Stationkeeping of halo orbits in Jupiter-Europa-Io system

Exploration and Maintenance of Homeomorphic Orbit Revs in the Elliptic Restricted Three-Body Problem

“…Previous studies have demonstrated that rather expectantly, LPOs in the CR3BP lose their periodicity when realistic perturbations are embedded into the dynamical system [1,. Since unmodeled perturbations significantly affect nominal spacecraft trajectory, it has been demonstrated that autonomous trajectory re-planning, guidance, and station-keeping analyses are of utmost importance for the success of these missions [17][18][19]25,[27][28][29][30]. Several methods have been used so far by researchers ranging from location-based Target Point Approach (TPA), shape-similar trajectories, to finite-time Lyapunov exponents (FTLEs) in the form of the Cauchy Green Tensor (CGT) [17,18,25,27,28].…”

“…Studies performed on the effects of the Sun's gravity on the spacecraft as an additional perturbing force, through the Bi-Circular Restricted Four-Body Problem (BCR4BP) in the Sun-Earth-Moon system which presented significant positional deviation from a perfectly periodic halo orbit [6][7][8][9][10]. For Europa, due to the proximity to both Io and Ganymede, the Concentric Circular Restricted Four-Body Problem (CCR4BP) was a better approximation as all three moons are in resonance with each other [19,20]. Another paper that focuses on the Sun-Earth-Moon system also includes the effect of albedo on the celestial bodies themselves as an additional parameter [10].…”