This paper investigates the disposal of end-of-life spacecraft from selected orbit families in the Earth-Moon system, specifically the \(L_2\) Lyapunov and Halo families. Rather than focusing on impulsive burns with chemical propulsion systems, this paper examines disposal using continuous thrust generated by Hall thrusters, a form of electric propulsion. Leveraging the Circular Restricted Three Body Problem (CR3BP) as the dynamical framework, various levels of \(\Delta V\) are evaluated in single-maximum burn and multiple-burn concepts of operation to evaluate the potential for spacecraft minimizing their transit of cislunar space and reaching the Earth’s gravitational sphere of influence in order to enter heliocentric space. Analysis indicates that disposal into heliocentric space is possible from the \(L_2\) Lyapunov and Halo families for \(\Delta V\) burns in the range of 10–100 m/s depending on the initial starting location and burn direction. Due to its comparatively higher stability, disposal burns from the \(L_2\) Halo family may need to be higher than 100 m/s in order to exit the Earth’s gravitational sphere of influence. These findings establish a preliminary baseline for cislunar disposal research for the \(L_2\) Lagrange point, contributing to the emerging dialogue concerning sustainable space traffic management practices.
