Space Debris Removal Using Electromagnetic Fields

With the increasing population of artificial objects in Earth's orbit, space debris has become a growing threat to global satellite infrastructure. Debris fragments within the 1–10 cm diameter range are particularly hazardous. Large debris (>10 cm) can be tracked and avoided through orbital maneuvering, while particles smaller than 1 cm can often be mitigated using protective shielding. However, medium-sized debris remains difficult to detect and cannot be effectively shielded against, creating a significant gap in current mitigation strategies. Recent estimates suggest that over 1.2 million untracked fragments larger than 1 cm remain in orbit (ESA, 2025). This study proposes a non-contact active debris removal method using electromagnetic forces to induce orbital decay. Specifically, the concept utilizes the Lorentz force, allowing a charged object moving through Earth's geomagnetic field to experience a force that alters its orbit. The proposed model was first evaluated using numerical simulations, followed by high-fidelity orbital simulations in General Mission Analysis Tool (GMAT) utilizing the IGRF-13 geomagnetic field model. Simulation results indicate a direct relationship between applied charge and orbital decay rate. Under maximum simulated conditions (charge ≈ 1 × 10⁻³ C), the model suggests rapid orbital decay from an initial altitude of 800 km, leading to atmospheric re-entry within approximately 48 hours under idealized assumptions including constant charge maintenance and a simplified dipole magnetic field.