中文摘要：

针对基于小行星观测的自主光学导航在深空巡航段应用中存在的问题,提出了两种基于太阳观测的自主导航方法。以太阳视线矢量为基本观测量,分别利用分光计和星载导航相机测量探测器相对于太阳的径向速度和导航天体相对于探测器的视线矢量,进而构建了基于太阳信息和视线信息的两种观测方案。对两种观测方案的原理和观测方程进行了详细分析和推导,并采用扩展卡尔曼滤波算法实时估计探测器轨道。最后,以深度撞击任务的实际飞行数据对本文提出的两种自主导航方法进行仿真验证。结果表明,两种自主导航方法的轨道估计精度满足深空巡航段的要求。

英文摘要：

In this paper,two types of autonomous navigation method based on the Sun observation are proposed for the problem of orbit determination during the deep space cruise phase.The radial velocity of the spacecraft relative to the Sun is measured by a spectrometer,and the line-of-sight vector of the reference celestial body relative to the spacecraft is measured by the onboard camera.Then,two kinds of observation scheme,one is based on the Sun information and the other is based on line-of-sight information,are constructed combined with the line-of-sight vector from the spacecraft to the Sun.The fundamental of the observation schemes is analyzed and the measurement equations are educed in detail.The orbit parameters of the spacecraft are estimated in real time by utilizing extended Kalman filter.Finally,the autonomous navigation methods presented are verified by the practical data of deep impact mission.The estimation accuracy of the orbit is demonstrated to meet the requirement of the deep space cruise phase.