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A method and apparatus for changing the orbit of an artificial satellite. The apparatus is caused to approach a target satellite and to be coupled thereto in space so as to constitute a dumbbell-like coupled system. The apparatus has a propulsion unit. The unit generates a thrust, whereby the veloci

A method and apparatus for changing the orbit of an artificial satellite. The apparatus is caused to approach a target satellite and to be coupled thereto in space so as to constitute a dumbbell-like coupled system. The apparatus has a propulsion unit. The unit generates a thrust, whereby the velocity of the center of gravity of the apparatus increases, and the apparatus rotates around the center of gravity. As a result, the coupling system is placed in transition orbit. In the transition orbit, the coupled system is released at a timing when the direction of elongation of the coupled system becomes perpendicular to the orbital velocity vector. Subsequently, the target satellite is placed in a final target orbit, and the separated orbit changing apparatus is placed in an orbit different from the target orbit.

대표청구항 ▼

A method of changing an orbit of an artificial satellite, comprising the steps of: causing an orbit changing apparatus to approach a target satellite in an orbit around the earth, causing a catching member mounted on said orbit changing apparatus and arranged at a distal end of an elongated coupling

A method of changing an orbit of an artificial satellite, comprising the steps of: causing an orbit changing apparatus to approach a target satellite in an orbit around the earth, causing a catching member mounted on said orbit changing apparatus and arranged at a distal end of an elongated coupling member to catch the target satellite, and forming a coupled system by coupling said orbit changing apparatus to the target satellite through said elongated coupling member; simultaneously placing the center of gravity of said coupled system in a transition orbit and generating a rotational motion around the center of gravity by causing a propulsion unit mounted on said orbit changing apparatus to generate a thrust at least once in a direction perpendicular to a direction of elongation of said coupling member; and releasing said coupled system at a timing when the direction of elongation of said coupling member of said coupled system becomes perpendicular to an orbital velocity vector in the transition orbit thereby separating said target satellite from said orbit changing apparatus, placing the target satellite in a final target orbit, and placing said orbit changing apparatus in an orbit different from the target orbit.