Consecutive Collision Orbits to Obtain EGA Maneuvers

摘要

Studying optimal space maneuvers that searches the minimum fuel consumption for interplanetary missions is an important field of research for development of space technologies. This paper analyzes optimal maneuvers of a spacecraft that leaves one celestial body and goes back to this same body, using this return passage to perform a gravity assisted maneuvers using the mother planet to change its velocity, energy and angular momentum. During this approach, the space vehicle place itself in another orbit of interest of the mission. The dynamics used to solve this problem is the traditional model of the Restricted Three Body Problem, so it is assumed that the three bodies involved are mass points and don't suffer external disturbances. Using the gravitational attraction and the geometric configuration of the bodies involved, the passage next to the body causes a considerable change in velocity (ΔV), energy (ΔE) and angular momentum of the spacecraft. Several orbits are simulated.