Regularized Lagrange's planetary equations for numerical use
Abstract
The object of this study is a satellite in a highly-inclined highly-eccentric orbit around the earth, characterized by the solar-lunar-J(2) (SLJ/2/) model. Two dynamical systems - the circular restricted three-body problem and the oblate central-body problem, are discussed, and results from this analysis is used to examine and make decisions regarding the integration of the model. To study the effect of different time transformations on the numerical integration, the planetary equations are derived with time transformations involving the moon-probe distance. This process is applied to both the SLJ(2) and the circular restricted three-body problem dynamic models. It is demonstrated that the time transformation with the moon-satellite distance to the first power achieves the best results, followed by the time transformation not employing this distance.
- Publication:
-
Astrodynamics 1989
- Pub Date:
- 1990
- Bibcode:
- 1990asdy.conf...29S
- Keywords:
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- Lagrange Coordinates;
- Numerical Integration;
- Orbit Calculation;
- Planetary Orbits;
- Dynamical Systems;
- Three Body Problem;
- Astrophysics