A vertical take-off and landing aircraft using a hybrid electric propulsion system, according to an embodiment of the present invention, includes: a first control step (S1) of changing a destination when an engine (10), a power generator (20), an engine control unit (30), a power management device (40), a control unit (50), a battery management system (60), a main battery (62) and the like malfunction, thereby causing a normal flight to be difficult; a second control step (S2) of performing control so that an aerial vehicle (1) glides to a point (T), at which same has entered a first space (CEP-1) required for landing or a wider second space (CEP-2) considered safe, and maintains lift and has minimized flight air resistance after passing through the point (T); a third control step (S3) of performing control so that lift is increased and performing control so that a nose cone is switched into an upward direction; and a fourth control step (S4) of performing control so that lift is gradually reduced, and controlling a second variable-pitch control device (122) so that thrust does not act on the aerial vehicle at the moment the aerial vehicle lands, and thus the present invention can vertically land while minimizing impact to be applied to the aerial vehicle. (Representative drawing) figure 7

    L'invention concerne, selon un mode de réalisation, un aéronef à décollage et atterrissage verticaux utilisant un système de propulsion électrique hybride comprenant : une première étape de commande (S1) consistant à changer une destination lorsqu'un moteur (10), un générateur de puissance (20), une unité de commande de moteur (30), un dispositif de gestion de puissance (40), une unité de commande (50), un système de gestion de batterie (60), une batterie principale (62) et analogues fonctionnent mal, ce qui complique un vol normal ; une deuxième étape de commande (S2) consistant à réaliser une commande de sorte qu'un aéronef (1) glisse vers un point (T), au niveau duquel il est entré dans un premier espace (CEP-1) requis pour un atterrissage ou un second espace plus large (CEP-2) considéré sans danger et maintient la portance et présente une résistance à l'air en vol minimisée le passage par le point (T) ; une troisième étape de commande (S3) consistant à réaliser une commande de sorte que la portance soit augmentée et réaliser une commande de sorte qu'un cône avant soit basculé dans une direction vers le haut ; et une quatrième étape de commande (S4) consistant à réaliser une commande de sorte que la portance soit progressivement réduite et commander un second dispositif de commande à pas variable (122) de sorte qu'une poussée n'agisse pas sur l'aéronef au moment où atterrit l'aéronef et ainsi la présente invention peut atterrir verticalement tout en minimisant l'impact à appliquer à l'aéronef. (Dessin représentatif) figure 7

    본 발명의 실시예에 따른 하이브리드 전기 추진시스템을 이용하는 수직이착륙 항공기는, 엔진(10), 발전기(20), 엔진제어장치(30), 파워 관리장치(40), 제어부(50), 배터리 관리 시스템(60), 메인 배터리(62) 등에 이상이 발생하여 정상 비행이 곤란하면, 목적지로 변경하는 제1 제어 단계(S1); 상기 비행체(1)가 착륙하는 데 필요한 제1 공간(CEP-1) 또는 안전을 고려하여 좀 더 넓은 제2 공간(CEP-2)에 진입한 지점(T)까지 활공 비행하고, 상기 지점(T)을 통과한 후에 양력을 유지하고 비행의 공기 저항이 최소화하도록 제어하는 제2 제어 단계(S2); 양력이 향상하도록 제어하고, 기수를 상향 방향으로 전환하도록 제어하는 제3 제어 단계(S3); 및 양력이 점차 감소하도록 제어하고, 착지하는 순간에 비행체에 추력이 작용하지 않도록 상기 제2 가변 피치 제어장치(122)를 제어하는 제4 제어 단계(S4);를 포함하여 비행체에 작용할 충격을 최소화하여 수직 착륙할 수 있다. [대표도] 도 7


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    Title :

    VERTICAL TAKE-OFF AND LANDING AIRCRAFT USING HYBRID ELECTRIC PROPULSION SYSTEM


    Additional title:

    AÉRONEF À DÉCOLLAGE ET ATTERRISSAGE VERTICAUX UTILISANT UN SYSTÈME DE PROPULSION ÉLECTRIQUE HYBRIDE
    하이브리드 전기 추진시스템을 이용하는 수직이착륙 항공기


    Contributors:
    MOON CHANG MO (author) / MOON JI HO (author) / KIM SUNG SU (author)

    Publication date :

    2020-09-17


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Korean


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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