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WO2016068383A1 - Objet volant sans pilote - Google Patents

Objet volant sans pilote Download PDF

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Publication number
WO2016068383A1
WO2016068383A1 PCT/KR2014/011517 KR2014011517W WO2016068383A1 WO 2016068383 A1 WO2016068383 A1 WO 2016068383A1 KR 2014011517 W KR2014011517 W KR 2014011517W WO 2016068383 A1 WO2016068383 A1 WO 2016068383A1
Authority
WO
WIPO (PCT)
Prior art keywords
unmanned aerial
aerial vehicle
rotating plate
base
propulsion
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/KR2014/011517
Other languages
English (en)
Korean (ko)
Inventor
유규형
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hanwha Vision Co Ltd
Original Assignee
Hanwha Techwin Co Ltd
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 Hanwha Techwin Co Ltd filed Critical Hanwha Techwin Co Ltd
Publication of WO2016068383A1 publication Critical patent/WO2016068383A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/26—Ducted or shrouded rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
    • B64U30/293—Foldable or collapsible rotors or rotor supports
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography

Definitions

  • the present invention relates to an unmanned aerial vehicle.
  • Unmanned Aerial Vehicles are aircraft that can perform their assigned missions without boarding a pilot.
  • the drone may fly based on remotely controlled or preset programs or automation systems.
  • the drone generates both horizontal and vertical thrust and can be equipped with a vertical takeoff and landing (VTOL) function.
  • the propeller or rotor can generate thrust in the vertical direction to lift the aircraft and generate thrust in the horizontal direction to provide forward movement.
  • the vertical take-off and landing feature allows the drone to not perform the flight, making it easier to perform tasks.
  • Drones can be used for military or reconnaissance purposes to scout enemies or explore terrain to gather information.
  • drones can carry out ground operations in difficult-to-penetration terrain in parallel with mobile robots.
  • Drones can be used for industrial purposes to survey land or spray pesticides.
  • the drone can be quickly put into an emergency based on the location tracking function to rescue the distress and fallout in the emergency.
  • Embodiments of the present invention to provide an unmanned aerial vehicle that can fold the thrust generating thrust.
  • One aspect of the present invention includes a base portion, a propeller having a first actuator and a propeller rotating by power of the first actuator, and being provided to be rotatable outside the base portion, and one surface of the base portion. It is possible to provide an unmanned aerial vehicle including a rotating plate installed to be rotatable in and a connecting arm connecting the rotating plate and the driving unit.
  • Embodiments of the present invention can be minimized in size when storing the unmanned vehicle by folding the propulsion generating thrust.
  • the propeller may be disposed into the inner space of the unmanned aerial vehicle, thereby facilitating durability and storage of the unmanned aerial vehicle.
  • the scope of the present invention is not limited by these effects.
  • FIG. 1 is a perspective view showing an unmanned aerial vehicle according to an embodiment of the present invention.
  • FIG. 2A is a rear perspective view of the unmanned aerial vehicle of FIG. 1.
  • FIG. 2A is a rear perspective view of the unmanned aerial vehicle of FIG. 1.
  • Figure 2b is a rear perspective view showing another state of the unmanned aerial vehicle shown in FIG.
  • FIG. 3 is an exploded perspective view showing the connecting arm shown in FIG.
  • FIG. 4A is a bottom view of a portion of the unmanned aerial vehicle of FIG. 1.
  • FIG. 4B is an enlarged partial view of region A of FIG. 4A.
  • FIG. 5A is a bottom view illustrating another state of the unmanned aerial vehicle by extracting a portion of the unmanned aerial vehicle illustrated in FIG. 1.
  • FIG. 5B is an enlarged partial view of region B of FIG. 5A.
  • FIG. 6 is a bottom view of a portion of the unmanned aerial vehicle of FIG. 2B.
  • FIG. 6 is a bottom view of a portion of the unmanned aerial vehicle of FIG. 2B.
  • One aspect of the present invention includes a base portion, a propeller having a first actuator and a propeller rotating by power of the first actuator, and being provided to be rotatable outside the base portion, and one surface of the base portion. It provides an unmanned aerial vehicle including a rotating plate installed to be rotatable in and a connecting arm connecting the rotating plate and the propulsion unit.
  • the connecting arm can rotate the driving unit.
  • the rotating plate may be disposed in the center of the base portion.
  • connection arm may have a bent portion bent to protrude in the longitudinal direction.
  • a first hole is formed at one end of the connection arm, and the first pin is inserted into the first hole to be connected to the rotating plate, and a second hole is provided at the other end of the connection arm to the second hole.
  • the second pin is inserted and connected to the driving unit, and the central axis of the first hole and the central axis of the second hole may be displaced.
  • the driving unit when the first hole is away from the driving unit, the driving unit may be folded to the base unit.
  • the propulsion unit may rotate in a state in which the propulsion unit is folded in the base unit in a state in which it is deployed to form the same plane as the base unit.
  • the propulsion unit rotates in a folded state in the unfolded state of the base portion, and when the rotating plate rotates in a direction opposite to the first direction, the pushing portion is folded in the base portion. You can rotate from the state to the unfolded state.
  • the apparatus may further include a supporter portion extending from the base portion to support the base portion.
  • At least a part of the pushing part may be inserted into the supporter part.
  • a base portion a plurality of propulsion portions provided on each side of the base portion, rotatably installed on the base portion, a rotating plate rotatably installed on one surface of the base portion, and the rotating plate
  • a plurality of connection arms installed to connect the plurality of propulsion units, respectively, and when the rotating plate rotates, the plurality of connection arms rotate to provide an unmanned aerial vehicle for rotating the plurality of propulsion units simultaneously.
  • the rotating plate may be disposed in the center of the base portion.
  • the propulsion part may rotate in a state where the propulsion part is folded in the base part in a state in which the plurality of propulsion parts are deployed to form the same plane as the base part.
  • connection arms may have a bent portion formed to be bent in a longitudinal direction.
  • any one of the connection arm of the plurality of connection arms may be arranged to intersect at the lower portion of the bent portion with other adjacent connection arm.
  • the base portion and the plurality of propulsion portions may be disposed on each surface to form an internal space of a three-dimensional shape.
  • the x-axis, y-axis and z-axis are not limited to three axes on the Cartesian coordinate system, but may be interpreted in a broad sense including the same.
  • the x-axis, y-axis, and z-axis may be orthogonal to each other, but may refer to different directions that are not orthogonal to each other.
  • FIG. 1 is a perspective view showing an unmanned aerial vehicle 100 according to an embodiment of the present invention
  • FIG. 2A is a rear perspective view illustrating the unmanned aerial vehicle 100 of FIG. 1
  • FIG. 2B is an unmanned aerial vehicle 100 shown in FIG. 1. Is a rear perspective view showing another state of
  • the unmanned aerial vehicle 100 may include a base portion 10, a propulsion portion 20, a supporter portion 30, a rotation plate 40, and a connection arm 50. Can be.
  • the base unit 10 may be disposed at the center of the unmanned aerial vehicle 100 to form a center of balance of the unmanned aerial vehicle 100.
  • the base unit 10 provides a space for installing a communication component, a control component or an image photographing component mounted on the unmanned aerial vehicle 100.
  • the base unit 10 may support the propulsion unit 20 for generating thrust in the unmanned aerial vehicle 100.
  • the propelling part 20 may be installed outside the base part 10.
  • the propulsion unit 20 may be disposed to radially unfold at the center of the base unit 10 to increase the amount of air passing through the propulsion unit 20 when the propulsion unit 20 generates thrust.
  • the shape of the base part 10 is not limited to a particular shape, and the base part 10 may be formed in a polygonal or cylindrical shape. However, hereinafter, the description will be made with respect to the case formed in a substantially rectangular pillar shape for convenience of description.
  • the propelling part 20 may be installed to be rotatable along the side of the base part 10.
  • the base part 10 has four side surfaces, and along each side surface of the base part 10, the first propulsion part 20a, the second propulsion part 20b, the third propulsion part 20c and the fourth propulsion part are provided.
  • the part 20d may be installed.
  • a control unit (not shown) may be installed in the internal space of the base unit 10.
  • the controller may include sensors for flight manipulation of the unmanned aerial vehicle 100 or various sensors for aviation observation, and control each sensor.
  • the controller may include a gyro sensor, an acceleration sensor, a position sensor, or a pressure sensor.
  • the gyro sensor may measure the rotation speed of the unmanned aerial vehicle 100 that rotates by measuring the angular acceleration of the unmanned aerial vehicle 100.
  • the acceleration sensor may measure a moving speed of the unmanned aerial vehicle 100 by measuring the acceleration of the unmanned aerial vehicle 100.
  • the position sensor may measure the position of the unmanned aerial vehicle 100 by measuring the position coordinates of the unmanned aerial vehicle 100.
  • the pressure sensor may measure the altitude of the unmanned aerial vehicle 100 by measuring the atmospheric pressure of the outside of the unmanned aerial vehicle 100.
  • the controller may control a position, speed, or altitude of the unmanned aerial vehicle 100 by receiving a signal input through a communication module (not shown).
  • the communication module may receive a signal related to global positioning system (GPS) information from an external controller (not shown) and transmit a signal related to position information to the controller. Then, the controller may control the position, speed or altitude of the unmanned aerial vehicle 100 by adjusting the rotational speed of the first actuator 22.
  • GPS global positioning system
  • the controller may generate information about the position, speed, or altitude measured by the unmanned aerial vehicle 100 as a signal and transmit the signal to a communication module (not shown).
  • the communication module may transmit the received signal to the controller.
  • the unmanned aerial vehicle 100 may be installed with a camera module (not shown) to collect image or video information by taking an aerial photo or video.
  • the camera module may be installed on one surface of the base unit 10, and the image or video taken by the camera module may be stored or transmitted to the controller through the communication module.
  • the unmanned aerial vehicle 100 may be installed with a speaker module (not shown) or a microphone module (not shown) to emit voice information or to collect voice information.
  • the propulsion unit 20 may be installed to be rotatable with the base unit 10.
  • the propulsion unit 20 may be provided in plural radially from the center of the base 10.
  • the propulsion unit may generate thrust driving the unmanned aerial vehicle 100, and may include a duct 21, a first actuator 22, a propeller 23, and a rib 25.
  • At least one propulsion unit may be provided in plurality, and may be disposed at a side surface of the base unit 10.
  • the unmanned aerial vehicle 100 is, for convenience of explanation, hereinafter, the first propulsion part 20a, the second propulsion part 20b, the third propulsion part 20c, and the fourth propulsion on each side of the base part 10.
  • the case where the part 20d is installed will be described below. Only the positions of the first to fourth propulsion units arranged in the base portion 10 have the same configuration and will be described below with reference to the first propulsion portion 20a.
  • the duct 21 may be installed to be rotatable on the side of the base portion 10.
  • the duct 21 may include an o-ring 21a installed outside the rotating propeller 23 and a frame 21b in contact with the base portion 10.
  • the o-ring 21a may be connected to the frame 21b to surround the outside of the propeller 23.
  • the o-ring 21a may be formed in an annular shape to guide the flow of air passing through the propeller 23.
  • the o-ring 21a may guide the flow of air in the direction of the rotation axis of the propeller 23.
  • the frame 21b may be connected to the base 10 to rotate.
  • the base portion 10 and the frame 21b form a hinge coupling so that the duct 21 can rotate at a predetermined angle.
  • the O-ring 21a is connected to extend to the frame 21b and may rotate in the base portion 10 by the rotation of the frame 21b.
  • the first actuator 22 may generate propulsion by rotating the propeller 23.
  • the first actuator 22 may be supported by a plurality of ribs 25 crossing the O-ring 21a.
  • the first actuator 22 may be independently controlled by the controller. According to the signal of the controller, the first actuator 22 may adjust the thrust by adjusting the rotational speed (rpm). The first actuator 22 may receive power from a battery (not shown) installed in the base unit 10, and transmit power to the propeller 23.
  • the rib portion 25 is installed to cross the O-ring 21a, and the first actuator 22 may be installed at the center of the O-ring 21a.
  • the rib portion 25 may include a second through hole for coupling with the connection arm 50.
  • the first connection arm 50 may be connected to the rib portion 25 by the second pin 62.
  • the second pin 62 may be inserted into the second hole 51 ′ e formed in the first connection arm 50 and the second through hole.
  • the supporter part 30 may protrude from the base part 10 and support the base part 10.
  • the supporter part 30 is formed to extend from one surface of the base part 10. When the unmanned aerial vehicle 100 is installed, the supporter unit 30 may contact the ground to support the base unit 10.
  • the supporter part 30 may be provided in plurality.
  • the supporter unit 30 may maintain the balance of the unmanned aerial vehicle 100 by dispersing the weight of the base unit 10.
  • the supporter part 30 may be formed to correspond to each side of the base part 10.
  • the supporter part 30 may be formed radially.
  • the case will be described based on the case in which two supporter units 30 are formed on both side surfaces of the base unit 10 so as to face each other for convenience of description.
  • the supporter part 30 may include a pair of first supporters 31 connected to the base part 10 and a second supporter 32 connecting the first supporters 31 to each other.
  • the first supporter 31 may maintain a gap between the base part 10 and the ground.
  • the second supporter 32 may connect between the first supporters 31 to improve strength and balance of the supporter part 30.
  • the second supporter 32 may be formed thicker than the first supporter 31.
  • the second supporter 32 may be formed to protrude inward to improve the area of the part in contact with the ground. If the contact area of the unmanned aerial vehicle 100 and the ground is increased, the stability of the unmanned aerial vehicle may be increased.
  • the angle formed by the supporter 30 and the base 10 is not limited to a specific angle.
  • the base part 10 and the first supporter 31 may be formed to be substantially perpendicular, or an angle between the base part 10 and the first supporter 31 may form an obtuse angle.
  • the base unit 10 and the first supporter 31 are formed to be substantially perpendicular to each other, and thus the driving unit 20 will be described with reference to the case where the unmanned aerial vehicle 100 forms a substantially hexahedron. .
  • Rotating plate 40 may be installed to be rotatable on one surface of the base portion (10).
  • the rotating plate 40 may be disposed at the center of the base portion 10.
  • Rotating plate 40 may be connected to the driving unit 20 by a connecting arm (50).
  • Rotating plate 40 is installed on the lower surface of the base portion 10 can rotate the driving unit 20 by the rotation of the rotating plate (40).
  • the second actuator 41 may be installed in the base portion 10 to transmit a driving force to the rotating plate 40.
  • the second actuator 41 may include an encoder and a reducer to adjust the rotational force or the rotational speed of the second actuator 41.
  • the outer side of the rotating plate 40 may be provided with a first through hole connecting to the plurality of connection arms (50).
  • a plurality of first through holes may be formed to correspond to the number of connection arms installed in the rotating plate 40. Due to the rotation of the rotation plate 40, the plurality of connection arms may move in the rotation direction of the rotation plate 40 at the same time.
  • an outer side of the rotating plate 40 may include a first through hole into which the first pin 61 is inserted.
  • a first pin 61 is inserted into the first hole 51 ′ d of the first connecting arm 50 and the first through hole, and thus the first connecting arm 50 is inserted into the rotating plate 40.
  • the first through hole may be disposed outside from the center of the rotating plate 40 to increase the magnitude of the torque formed by the rotating plate 40.
  • the connecting arm 50 may connect the rotating plate 40 and the pushing unit 20. When the rotating plate 40 rotates, the connection arm is interlocked to rotate the propulsion unit 20.
  • the connecting arm 50 may be provided in plural numbers so as to correspond to each propulsion unit 20.
  • the connecting arm 50 may include a first connecting arm 50 connected to the first pushing unit 20a, a second connecting arm 50 connected to the second pushing unit 20b, and a third pushing unit 20c. It may be provided with a third connecting arm 50 to be connected and a fourth connecting arm 50 connected to the fourth propulsion unit 20d.
  • the first connecting arm 50 and the third connecting arm 50 facing the same will be described with reference to the first connecting arm 50, which is substantially the same only in the arrangement position.
  • the second connection arm 50 and the fourth connection arm 50 facing the same will be described with reference to the second connection arm 50, which is substantially the same only in the arrangement position.
  • FIG. 3 is an exploded perspective view showing the first connection arm 50 shown in FIG.
  • the first connection arm 50 may have a bent portion 51c that is bent to protrude in the longitudinal direction.
  • the first connecting arm 50 has a first end 51a connected with the propulsion unit 20, a second end 51b connected with the rotating plate 40, and a first end 51a and a second end 51b. May be provided with a bent portion 51c.
  • the first connecting arm 50 may be connected to the rotating plate 40 by the first joint 51d.
  • the first joint 51d is inserted into the first end 51a and may have a first hole 51'd.
  • the first pin 61 may be inserted into the first hole 51'd and the first through hole to connect the rotating plate 40 and the first connection arm 50.
  • the first connection arm 50 may be connected to the propulsion unit 20 by the second joint 51e.
  • the second joint 51e is inserted into the second end 51b and may have a second hole 51'e.
  • the second pin 62 may be inserted into the second hole 51 ′ e and the second through hole to connect the propulsion unit 20 and the first connection arm 50.
  • the central axis of the first hole 51'd and the central axis of the second hole 51'e may be displaced. Since the rotational direction of the propulsion unit 20 and the plane formed by the rotation of the rotation plate 40 do not coincide, the center axis of the first hole 51'd and the center axis of the second hole 51'e may be displaced. Can be.
  • the central axis of the first hole 51'd and the central axis of the second hole 51'e may be formed to be orthogonal to each other.
  • the first fin 61 and the second fin 62 may be formed in the form of a ball joint. Since the rotational direction of the propulsion unit 20 and the plane formed by the rotation of the rotating plate 40 do not coincide, the first connection arm 50 requires a plurality of degrees of freedom.
  • the first fin 61 and the second fin 62 may be formed in the form of a ball joint to increase the degree of freedom of the first connection arm 50.
  • the second connection arm 50 and the fourth connection arm 50 may be formed in a cylindrical shape.
  • the second connection arm 50 and the fourth connection arm 50 may be formed in a bar shape to connect the propulsion unit 20 and the rotation plate 40.
  • FIG. 4A is a bottom view of a portion of the unmanned aerial vehicle 100 of FIG. 1, and FIG. 4B is an enlarged view of a portion A of FIG. 4A.
  • the driving unit 20 may form an unfolded state to form the same plane as the base unit 10.
  • the propulsion unit 20 when the propulsion unit 20 is placed in an unfolded state, the unmanned aerial vehicle 100 is defined as being placed in a first position.
  • the first joint 51d and the first pin 61 are arranged at the position of P1.
  • P1 is disposed adjacent to the propulsion unit 20 to which the first connection arm 50 is connected.
  • the axis i perpendicular to the base part 10 is disposed to be orthogonal to the axis j included in the surface formed by the driving part 20. 90 degrees
  • the plurality of driving units 20 may form the same plane as the base unit 10 so that air passing through each propeller 23 flows in one direction. That is, the propulsion unit 20 may be disposed to allow air to flow in a direction perpendicular to the base unit 10 to improve the maneuvering force of the unmanned aerial vehicle 100.
  • FIG. 5A is a bottom view illustrating another state of the unmanned aerial vehicle 100 by extracting a part of the unmanned aerial vehicle 100 shown in FIG. 1, and FIG. 5B is an enlarged partial view of an enlarged area B of FIG. 5A. .
  • the driving unit 20 may form a state in which the base unit 10 is folded at a predetermined angle.
  • the driving unit 20 and the base unit 10 are placed in a folded state to form an acute angle, the unmanned aerial vehicle 100 is defined as being placed in the second position.
  • the first connection arm 50 may rotate by the rotation of the rotation plate 40.
  • the first joint 51d and the first pin 61 are arranged at the P2 position. That is, the rotation plate 40 is rotated counterclockwise by a predetermined rotation angle ⁇ 3 so that the first joint 51d and the first pin 61 move from the P1 position to the P2 position.
  • the axis i perpendicular to the base part 10 may form an acute angle with the axis j included in the surface formed by the driving unit 20. (0 degree ⁇ 2 ⁇ 90 degree)
  • FIG. 6 is a bottom view of a portion of the unmanned aerial vehicle 100 of FIG. 2B.
  • the pushing unit 20 may form a state in which the base unit 10 is folded substantially vertically. At least a part of the pushing unit 20 may be disposed to be inserted into the supporter unit 30.
  • the unmanned aerial vehicle 100 is defined as being in a third position.
  • the first joint 51d and the first pin 61 are disposed in the P3 position. That is, the rotation plate 40 rotates counterclockwise so that the first joint 51d and the first pin 61 move from the P2 position to P3.
  • an axis perpendicular to the base part 10 may be included in a surface formed by the driving unit 20. That is, the pushing unit 20 may be folded to be perpendicular to the base unit 10.
  • the second connecting arm 50 and the fourth connecting arm 50 which are adjacent to the first connecting arm 50 and the first connecting arm 50 may be disposed to intersect.
  • the second connecting arm 50 is disposed below the bent portion 51c of the first connecting arm 50
  • the fourth connecting arm 50 is disposed above the first end 51a of the first connecting arm 50. This can be arranged.
  • the first connecting arm 50 When the first connecting arm 50 moves from the first position to the second position, the first connecting arm 50 may interfere with another neighboring connecting arm. By forming a space in which the second connection arm 50 of the bent portion 51c may move, interference that may occur between the first connection arm 50 and the second connection arm 50 may be eliminated.
  • the third connection arm 50 may also eliminate interference that may be caused by the fourth connection arm 50 in the same manner as the first connection arm 50.
  • the plurality of driving units 20 may be folded to be inserted into the supporter unit 30 and disposed at a third position.
  • the plurality of driving units 20 may be disposed to be orthogonal to the base unit 10.
  • the unmanned aerial vehicle 100 may form a cubic or approximately hexahedral shape.
  • it is formed by the number of the pushing unit 20, it may be formed in the shape of a triangular prism, pentagonal pillar, hexagonal, octagonal cylinder or cylinder according to the number of the pushing unit 20.
  • the base unit 10 and the propelling unit 20 may form an internal space of the unmanned aerial vehicle 100.
  • the first actuator 22 and the propeller 23 may be located in the inner space.
  • the front end of the propeller 23 may be disposed so as not to protrude from the propulsion unit 20. Since the propeller 23 is made to be stubborn ( ⁇ ⁇ ) protruding to the outside may cause a safety problem during storage and transport.
  • the propeller 23 is disposed in the second position, the propeller 23 does not protrude to the outside.
  • the unmanned aerial vehicle 100 may increase safety of storage because the propeller 23 does not protrude to the outside. In addition, it is possible to increase the space utilization by minimizing the size of the unmanned aerial vehicle 100, it is possible to reduce the damage of the propeller (23).
  • the second supporter 32 may be formed to protrude while facing each other inside the unmanned aerial vehicle 100.
  • the protruding portion of the second supporter 32 may be disposed in the internal space to minimize the size of the unmanned aerial vehicle 100.
  • the unmanned aerial vehicle 100 can be easily stored, thereby increasing the space utilization of the unmanned aerial vehicle 100.
  • the unmanned aerial vehicle 100 may fly under the propulsion force of the propulsion unit 20.
  • it is possible to change the direction or change the altitude by adjusting the rotational speed of the propeller 23 of each propulsion unit (20).
  • the propeller 23 may be maintained at the same speed to stop the flight.
  • the unmanned aerial vehicle 100 When the propulsion unit 20 is disposed in the third position, the unmanned aerial vehicle 100 may be easily stored. The volume of the unmanned aerial vehicle 100 may be minimized to improve space utilization.
  • the unmanned aerial vehicle 100 may simultaneously rotate the propulsion unit 20 by a simple operation by forming the plurality of propulsion units 20 to be rotatable at the same time by the rotation of the rotation plate 40.
  • an unmanned aerial vehicle having improved space utilization
  • the embodiments of the present invention may be applied to all military, emergency, industrial transport apparatuses or toys having an unmanned aerial vehicle for industrial use.

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  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Toys (AREA)

Abstract

La présente invention concerne un objet volant sans pilote. La présente invention comprend une unité de base, un premier actionneur, et une hélice qui tourne au moyen de la puissance du premier actionneur, et la présente invention comprend : une unité de propulsion qui est installée de façon rotative sur l'extérieur de l'unité de base ; une plaque de rotation qui est installée de façon rotative sur une surface de l'unité de base ; et un bras de liaison qui relie la plaque de rotation et l'unité de propulsion.
PCT/KR2014/011517 2014-10-31 2014-11-28 Objet volant sans pilote Ceased WO2016068383A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KR1020140150641A KR20160051163A (ko) 2014-10-31 2014-10-31 무인 비행체
KR10-2014-0150641 2014-10-31

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WO2016068383A1 true WO2016068383A1 (fr) 2016-05-06

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PCT/KR2014/011517 Ceased WO2016068383A1 (fr) 2014-10-31 2014-11-28 Objet volant sans pilote

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KR (1) KR20160051163A (fr)
WO (1) WO2016068383A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107539457A (zh) * 2016-06-28 2018-01-05 比亚迪股份有限公司 无人机
WO2018119620A1 (fr) * 2016-12-27 2018-07-05 深圳市大疆创新科技有限公司 Véhicule aérien multirotor sans pilote

Families Citing this family (3)

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Publication number Priority date Publication date Assignee Title
KR102658525B1 (ko) * 2016-10-06 2024-04-18 삼성전자주식회사 무인 비행체 및 그의 동작 방법
CN108609165A (zh) * 2016-12-09 2018-10-02 北京京东尚科信息技术有限公司 无人机
KR200497696Y1 (ko) * 2021-10-29 2024-01-30 굿세라 주식회사 덕트형 프로펠러

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