Orbit determination and accuracy evaluation of Tianwen-1 probe

doi:10.11947/j.AGCS.2024.20230126

Abstract

Abstract:

For China's first Mars exploration mission, Tianwen-1, high accuracy orbit determination is the cornerstone for fulfilling engineering goals and scientific exploratory objectives. This study adopts a variety of orbit determination approaches based on the characteristics of the orbit, the dynamic environment, and the observational quality of different stages. It then evaluates the orbit accuracy by comparing overlapping arcs. Modeling errors for solar radiation pressure and attitude control thrust are the main obstacles preventing the high accuracy orbit of Tianwen-1. Some model errors can be removed by resolving the solar radiation pressure coefficient and empirical acceleration parameters during the orbit determination estimation. However, because of the special spacecraft attitude, the combined estimation of the solar radiation pressure coefficient and empirical acceleration parameters leads a clear coupling relationship, but adding a priori constraint information is a way to decrease the correlation between them. In the interplanetary cruise stage, the orbit accuracy is better than 4 km, 1 km in the parking stage, and 100 m in the relay communication stage, according to the results of an overlapping orbit. Furthermore, the accuracy of two-way range measurement is about 0.5 m, the two-way Doppler measurement is about 0.2 mm/s at 1 s integration time, and the VLBI delay measurement is around 0.3 ns.

Key words: Tianwen-1, precise orbit determination, solar pressure, attitude control thrust

CLC Number:

P228

Haijun MAN, Jianfeng CAO, Bing JU, Xie LI, Jing KONG, Shanhong LIU. Orbit determination and accuracy evaluation of Tianwen-1 probe[J]. Acta Geodaetica et Cartographica Sinica, 2024, 53(7): 1288-1297.

Figures/Tables 11

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项目	模型设置
中心天体	太阳（地火转移段）、火星（火星环绕段）
N体摄动	太阳、地球、月球、大行星，采用DE436历表火卫一、火卫二，采用SPICE（Mars_097.bsp）历表
火星非球形引力	JGMRO_120d模型
太阳辐射压	固定面质比模型
火星大气	火星季节数据库MCD5.3
相对论效应	一阶后牛顿效应
经验力	R、T、N方向，常值经验加速度模型

轨道事件	时间（BJT）	对地距离/km
第1次中途修正TCM1	2020-08-02T07：00	3.0×10⁶
第2次中途修正TCM2	2020-09-20T23：00	1.9×10⁷
深空机动DSM	2020-10-09T23：00	2.94×10⁷
第3次中途修正TCM3	2020-10-28T22：00	4.40×10⁷
第4次中途修正TCM4	2021-02-05T20：00	1.84×10⁸
近火捕获（MOI）	2021-02-10T20：00	1.92×10⁸