Conceptual Design Approaches for a Small Satellite Orbital Debris Mechanical Mitigation Mission

Orbital debris poses a persistent and escalating threat to active satellite systems, with collision and fragmentation events becoming increasingly frequent. In response, active debris removal has emerged as a critical necessity for ensuring the sustainability of space operations. This study investigates a mechanical passivation approach, where small debris particles are de-energized through in-orbit impacts to induce deorbiting or fragmentation into less hazardous components. A systematic mission design framework is proposed, beginning with the formulation of an optimization method to identify candidate orbits for effective debris mitigation. Multiple fitness functions are evaluated, incorporating debris flux forecasts, active satellite distributions, and natural deorbit timescales. The selection of debris impactor materials is also framed as a constrained optimization problem, allowing material properties and experimental studies to be integrated into the mission design process. Results indicate that sun-synchronous orbits at an inclination of 98.7° and altitudes of 800, 950, and 1200 km offer optimal trade-offs between debris density, satellite traffic, and orbital lifetime for a debris mitigation mission. A reduction in orbital velocity by 1–4% is sufficient to initiate deorbiting for debris in the 1–10 mm size range. A 350 kg-class small satellite is presented as a reference design to illustrate key trade-offs in mass allocation, delta-v requirements, propellant estimation, and power system sizing. This work provides a high-level yet practical framework for the design of future orbital debris mitigation missions using mechanical passivation techniques.