Small eccentricity satellite orbits: Linear perturbations

被引：0

作者：

Giacaglia, G. E. O. ^{[1
]}

Schutz, B. E. ^{[2
]}

机构：

[1] Univ Taubate, Dept Mech Engn, BR-12060440 Taubate, SP, Brazil

[2] Univ Texas Austin, Dept Aerospace Engn & Engn Mech, Ctr Spce Res, Austin, TX 78712 USA

来源：

SPACEFLIGHT MECHANICS 2008, VOL 130, PTS 1 AND 2 | 2008年 / 130卷

关键词：

D O I：

暂无

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The well known linearized theory of satellite motion given by Kaula in 1966 has proven to be very useful in categorizing the nature of gravitational perturbations associated with the mass distribution of the planet that defines the satellite orbits. The secular and periodic perturbations produced by zonal, tesseral and sectorial gravity coefficients can be readily identified. In fact, the expressions for secular variations and amplitude of some periodic variations are well represented by the theory. Nevertheless, potential problems exist when the eccentricity is small, for example, because of the use of classical orbit elements in Kaula's theory. This paper examines an alternate theory, based on nonsingular elements for small eccentricity, which is the typical case for most Earth observing and geodetic satellites.

引用

页码：1557 / +

页数：2