Articolo in rivista, 2021, ENG, 10.3390/universe7120482
T. Talu, E.M. Alessi, and G. Tommei
Dipartimento di Matematica, Università di Pisa; IMATI-CNR; IFAC-CNR
The aim of this work is to investigate the main dominant terms of lunisolar perturbations, that affect the orbital eccentricity of a Molniya satellite in the long term. From a practical point of view, these variations are important in the context of the space situational awareness, for instance to model the long-term evolution of an artificial debris in a highly elliptical orbit or to design a reentry end-of-life strategy for a satellite in a highly elliptical orbit. The study assumes a doubly-averaged model including the Earth's oblateness effect and the lunisolar perturbations up to the third-order expansion. The work presents three important novelties with respect to the literature. First, the perturbing terms are ranked according to their amplitudes and periods. Second, the perturbing bodies are not assumed to move on circular orbits. Third, the lunisolar effect on the precession of the argument of pericenter is analyzed and discussed. As example of theoretical application, we depict the phase space description associated with each dominant term, taken as isolated, and we show which terms can apply to the relevant dynamics in the same region.
Universe (Basel) 7 (12), pp. 482–?
Molniya satellites, lunisolar perturbation, third-body effect, secular eccentricity variation, perturbative models
IFAC – Istituto di fisica applicata "Nello Carrara", IMATI – Istituto di matematica applicata e tecnologie informatiche "Enrico Magenes"
ID: 460399
Year: 2021
Type: Articolo in rivista
Creation: 2021-12-07 22:17:13.000
Last update: 2022-02-09 18:03:02.000
CNR authors
External IDs
CNR OAI-PMH: oai:it.cnr:prodotti:460399
DOI: 10.3390/universe7120482
ISI Web of Science (WOS): 000738772200001
Scopus: 2-s2.0-85121341763