仅测角定轨问题迭代格式的推导与应用  

Derivation and application of iterative scheme for angle-only orbit determination

作　　者：孙玉泉[1] 强浩然 东楷涵 郑红[2] SUN Yuquan;QIANG Haoran;DONG Kaihan;ZHENG Hong(School of Mathematical Sciences,Beihang University,Beijing 100191,China;School of Automation Science and Electrical Engineering,Beihang University,Beijing 100191,China)

机构地区：[1]北京航空航天大学数学科学学院,北京100191 [2]北京航空航天大学自动化科学与电气工程学院,北京100191

出　　处：《北京航空航天大学学报》2023年第12期3245-3252,共8页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：针对由仅测角信息确定卫星轨道的问题,建模为求解相应适应度函数零点的一类方法,分析了求解该问题的高斯-牛顿迭代法中涉及的观测时间步长、动力学方程求解步长和迭代格式步长三者之间的区别与联系。针对一般精定轨方法由于适应度函数高度非线性而难以构造有效迭代格式的问题,提出了初定轨与精定轨方法结合的定轨方法,并在理论上分析了该方法的可行性。通过数值实验验证了所提求解方法的准确性、有效性和高效性。Regarding the problem of the angle-only orbit determination,we transformed into a method for solving the minimum value of the fitness function.The difference and relationship between the observation time step,the dynamic equation solution step and the iterative format step are analyzed.It is pointed out that the difficulty of precise orbit determination mainly lies in the high nonlinearity of the fitness function.A new method combining the initial and precise orbit determination is thus proposed,and its feasibility is analyzed theoretically.Finally,the accuracy,effectiveness and efficiency of the proposed method are verified by numerical experiments.

关 键 词：仅测角定轨 高斯-牛顿法 迭代格式 适应度函数 参数计算 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计] TB553[理学—物理]