期刊文献+
共找到1篇文章
< 1 >
每页显示 20 50 100
CALCULATING METHOD OF SERIES FOR TRUE ANOMALY OF A SPACECRAFT ELLIPTIC ORBIT
1
作者 顾晓勤 谭朝阳 MA Xing-rui 《Applied Mathematics and Mechanics(English Edition)》 SCIE EI 2005年第11期1435-1441,共7页
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 an... 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. 展开更多
关键词 spacecraft orbit true anomaly eccentric anomaly iterative method
下载PDF
上一页 1 下一页 到第
使用帮助 返回顶部