WO2019132285A1 - Ensemble de pales inclinables pour drone - Google Patents

Ensemble de pales inclinables pour drone Download PDF

Info

Publication number
WO2019132285A1
WO2019132285A1 PCT/KR2018/015309 KR2018015309W WO2019132285A1 WO 2019132285 A1 WO2019132285 A1 WO 2019132285A1 KR 2018015309 W KR2018015309 W KR 2018015309W WO 2019132285 A1 WO2019132285 A1 WO 2019132285A1
Authority
WO
WIPO (PCT)
Prior art keywords
tilting
connection
power
blade assembly
tilting blade
Prior art date
Application number
PCT/KR2018/015309
Other languages
English (en)
Korean (ko)
Inventor
이종경
정용범
김제중
김영수
정승규
Original Assignee
(주)프리뉴
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by (주)프리뉴 filed Critical (주)프리뉴
Publication of WO2019132285A1 publication Critical patent/WO2019132285A1/fr

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/44—Blade pitch-changing mechanisms electric
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/25—Fixed-wing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/13—Propulsion using external fans or propellers

Definitions

  • the present technique relates to a blade assembly for a drone.
  • the drones are radio-controlled, unmanned aircrafts that were developed for military use but have expanded in recent years to high-end shooting and delivery, and nowadays the hobby of maneuvering drones, both male and female, has come .
  • a fixed-wing type of dron which is a wing-like fixed type like an aircraft type that is pronounced of a general airplane, and a propeller that rotates like a helicopter is classified as a rotary wing type dron can do.
  • the rotor blade system can not achieve a high speed, but the runway is not necessary and the vertical and horizontal movement is free compared to the fixed blade system.
  • the rotor-type drones are capable of vertical takeoff and landing, but they are disadvantageous in that they depend on external variables such as slow moving speed and strong wind.
  • the dowels of the fixed-wing type and the dowels of the wing-wing type have advantages and disadvantages, respectively. If a fixed-wing type dowel capable of vertical landing and landing can be manufactured, a dowel having merits can be produced.
  • a tilting blade assembly for a drone, comprising: a mounting space formed on both sides of the tilting blade assembly so as to be at least symmetrical on both sides thereof, A main housing having a connecting portion formed therein; A body portion having a predetermined shape, a shaft portion connected to the body portion at one side to generate a rotational power at an angle set in accordance with a control signal, a power portion connected to the shaft portion to change a part of the rotational power to transmit the linear power, A control motor including a carrier and disposed in the installation space; And a wing portion for providing power through rotation and both sides thereof being pivotally connected to the pivotal connection portion. One end of the wing portion is connected to the operation of the power transmission member, and is tilted according to a rotational power of the angle of the shaft portion, And a tilting body including a tilting body for changing the direction of the tilting body.
  • the power transmission body of the control motor includes at least a vehicle body having a predetermined length and not a straight line shape, one end connected to the tilt body, one end connected to the shaft, and the other end connected to the power transmission bar .
  • the installation space is formed in a shape corresponding to that of the shape of the body portion of the control motor, the shape of the shaft portion, and the shape of the medium.
  • a guide wall is formed at a predetermined position in the body of the control motor, and a connection bracket is formed on the outer side of the body of the control motor, in which the guide protrusion is formed in a shape symmetrical to a position not in contact with the guide wall .
  • the installation space is formed with a space corresponding to the guide wall.
  • the main housing includes a connecting body connected to the drone, and a rotating connecting body disposed on one side of the connecting body.
  • the main housing has a shape corresponding to a space for installing the main housing between the connecting body and the rotating force connecting body And an intermediate bracket for a branch is installed.
  • the mediating bracket is provided with an installation space corresponding to the guide wall, and has a thickness not smaller than at least the thickness of the guiding wall of the connection bracket, so that when the guiding wall of the connection bracket is disposed, A fixing pin is disposed to fix the position of the connection bracket.
  • connection hole is formed at a corresponding position of the connecting body, the pivoting connection body, and the intermediate bracket at positions where the installation space is not formed.
  • the wing includes a blade and a power motor for applying power to the blade, wherein the power motor includes a protruding connection portion, and the tilde body is formed with a receiving hole for receiving the protruding connection portion, And the position is fixed.
  • an intermediate connector is formed between the power motor and the till body so as to form a receiving hole.
  • connection hole is formed at a position corresponding to the periphery of the protruding connection portion of the power motor, and the periphery of the reception hole of the tilt body and the intermediate connection member.
  • the tilt body supports the power motor and is formed with the receiving hole, one side is formed as a straight surface cut in a straight line shape, and the opposite side is protruded in a predetermined shape so that only the protruding portion rotates
  • a main body part connected to the connection part is provided with a connecting part protruding in the direction of the power transmitting part to receive the power of the power transmitting part and turn to tilt the main body part,
  • a pivot connection part is provided between the connecting part and the pivot connection part of the main housing such that only an area set to be the same as the opposite side of the main body part is connected to the pivot connection part.
  • a rounding guide portion formed in an inward direction to round the tilting body is formed, and a connecting portion connected to the opposite side of the main body portion and the tilting connector is formed at a predetermined distance from the rounding guide portion, So that the tilt is guided.
  • the present invention enables vertical landing and landing by making the tilting according to the wing part control motor that provides power through rotation to the fixed-wing type dron so that the existing fixed wing type dron does not need a runway when taking off, .
  • the dron including the tilting blade assembly for a drone of the present invention can apply lifting force even when flying, so that altitude is not calculated from the beginning.
  • FIG. 1 is a view showing a dron equipped with a tilting blade assembly for a drone according to the present invention.
  • FIG. 2A shows a state before the tilting blade assembly for a drone is operated
  • FIG. 2B shows a state after the tilting blade assembly for a drone is operated.
  • FIG 3 is an exploded view of a tilting blade assembly for a drone according to the present invention.
  • FIG. 4 is an enlarged view of a power transmission bar of a tilting blade assembly for a drone according to the present invention.
  • FIG. 5 is a view showing the size difference between the guide bracket of the bracket and the connection bracket of the tilting blade assembly for a drone according to the present invention.
  • FIG. 6 is an exploded view of a tilting body of a tilting blade assembly for a drone according to the present invention.
  • FIG. 7 illustrates a pivotal connection of a pivotal connection body of a tilting blade assembly for a drone according to the present invention.
  • FIG. 1 is a view showing a dron equipped with a tilting blade assembly for a drone according to the present invention.
  • FIG. 2A shows a state before the tilting blade assembly for a drone is operated
  • FIG. 2B shows a state after the tilting blade assembly for a drone is operated.
  • the front blade assembly 311 is tilted at an angle of 180 degrees with the ground and the rear tilting blade 311 assembly is tilted and operated to face the ground. This allows vertical takeoff and landing.
  • the tilting blade 311 assembly on the rear side is tilted in the horizontal direction with respect to the ground to apply power to enable the flight of the drones, and the assembly of the tilting blades 311 for drones installed on the front side And the tilting blade 311 assembly on the rear side of the front side can be tilted according to the user's control to maintain the dron's posture.
  • FIG 3 is an exploded view of a tilting blade assembly for a drone according to the present invention.
  • the tilting blade 311 assembly for drone includes a main housing, a control motor 200, and a tilting operation body 300.
  • the main housing 100 is connected to the drones.
  • the main housing 100 includes a connecting body 110 and a pivoting connection body 120.
  • the pivoting connection body 120 is connected to the front of the connecting body 110.
  • a mounting space 130 is formed in the connecting body 110.
  • the pivot connection body 120 is provided with an intermediate bracket 500 to be described later.
  • the pivot connection body 120 has a pivot connection portion 121 formed therein.
  • the tilting operation body 300 is installed in the pivot connection part 121.
  • the tilting operation body 300 can be tilted at a predetermined angle by the control motor 200 disposed in the installation space 130 of the main housing 100. This will be described later.
  • the mounting space 130 of the connecting body 110 is formed so that both sides thereof are at least symmetrical with respect to the center. This is because the shape is formed to correspond to the shape of the control motor 200 and the connection bracket 400. The space in which the control motor 200 and the connection bracket 400 are disposed in the connecting body 110 and the pivoting connection body 120 is very limited.
  • the body 210 of the control motor 200 is biased to one side, It is most preferable that the shaft portion 220 is formed in a direction opposite to the biasing direction.
  • the installation space 130 since the installation space 130 must also interfere with the operation of the power transmission body 230, it is natural that the installation space 130 is formed to correspond to the shape of the power transmission body 230.
  • the control motor 200 includes a body portion 210, a shaft portion 220, and a power transmission body 230.
  • the body 210 has a predetermined shape. Referring to FIG. 3, the body 210 may have a rectangular shape.
  • the shaft portion 220 is connected to one side of the body portion 210.
  • the shaft portion 220 is formed with a predetermined length.
  • the shaft portion 220 generates rotational power at a set angle in accordance with the control signal.
  • the rotational power means that the shaft portion 220 is not rotated continuously but is rotated in one direction at a set angle, and then rotated in the other direction.
  • the power transmission body 230 includes a medium 231 and a power transmission bar 232.
  • the mediator 231 has an oval shape as an example and is connected to the shaft portion 220 at one side. The other side of the medium 231 is connected to the power transmission bar 232.
  • the power transmission bar 232 is formed with a predetermined length. One side of the power transmission bar 232 is connected to the tilt body 330 and the other side is connected to the other side of the medium 231. Since the power transmitting bar 232 has a predetermined length, a part of the rotational power of the medium 231 rotated according to the rotational power of the shaft portion 220 is changed to a straight line. That is, the power transmission bar 232 is moved in the diagonal direction. The movement of the power transmission bar 232 in the diagonal direction pushes the tilting body 330 in the diagonal direction to tilt the tilting operation body 300.
  • FIG. 4 is an enlarged view of a power transmission bar of a tilting blade assembly for a drone according to the present invention.
  • the power transmission bar 232 is not at least in the form of a straight line. That is, the power transmission bar 232 is preferably formed with a predetermined angle. This is because the power transmission bar 232 may rotate slightly when the power transmission bar 232 is formed with a predetermined angle in comparison with the case where the power transmission bar 232 is straight when transmitting the rotational power of the medium 231 in the diagonal direction. Which can be efficiently operated in the main housing 100 having a very narrow space.
  • a connection bracket 400 is provided on the outside of the body 210 of the control motor 200.
  • a guide wall 211 is formed in the body 210 of the control motor 200 at a predetermined position.
  • the guide wall 211 is formed at a position offset from the center of the body 210 toward the shaft 220 side.
  • the guide wall 211 protrudes forward and rearward of the body 210 to prevent the connection bracket 400 from moving.
  • connection hole may be formed at a portion where the connection bracket 400 and the guide wall 211 abut each other.
  • a fixing device may be installed in the connection hole between the connection bracket 400 and the guide wall 211. So that the connection bracket 400 can be fixed to the guide wall 211.
  • the connection bracket 400 has a guide protrusion 410 formed therein.
  • the guide protrusion 410 is formed in a shape symmetrical to a position not in contact with the guide wall 211. That is, when the guide protrusion 410 is viewed through FIG. 3, the guide protrusion 410 is formed at a symmetrical position above and below the connection bracket 400.
  • the installation space 130 of the main housing 100 is formed to be symmetrical with the control protrusion 410 of the control motor 200 and the connection bracket 400. Therefore, the control motor 200 is connected to the connection bracket 400, and the guide protrusion 410 of the connection bracket 400 is fixed to the installation space 130 and can be stably fixed.
  • an intermediate bracket 500 may be installed between the connecting body 110, which is the main housing 100, and the pivoting connection body 120.
  • the intermediate bracket 500 is formed with a mounting space 130 similar to the connecting body 110.
  • the installation space 130 corresponding to the guide protrusion 410 of the connection bracket 400 of the installation space 130 of the intermediate bracket 500 is formed differently from the connection body 110 and the rotation connection body 120 .
  • FIG. 5 shows the size difference between the guide bracket 500 of the tilting blade assembly for a drone and the guide protrusion 410 of the connection bracket 400 according to the present invention.
  • the thickness of the portion of the connection bracket 400 corresponding to the guide protrusion 410 of the connection bracket 400 is not thinner than the thickness of the guide protrusion 410. [ Therefore, when the guide protrusion 410 is disposed in the installation space 130 of the intermediate bracket 500, a space corresponding to the difference between the thickness of the guide protrusion 410 and the size (thickness) of the installation space 130 is generated. A fixing pin 600 is disposed in the space.
  • the fixing pin 600 is disposed in a space corresponding to the difference between the thickness of the guide protrusion 410 and the size (thickness) of the installation space 130 to press the guide protrusion 410.
  • the guide protrusion 410 is stably fixed to the installation space 130 of the intermediate bracket 500 by the pressing force of the fixing pin 600.
  • a connection hole is formed at a portion where the fixing pin 600 and the guide protrusion 410 are in contact with each other, and these connection holes are in contact with each other. But the fixing device is not shown. So that the connection bracket 400 is stably fixed to the intermediate bracket 500.
  • the control motor 200 is disposed in the installation space 130 of the connecting body 110 and the intermediate bracket 500 and stably fixed so that the fixed position is not changed even when the drone is shaken severely.
  • the tilting operation body 300 includes a wing portion 310 and a tilting body 330.
  • the wing portion 310 includes a blade 311 and a power motor 312.
  • the blade 311 is connected to the power motor 312 and is rotated to apply power to the drones.
  • the power of the blade 311 can be changed to a lifting force, a moving force, or the like depending on the degree of tilting.
  • the power motor 312 is formed with a protruding connection portion 313 on the rear side with reference to Fig.
  • the protruding connection portion 313 of the power motor 312 is fitted into the receiving hole 370 of the tilt body 330.
  • the tilt body 330 seats the power motor 312.
  • the tilt body 330 is formed in a predetermined shape and a receiving hole 370 having a predetermined size is formed at the center. Accordingly, the tilt body 330 can fix and seat the power motor 312.
  • An intermediate connector 320 is provided between the power motor 312 and the tilt body 330.
  • the intermediate connector 320 is formed with a receiving hole 370.
  • the protruding connection portion 313 of the power motor 312 may be disposed in the receiving hole 370 of the tilt body 330 through the receiving hole 370 of the intermediate connecting member 320.
  • a connection hole is formed at a position corresponding to the periphery of the protruding connection portion 313 of the power motor 312, the intermediate connector 320 and the reception hole 370 of the tilt bar body. Therefore, the tilt body 330, the intermediate connector 320, and the power motor 312 can be stably fixed.
  • the tilt body 330 on which the power motor 312 is mounted is rotatably connected to the pivotal connection part 121 of the pivotal connection body 120 and can be tilted at a predetermined angle according to the operation of the power transmission bar 232. This makes vertical landing and landing possible even with fixed wing drones.
  • FIG. 6 is an exploded view of a tilting body of a tilting blade assembly for a drone according to the present invention.
  • the tilt body 330 includes a main body part 340, a connecting part 350, and a turning connecting part 360.
  • the main body portion 340 is a portion where the receiving hole 370 is installed and is the most central body.
  • One side of the main body part 340 is formed with a cut surface 341 cut in a straight line shape.
  • a protruding pivot projection 342 is formed on the opposite side of the main body portion 340.
  • the tilting body 330 is connected to the pivoting connection body 120 and the pivoting protrusion 342 at one side thereof. Meanwhile, the size of the main body part 340 is not larger than the size of the pivot connection part 121 formed in a symmetrical shape apart from the pivot connection body 120.
  • the connecting part 350 is in contact with the straight surface, and the tilt connecting part protruding rearward with reference to FIG. 3 is formed on the lower side.
  • the tilt connection portion is in contact with one side of the power transmission bar 232 described above.
  • the main body portion 340 is tilted through the tilted connection portion. This tilts the power motor 312 and the blade 311, which are seated in the main body portion 340, .
  • the connecting part 350 may be provided with a rotating connecting part 360.
  • the tilting body 330 In order for the tilting body 330 to stably rotate, only the predetermined area must be connected to the pivoting connection body 120. The opposite surface of the main body of the tilting body 330 is brought into contact with the pivoting projection 342, but when the connecting part 350 is abutted, a large area will not be easily pushed to abut.
  • the pivoting connection part 360 is connected to the connection part 350.
  • the pivotal connection component 360 has a set area, which may be similar to the area of the pivot projection 342. [ Accordingly, when tilted according to the operation of the power transmission bar 232, the tilting can be stably performed in contact with the pivoting connection body 120 and pivoting.
  • FIG. 7 illustrates a pivotal connection of a pivotal connection body of a tilting blade assembly for a drone according to the present invention.
  • the rotation connecting portion 121 of the pivoting connection body 120 is formed with a rounding guide portion 122.
  • the rounding guide portion 122 is formed to round inward. Therefore, the rounding guide part 122 does not interfere with the rotation when the pivot projection part 342 formed in a square shape and the pivoting connection part 360 are rotated at a predetermined angle, and is not separated by an impact or the like.
  • connection portion is formed at a position spaced apart from the rounding guide portion 122 of the pivotal connection portion 121.
  • the connecting portion may be formed in each of the pivot projection 342, the connecting part 350, and the pivoting connecting part 360, respectively.
  • the connection unit is provided with a connecting device so that the tilt body 330 is rotatable.
  • the angle of the dron can be adjusted freely by using a motor, a gear, and a link, a vertical landing and landing is possible, so that a runway is not required when the dron is taken off.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Toys (AREA)

Abstract

La présente invention concerne un ensemble de pales inclinables d'un drone qui est capable d'assurer un décollage et un atterrissage verticaux et n'a donc pas besoin d'une piste, l'ensemble de pales inclinables comprenant : un boîtier principal muni d'un espace d'installation formé à l'intérieur de celui-ci et de parties de liaison rotative sur les côtés respectifs ; un moteur de commande, qui est monté à l'intérieur du boîtier principal, pour incliner une pale ; un émetteur de puissance, qui est connecté à un arbre du moteur de commande, pour transmettre la puissance de rotation du moteur de commande en changeant celle-ci en une puissance linéaire ; et un corps d'inclinaison qui est relié au fonctionnement de l'émetteur de puissance et est incliné en fonction de la puissance de rotation d'un angle défini de la partie d'arbre de façon à changer la direction de propulsion d'une partie d'aile.
PCT/KR2018/015309 2017-12-29 2018-12-05 Ensemble de pales inclinables pour drone WO2019132285A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KR10-2017-0183839 2017-12-29
KR1020170183839A KR102038321B1 (ko) 2017-12-29 2017-12-29 드론용 틸팅 블레이드 어셈블리

Publications (1)

Publication Number Publication Date
WO2019132285A1 true WO2019132285A1 (fr) 2019-07-04

Family

ID=67067820

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/KR2018/015309 WO2019132285A1 (fr) 2017-12-29 2018-12-05 Ensemble de pales inclinables pour drone

Country Status (2)

Country Link
KR (1) KR102038321B1 (fr)
WO (1) WO2019132285A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112340010A (zh) * 2020-09-11 2021-02-09 广州极飞科技有限公司 无人机
KR102673773B1 (ko) 2023-11-09 2024-06-11 주식회사 네스앤텍 드론암에 장착되는 틸트 장치

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20220028849A (ko) 2020-08-31 2022-03-08 양범승 하이브리드 틸트 드론
KR102450884B1 (ko) 2020-11-27 2022-10-05 한종수 천이비행을 위한 무인항공기 및 드론 암의 틸팅 시스템

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6260793B1 (en) * 1999-03-30 2001-07-17 Eurocopter Convertible aircraft with tilting rotors
KR100555176B1 (ko) * 2004-12-31 2006-03-03 한국항공우주연구원 틸트 로터 항공기
KR20130077242A (ko) * 2011-12-29 2013-07-09 김성남 무인항공기의 틸팅 시스템
US20160229531A1 (en) * 2014-12-11 2016-08-11 Bell Helicopter Textron Inc. Convertible tiltrotor aircraft
KR101772224B1 (ko) * 2016-12-30 2017-08-28 주식회사 샘코 틸팅형 로터
KR20170135577A (ko) * 2016-05-31 2017-12-08 김성남 틸팅 및 가변 피치 시스템이 적용된 무인 비행체

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6260793B1 (en) * 1999-03-30 2001-07-17 Eurocopter Convertible aircraft with tilting rotors
KR100555176B1 (ko) * 2004-12-31 2006-03-03 한국항공우주연구원 틸트 로터 항공기
KR20130077242A (ko) * 2011-12-29 2013-07-09 김성남 무인항공기의 틸팅 시스템
US20160229531A1 (en) * 2014-12-11 2016-08-11 Bell Helicopter Textron Inc. Convertible tiltrotor aircraft
KR20170135577A (ko) * 2016-05-31 2017-12-08 김성남 틸팅 및 가변 피치 시스템이 적용된 무인 비행체
KR101772224B1 (ko) * 2016-12-30 2017-08-28 주식회사 샘코 틸팅형 로터

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112340010A (zh) * 2020-09-11 2021-02-09 广州极飞科技有限公司 无人机
KR102673773B1 (ko) 2023-11-09 2024-06-11 주식회사 네스앤텍 드론암에 장착되는 틸트 장치

Also Published As

Publication number Publication date
KR102038321B1 (ko) 2019-10-30
KR20190081361A (ko) 2019-07-09

Similar Documents

Publication Publication Date Title
WO2019132285A1 (fr) Ensemble de pales inclinables pour drone
EP3621877B1 (fr) Aéronef modulaire à capacité de décollage et d'atterrissage verticaux
CN205554584U (zh) 无人飞行器及其机架
WO2018110987A1 (fr) Véhicule aérien à soufflante dans aile et son procédé de commande de posture
CN112334384B (zh) 推进单元和包括其的飞行器
KR101564380B1 (ko) 무인비행체
US9387939B2 (en) VTOL—twin—propeller—attitude—control—air—vehicle
US20100108801A1 (en) Dual rotor helicopter with tilted rotational axes
WO2021078267A1 (fr) Véhicule aérien sans pilote
WO2010005203A2 (fr) Véhicule volant de type pale de fond rotationnelle
WO2018058328A1 (fr) Couvercle de protection d'hélice et véhicule aérien sans pilote utilisant un couvercle de protection d'hélice
WO2017039233A1 (fr) Drone pouvant faire varier la forme d'un agencement d'hélice
US20180334252A1 (en) Lightweight flying vehicle
WO2020062758A1 (fr) Véhicule aérien sans pilote et mécanisme d'inclinaison
KR102221381B1 (ko) 멀티 어댑터를 구비하는 드론
CN110844069A (zh) 一种微小型可折叠轮状飞行器
WO2020130333A1 (fr) Drone hybride du type à décollage et atterrissage verticaux
WO2018018503A1 (fr) Ensemble châssis et véhicule aérien sans pilote utilisant celui-ci
KR20190088208A (ko) 무인 비행체용 붐 결합 장치 및 이를 이용하는 무인 비행체
WO2022206852A1 (fr) Aile inclinable et véhicule aérien sans pilote
WO2022004965A1 (fr) Drone à mode de vol à degrés de liberté multiples
KR102375492B1 (ko) 모듈형 테일시터 수직이착륙 드론
CN106927043B (zh) 一种飞行器
WO2018038323A1 (fr) Aéronef à voilure tournante à engrènement à plateau oscillant symétrique
EP3699082A1 (fr) Commande de vol cyclique montée de façon compacte pour giravion

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 18896019

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 18896019

Country of ref document: EP

Kind code of ref document: A1