基于改进因子图模型的航天器组合姿态确定算法

doi:10.12305/j.issn.1001-506X.2021.08.29

Abstract

Abstract:

Spacecraft attitude determination is the key to spacecraft attitude and orbit control and on-orbit normal operation. In view of the problem of the non-Gaussian distribution of measurement noise of spacecraft multi-sensors, and the problem of possible sensor failures and malfunctions, the spacecraft integrated attitude determination method based on improved factor graph model is proposed. By establishing a factor graph model, the geomagnetism/star sensitivity/gyro measurement information is added to the factor graph model as a factor node, and the observation data set is refined and adaptively adjusted by the observation distillation method for realizing the attitude determination of the spacecraft. Under the complex conditions, this method has strong scalability, can realize plug-and-play, reasonably and fully utilize other attitude measurement information, and avoid the complex system reconstruction process based on Kalman filter algorithm, which is beneficial to multi-sensor fusion. The experimental results show that the algorithm can improve the accuracy of attitude determination using magnetometer/star sensor/gyro, which has better dynamic stability, and realizes plug and play. This method is highly flexible and provides a new idea for solving the multi-sensor fusion for spacecraft attitude determination under complex conditions.

Key words: spacecraft attitude determination, factor graph, star sensor, magnetometer

CLC Number:

V412.4

Bing HUA, Yingying LIANG, Rui NI. Spacecraft integrated attitude determination method based on improved factor graph model[J]. Systems Engineering and Electronics, 2021, 43(8): 2273-2281.

Figures/Tables 15

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属性	基于卡尔曼滤波模型组合测姿	基于改进因子图模型的组合测姿
对系统模型处理	重建系统模型	不变
对观测模型处理	重构观测模型	构建新的节点
组合方式	分布式卡尔曼	因子图优化
复杂性	组合测姿越多, 越复杂	结构简单, 即插即用
自主性	弱	可以自主优化
优劣	难解异步、时延、强非线性问题	异步、时延亦可使用

属性	数值
半长轴/km	6 878.13
偏心率	0
轨道倾角/(°)	97.50
近地点幅角/(°)	0
升交点赤经/(°)	220
真近点角/(°)	110

系统参数	取值
传感器测量精度	同因子图
初始状态量	[1, 1, 1, 0.5, 0.5, 0.5]
初始误差	[1, 1, 1, 0.5, 0.5, 0.5]
系统噪声Q	diag[10^-4, 10^-4, 10^-4, 4×10^-6, 4×10^-6, 4×10^-6]
量测噪声R	同因子图

姿态确定方法	欧拉角精度/(″)
基于卡尔曼滤波姿态确定	11.140 7
基于因子图模型组合姿态确定	12.717 8
基于改进因子图模型的组合姿态确定	1.349 2

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Spacecraft integrated attitude determination method based on improved factor graph model

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