On the benefit of ∈-efficient solutions in multi objective space mission design

In this work we consider multi-objective space mission design problems. We will show that it makes sense from the practical point of view to consider in addition to the (Pareto) optimal solutions also nearly optimal ones since this increases significantly the number of options for the decision maker, whereas the possible loss of such approximate solutions compared to optimal - and possibly even 'better' - ones is dispensable. For this, we will examine several typical problems in space trajectory design - a bi-impulsive transfer from the Earth to the asteroid Apophis and several low-thrust multi-gravity assist transfers - and demonstrate the possible benefit of the novel approach. Further, we will present an evolutionary multi-objective algorithm which is designed for this purpose.