CALCULATING METHOD OF SERIES FOR TRUE ANOMALY OF A SPACECRAFT ELLIPTIC ORBIT  

作　　者：顾晓勤 谭朝阳 MA Xing-rui 

机构地区：[1]Zhongshan College, University of Electronic Science and Technology of China, Zhongshan 528403, Guangdong Province, P. R. China [2]不详

出　　处：《Applied Mathematics and Mechanics(English Edition)》2005年第11期1435-1441,共7页应用数学和力学（英文版）

摘　　要：The transcendental equation of a true anomaly was written in a power series instead of a differential form. When the sufficient condition of the iterative convergence is satisfied, the relationship between the true anomaly and the time was gotten by the iterative method. And for the others, the transcendental equation of an eccentric anomaly was solved by the iterative method. After the eccentric anomaly had been calculated, the relationship between the true anomaly and the time was gotten with the numerical integral method. The approximate equation, which included the first five terms in general expansion, was written for the spacecraft quasi-circular orbit. And the true anomaly as the function of the time was also gotten by the iterative method. The numerical simulation results show that these methods are efficient.The transcendental equation of a true anomaly was written in a power series instead of a differential form. When the sufficient condition of the iterative convergence is satisfied, the relationship between the true anomaly and the time was gotten by the iterative method. And for the others, the transcendental equation of an eccentric anomaly was solved by the iterative method. After the eccentric anomaly had been calculated, the relationship between the true anomaly and the time was gotten with the numerical integral method. The approximate equation, which included the first five terms in general expansion, was written for the spacecraft quasi-circular orbit. And the true anomaly as the function of the time was also gotten by the iterative method. The numerical simulation results show that these methods are efficient.

关 键 词：spacecraft orbit true anomaly eccentric anomaly iterative method 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]