DEORBITING SYSTEM FOR MICRO-SATELLITES

An objective of the present invention is to provide a deorbiting system for an ultrasmall satellite which is small and is capable of deorbiting regardless of arrangement directions. According to one embodiment of the present invention, the deorbiting system for an ultrasmall satellite comprises: a d...

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Bibliographische Detailangaben
Hauptverfasser:	BOROVIK IGOR, DO RYOON HO, KIM DOE HEE, VEDENKIN NIKOLAY
Format:	Patent
Sprache:	eng ; kor
Schlagworte:	AIRCRAFT AVIATION CHEMISTRY COMPOUNDS THEREOF COSMONAUTICS INORGANIC CHEMISTRY METALLURGY NON-METALLIC ELEMENTS PERFORMING OPERATIONS TRANSPORTING VEHICLES OR EQUIPMENT THEREFOR
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Beschreibung
Zusammenfassung:	An objective of the present invention is to provide a deorbiting system for an ultrasmall satellite which is small and is capable of deorbiting regardless of arrangement directions. According to one embodiment of the present invention, the deorbiting system for an ultrasmall satellite comprises: a deorbiting body installed on an ultrasmall satellite; a gas generation part installed in the deorbiting body and generating gas; a drag providing pat installed in the deorbiting body and expanded by gas generated by the gas generation part to provide drag for the ultrasmall satellite; and a power supply part installed in the deorbiting body and supplying power to the gas generation part. 본 발명의 일 실시예에 따른 초소형 위성용 궤도 이탈 시스템은 초소형 위성에 설치되는 궤도 이탈 본체, 상기 궤도 이탈 본체 내부에 설치되며 가스를 발생시키는 가스 발생부, 상기 궤도 이탈 본체 내부에 설치되며 상기 가스 발생부에 의해 발생한 가스에 의해 확장되어 상기 초소형 위성에 항력을 제공하는 항력 제공부, 그리고 상기 궤도 이탈 본체 내부에 설치되며 상기 가스 발생부에 전원을 공급하는 전원 공급부를 포함한다.