Energetic Feasibility of Redirecting Trans-Neptunian Objects onto Mars-Impacting Orbits: Continuous Thrust and Gravity Assist Trajectories

We assess the dynamical feasibility of redirecting small volatile-bearing trans-Neptunian objects (TNOs) onto Mars-impacting orbits using continuous low-thrust propulsion and a single gravity-assist encounter. The study considers two representative dynamical classes: classical Kuiper Belt--like and Scattered Disk--like initial orbits, and determines the minimum characteristic velocity increment V required to drive the objects onto a Mars-impacting trajectory within a specified transfer time T. The dynamics is modelled in the two-body problem with a fixed maximum low thrust included, allowing the computed V to represent a dynamical lower bound independent of specific propulsion-technical implementation. Three trajectory classes are investigated: (i) inward spiral transfer, (ii) time-dependent thrust-direction steering optimized via global evolutionary algorithms, and (iii) hybrid transfers combining low thrust with a single Neptune flyby. Pure spiral trajectories yield very high velocity expenditures (V 22 km s-1) and millennia durations, confirming that monotonic inward migration is dynamically inefficient for TNO redirection. In contrast, optimized steering strategies systematically increase orbital eccentricity and achieve Mars-impacting geometries with V about 2.5 -- 3.2 km s-1 over 380--540 yr timescales. A single Neptune encounter further reduces the total V in favourable cases, with minimum values falling below those of direct optimized transfers. These results establish a quantitative lower bound on the energy cost of importing volatiles from the outer Solar System to Mars, showing that controlled redirection is feasible under modest V budgets when target bodies are chosen from favourable regions of orbital phase space.