Extended analytical formulae for the perturbed Keplerian motion under low-thrust acceleration and orbital perturbations

This paper presents a collection of analytical formulae that can be used in the long-term propagation of the motion of a spacecraft subject to low-thrust acceleration and orbital perturbations. The paper considers accelerations due to: a low-thrust profile following an inverse square law, gravity pe...

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Bibliographic Details
Published in:Celestial mechanics and dynamical astronomy 2021-03, Vol.133 (3), Article 13
Main Authors: Di Carlo, Marilena, Graça Marto, Simão da, Vasile, Massimiliano
Format: Article
Language:English
Subjects:
Acceleration
Aerospace Technology and Astronautics
Astrophysics and Astroparticles
Classical Mechanics
Dynamical Systems and Ergodic Theory
Geophysics/Geodesy
Gravitational fields
Kepler laws
Mathematical analysis
Orbit perturbation
Orbital elements
Original Article
Physics
Physics and Astronomy
Solar orbits
Spacecraft
Thrust
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Summary:This paper presents a collection of analytical formulae that can be used in the long-term propagation of the motion of a spacecraft subject to low-thrust acceleration and orbital perturbations. The paper considers accelerations due to: a low-thrust profile following an inverse square law, gravity perturbations due to the central body gravity field and the third-body gravitational perturbation. The analytical formulae are expressed in terms of non-singular equinoctial elements. The formulae for the third-body gravitational perturbation have been obtained starting from equations for the third-body potential already available in the literature. However, the final analytical formulae for the variation of the equinoctial orbital elements are a novel derivation. The results are validated, for different orbital regimes, using high-precision numerical orbit propagators.
ISSN:0923-2958
1572-9478
DOI:10.1007/s10569-021-10007-x