The increasing interest in large interplanetary missions, coupled with the need for efficient propellant consumption to achieve substantial DeltaVs, has driven the increasing adoption of electric propulsion systems. While these high specific impulse and low-thrust technologies significantly enhance mission efficiency, they also introduce substantial design challenges. These challenges necessitate the use of more complex and costly trajectory optimization models and tools compared to the traditional methods employed for impulsive maneuver mission analysis. Within this thesis a flexible low-thrust interplanetary trajectory optimization tool is proposed and developed, designed for seamless integration and implementation in industrial contexts, particularly for preliminary mission analysis studies.