Development of Practical Earth-Mars Cycler Trajectories
Faculty Mentor Name
David Conte
Format Preference
Poster
Abstract
NASA and similar space-fairing organizations have long expressed goals to send crewed missions to Mars before the year 2035. Likeminded ambitions have also driven some to believe that humanity’s long-lasting presence could also be established on the red planet in the near future. In preparing for these events, the ability to develop trajectories capable of regularly transporting payloads between the two planets has become exceedingly meaningful. A previously proposed solution to this is the Aldrin Cycler, which would be capable of “cycling” between both Earth and Mars without expending propellant to maintain its orbit. However, this trajectory and those like it make large simplifications to the Solar System’s geometry that limits their real-life practicality. Our research aims to utilize the primary concepts behind cycler orbits to develop, optimize, and configure possible preliminary spacecraft trajectories using state-of-the-art planetary data. In order to develop a robust computational structure, the implementation of several orbital mechanics functions and optimization schemes are necessary. Moreover, 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 we’re currently working on will supply optimal, yet practical, mission trajectories spanning across the next 10+ years, including necessary maneuvers needed to maintain such orbits.
Development of Practical Earth-Mars Cycler Trajectories
NASA and similar space-fairing organizations have long expressed goals to send crewed missions to Mars before the year 2035. Likeminded ambitions have also driven some to believe that humanity’s long-lasting presence could also be established on the red planet in the near future. In preparing for these events, the ability to develop trajectories capable of regularly transporting payloads between the two planets has become exceedingly meaningful. A previously proposed solution to this is the Aldrin Cycler, which would be capable of “cycling” between both Earth and Mars without expending propellant to maintain its orbit. However, this trajectory and those like it make large simplifications to the Solar System’s geometry that limits their real-life practicality. Our research aims to utilize the primary concepts behind cycler orbits to develop, optimize, and configure possible preliminary spacecraft trajectories using state-of-the-art planetary data. In order to develop a robust computational structure, the implementation of several orbital mechanics functions and optimization schemes are necessary. Moreover, 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 we’re currently working on will supply optimal, yet practical, mission trajectories spanning across the next 10+ years, including necessary maneuvers needed to maintain such orbits.