Third-Body Perturbation Using a Single Averaged Model: Application in Nonsingular Variables
The Lagrange's planetary equations written in terms of the classical orbital elements have the disadvantage of singularities in eccentricity and inclination. These singularities are due to the mathematical model used and do not have physical reasons. In this paper, we studied the thir...
| Main Authors: | , |
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| Format: | Article |
| Language: | English |
| Published: |
Hindawi Limited
2007-01-01
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| Series: | Mathematical Problems in Engineering |
| Online Access: | http://dx.doi.org/10.1155/2007/40475 |
| Summary: | The Lagrange's planetary equations written in terms of the classical orbital elements have the
disadvantage of singularities in eccentricity and inclination. These singularities are due to the mathematical
model used and do not have physical reasons. In this paper, we studied the third-body perturbation
using a single averaged model in nonsingular variables. The goal is to develop a semianalytical study of
the perturbation caused in a spacecraft by a third body using a single averaged model to eliminate
short-period terms caused by the motion of the spacecraft. This is valid if no resonance occurs with the moon
or the sun. Several plots show the time histories of the Keplerian elements of equatorial and circular orbits, which
are the situations with singularities. In this paper, the expansions are limited only to second order in eccentricity
and for the ratio of the semimajor axis of the perturbing and perturbed bodies and to the fourth order for the
inclination. |
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| ISSN: | 1024-123X 1563-5147 |