METHOD AND SYSTEM FOR SPACE DEBRIS ORBIT DESCENT, AND METHOD AND SYSTEM FOR CHANGING ORBIT OF ARTIFICIAL SATELLITE

摘要

Provided are a method and system for space debris orbit descent with which collision avoidance operation and re-entry control is possible without a complicated and heavy removal satellite, and a method and system for changing the orbit of an artificial satellite that use the same principles. Provided are: an orbit descent method and an associated system whereby an artificial satellite for extendably holding an electroconductive tether is brought near space debris orbiting a heavenly body, one end of the electroconductive tether is attached to the space debris by an electroconductive tether attachment mechanism, the electroconductive tether is extended by an electroconductive tether extension mechanism while the artificial satellite holds the other end of the electroconductive tether, the electroconductive tether is integrated by the electromagnetic effect incurred from the magnetic field around the heavenly body causing the orbits of the orbiting artificial satellite, electroconductive tether, and space debris to descend toward the heavenly body, and the orbital motions are altered by control from the artificial satellite; and a method and system for changing the orbit of the artificial satellite that use the same principles.