HEOSAT: a mean elements orbit propagator program for highly elliptical orbits
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 ins...
| Autores: | , , |
|---|---|
| Tipo de recurso: | artículo |
| Estado: | Versión aceptada para publicación |
| Fecha de publicación: | 2018 |
| País: | España |
| Institución: | Universidad de La Rioja (UR) |
| Repositorio: | RIUR. Repositorio Institucional de la Universidad de La Rioja |
| OAI Identifier: | oai:portal.dialnet.es:doc/5bbc68ebb750603269e811b3 |
| Acceso en línea: | https://investigacion.unirioja.es/documentos/5bbc68ebb750603269e811b3 |
| Access Level: | acceso abierto |
| Palabra clave: | Atmospheric drag Geopotential HEO Mean elements Semi-analytic propagation SRP Tesseral resonances Third-body perturbation |
| Sumario: | 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. © 2017, CEAS. |
|---|