WO2022045539A1 - Aile d'aéronef ayant une fonction de protection contre la foudre et une fonction d'absorption d'ondes électromagnétiques - Google Patents

Aile d'aéronef ayant une fonction de protection contre la foudre et une fonction d'absorption d'ondes électromagnétiques Download PDF

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Publication number
WO2022045539A1
WO2022045539A1 PCT/KR2021/007259 KR2021007259W WO2022045539A1 WO 2022045539 A1 WO2022045539 A1 WO 2022045539A1 KR 2021007259 W KR2021007259 W KR 2021007259W WO 2022045539 A1 WO2022045539 A1 WO 2022045539A1
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WO
WIPO (PCT)
Prior art keywords
electromagnetic wave
lightning protection
aircraft wing
protection device
wave absorption
Prior art date
Application number
PCT/KR2021/007259
Other languages
English (en)
Korean (ko)
Inventor
남영우
권진회
명노신
최원호
신준형
김민준
김윤곤
박세웅
황반토
Original Assignee
경상국립대학교 산학협력단
(주)대한항공
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 경상국립대학교 산학협력단, (주)대한항공 filed Critical 경상국립대학교 산학협력단
Publication of WO2022045539A1 publication Critical patent/WO2022045539A1/fr

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Classifications

    • 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
    • B64D45/02—Lightning protectors; Static dischargers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
    • H02G13/00—Installations of lightning conductors; Fastening thereof to supporting structure
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
    • H02G13/00—Installations of lightning conductors; Fastening thereof to supporting structure
    • H02G13/80—Discharge by conduction or dissipation, e.g. rods, arresters, spark gaps
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K9/00—Screening of apparatus or components against electric or magnetic fields
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K9/00—Screening of apparatus or components against electric or magnetic fields
    • H05K9/0073—Shielding materials
    • H05K9/0081—Electromagnetic shielding materials, e.g. EMI, RFI shielding
    • H05K9/0088—Electromagnetic shielding materials, e.g. EMI, RFI shielding comprising a plurality of shielding layers; combining different shielding material structure
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K9/00—Screening of apparatus or components against electric or magnetic fields
    • H05K9/0073—Shielding materials
    • H05K9/0081—Electromagnetic shielding materials, e.g. EMI, RFI shielding
    • H05K9/009—Electromagnetic shielding materials, e.g. EMI, RFI shielding comprising electro-conductive fibres, e.g. metal fibres, carbon fibres, metallised textile fibres, electro-conductive mesh, woven, non-woven mat, fleece, cross-linked

Definitions

  • the present invention relates to an aircraft wing, and more particularly, to an aircraft wing comprising a lightning protection device that transmits electrical energy of lightning to the surroundings and an electromagnetic wave absorber that absorbs electromagnetic waves when being struck by lightning.
  • the stealth function for radar detection can be implemented by configuring the aircraft to absorb electromagnetic waves to reduce the radar reflection area (RCS). .
  • the lightning protection function can minimize the damage from lightning strikes by rapidly spreading the incoming electrical energy. is applied to
  • Zone 1A which has a high probability of initial attachment of lightning, will be hit by lightning. Therefore, for the lightning protection function of the aircraft wing, a patterned metal mesh with high electrical conductivity is installed on the surface of the aircraft wing.
  • Korean Patent Laid-Open Patent Publication No. 1998-045670 discloses a skin of an auxiliary wing for an aircraft made of a metal mesh to prevent damage by lightning.
  • the metal mesh installed on the surface of the aircraft wing prevents damage to the aircraft wing by rapidly transferring electrical energy to the ground area when struck by lightning.
  • a pattern having a large surface area is formed in a metal mesh installed to protect an aircraft wing from lightning in order to rapidly transfer electrical energy to a ground area, most of the incident electromagnetic waves are reflected.
  • An object of the present invention is to configure a lightning protection device so that an aircraft wing has a lightning protection function without increasing a radar reflection area (RCS).
  • RCS radar reflection area
  • Another object of the present invention is to configure an electromagnetic wave absorption device so that an aircraft wing effectively absorbs electromagnetic waves.
  • An aircraft wing according to an embodiment of the present invention for solving the above problems is installed on the surface of an aircraft wing to transmit electrical energy of lightning to the surroundings when struck by lightning, and a lightning protection device having a pattern formed in an embossed shape on a metal plate; Installed to contact the lightning protection device to absorb electromagnetic waves, and an electromagnetic wave absorption device including an electromagnetic wave absorption layer formed of a dielectric fiber, wherein the pattern of the lightning protection device includes a first parallel portion including a plurality of parallel lines; It may include a second parallel portion including a plurality of parallel lines that intersect the first parallel portion to form a plurality of cells, and a cross reinforcement portion installed at a portion where the first parallel portion and the second parallel portion intersect. .
  • first parallel portion and the second parallel portion may be orthogonal to form a plurality of square-shaped cells.
  • the metal plate may be a plate formed of a metal having an electrical conductivity of 1.25*10 6 S/m, and the length of one side of the cell may be 25 mm or more and 30 mm or less, and the thickness of the side may be 0.5 mm or more and 1 mm or less.
  • the cross-reinforcement portion may be formed in a shape having four edges having a radius of curvature of 0.05 mm or more and 1.5 mm or less.
  • the angle between the plurality of parallel lines constituting the first parallel part and the longitudinal line segment of the aircraft wing is 5 degrees or more and 85 degrees or less, or the plurality of parallel lines constituting the second parallel part is formed with the longitudinal line segment The angle may be 5 degrees or more and 85 degrees or less.
  • a first electromagnetic wave absorbing layer formed of a metal-coated dielectric fiber and a second electromagnetic wave absorbing layer that is installed under the first electromagnetic wave absorbing layer and formed of a dielectric fiber may include
  • the electromagnetic wave absorption device installed to cover the surface of the lightning protection device, may include a third electromagnetic wave absorption layer formed of a dielectric fiber.
  • the lightning protection device may be installed in front of the wing for the aircraft.
  • the dielectric fiber may be formed of glass fabric or Kevlar fabric.
  • Aircraft wing according to the present invention since the lightning protection device has a specific pattern including the cross reinforcement portion is formed, the aircraft wing effectively absorbs electromagnetic waves while providing the effect of having a lightning protection function.
  • the electromagnetic wave absorbing device is composed of a plurality of electromagnetic wave absorbing layers including an electromagnetic wave absorbing layer formed of a metal-coated dielectric fiber, it provides an effect that an aircraft wing can effectively absorb electromagnetic waves.
  • FIG. 1 is a view showing a lightning protection device and an electromagnetic wave absorption device constituting a wing for an aircraft according to an embodiment of the present invention
  • FIG. 2 is a view showing a wing for an aircraft in which the lightning protection device of FIG. 1 is installed;
  • FIG. 3 is a view showing a first parallel part and a second parallel part constituting the pattern of the lightning protection device of FIG. 1;
  • FIG. 4 is a view showing a cell and a cross reinforcement part formed by crossing the first parallel part and the second parallel part of the lightning protection device of FIG. 1;
  • FIG. 5 is a view showing an angle formed by a longitudinal line segment of an aircraft wing and a first parallel part
  • FIG. 6 is a view showing an angle formed by a longitudinal line segment of an aircraft wing and a second parallel part
  • FIG. 7 is a view illustrating electromagnetic wave absorption efficiency according to an angle formed by a longitudinal line segment of an aircraft wing and a first parallel part.
  • Aircraft wing 100 Lightning protection device
  • electromagnetic wave absorption device 210 first electromagnetic wave absorption layer
  • FIG. 1 is a view showing a lightning protection device and an electromagnetic wave absorption device constituting a wing for an aircraft according to an embodiment of the present invention.
  • the wing 1 for an aircraft is a lightning protection device 100 that transmits electrical energy to a periphery or a grounding point when being struck by lightning so that the aircraft has a stealth function. It may include an electromagnetic wave absorption device 200 that absorbs an incident electromagnetic wave.
  • the lightning protection device 100 is an aircraft wing ( 1) is installed in the upper direction close to the surface
  • the electromagnetic wave protection device 200 may be installed on the upper surface and the lower surface of the lightning protection device (1).
  • FIG. 2 is a view showing a wing for an aircraft in which the lightning protection device of FIG. 1 is installed.
  • the lightning protection device 100 is formed so that a thin metal plate with high electrical conductivity has a specific embossed pattern, and may be installed on the surface of the wing 1 for an aircraft.
  • the metal plate may be formed of a metal having a thickness of 0.102 mm and an electrical conductivity of 1.25*10 6 S/m.
  • the lightning protection device 100 may be installed long in a specific portion of the wing 1 for an aircraft along the longitudinal direction.
  • the lightning protection device 100 may be installed along the longitudinal direction on the leading edge of the wing 1 for an aircraft.
  • FIG. 3 is a view showing a first parallel part and a second parallel part constituting the pattern of the lightning protection device of FIG. 1 .
  • the lightning protection device 100 may be configured such that an embossed pattern including the first parallel portion 110 and the second parallel portion 220 is formed on the metal film.
  • the first parallel portion 110 may be configured to include a plurality of parallel lines (refer to (a) of FIG. 3).
  • the second parallel portion 120 may be configured to include a plurality of parallel lines orthogonal to the first parallel portion 110 (see FIG. 3B ).
  • FIG. 4 is a view illustrating a cell and a cross reinforcement part formed by crossing the first parallel part and the second parallel part of the lightning protection device of FIG. 1 .
  • a plurality of cells 130 may be formed in the lightning protection device 100 as the first parallel portion 110 and the second parallel portion 120 are orthogonal to each other, and cross reinforcement is provided at each vertex.
  • the portion 140 may have a square shape in which the four sides have the same length.
  • the cell 130 may have a square shape consisting of four sides with a length l of each side of 25 mm or more and 35 mm or less, and a thickness d of each side of 0.5 mm or more and 1 mm or less.
  • the length l of the side constituting the cell 130 is formed longer than that of the conventional lightning protection metal mesh, so that the pattern for electric conduction formed in the embossed shape of the lightning protection device 100 is the lightning protection device 100 . occupies less surface area. Therefore, in the lightning protection device 100 , the radar reflection area (RCS) is not increased to such an extent that the stealth function is deteriorated, so that the electromagnetic wave absorption device 200 installed under the lightning protection device 100 can effectively absorb electromagnetic waves. .
  • RCS radar reflection area
  • the cross reinforcement part 140 is formed in a portion corresponding to the vertex of the cell 130 where the first parallel part 110 and the second parallel part 120 intersect, and has a function of effectively transferring the electrical energy of lightning to the surroundings.
  • the lightning protection device 100 includes the cross reinforcement portion 140, so that the first parallel portion 110 and the second parallel portion 120 are struck by lightning. Even if the pattern formed in the relief on the protection device 100 has a small surface area, it is possible to effectively transmit electrical energy to the surroundings.
  • the cross reinforcement portion 140 may be configured to include a portion where the first parallel portion 110 and the second parallel portion 120 intersect.
  • the cross-reinforcement unit 140 may be formed of a figure having four edges cut in a curve having a radius of curvature of 0.05 mm or more and 1.5 mm or less.
  • the cross reinforcing portion 140 includes a portion where the first parallel portion 110 and the second parallel portion 120 intersect and is formed in a figure having a sufficient surface area, so that the lightning protection device 100 is protected from lightning strikes. It is possible to effectively transfer electrical energy to the surroundings.
  • first parallel portion 110 and the second parallel portion 120 formed in the lightning protection device 100 described above are disposed to have a specific angle to the wing 1 for the aircraft, so that electrical energy is saved when being struck by lightning. It can be effectively communicated to the surroundings.
  • FIG. 5 is a view illustrating an angle formed by a longitudinal line segment of an aircraft wing and a first parallel portion
  • FIG. 6 is a view illustrating an angle formed by a longitudinal line segment of an aircraft wing and a second parallel portion.
  • the angle ( ⁇ 1 ) formed by the plurality of parallel lines constituting the first parallel part 110 with the longitudinal line segment (y-axis line segment) of the aircraft wing 1 is 5
  • the lightning protection device 100 may be installed on the wing 1 for the aircraft so that the degree is greater than or equal to 85 degrees or less.
  • the angle ( ⁇ 2 ) formed by a plurality of parallel lines constituting the second parallel part 120 with the longitudinal line segment (y-axis line segment) of the wing 1 for aircraft is To be 5 degrees or more and 85 degrees or less, the lightning protection device 100 may be installed on the wing 1 for an aircraft.
  • FIG. 7 is a view illustrating electromagnetic wave absorption efficiency according to an angle formed by a longitudinal line segment of an aircraft wing and a first parallel part.
  • the lightning protection device 100 when the lightning protection device 100 is installed on the aircraft wing 1 so that the first parallel portion 110 or the second parallel portion 120 forms a specific angle with the longitudinal line segment of the aircraft wing 1, The lightning protection device 100 may more effectively transmit electrical energy to the surroundings when being struck by lightning.
  • the electromagnetic wave absorbing device 200 may be configured by combining a plurality of electromagnetic wave absorbing layers.
  • the electromagnetic wave absorbing device 200 is formed of a metal-coated dielectric fiber, and the first electromagnetic wave absorbing layer 210 and the first electromagnetic wave absorbing layer 210 are installed under the lightning protection device 100 . It may include a second electromagnetic wave absorption layer 220 formed of dielectric fibers and a third electromagnetic wave absorption layer 230 installed on the lightning protection device 100 .
  • the electromagnetic wave absorption device 200 includes the first electromagnetic wave absorption layer 210 and the second electromagnetic wave absorption layer 220 , thereby effectively absorbing electromagnetic waves introduced from the outside.
  • the electromagnetic wave absorption device 200 includes the third electromagnetic wave absorption layer 230 on the lightning protection device 100 , electromagnetic waves are effectively absorbed and the lightning protection device 100 can be protected from being damaged.
  • the lightning protection device 100 transmits the electrical energy caused by the lightning to the periphery or the ground part. To prevent the wing (1) for the aircraft from being damaged.
  • the pattern for electric conduction formed in the lightning protection device 100 has a small surface area, but the cross reinforcement part 140 is formed to have a sufficient surface area, so that the electric energy caused by the lightning strike is effectively transmitted to the peripheral part or the ground part.
  • the pattern for electric conduction formed in the lightning protection device 100 has a small surface area, electromagnetic waves entering from the outside can be effectively introduced into the electromagnetic wave absorption device 200 installed under the lightning protection device 100 and absorbed. there is.
  • the electromagnetic wave absorbing device 200 is formed of a combination of a plurality of electromagnetic wave absorbing layers including dielectric fibers coated with metal, it is possible to effectively absorb incoming electromagnetic waves.
  • an electromagnetic wave absorbing layer may be installed on the upper portion of the lightning protection device 100 , and the installed electromagnetic wave absorbing layer may protect the lightning protection device 100 so that the lightning protection device 100 is not damaged.
  • the aircraft wing according to the present invention provides an effect that the lightning protection device can have a lightning protection function while effectively absorbing electromagnetic waves while the lightning protection device has a specific pattern including the cross reinforcement.
  • the electromagnetic wave absorbing device is composed of a plurality of electromagnetic wave absorbing layers including an electromagnetic wave absorbing layer formed of a metal-coated dielectric fiber, it provides an effect that an aircraft wing can effectively absorb electromagnetic waves.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Microelectronics & Electronic Packaging (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Mechanical Engineering (AREA)
  • Textile Engineering (AREA)
  • Elimination Of Static Electricity (AREA)
  • Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
  • Aerials With Secondary Devices (AREA)

Abstract

La présente invention concerne une aile d'aéronef. L'aile d'aéronef comprend : un appareil de protection contre la foudre qui est installé sur la surface de l'aile d'aéronef pour transmettre l'énergie électrique de la foudre à l'environnement quand l'aile d'aéronef est frappée par la foudre, et qui a un motif gaufré formé sur une plaque métallique; et un appareil d'absorption d'ondes électromagnétiques qui est installé de manière à entrer en contact avec l'appareil de protection contre la foudre et qui absorbe des ondes électromagnétiques, et qui comprend une couche d'absorption d'ondes électromagnétiques formée à partir de fibres diélectriques. Le motif de l'appareil de protection contre la foudre peut comprendre : une première partie parallèle ayant une pluralité de lignes parallèles; une deuxième partie parallèle agencée de manière perpendiculaire par rapport à la première partie parallèle afin de former une pluralité de cellules de forme carrée, et comprenant une pluralité de lignes parallèles; et une partie de renfort transversal circulaire comprenant une partie dans laquelle la première partie parallèle et la deuxième partie parallèle se croisent.
PCT/KR2021/007259 2020-08-27 2021-06-10 Aile d'aéronef ayant une fonction de protection contre la foudre et une fonction d'absorption d'ondes électromagnétiques WO2022045539A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KR10-2020-0108659 2020-08-27
KR1020200108659A KR102391715B1 (ko) 2020-08-27 2020-08-27 낙뢰 보호 기능 및 전자기파 흡수 기능을 구비하는 항공기용 날개

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WO2022045539A1 true WO2022045539A1 (fr) 2022-03-03

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PCT/KR2021/007259 WO2022045539A1 (fr) 2020-08-27 2021-06-10 Aile d'aéronef ayant une fonction de protection contre la foudre et une fonction d'absorption d'ondes électromagnétiques

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WO (1) WO2022045539A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120271564A1 (en) * 2011-04-21 2012-10-25 U.S.A. As Represented By The Administrator Of The National Aeronautics And Space Administration Lightning Protection and Detection System
EP3284680A1 (fr) * 2016-08-16 2018-02-21 The Boeing Company Réseau de retour de courant intégré dans des structures composites
KR20180100348A (ko) * 2015-12-30 2018-09-10 사이텍 인더스트리스 인코포레이티드 용락 저항성이 있는 다기능성 표면 재료
KR20180113120A (ko) * 2017-04-05 2018-10-15 한국과학기술원 금속 코팅 섬유를 포함하는 항공기용 전자파 흡수 날개 구조물
KR20200059363A (ko) * 2018-11-20 2020-05-29 국방과학연구소 복합재 레이어와 이를 포함하는 구조 일체형 연료 탱크 및 항공기

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120271564A1 (en) * 2011-04-21 2012-10-25 U.S.A. As Represented By The Administrator Of The National Aeronautics And Space Administration Lightning Protection and Detection System
KR20180100348A (ko) * 2015-12-30 2018-09-10 사이텍 인더스트리스 인코포레이티드 용락 저항성이 있는 다기능성 표면 재료
EP3284680A1 (fr) * 2016-08-16 2018-02-21 The Boeing Company Réseau de retour de courant intégré dans des structures composites
KR20180113120A (ko) * 2017-04-05 2018-10-15 한국과학기술원 금속 코팅 섬유를 포함하는 항공기용 전자파 흡수 날개 구조물
KR20200059363A (ko) * 2018-11-20 2020-05-29 국방과학연구소 복합재 레이어와 이를 포함하는 구조 일체형 연료 탱크 및 항공기

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KR102391715B1 (ko) 2022-05-02
KR20220030353A (ko) 2022-03-11

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