PROBLEM TO BE SOLVED: To provide a space debris descent method and system that enable collision avoidance operation or reentry without a complicated heavy removal satellite and an orbital conversion method and system based on a similar principle.SOLUTION: There are provided an orbital descent method, a related system that make an artificial satellite retaining a conductive tether 7 to be capable of extension approach a space debris 27 orbitally moving around a celestial body to mount one end of the conductive tether to the space debris with conductive tether mounting mechanisms 5,6, make the conductive tether extend the conductive tether with a conductive tether extension mechanism 8 in a condition that the artificial satellite retains the other end of the conductive tether to descend the orbit of the artificial satellite, that of the conductive tether, and that of the space debris orbitally moving in an integral body under an electromagnetic effect the conductive tether receives from an ambient magnetic field of the celestial body, toward the celestial body for a change in the orbital movement by control from the artificial satellite, and an orbital conversion method and system based on a similar principle.
【課題】複雑で重量の大きい除去衛星なしに衝突回避運用や再突入制御を可能とするスペースデブリの軌道降下方法、システム、及び同様の原理による人工衛星の軌道変換方法、システムを提供する。【解決手段】導電性テザー7を伸展可能に保持する人工衛星を天体の周りを軌道運動するスペースデブリ27に接近させ、導電性テザーの一端を導電性テザー取り付け機構5,6によってスペースデブリに取り付け、人工衛星が導電性テザーの他端を保持した状態で導電性テザー伸展機構8により導電性テザーを伸展させて、導電性テザーが天体の周囲磁場から受ける電磁気的作用により一体となって軌道運動する人工衛星、導電性テザー、スペースデブリの軌道を天体に向かって降下させ、人工衛星からの制御により上記軌道運動を変化させる、軌道降下方法、関連するシステム、及び同様の原理による人工衛星の軌道変換方法、システムを提供する。【選択図】図5
SPACE DEBRIS ORBIT DESCENT METHOD, ORBIT DESCENT SYSTEM, AND SATELLITE ORBIT CONVERSION METHOD, ORBIT CONVERSION SYSTEM
スペースデブリの軌道降下方法、軌道降下システム、及び、人工衛星の軌道変換方法、軌道変換システム
2016-01-12
Patent
Electronic Resource
Japanese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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