An active time-optimal control for space debris deorbiting via geomagnetic field

This paper is concerned with an approach for active removing of space debris by electrodynamic tether (EDT) systems in a time-optimal maneuver. In this regard, a collector–emitter system is comprised of the insulated EDT in order to generate the required electric current over a virtual circuit once the induced electric current is adopted as control force producer. To this end, a simulation program is initially developed, during which dynamic and mathematical models of the EDT as well as the geomagnetic field are encompassed, respectively. This toolset is first utilized for prediction of orbital characteristics during the deorbit process; and subsequently, using the direct transcription method, the time-optimal problem is well solved. The efficacy of the suggested technique is verified through extensive simulations once all hard constraints of the underlying problem are well satisfied. In short, while the altitude varies from 1413 to 200 km, the optimized deorbit time would reduce about 17 days.