Spacecraft trajectory optimization

Abstract

Space is massive and poses challenges which are normally not found when dealing with problems set in a terrestrial environment. The vast distances, radiation from stars and even planets along with gravity and the distances involves complicate even a task seemingly as simple as sending a spacecraft to a distant celestial object. Here mistakes in calculation, even if it is minute can result in complete disaster, resulting in the trajectory of the craft falling short of the mission objective. Spacecraft trajectory problems are considered non-linear without a clear final solution. We will attempt to answer this problem by using Differential Evolution to optimize the Messenger and Cassini problems, using the results of CEC 2011 to do so.