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针对深空探测器在行星际飞行的轨道确定问题,研究了一种基于视线矢量的自主导航算法.结合深空探测任务的特点,以太阳视线矢量和地球视线矢量作为导航系统的观测量,在详细分析太阳敏感器测量原理的基础上,给出了太阳视线矢量的观测模型及其观测误差表达式.通过分析导航相机观测原理,给出像元像线观测模型,并推导了地球视线矢量的观测误差.根据惯性空间内视线矢量间的几何关系,详细推导了探测器的位置矢量及其误差表达式,结合非线性扩展卡尔曼滤波建立自主导航算法.利用深度撞击任务的实际飞行数据对本文提出的深空自主导航算法进行了仿真验证.
Aiming at the orbit determination problem of deep space probe in interplanetary flight, an autonomous navigation algorithm based on line-of-sight vector is studied.Combining with the characteristics of deep space exploration mission, taking the solar horizon vector and the earth’s horizon vector as the observation of the navigation system, Based on the detailed analysis of the measuring principle of the solar sensor, the observational model of the solar line of sight vector and the expression of its observation error are given. By analyzing the observation principle of the navigation camera, the pixel-line observation model is given and the vector of the earth’s line of sight Based on the geometric relationship between the line of sight vector in inertial space, the position vector of the detector and its error expression are deduced in detail, and combined with nonlinear extended Kalman filter to build autonomous navigation algorithm.Using the actual flight data of deep impact mission, The proposed deep space autonomous navigation algorithm is verified by simulation.