An integrated celestial navigation scheme for spacecrafts based on an optical interferometer and an ultraviolet Earth sensor is presented in this paper. The optical interferometer is adopted to measure the change in inter-star angles due to stellar aberration, which provides information on the velocity of the spacecraft in the plane perpendicular to the direction of the observed star. In order to enhance the navigation performance, the measurements obtained from the ultraviolet Earth sensor is used to eliminate the unfavorable effect caused by the gravitational deflection of starlight. As the prior knowledge about the optical path delay bias of the optical interferometer may be ambiguous, a Q-learning extended Kalman filter is derived to fuse the two types of measurements, and estimate the kinematic state together with the optical path delay bias. The solution of the autonomous navigation system consists of position, velocity and attitude of the spacecraft. Numerical simulation shows that an evident improvement in navigation accuracy can be achieved by introducing the ultraviolet Earth sensor into the navigation system. In addition, it is shown that the Q-learning extended Kalman filter performs better than the traditional extended Kalman filter.

中文翻译：

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使用干涉仪和地球传感器的航天器集成天文导航

本文提出了一种基于光学干涉仪和紫外地球传感器的航天器综合天文导航方案。光学干涉仪用于测量由于星差引起的星间角变化，提供航天器在垂直于被观测星方向的平面内的速度信息。为了提高导航性能，利用紫外地球传感器的测量结果来消除星光引力偏转带来的不利影响。由于关于光学干涉仪光路延迟偏差的先验知识可能不明确，因此推导出 Q-learning 扩展卡尔曼滤波器来融合两种类型的测量，并将运动学状态与光路延迟偏差一起估计。自主导航系统的解决方案包括航天器的位置、速度和姿态。数值模拟表明，将紫外地球传感器引入导航系统可以显着提高导航精度。此外，还表明 Q-learning 扩展卡尔曼滤波器的性能优于传统的扩展卡尔曼滤波器。