SELENA: Semi-analytical Integrator for Lunar Artificial Satellites

TL;DR

SELENA is a semi-analytical propagator designed for lunar satellite orbits, utilizing canonical perturbation theory and symbolic computation to improve orbit prediction accuracy without eccentricity expansion.

Contribution

The paper introduces a novel semi-analytical method for lunar satellite orbit propagation using Lie series in closed form, with a symbolic package for implementation.

Findings

Developed a symbolic algebra package for orbit propagation

Derived the Hamiltonian and equations of motion for lunar satellites

Achieved orbit averaging without eccentricity expansion

Abstract

The present report summarizes the main theory and implementation steps associated with SELENA (SEmi-anaLytical intEgrator for a luNar Artificial satellite), i.e. the semi-analytical propagator for lunar satellite orbits developed in the framework of the the R&T R-S20/BS-0005-062 CNES research activity in collaboration between the University of Padova (UniPd), and the Aristotle University of Thessaloniki (AUTH), both acting as contractors with CNES. A detailed account of the method, algorithms and symbolic manipulations employed in the derivation of the final theory are described in detail in this report: they invoke the use of canonical perturbation theory in the form of Lie series computed in `closed form', i.e., without expansions in the satellite's orbital eccentricity. These algorithms are provided in the form of a symbolic package accompanying the present report. The package contains symbolic algebra programs, as well as explicit data files containing the final Hamiltonian, equations of motion and transformations (i.e. the coefficients and exponents of each variable in each term) leading to the averaging of the short-periodic terms in the satellite's equations of motion.