A flight device of the present invention is a flight device having one or more wings on the left and right sides of a fuselage, respectively, to generate a buoyancy force by performing relative motion to the fuselage by means of a driving source, wherein each of the left and right sides of the fuselage is provided with at least one orbital crank mechanism that receives a driving force from the driving source, wherein the crank mechanism is provided with a crankshaft extending in the front and rear direction of the fuselage, a crankpin, and a crank arm, wherein the crankpin revolves in the direction of rotation passing through a point closest to the fuselage when descending, wherein the fuselage is provided with one or more flapping rotation shafts serving as a rotation axis of flapping motion of each wing, and wherein each of the wings has an outer end portion thereof that is in a free end state and an inner end portion thereof that is hinged with the flapping rotation shaft in such a manner as to be able to be rotated in place. Some sections between the outer end and the inner end of the wing are provided with a slit-type opening having a through-space shape along the left and right width directions of the wing, the opening having a length that is slightly longer than the diameter of revolution of the crankpin, and a height that is slightly higher than the diameter of the crankpin.

    La présente invention concerne un dispositif volant ayant une ou plusieurs ailes sur les côtés gauche et droit d'un fuselage, respectivement, destinées à générer une force ascensionnelle en effectuant un mouvement relatif au fuselage au moyen d'une source d'entraînement, chacun des côtés gauche et droit du fuselage étant pourvu d'au moins un mécanisme de manivelle orbital qui reçoit une force d'entraînement de la source d'entraînement, le mécanisme de manivelle étant pourvu d'un vilebrequin s'étendant dans la direction avant et arrière du fuselage, d'un maneton, et d'un bras de manivelle, le maneton tournant dans le sens de rotation passant par un point le plus proche du fuselage lors de la descente, le fuselage étant pourvu d'un ou de plusieurs arbres de rotation de battement servant d'axe de rotation de mouvement de battement de chaque aile, et chacune des ailes ayant une partie d'extrémité externe dans un état d'extrémité libre et une partie d'extrémité interne articulée avec l'arbre de rotation de battement de manière à pouvoir tourner en place. Certaines sections entre l'extrémité externe et l'extrémité interne de l'aile sont pourvues d'une ouverture de type fente ayant une forme d'espace de passage le long des directions de largeur gauche et droite de l'aile, l'ouverture ayant une longueur légèrement supérieure au diamètre de révolution du maneton, et une hauteur légèrement supérieure au diamètre du maneton.

    본 발명의 비행장치는, 구동원에 의해 동체에 대한 상대운동을 하여 부양력을 발생시키는 날개를 상기 동체에 좌측과 우측에 각각 1개 이상 가지는 비행장치에 있어서, 상기 동체의 좌측과 우측에는, 상기 구동원에서 구동력을 전달받는 공전크랭크기구가 각각 1개 이상 구비되고, 상기 크랭크기구에는, 동체의 앞뒤 방향으로 뻗은 크랭크축과, 크랭크핀 및, 크랭크암이 구비되고, 상기 크랭크핀은 하강할 때에 동체에서 가장 가까운 지점을 통과하는 회전방향으로 공전하며, 상기 동체에는, 각 날개의 날갯짓 운동의 회전축 역할을 하는 날갯짓회동축이 1개 이상 구비되고, 각 상기 날개는, 외측 말단부위는 자유단 상태이며, 내측 말단부위는 상기 날갯짓회동축에 제자리회전이 가능한 방식으로 힌지결합되며, 상기 날개의 외측말단부와 내측말단부 사이의 일부 구간에는 길이가 상기 크랭크핀의 공전 지름보다 약간 길고, 높이는 상기 크랭크핀의 지름보다 약간 높은 관통공간 형상의 슬릿형개구부가, 날개의 좌우 폭 방향을 따라 구비된다.


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    Title :

    HIGH-SPEED DOWNWARD FLAPPING FLIGHT DEVICE


    Additional title:

    DISPOSITIF VOLANT À BATTEMENT VERS LE BAS À GRANDE VITESSE
    고속 하향 날갯짓 비행장치


    Contributors:

    Publication date :

    2021-04-08


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Korean


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F16H Getriebe , GEARING



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