HEOSAT: A mean elements orbit propagator program for Highly Elliptical Orbits

Abstract

The algorithms used in the construction of a semi-analytical propagator for the long-term propagation of Highly Elliptical Orbits (HEO) are described. The software propagates mean elements and include the main gravitational and non-gravitational effects that may affect common HEO orbits, as, for instance, geostationary transfer orbits or Molniya orbits. Comparisons with numerical integration show that it provides good results even in extreme orbital configurations, as the case of SymbolX.

arXiv comment18 pages, 5 figures

References in corpus (3)

• Gauge Freedom in Orbital Mechanics
• Delaunay variables approach to the elimination of the perigee
• Intermediary LEO propagation including higher order zonal harmonics

Cited by in corpus (7)

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• Non-singular recursion formulas for third-body perturbations in mean vectorial elements
• On mean elements in artificial satellite theory
• A torsion-based solution to the hyperbolic regime of the J2-problem
• Higher-order composition of short- and long-period effects for improving analytical ephemeris computation