Antonio F. B. A. Prado

TL;DR: To solve the stabilization problem in the system, a robust path following control law to control the orbital geometry of a spacecraft is applied and an example of successful operation of the orbit control is presented.

TL;DR: In this paper, the authors describe the motion of a spacecraft around an artificial equilibrium point in the circular restricted three-body problem, where the spacecraft is under the gravitational influence of the Sun and the Earth, as primary and secondary bodies, subjected to the force due to the solar radiation pressure and some extra perturbations.

TL;DR: The main idea of this paper is to propose the construction of an “Escape Portal” to send a spacecraft to the exterior planets, or even to make it escape from the Solar System, using a Tethered Sling Shot Maneuver with an asteroid.

TL;DR: In this paper, the velocity increments required to start or stop the spacecraft at the Earth and the flight path angle at the meeting point for trajectories that cross the Earth's orbit around the Sun before or after the passage by Jupiter were derived.

TL;DR: In this article , the authors used mathematical models with forces that have symmetry/asymmetry phenomena, depending on the force, applied to orbits around Titan and evaluated the effects due to the gravitational attraction of the Saturn, together with the perturbative effects coming from the nonsphericity of Titan (the gravitational coefficient J2) and the effects of the atmospheric drag present in the natural satellite.