WO2017086639A1 - Aéronef - Google Patents

Aéronef Download PDF

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Publication number
WO2017086639A1
WO2017086639A1 PCT/KR2016/012711 KR2016012711W WO2017086639A1 WO 2017086639 A1 WO2017086639 A1 WO 2017086639A1 KR 2016012711 W KR2016012711 W KR 2016012711W WO 2017086639 A1 WO2017086639 A1 WO 2017086639A1
Authority
WO
WIPO (PCT)
Prior art keywords
fuselage
unit
energy storage
battery
solar cell
Prior art date
Application number
PCT/KR2016/012711
Other languages
English (en)
Korean (ko)
Inventor
이융교
Original Assignee
한국항공우주연구원
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 한국항공우주연구원 filed Critical 한국항공우주연구원
Priority to CN201680059360.6A priority Critical patent/CN108137159B/zh
Publication of WO2017086639A1 publication Critical patent/WO2017086639A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • 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
    • B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/32—Wings specially adapted for mounting power plant
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D41/00—Power installations for auxiliary purposes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/50—On board measures aiming to increase energy efficiency
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a vehicle, and more particularly to a vehicle driven by a plurality of unit solar cells attached to the upper surface of the main wing.
  • a device such as a solar panel capable of converting sunlight into electrical energy is required, and it is preferable to be mounted on a wing that can easily secure sunlight.
  • the solar panel is made of a material such as brittle wafer or glass, there is a problem that it can be easily destroyed with only a small bending.
  • the wing is subjected to a load such as bending by aerodynamic or gravity when operating the aircraft thereby has a problem that it is difficult to use because the bending load can be applied to the solar panel.
  • Korean Patent Publication No. 10-1275883 discloses a flexible solar panel wing structure.
  • a plurality of unit solar cells are provided on a main wing to improve solar cell efficiency, and may be a vehicle capable of long-term flight by electric energy generated from a solar cell during the day and electric energy stored in an energy storage unit at night. To provide.
  • An object according to an embodiment is provided with a mylar skin on the upper surface of the main wing, the unit solar cell is attached by a Kapton tape, to provide a vehicle that is easy to attach the unit solar cell on the upper surface of the main wing, the weight can be reduced. It is.
  • An object according to an embodiment is to provide a vehicle that can reduce the drag caused by the vortex by the shape of the main wing, control the wheels to minimize drag and realize light weight.
  • An object according to an embodiment is to apply a Kapton tape to the fuselage internal parts to prevent damage to the fuselage internal parts, in particular to provide a vehicle that can prevent the memory damage of the flight control computer by a cosmic ray (cosmic ray) will be.
  • a cosmic ray cosmic ray
  • An object according to an embodiment is to provide a vehicle that can be stably taken off by the take-off aid, the propeller is fixed to a horizontal position by the control unit to prevent the aircraft from being damaged during landing of the aircraft.
  • Aircraft for achieving the above object, a fuselage; A main blade having an upper surface curved and extending from both sides of the fuselage; A solar cell provided on an upper surface of the main blade to convert solar energy into electrical energy; And an energy storage unit disposed in the fuselage or the main wing to store electrical energy generated from the solar cell, wherein the solar cell is provided as a plurality of unit solar cells, and the efficiency of the solar cell is improved, and the plurality of solar cells is improved.
  • the flight time may be extended by the electrical energy output from the unit solar cells or the electrical energy stored in the energy storage unit.
  • the upper surface of the main wing is provided with a mylar skin
  • the plurality of unit solar cells may be attached to the upper surface of the main wing using Kapton tape, respectively.
  • the end of the main wing is provided in a pointed shape, it may be formed to be bent toward the lower portion of the main wing to reduce drag caused by vortex.
  • a Kapton film is applied to the inner body parts to prevent damage to the inner body parts.
  • the energy storage unit the first battery disposed in the center of the body; A second battery disposed on the right side from the center of the fuselage; And a third battery disposed at a left side from the center of the fuselage, wherein the electrical energy generated from the plurality of unit solar cells is stored in at least one of the first battery, the second battery, and the third battery.
  • the first battery disposed in the center of the body
  • a second battery disposed on the right side from the center of the fuselage
  • a third battery disposed at a left side from the center of the fuselage, wherein the electrical energy generated from the plurality of unit solar cells is stored in at least one of the first battery, the second battery, and the third battery.
  • a plurality of propellers are provided to rotate in front of the main wing, the second battery and the third battery may be disposed in a position adjacent to one of the plurality of propellers.
  • an energy storage management unit connected to the energy storage unit, the energy storage unit and the energy storage management unit may be integrally formed.
  • Aircraft for achieving the above object, a fuselage; Main wings extending from the fuselage to both sides; A propeller provided and rotated in front of the main blade; A take-off aid that is detachable from the fuselage and helps take off of the fuselage; And a control unit for controlling the operation of the fuselage, the propeller, or the takeoff auxiliary unit.
  • a solar cell is provided on an upper surface of the main wing to convert solar energy into electrical energy. The fuselage, the takeoff aid, or the control unit can be operated.
  • the takeoff aid is mounted to the fuselage for takeoff of the fuselage, when the aircraft reaches a certain speed can be detached from the fuselage.
  • control unit may control a motor for transmitting power to the propeller so that the propeller is fixed in a horizontal position when the fuselage landing.
  • the fuselage in order to prevent damage to the aircraft during landing of the fuselage, it may be provided with a shock absorbing material provided on the lower portion of the fuselage and a skid mounted on the lower portion of the main wing.
  • a plurality of unit solar cells are provided on the main wing to improve solar cell efficiency, and may allow long-term flight by electric energy generated from solar cells during the day and electric energy stored in the energy storage unit at night. Do.
  • the upper surface of the main wing is provided with a mylar skin
  • the unit solar cell is attached by the Kapton tape
  • the unit solar cell can be easily attached to the upper surface of the main wing, and the weight can be reduced.
  • the drag caused by the vortex may be reduced by the shape of the main wing, and the drag may be controlled to minimize drag and reduce weight.
  • the Kapton tape is applied to the internal parts of the fuselage to prevent damage to the internal parts of the fuselage, and in particular, to prevent the damage of the memory of the flight control computer by the cosmic ray.
  • the aircraft can be stably taken off by the takeoff aid, and the propeller is fixed to the horizontal position by the control unit to prevent the aircraft from being damaged during landing of the aircraft.
  • FIG. 1 illustrates a vehicle according to one embodiment.
  • FIGS. 2A-2C illustrate a streamline analysis of the main wing in a vehicle according to one embodiment.
  • FIG. 3 illustrates a flutter analysis model of a vehicle, according to an embodiment.
  • FIG 4 is an enlarged view of a solar cell in a vehicle according to an embodiment.
  • FIG. 5 illustrates an energy storage unit in a vehicle according to an embodiment.
  • FIG. 6 illustrates a fuselage interior arrangement in a vehicle according to one embodiment.
  • FIG. 7 illustrates a state in which the takeoff aid is mounted in the fuselage according to the embodiment.
  • FIG. 8 is a graph showing an ascending rate and a descending rate with time as an experimental result using a vehicle according to an embodiment.
  • FIG. 9 is a graph illustrating an internal and external temperature value of a fuselage with time as a test result using a vehicle according to an embodiment.
  • FIG. 10 is a graph showing an internal and external humidity value of a fuselage with time as a test result using a vehicle according to an embodiment.
  • FIG. 11 is a graph illustrating a state of charge of an energy storage unit over time as a test result using a vehicle according to an embodiment.
  • first, second, A, B, (a), and (b) may be used. These terms are only for distinguishing the components from other components, and the nature, order or order of the components are not limited by the terms. If a component is described as being “connected”, “coupled” or “connected” to another component, that component may be directly connected or connected to that other component, but between components It will be understood that may be “connected”, “coupled” or “connected”.
  • FIGS. 2A to 2C illustrate a streamlined analysis of a main wing in a vehicle according to an embodiment
  • FIG. 3 illustrates an enlarged view of a solar cell in the vehicle according to an embodiment
  • 4 illustrates an energy storage unit in a vehicle according to an embodiment
  • FIG. 5 illustrates an internal arrangement of a fuselage in a vehicle according to an embodiment
  • FIG. 6 illustrates a takeoff aid mounted in a fuselage in a vehicle according to an embodiment. It shows the appearance.
  • a vehicle 10 may include a fuselage 100, a main wing 200, a propeller 300, and a solar cell 400.
  • the fuselage 100 may be located at the center of the vehicle 10 as a main structural part of the vehicle 10.
  • the fuselage of a long-haul aircraft or a high altitude vehicle may be a gastight structure by a double shell, and air conditioning may be achieved.
  • the fuselage 100 may be, for example, a fuselage of an unmanned aerial vehicle (UAV).
  • UAV unmanned aerial vehicle
  • the main blade 200 may be coupled to the fuselage 100.
  • the main blade 200 may be formed to extend from the fuselage to both sides, for example, in the left and right directions of the fuselage.
  • the fuselage 100 may be disposed at the center of the main blade 200.
  • a curved surface may be formed on the upper surface of the main blade 200.
  • the end of the main blade 200 is provided in a pointed shape, and may be formed to be bent toward the ground, for example, from the air toward the bottom of the main blade 200 to reduce drag caused by vortex.
  • the drag reduction effect was analyzed using the main blades 200 having various shapes.
  • FIG. 2A shows the case where the end of the main wing 200 is elliptic wingtip
  • FIGS. 2B and 2C show the case where the end of the main wing 200 is raked wingtip.
  • the main blade 200 may be provided in a super lightweight high rigid composite structure.
  • the upper surface of the main blade 200 may be provided with a vinyl or mylar skin.
  • the myler is a trade name of polyethylene terephthalate (telephthalate polyethylene or telephthalic acid polyester) and is one of thermoplastic resins. Mylar in particular is very strong mechanically and electrically.
  • the aircraft 10 can be further reduced in weight.
  • the propeller 300 may be connected to the main blade 200.
  • the propeller 300 may be designed to be suitable for low Reynolds flows to improve performance at high altitudes.
  • the propeller 300 may be connected toward the front of the body 100 in the main blade (200).
  • the propeller 300 may be provided in plural numbers and symmetrically disposed in the left and right directions with respect to the body 100.
  • the propeller 300 may be rotated by a motor and control the rotation of the propeller 300 by controlling the motor.
  • the propeller 300 can be in a horizontal position so as not to collide with the ground.
  • the solar cell 400 may be disposed on the upper surface of the main blade 200.
  • the solar cell 400 converts solar energy into electrical energy, for example, when the aircraft 10 is flying during the day, the aircraft 10 is flying using the electrical energy output from the solar cell 400. Can be done.
  • the solar cell 400 may be provided as a plurality of unit solar cells 410 or a single crystal solar cell.
  • the efficiency of the solar cell 400 can be improved.
  • the plurality of unit solar cells 410 may be attached to the upper surface of the main blade 200 using a Kapton tape.
  • the Kapton tape is excellent in heat resistance, chemical resistance, electrical insulation and can be used at high temperatures, and can be used for insulation and masking of parts requiring high heat resistance and PVC plating.
  • the plurality of unit solar cells 410 may be easily attached to the upper surface of the main blade 200, and in some cases, the plurality of unit solar cells 410 attached to the upper surface of the main blade 200. Can be arranged or numbered. At this time, it is obvious that the plurality of unit solar cells 410 attached to the upper surface of the main blade 200 may have the same or different sizes or shapes.
  • the plurality of unit solar cells 410 may be attached to a portion of the upper surface of the main blade 200.
  • the plurality of unit solar cells 410 may be attached to an area near the body 100 on the upper surface of the main blade 200, and may not be attached near an end of the main blade 200.
  • the energy storage unit 500 may be connected to the solar cell 400 described above.
  • the energy storage unit 500 may be disposed in the fuselage 100 or the main wing 200 to store electrical energy generated by the solar cell 400.
  • the energy storage unit 500 may be provided as a lithium ion battery.
  • the energy storage unit 500 may include a first battery 510, a second battery 520, and a third battery 530.
  • the first battery 510 may be disposed at the center of the fuselage 100, for example, inside the fuselage 100, and the second battery 520 may be disposed at the center of the fuselage 100 below the main blade 200.
  • the third battery 530 may be disposed on the left side from the center of the fuselage 100 at the bottom of the main blade 200.
  • the first battery 510 may be utilized to drive components inside the fuselage 100, and the second battery 520 rotates the propeller 300 disposed on the right side from the center of the fuselage 100.
  • the third battery 530 may be used to drive a motor for rotating the propeller 300 disposed on the left side from the center of the body 100.
  • the energy storage unit 500 is illustrated in FIG. 5 as including three batteries, the energy storage unit 500 may include more or less than three batteries. For example, two or more batteries may be included in the fuselage 100.
  • the above-described energy storage unit 500 may be utilized especially during the night when solar energy cannot be obtained.
  • the long-term cavities of the aircraft 10 may be enabled by using the solar cell 400 and the energy storage unit 500 together.
  • an energy storage management unit (not shown) may be further connected to the energy storage unit 500, and the energy storage management unit may be provided as, for example, a battery management system (BMS).
  • BMS battery management system
  • the energy storage management unit may be integrally formed with the energy storage unit 500, and may be heated with its own energy at subzero temperatures in order to minimize energy loss of the energy storage unit 500 in the cold.
  • vehicle 10 may further include a controller (not shown) for controlling the overall flight of the vehicle 10.
  • the controller may control the operation of the fuselage 100, the propeller 300, the solar cell 400, or the energy storage unit 500.
  • various components may be disposed in the body 100.
  • the fuselage 100 may be equipped with various antennas, for example, a transponder antenna, a GPS antenna, and a UHF antenna.
  • the various antennas may enable the aircraft 10 to transmit and receive signals to and from the outside smoothly.
  • the fuselage 100 may be provided with an HD camera and an image storage device, and may photograph an image during flight of the aircraft 10 and utilize the captured image, and may further include a communication modem and a signal distributor.
  • the fuselage 100 may include a fan to prevent overheating of the internal components of the fuselage 100, and a hatch door may be provided to facilitate maintenance of the internal components of the fuselage 100.
  • Various information obtained from the internal parts of the fuselage 100 may be transmitted to, for example, a flight control computer that controls the flight of the vehicle 10.
  • the above-described parts of the body 100 may be coated with a Kapton film to prevent damage due to external influences.
  • a Kapton film to prevent damage due to external influences.
  • the vehicle 10 may further include a takeoff aid 600.
  • the takeoff aid 600 may be detachable from the fuselage 100 and help take off of the fuselage 100.
  • the takeoff assistance unit 600 may be provided as a mobile vehicle, and it may be determined whether to be detached or not by the flight speed of the fuselage 100 or the vehicle 10.
  • the takeoff aid 600 may be mounted on the fuselage 100 at the initial takeoff of the vehicle 10, and may be detached from the fuselage 100 when the vehicle 10 reaches a predetermined speed.
  • the takeoff assistance unit 600 may be mechanically detached from the body 100 or automatically detached by the control unit.
  • takeoff aid 600 may also be operated by the electrical energy generated by the solar cell 400.
  • the vehicle 10 may be stably taken off from the ground by the takeoff auxiliary part 600.
  • the aircraft 10 is provided with a shock absorber (not shown) in the lower portion of the fuselage 10 in order to prevent damage to the aircraft 10 during landing of the aircraft 10 or the fuselage 100, the main wing A skid (not shown) may be provided below the 200.
  • the aircraft according to the embodiment has a plurality of unit solar cells provided on the main wing to improve solar cell efficiency, and may allow long-term flight by electric energy generated from solar cells during the day and electric energy stored in the energy storage unit at night. Do. And the shape of the main wing can reduce the drag caused by the vortex, can control the wheel to minimize the drag and reduce the weight, it can be easy to detach the unit solar cell on the upper surface of the main wing. In addition, the takeoff and landing of the vehicle can be made more stable.
  • FIG. 8 is a graph showing an ascending rate and a descending rate according to time as an experimental result using a vehicle according to an embodiment
  • FIG. 9 is an experimental result using a vehicle according to an embodiment
  • 10 is a graph illustrating an experimental result using an air vehicle according to an embodiment, and a graph illustrating internal and external humidity values of a fuselage according to time
  • FIG. 11 is an experimental result using an air vehicle according to an embodiment. It is a graph showing the state of charge of the energy storage unit according to.
  • the aircraft according to the embodiment was raised at 32 kph and the descending was at 35 kph, and the rising rate and the falling rate were maintained at about 1.0 m / s.
  • the fuselage exterior air of the aircraft has dropped to ⁇ 53 degrees, and the temperature difference between the body and the exterior is up to 30 degrees.
  • the humidity of the air was measured to be 20% or less at an altitude of 4 km or more, and the internal humidity tracks the external humidity with a time difference.
  • the remaining amount of the battery described as the energy storage unit was fully charged while descending to 75% at an altitude of 14 km.
  • the aircraft according to the embodiment was flying stably, it was confirmed that the aircraft can be efficiently driven by the solar cell.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Photovoltaic Devices (AREA)
  • Electric Propulsion And Braking For Vehicles (AREA)

Abstract

Un aéronef selon un mode de réalisation de la présente invention comprend : un fuselage ; des ailes principales dont les surfaces supérieures sont formées sous forme de surfaces courbées, et qui sont étendues depuis le centre du fuselage vers les deux côtés de celui-ci ; des cellules solaires disposées sur les surfaces supérieures des ailes principales de manière à convertir l'énergie solaire en énergie électrique ; et une partie de stockage d'énergie disposée au niveau de la partie inférieure de l'aile principale de manière à stocker l'énergie électrique générée dans les cellules solaires, les cellules solaires étant disposées sous la forme d'une pluralité de cellules solaires unitaires de sorte que le rendement des cellules solaires soit amélioré, et la durée de vol peut être prolongée par l'énergie électrique produite par la pluralité de cellules solaires unitaires ou l'énergie électrique stockée dans la partie de stockage d'énergie.
PCT/KR2016/012711 2015-11-18 2016-11-07 Aéronef WO2017086639A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201680059360.6A CN108137159B (zh) 2015-11-18 2016-11-07 飞行体

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KR10-2015-0161845 2015-11-18
KR20150161845 2015-11-18

Publications (1)

Publication Number Publication Date
WO2017086639A1 true WO2017086639A1 (fr) 2017-05-26

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Family Applications (1)

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PCT/KR2016/012711 WO2017086639A1 (fr) 2015-11-18 2016-11-07 Aéronef

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CN (1) CN108137159B (fr)
WO (1) WO2017086639A1 (fr)

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CN108216569A (zh) * 2018-03-02 2018-06-29 朱幕松 垂直升降太阳能无人机
CN108216569B (zh) * 2018-03-02 2020-02-04 朱幕松 垂直升降太阳能无人机

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