Low orbit debris mitigation using momentum exchange tether system

Research implies that re-entering certain number of large debris every year could significantly relieve the problem. Compared to conventional removal method using spacecraft, momentum exchange tether system (MET) provides a low-cost and reusable solution to the problem. A scheme capable of de-orbiting large-scale debris through MET is proposed in this paper. System dynamic properties and its control are then studied in this paper based on proposed scheme. For the insufficient thrust problem of propellant-saving ion thruster, multi-stage swing acceleration method is adopted to calculate open-loop control law in Newtonian elastic model. Flexibility is found to be non-negligible when payload is heavier. One de-orbiting example is simulated and analyzed in the end. Numerical result implies that the proposed scheme is able to accomplish expected de-orbit maneuver, and tether is always tensed in acceptable level. The de-orbit acceleration is completed within dozens of orbital periods, and de-orbit maneuver is completed instantaneously, which reduces the risk of collision by decreasing mission time in debris area. By using momentum exchange tether system, large space debris could be de-orbited with lower cost and better availability.