Multidisciplinary System Design Optimization of Interplanetary Transfer Vehicle from Geostationary Transfer Orbit to Low Mars Orbit

Mars exploration is driven by its proximity and scientific goals, such as search for life, studying surface features and planetary evolution as well as preparation for human missions. Designing a spacecraft for sizable payloads to Mars is challenging, especially with chemical propulsion systems that inherently require substantial mass of propellant for trajectory maneuvers. The interdependent subsystems managing mass and power budgets add complexity, which would inevitably need diverse expertise and substantial iterations in conventional design approaches. This intricate interplay significantly complicates spacecraft development. Multidisciplinary system design optimization offers a promising solution to these challenges by simultaneously considering multiple disciplines to achieve an optimal system design, accounting for the interdependencies among various subsystems. This study proposes a multidisciplinary system design optimization approach specifically tailored for interplanetary missions between Earth and Mars. This approach allows for design exploration simultaneously considering subsystems such as trajectory, propulsion, thermal control, attitude control, structure, mass, and power to optimize the overall system performance in terms of required velocity increments and time offlight while maximizing payload mass and fulfilling the requirements of each subsystem.