Aerospace engineering Ph.D. student Bryan Cline emphasized the project's groundbreaking nature: “This is the first high-fidelity analysis of multimode mission design for lunar missions relevant to NASA, particularly utilizing CubeSats.

” By employing a standard 12-unit CubeSat, the team was able to explore various mission profiles effectively. One of the primary benefits of multimode propulsion lies in its ability to significantly reduce the spacecraft's dry mass. Cline explained that utilizing a single fuel tank streamlines mass and volume, which is a distinct advantage over traditional hybrid systems that require multiple propellants.

“With multimode systems, the flexibility to switch between high-thrust and low-thrust modes allows for better maneuverability and reduced fuel consumption,” he noted. Cline's team manually determined when to employ high-thrust or low-thrust during their mission simulations, which resulted in suboptimal trajectories. To enhance this process, he developed an algorithm that automatically identifies the optimal moments to switch thrust modes, ensuring the most efficient flight path.

“We created the first indirect optimal control technique tailored for multimode mission design, enabling us to achieve specific objectives such as minimizing fuel use and transfer time,” Cline stated. The researchers successfully tested this method on both two-dimensional transfers between Earth and Mars and three-dimensional transfers to geostationary orbit.