Abstract
The space debris removal problem needs to be solved urgently. Over 70% of debris is distributed between the 500 km and 1000 km low Earth orbits (LEO), and existing methods may be theoretically feasible but are not the high-efficiency and low-consumption methods for LEO debris removal. Based on the torque effect of a static magnet interacting with the geomagnetic field, a new spin angular momentum exchange (SAME) method by geomagnetic excitation (without working medium consumption) for LEO active debris deorbiting is proposed. The LEO delivery capability of this method is researched. Two kinds of spin angular momentum accumulation (SAMA) strategies are proposed. Then through numerical simulation under the dipole model and International Geomagnetic Reference Field (IGRF11) model, the results confirm the physical feasibility and basic performance of the proposed method. The method can be applied to the regions of the LEO below 1000 km with different altitudes/inclinations and eccentricities, and with existent magnetorquer technology, only several days of preparation is required for about 104 m·kg mechanism-scale-debris-mass deorbiting, which can be used for deorbiting missions in debris-intensive areas (altitude≤1000 km); without consideration of external effects on the geomagnetic field distribution, it has the same deorbiting capability with that of the LEO below 1000 km when the altitude is over 1000 km. Besides, the method is characterized by explicit mechanism, flexible control strategy and application, and low dependence on the scale. Finally, the key technology requirements and future application of LEO active debris removal and on-orbit delivery by using SAME are prospected.
Highlights
Since the Soviet Union launched the first satellite in 1950s, space debris increases rapidly in the low Earth orbit (LEO) with the increasing frequent space activities of human beings [1, 2]
Studies by Liou in Ref. [5] show that mass distribution in the LEO concentrates in three regions, namely, the altitude of around 600 km, 800 km, and 1000 km, and that 99% of the total mass in the orbit is 10 cm and larger debris; besides, studies at ESA (European Space Agency) indicate that the most densely populated region in the LEO is at the altitude of about 800–1000 km with high inclinations, i.e., 800 km and 98° inclination, 850 km and 71° inclination, and 1000 km and 82° inclination [6]
To solve the tether dynamics and orbital motional limited (OML) theory simultaneously, Li and Zhu in Ref. [29] developed a multiphysics finite element method for the dynamic analysis of debris deorbiting by a flexible electrodynamic tethers (EDT) and discussed the influence of the environment and tether parameters on the electron collection efficiency in Ref. [28]
Summary
Since the Soviet Union launched the first satellite in 1950s, space debris increases rapidly in the low Earth orbit (LEO) with the increasing frequent space activities of human beings [1, 2]. Techniques of active debris removal (ADR) and capturing in the LEO were proposed and studied over the past two decades [9, 10] and we will discuss as follows. [29] developed a multiphysics finite element method for the dynamic analysis of debris deorbiting by a flexible EDT and discussed the influence of the environment and tether parameters on the electron collection efficiency in Ref. An electrical propulsion system uses electrical energy usually generated by solar panels (i.e., solar electrical propulsion (SEP) [36]) or electrically expelling propellant (i.e., working mass) to meet deorbiting velocity requirements, and its principle is different with those of EDT systems by the interaction with the geomagnetic field [22].
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