The present invention relates to a deployable solar panel restraint apparatus for a microsatellite, which comprises: a launch tube equipped with a rail inside; a satellite body mounted inside the launch tube and moving along the rail; a driving unit for providing power to move the satellite body along the rail; a restraint unit provided on a side of the satellite body; a solar panel coupled to the side of the satellite body; and a coupling unit provided on the solar panel and coupled to the restraint unit. The coupling unit coupled to the restraint unit is restrained by the launch tube or the rail to suppress deployment of the solar panel, wherein when the satellite body is ejected from the launch tube, the solar panel is deployed. The present invention can prevent the solar panel from being damaged by the satellite body or the launch tube.

    본 발명은 본 발명은 초소형위성의 전개형 태양전지판 구속 장치에 관한 것으로, 내부에 레일이 구비된 발사관; 상기 발사관 내부에 장착되며, 상기 레일을 따라 이동하는 위성 본체; 상기 레일을 따라 상기 위성 본체를 이동시키기 위한 동력을 제공하는 구동부; 상기 위성 본체의 측부에 구비되는 구속부; 상기 위성 본체의 측부에 결합되는 태양전지판; 상기 태양전지판에 구비되며, 상기 구속부에 결합되는 결합부;를 포함하며, 상기 구속부에 결합된 상기 결합부는 상기 발사관 또는 상기 레일에 의해 구속되면서 상기 태양전지판의 전개가 억제되며, 상기 위성 본체가 상기 발사관에서 사출되면, 상기 태양전지판이 전개되는 것을 특징으로 하는 것이다.


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    Title :

    Deployable solar panel restraint apparatus for microsatellite


    Additional title:

    초소형위성의 전개형 태양전지판 구속 장치


    Contributors:
    KIM MIN KI (author) / KIM HAE DONG (author) / CHOI WON SUB (author) / KIM JIN HYUNG (author)

    Publication date :

    2023-03-21


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Korean


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS / H02S GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRA-RED RADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, E.G. USING PHOTOVOLTAIC [PV] MODULES , Erzeugung elektrischer Energie durch Umwandlung von Infrarot-Strahlung, sichtbarem Licht oder ultraviolettem Licht, z.B. unter Verwendung von Photovoltaik [PV]-Modulen



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