] Wu W R, Cui P Y, Qiao D, et al. Design and performance of exploring trajectory to Sun-Earth L2 point for Chang’E-2 mission (in Chinese). Chin Sci Bull, 2012, 57: 1987-1991 CrossRef Google Scholar
[4] Cao J, Liu Y, Hu S, et al. Navigation of Chang’E-2 asteroid exploration mission and the minimum distance estimation during its fly-by of Toutatis. Adv Space Res, 2015, 55: 491-500 CrossRef ADS Google Scholar
[5] Huang Y, Chang S Q, Li P J, et al. Orbit determination of Chang’E-3 and positioning of the lander and rover (in Chinese). Chin Sci Bull, 2014, 59: 2268-2277 CrossRef Google Scholar
[6]
Li P J, Huang Y, Chang S Q, et al. Positioning for the Chang’E-3 lander and rover using Earth-based observations.
[7] Fan M, Hu X G, Dong G, et al. Orbit improvement for Chang’E-5T lunar returning probe with GNSS technique. Adv Space Res, 2015, 56: 2473-2482 CrossRef ADS Google Scholar
[8] Gao S, Zhou W Y, Liang W G, et al. Trajectory analysis and design for relay satellite at Lagrange L2 point of earth-moon system (in Chinese). J Deep Space Expl, 2017, 4: 122–129 [高珊, 周文艳, 梁伟光, 等. 地月拉格朗日L2点中继星轨道分析与设计. 深空探测学报, 2017, 4: 122–129]. Google Scholar
[9] Woodard M, Cosgrove D, Morinelli P, et al. Orbit determination of spacecraft in Earth-Moon L1 and L2 libration point orbits. In: Proceedings of AAS/A1AA Astrodynamics Specialist Conference. Girdwood, 2011. 1701–1714. Google Scholar
[10] Wu W R, Wang Q, Tang Y H. Design of Chang’E-4 lunar farside soft-landing mission (in Chinese). J Deep Space Expl, 2017, 4: 111–117 [吴伟仁, 王琼, 唐玉华, 等. “嫦娥4号”月球背面软着陆任务设计. 深空探测学报, 2017, 4: 111–117]. Google Scholar
[11] Wu W R, Wang G L, Jie D G. High-accuracy VLBI technique using ΔDOR signals (in Chinese). Sci Sin Inform, 2013, 43: 185-196 CrossRef Google Scholar
[12] Liu L, Cao J F, Hu S J. Maintenance of relay orbit about the earth-moon collinear libration points (in Chinese). J Deep Space Expl, 2015, 2: 318–324 [刘磊, 曹建峰, 胡松杰, 等. 地月平动点中继应用轨道维持. 深空探测学报, 2015, 2: 318–324]. Google Scholar
[13] Huang Y, Hu X G, Huang C. Precise orbit determination of a maneuvered GEO satellite using CAPS ranging data (in Chinese). Sci China Ser G Phys Mech Astron, 2008, 38: 1750-1758 CrossRef Google Scholar
Copyright 2019 Science China Press Co., Ltd. 科学大众杂志社有限责任公司 版权所有
京ICP备18024590号-1
Download PDF