On the Motion of Small Satellite near the Planet in ER3BP

Abstract

In the current study, we explore stability of motion of satellite around the natural moons of planets in Solar system using the novel concept of ER3BP with variable eccentricity. This concept was introduced earlier when novel type of ER3BP (Sunplanet-satellite) was investigated with variable spin state of secondary planet correlated implicitly to the motion of satellite (in the synodic co-rotating Cartesian coordinate system) for its trapped orbit near the secondary planet (which is involved in kepler duet "Sun-planet"). But it is of real interest to explore another kind of aforedescribed problem, ER3BP (planet-moon-satellite) with respect to investigation of motion of satellite m around the natural moon m moon of planet in Solar system with variable eccentricity of the moon in its motion around the planet. So, we consider here two primaries, M planet and m moon, the last is orbiting around their common barycenter on quasi-elliptic orbit with slow-changing, not constant eccentricity (on a large-time scale) due to tidal phenomena. Our aim is to investigate motion of small dot satellite around the natural moon of planet on quasistable elliptic orbit. Both novel theoretical and numerical findings (for various cases of trio "planet-moon-satellite") are presented in the current research.

Revisiting the dynamics of finite-sized satellite near the planet in ER3BP

“…where true anomaly f is the dependent variable, f = f(t) (which is the angular distance of the radius vector from pericenter of the orbit) determined by Eq. (1), whereas ri (i =1, 2) are the distances of small mass m from each of primaries with mass M Sun and m planet, accordingly [12][13]:…”