Low-energy earth-moon mission analysis using low-thrust optimal and feedback control

This work is focused on designing a low-energy orbit transfer in the Earth-Moon system, aimed at reaching stable capture in a highly elliptical lunar orbit, with the use of low-thrust propulsion. The mission at hand includes three different phases: low-energy ballistic transfer starting from Earth, low-thrust minimum-fuel arc, and low-thrust lunar orbit insertion using variable-thrust nonlinear orbit control. First, a reference trajectory is generated in the framework of the Patched Planar Circular Restricted Three-Body Problem (PPCR3BP), leveraging invariant manifold dynamics. Trajectory propagation is performed using the Bicircular Restricted FourBody Problem (BR4BP) model. Particle swarm optimization is applied for trajectory refinement and to detect the subsequent minimum-fuel low-thrust arc. Finally, the lunar orbit is entered thanks to the use of variable-thrust nonlinear orbit control.