Improving QZSS precise orbit determination by considering the solar radiation pressure of the L-band antenna
Improving QZSS precise orbit determination by considering the solar radiation pressure of the L-band antenna
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DOI：
10.1007/s10291-020-0963-7
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发表时间：
2020-03
期刊：
影响因子：
4.9
通讯作者：
Yongqiang Yuan;Xingxing Li;Yiting Zhu;Yun Xiong;Jiande Huang;Jiaqi Wu;Xin Li;Keke Zhang
中科院分区：
文献类型：
--
作者：
Yongqiang Yuan;Xingxing Li;Yiting Zhu;Yun Xiong;Jiande Huang;Jiaqi Wu;Xin Li;Keke Zhang
日本准天顶卫星系统由三颗倾斜地球同步轨道卫星和一颗地球静止卫星组成。根据QZSS元数据，三颗IGSO卫星配备了大型L波段天线，可以假设为圆柱体和圆形截锥的组合。通过使用由元数据释放的几何和光学特性，QZS-1 L波段天线的侧表面可以分别针对沿轨道、跨轨道和径向分量产生约5.0 nm/s2、4.5 nm/s2和2.2 nm/s2的最大加速度。通过引入箱-翼-帽模型作为先验模型，估计扩展CODE轨道模型（ECOM）的参数，可以提高IGSO卫星的精密定轨和精密钟估计性能。在先验箱翼帽模型下，QZS-1在偏航操纵（YS）模式、QZS-1在轨道正常模式、QZS-2和QZS-4的三维轨道重叠均方根值分别为8.5 cm、27.5 cm、13.2 cm和15.3 cm。卫星激光测距验证表明，QZS-1、QZS-2和QZS-4在YS模式下先验箱翼帽模型的标准差（STD）分别为5.6 cm、5.5 cm和5.3 cm，小于ECOM、ECOM 2和先验箱翼模型的STD值。关于所估计的时钟偏移，通过使用先验箱翼帽模型，可以针对YS模式中的QZS-1、QZS-2和QZS-4实现小于0.1 ns的重叠STD值。此外，修正的Allan偏差的时钟估计，可以通过使用先验的盒翼帽模型的积分时间长于2000秒。
Japanese Quasi-Zenith Satellite System (QZSS) consists of three inclined geosynchronous orbit (IGSO) satellites as well as a geostationary satellite. According to the QZSS metadata, the three IGSO satellites are equipped with large L-band antennas, which can be assumed as a combination of a circular cylinder and a circular truncated cone. By using the geometrical and optical properties released by the metadata, maximum accelerations of about 5.0 nm/s2, 4.5 nm/s2, and 2.2 nm/s2can be generated by the side surface of the QZS-1 L-band antenna for the along-track, cross-track, and radial components, respectively. By introducing the so-called box-wing-hat model as an a priori one and estimating parameters of Extended CODE Orbit Model (ECOM), the performances of both precise orbit determination and precise clock estimation can be improved for IGSO satellites. With the a priori box-wing-hat model, the root mean square values of 3D orbit overlapping are 8.5 cm, 27.5 cm, 13.2 cm, and 15.3 cm for QZS-1 in yaw-steering (YS) mode, QZS-1 in orbit-normal mode, QZS-2, and QZS-4, respectively. Satellite laser ranging validation reveals that the standard deviation (STD) values of the a priori box-wing-hat model are 5.6 cm, 5.5 cm, and 5.3 cm for QZS-1 in YS mode, QZS-2, and QZS-4, which are smaller than those of ECOM, ECOM2, and the a priori box-wing model. Regarding the estimated clock offsets, overlapping STD values of smaller than 0.1 ns can be achieved for QZS-1 in YS mode, QZS-2, and QZS-4 by using the a priori box-wing-hat model. Also, the Modified Allan Deviation of the clock estimates can be improved by using the a priori box-wing-hat model for integration time longer than 2000s.