Strategy for Active Debris Removal Using Electrodynamic Tether

Abstract

In this study, the active removal of space debris is studied from the point of view of technological feasibility. First, the actual debris distribution is analyzed to determine which debris objects should be removed considering the effectiveness in preventing collisional cascading and feasibility such as the delta-V required for rendezvous with the objects. Target regions such as sun-synchronous orbit and a 1,000km altitude, 83 degree inclination orbit are then selected and rendezvous with debris object in these regions are studied. Electrodynamic tether is promising as a highly-efficient propulsion system required for debris de-orbit in these regions. A small piggyback-launched satellite to dispose of one debris object, and a dedicated debris removal satellite which removes several debris objects from crowded regions are proposed. Precise numerical simulations of EDT are performed to evaluate the de-orbit time.

Design of Maneuvering-Net Space Robot System

“…In order to protect the man-made space assets against these threats caused by the orbital debris, many orbital debris clearing systems have been proposed [4][5][6][7][8][9][10], such as the ROGER System [4][5], the Space Tether Net System [6][7] and the pulsed laser orbital debris removal (LODR)concept [8][9]. The ROGER System is proposed by EADS in 2003, which introduced two different mechanisms, including a gripper and a net, to capture the malfunction satellites.…”

“…In addition, the imaginable Manuscript received July 31, 2013. This work was supported by the National Natural Science Foundation of China (Grant No: 11272256) approach of removing the larger orbital debris by electrodynamics tethers is also discussed in reference [10]. However, the above orbital debris clearing systems still have several challenges during their clearing missions.…”

Experiments and Numerical Simulations of Electrodynamic Tether

“…From this perspective, electrodynamic tether (EDT) systems are very promising since they can generate sufficient thrust for orbital transfers without the need for propellant by utilizing interactions with Earth's magnetic field. Previous studies have shown that an EDT could deorbit many large debris items from the crowded orbits within one year 3,4) . Furthermore, the thrust of the EDT is so low that it does not have to be as firmly attached to the target as a conventional propulsion system, so attaching it to a debris object by a robot arm will be less challenging.…”

Control Technologies Required for Electrodynamic Tethers and Active Debris Removal

“…The orbits of debris objects are observed by the ground radars and optical telescopes of the North American Aerospace Defense Command (NORAD), and their orbital elements are published. It is found that many debris objects exist in some specific crowded regions such as Sun-Synchronous Orbit (SSO), 900-1,000 km altitude and 83 inclination, and 1,400-1,500 km altitude and 74, 83, or 52 inclinations 7) . Within these regions several debris objects can be found within an inclination difference of less than 1 and a RAAN (right accession of ascending node) difference of less than a few degrees, so it will be feasible for a single removal satellite to remove several objects.…”