Long-term Evolution of Mid-altitude Quasi-satellite Orbits
| Autor: | Lamberto Dell'Elce, Yasuhiro Kawakatsu, Nicola Baresi, Josué Cardoso dos Santos |
|---|---|
| Přispěvatelé: | Surrey Space Centre [Guildford], University of Surrey (UNIS), Mathematics for Control, Transport and Applications (McTAO), Inria Sophia Antipolis - Méditerranée (CRISAM), Institut National de Recherche en Informatique et en Automatique (Inria)-Institut National de Recherche en Informatique et en Automatique (Inria), Universidade Estadual Paulista Júlio de Mesquita Filho = São Paulo State University (UNESP), Japan Aerospace Exploration Agency [Sagamihara] (JAXA) |
| Jazyk: | angličtina |
| Rok vydání: | 2020 |
| Předmět: |
010504 meteorology & atmospheric sciences
Quasi-satellite [MATH.MATH-DS]Mathematics [math]/Dynamical Systems [math.DS] Aerospace Engineering Ocean Engineering Orbital eccentricity 01 natural sciences 0103 physical sciences Electrical and Electronic Engineering Invariant (mathematics) 010303 astronomy & astrophysics ComputingMilieux_MISCELLANEOUS 0105 earth and related environmental sciences Spacecraft business.industry Applied Mathematics Mechanical Engineering Torus Geophysics Numerical integration Moons of Mars Control and Systems Engineering Physics::Space Physics Astrophysics::Earth and Planetary Astrophysics business Longitude Geology |
| Zdroj: | Nonlinear Dynamics Nonlinear Dynamics, 2020, 99, pp.2743-2763 Nonlinear Dynamics, Springer Verlag, In press |
| ISSN: | 0924-090X 1573-269X |
| Popis: | Quasi-satellite orbits are of great interest for the exploration of planetary moons because of their dynamical features and close proximity with respect to the surface of scientifically relevant objects like Phobos and Deimos. This paper explores the equations of the elliptical Hill problem, offering a new analytical insight into the long-term evolution of mid-altitude quasi-satellite orbits. Our developments are based on the Yamanaka–Ankersen solution of the Tschauner–Hempel equations and capture the effects of the secondary’s gravity and orbital eccentricity on the shape and orientation of near-equatorial retrograde relative trajectories. The analytical solution of the in-plane and out-of-plane components of the secular motion is achieved by averaging over the relative longitude of a spacecraft as seen from the co-rotating frame of the two primaries. Developments are validated against the numerical integration of quasi-periodic trajectories that densely cover the surface of three-dimensional invariant tori. This analysis confirms the stable nature of quasi-satellite orbits and provides new tools for future spacecraft missions such as the Martian Moons eXploration envisaged by JAXA. |
| Databáze: | OpenAIRE |
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