A Perturbative Treatment of The Co-Orbital Motion

Details A Perturbative Treatment of The Co-Orbital Motion A Perturbative Treatment of The Co-Orbital Motion

Apr 2002

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002cemda..82..323n&link_type=abstract

Celestial Mechanics and Dynamical Astronomy, v. 82, Issue 4, p. 323-361 (2002).

Astronomy and Astrophysics

Astronomy

16

Restricted Three-Body Problem, Disturbing Function, Mean Motion Resonances, Lagrange Equilibrium Points, Co-Orbital Motion, Trojan Asteroids

Scientific paper

We develop a formalism of the non-singular evaluation of the disturbing function and its derivatives with respect to the canonical variables. We apply this formalism to the case of the perturbed motion of a massless body orbiting the central body (Sun) with a period equal to that of the perturbing (planetary) body. This situation is known as the ‘co-orbital’ motion, or equivalently, as the 1/1 mean motion commensurability. Jupiter's Trojan asteroids, Earth's co-orbital asteroids (e.g., (3753) Cruithne, (3362) Khufu), Mars' co-orbital asteroids (e.g., (5261) Eureka), and some Jupiter-family comets are examples of the co-orbital bodies in our solar system. Other examples are known in the satellite systems of the giant planets. Unlike the classical expansions of the disturbing function, our formalism is valid for any values of eccentricities and inclinations of the perturbed and perturbing body. The perturbation theory is used to compute the main features of the co-orbital dynamics in three approximations of the general three-body model: the planar-circular, planar-elliptic, and spatial-circular models. We develop a new perturbation scheme, which allows us to treat cases where the classical perturbation treatment fails. We show how the families of the tadpole, horseshoe, retrograde satellite and compound orbits vary with the eccentricity and inclination of the small body, and compute them also for the eccentricity of the perturbing body corresponding to a largely eccentric exoplanet's orbit.

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