A Hybrid Propulsion-Based Mission Architecture for the Removal of Debris from Low-Earth Orbit

Satellite technology has advanced with rising demand from the service sector, but increased accessibility also raises risks to the orbital environment. Space debris in low-Earth orbit (LEO) poses a major threat to satellite operations and access to space. Potential solutions for debris removal include using an onboard propulsion module to deorbit a satellite or employing a robotic arm on a “chaser” satellite to capture and remove debris. This study examines active debris removal from LEO at 2000 km altitude, focusing on a target debris weight of 100 kg and a chaser-satellite mass of 100 kg. The mission’s velocity change was calculated using the Hohmann transfer for different trajectories, and propellant requirements were derived using Tsiolkovsky’s rocket equation: ΔV = Isp × g0 × ln(mf/mi). Several scenarios were considered to assess the mission’s feasibility with respect to debris removal.