The singly averaged elliptical restricted three-body problem

被引：1
|
作者：
Elshaboury, S. M. [1 ]
Mostafa, A. [1 ,2 ]
机构：
[1] Ain Shams Univ, Fac Sci, Dept Math, Cairo, Egypt
[2] German Univ Cairo, Dept Math, Cairo, Egypt
来源：
ASTROPHYSICS AND SPACE SCIENCE | 2013年 / 348卷 / 02期
关键词：
Ristricted three body problem; ORBITS;
D O I：
10.1007/s10509-013-1586-z
中图分类号：
P1 [天文学];
学科分类号：
0704 ;
摘要：
The plane, singly averaged, elliptical restricted three body problem is considered in the article. The first three terms are taken in the perturbing function. The equations of motion in terms of the canonical elements of Delaunay are obtained. And the change of the elements of motion of the satellite due to the perturbing function is calculated. An application is given in the case of a satellite in the earth-moon system.
引用
收藏
页码：385 / 391
页数：7
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