Trajectory Optimization - Shuttle via Earth-Mars Cycler Orbit
Faculty Mentor Name
Davide Conte
Format Preference
Poster
Abstract
NASA and other space-faring organizations have long expressed hopes of sending crewed missions to Mars before the year 2035. Like-minded ambitions have also driven some to believe that a long-lasting human presence on the red planet could be soon to follow. As humanity prepares to strive toward these extraordinary feats, the ability to craft interplanetary pathways for consistent transportation between our planets holds profound significance. The Aldrin cycler, a namesake of the legendary astronaut, proposes a trajectory capable of “cycling” between Earth and Mars without the need for costly impulsive maneuvers. However, the basic concept of this trajectory and those like it often make notable simplifications to the Solar System’s geometry that limit their real-life practicality. Our research aims to leverage the primary concepts behind cycler orbits to develop and optimize possible spacecraft trajectories using state-of-the-art planetary data and optimization schemes. In order to develop a robust computational structure, the implementation of multiple orbital mechanics functions and embedded optimization loops are necessary. To further push accuracy, planetary ephemerides computed by NASA’s JPL Solar System Dynamics are used for each interplanetary segment of the trajectory. The computations produced by this project aim to supply practical, mission trajectories spanning across the next 10+ years, including necessary maneuvers needed to maintain and rendezvous with such orbits.
Trajectory Optimization - Shuttle via Earth-Mars Cycler Orbit
NASA and other space-faring organizations have long expressed hopes of sending crewed missions to Mars before the year 2035. Like-minded ambitions have also driven some to believe that a long-lasting human presence on the red planet could be soon to follow. As humanity prepares to strive toward these extraordinary feats, the ability to craft interplanetary pathways for consistent transportation between our planets holds profound significance. The Aldrin cycler, a namesake of the legendary astronaut, proposes a trajectory capable of “cycling” between Earth and Mars without the need for costly impulsive maneuvers. However, the basic concept of this trajectory and those like it often make notable simplifications to the Solar System’s geometry that limit their real-life practicality. Our research aims to leverage the primary concepts behind cycler orbits to develop and optimize possible spacecraft trajectories using state-of-the-art planetary data and optimization schemes. In order to develop a robust computational structure, the implementation of multiple orbital mechanics functions and embedded optimization loops are necessary. To further push accuracy, planetary ephemerides computed by NASA’s JPL Solar System Dynamics are used for each interplanetary segment of the trajectory. The computations produced by this project aim to supply practical, mission trajectories spanning across the next 10+ years, including necessary maneuvers needed to maintain and rendezvous with such orbits.