基于日地月信息的航天器全弧段自主容积卡尔曼滤波导航

高精度全弧段航天器自主导航是航天应用技术的发展方向，是实现航天器在轨任务执行的前提和基础。文章对仅利用日、地、月等天文信息进行航天器全弧段自主导航方法进行了研究。首先，以航天器轨道动力学方程和航天器与日地月之间的夹角信息及地心距作为自主导航系统的状态模型和观测模型，构建了非线性导航系统模型。其次，给出了全弧段自主导航算法,在日月可见弧段采用非线性容积卡尔曼滤波实现航天器自主导航，在星蚀时段利用航天器轨道动力学模型进行高精度轨道预报。最后，给出了数值仿真算例。结果表明，基于日地月天文信息的航天器全弧段自主导航精度保持在2km以内，能够满足其自主导航的要求。

Spacecraft autonomous navigation with cubature Kalman filter based on sun-earth-moon information#br#

High-precision and all-time spacecraft autonomous navigation is the development direction in the space technology application, and is also the foundation for the actual on-orbit application for the spacecraft. An autonomous navigation algorithm for spacecraft base on the astronomical information of the sun, the earth and the moon was researched. Firstly, by using the dynamics equations and the angles between the spacecraft, the earth, the sun and the moon, as well as the distance between the spacecraft and the earth as the state model and observation model respectively, the navigation system was established. Then, the autonomous navigation algorithm was presented. When the sun and the moon were observable, the autonomous navigation through the nonlinear cubature Kalman filter (CKF) was adopted; and the high-precise orbit prediction algorithm was used to predict the orbit by using the track dynamics directly during the eclipse. Finally, the numerical simulation was provided. Results show that the positioning accuracy of this method is lower than 2km, which is enough to satisfy the autonomous navigation.