WO2022045539A1 - Aircraft wing having lightning protection function and electromagnetic wave absorption function - Google Patents

Aircraft wing having lightning protection function and electromagnetic wave absorption function 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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WIPO (PCT)
Prior art keywords
electromagnetic wave
lightning protection
aircraft wing
protection device
wave absorption
Prior art date
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PCT/KR2021/007259
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French (fr)
Korean (ko)
Inventor
남영우
권진회
명노신
최원호
신준형
김민준
김윤곤
박세웅
황반토
Original Assignee
경상국립대학교 산학협력단
(주)대한항공
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Publication of WO2022045539A1 publication Critical patent/WO2022045539A1/en

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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.

Abstract

The present invention relates to an aircraft wing. The aircraft wing comprises: a lightning protection apparatus which is installed on the surface of the aircraft wing to transmit the electrical energy of lightning to the surroundings when the aircraft wing is struck by lightning, and has an embossed pattern formed on a metal plate; and an electromagnetic wave absorption apparatus which is installed so as to contact the lightning protection apparatus and absorbs electromagnetic waves, and which includes an electromagnetic wave absorption layer formed of dielectric fibers. The pattern of the lightning protection apparatus may comprise: a first parallel portion having a plurality of parallel lines; a second parallel portion arranged perpendicular to the first parallel portion so as to form a plurality of square-shaped cells, and including a plurality of parallel lines; and a circular cross-reinforcing portion including a portion in which the first parallel portion and the second parallel portion intersect.

Description

낙뢰 보호 기능 및 전자기파 흡수 기능을 구비하는 항공기용 날개Aircraft wing with lightning protection function and electromagnetic wave absorption function
본 발명은 항공기용 날개에 관한 것으로, 보다 상세하게는 낙뢰 피격 시 낙뢰의 전기 에너지를 주변으로 전달하는 낙뢰보호장치와 전자기파를 흡수하는 전자기파흡수장치를 포함하는 항공기용 날개에 관한 것이다.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.
최근 개발되는 전략/전술 항공기들은 생존성을 높이기 위하여 상대방의 탐지 신호에 쉽게 노출되지 않기 위한 스텔스 기능 및 항공기 운용 시 낙뢰로 인한 기체 손실 방지를 위한 낙뢰 보호 기능이 동시에 요구되고 있다. 특히, 항공전자 기술의 발전과 다양한 전자장비의 접목으로 항법 및 계기 디지털화에 따라 낙뢰에 의한 항공기 안전의 중요성이 더욱 증가하고 있다. 낙뢰는 고온의 열에너지와 강한 전자기장을 동반하므로 항공기 운항 환경에 있어 구조적 손상과 더불어 치명적인 전자기적 위협을 가하는 요소이다.In order to increase survivability, strategic/tactical aircraft that are recently developed are required at the same time to have a stealth function not to be easily exposed to an opponent's detection signal and a lightning protection function to prevent loss of airframe due to lightning during aircraft operation. In particular, with the development of avionics technology and the grafting of various electronic equipment, the importance of aircraft safety due to lightning is increasing due to the digitalization of navigation and instruments. Since lightning is accompanied by high-temperature thermal energy and a strong electromagnetic field, it is a factor that poses a fatal electromagnetic threat along with structural damage to the aircraft operating environment.
레이더 탐지에 대한 스텔스 기능은 항공기가 전자기파를 흡수하여 레이더 반사 면적(RCS)을 감소시키도록 구성함으로써 구현될 수 있으며, 항공기가 전자기파를 흡수하도록 하기 위하여 유전체 섬유 등으로 구성된 전자기파흡수층을 항공기에 설치한다.The stealth function for radar detection can be implemented by configuring the aircraft to absorb electromagnetic waves to reduce the radar reflection area (RCS). .
낙뢰에 대한 보호 기능은 유입되는 전기 에너지를 신속하게 확산시켜 낙뢰 피격 피해를 최소화할 수 있으며, 대표적인 예로 CM(Copper Mesh), EMF(Expanded Metal Foil)와 같은 높은 전기전도도를 가진 낙뢰보호장치를 항공기에 적용하고 있다. The lightning protection function can minimize the damage from lightning strikes by rapidly spreading the incoming electrical energy. is applied to
일반적으로, 항공기는 낙뢰초기부착확률이 높은 구역 Zone 1A인 주 날개가 낙뢰에 의해서 피격될 가능성이 높다. 따라서, 항공기 날개의 낙뢰 보호 기능을 위해서 패턴이 형성된 전기 전도도가 높은 금속 망(Metal Mesh) 등을 항공기 날개 표면에 설치한다. 예를 들어, 한국 공개특허 특1998-045670호는 낙뢰에 의한 손상을 방지하기 위한 금속망으로 구성된 항공기용 보조날개의 스킨을 개시하고 있다.In general, there is a high probability that the main wing of the aircraft, 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. For example, 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.
항공기 날개 표면에 설치된 금속 망 등은 낙뢰 피격 시 전기 에너지를 접지 영역으로 빠르게 전달시킴으로써, 항공기 날개의 파손을 방지한다. 그러나 일반적으로 낙뢰로부터 항공기 날개를 보호하기 위하여 설치되는 금속 망은 전기 에너지를 접지 영역으로 빠르게 전달시키기 위하여 큰 표면적을 가지는 패턴이 형성되므로, 입사되는 전자기파를 대부분 반사시킨다.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. However, in general, since 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.
즉, 낙뢰 보호 기능을 향상시키기 위해서 큰 표면적의 패턴이 형성된 금속 망 등을 항공기 날개 표면에 설치하는 경우, 항공기 날개의 레이더 반사 면적(RCS)이 증가하게 되어 항공기의 스텔스 기능이 저하되는 문제가 발생한다.That is, when a metal mesh having a large surface area pattern is installed on the surface of an aircraft wing in order to improve the lightning protection function, the radar reflection area (RCS) of the aircraft wing increases, which causes a problem in that the stealth function of the aircraft is deteriorated. do.
본 발명의 일 과제는, 항공기용 날개가 레이더 반사 면적(RCS)의 증가 없이 낙뢰 보호 기능을 갖추도록 낙뢰보호장치를 구성하는데 있다.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).
본 발명의 또 다른 과제는, 항공기용 날개가 전자기파를 효과적으로 흡수하도록 전자기파흡수장치를 구성하는데 있다.Another object of the present invention is to configure an electromagnetic wave absorption device so that an aircraft wing effectively absorbs electromagnetic waves.
본 발명의 과제는 이상에서 언급된 과제들로 제한되지 않으며, 언급되지 않은 다른 과제들은 아래의 기재로부터 당업자에게 명확하게 이해될 수 있을 것이다.The problems of the present invention are not limited to the problems mentioned above, and other problems not mentioned will be clearly understood by those skilled in the art from the following description.
상기 과제를 해결하기 위한 본 발명의 일 실시예에 따른 항공기용 날개는, 항공기용 날개 표면에 설치되어 낙뢰 피격 시 낙뢰의 전기 에너지를 주변으로 전달하며, 금속판에 양각으로 패턴이 형성된 낙뢰보호장치 및 상기 낙뢰보호장치와 접촉하도록 설치되어 전자기파를 흡수하며, 유전체 섬유로 형성된 전자기파흡수층을 포함하는 전자기파흡수장치를 포함하고, 상기 낙뢰보호장치의 상기 패턴은, 복수 개의 평행선을 포함하는 제1 평행부, 상기 제1 평행부와 교차하여 복수 개의 셀을 형성하는, 복수 개의 평행선을 포함하는 제2 평행부 및 상기 제1 평행부와 상기 제2 평행부가 교차하는 부분에 설치되는 교차보강부를 포함할 수 있다.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. .
또한, 상기 제1 평행부와 상기 제2 평행부는 직교하여 복수 개의 정사각형 형상의 셀을 형성할 수 있다.In addition, the first parallel portion and the second parallel portion may be orthogonal to form a plurality of square-shaped cells.
또한, 상기 금속판은 전기 전도도가 1.25*106 S/m 인 금속으로 형성된 판이고, 상기 셀의 한 변의 길이는 25mm 이상 30mm 이하이고, 상기 변의 두께는 0.5mm 이상 1mm 이하일 수 있다.In addition, 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.
또한, 상기 교차보강부는 곡률 반지름이 0.05mm 이상 1.5mm 이하인 테두리 4개를 가지는 도형으로 형성될 수 있다.In addition, 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.
또한, 상기 제1 평행부를 구성하는 복수 개의 평행선이 상기 항공기용 날개의 길이 방향 선분과 이루는 각도가 5도 이상 85도 이하이거나, 상기 제2 평행부를 구성하는 복수 개의 평행선이 상기 길이 방향 선분과 이루는 각도가 5도 이상 85도 이하일 수 있다.In addition, 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.
또한, 상기 전자기파흡수장치는, 상기 낙뢰보호장치 하부에 설치되며, 금속으로 코팅된 유전체 섬유로 형성되는 제1 전자기파흡수층 및 상기 제1 전자기파흡수층 하부에 설치되며, 유전체 섬유로 형성되는 제2 전자기파흡수층을 포함할 수 있다.In addition, the electromagnetic wave absorbing device is installed under the lightning protection device, 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
또한, 상기 전자기파흡수장치는, 상기 낙뢰보호장치의 표면을 덮도록 설치되며, 유전체 섬유로 형성되는 제3 전자기파흡수층을 포함할 수 있다.In addition, 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.
또한, 상기 낙뢰보호장치는 상기 항공기용 날개의 앞전에 설치될 수 있다.In addition, the lightning protection device may be installed in front of the wing for the aircraft.
또한, 상기 유전체 섬유는 유리섬유(Glass fabric) 또는 케블라(Kevlar fabric)으로 형성될 수 있다.In addition, the dielectric fiber may be formed of glass fabric or Kevlar fabric.
과제를 해결하기 위한 기타 실시예들의 구체적인 사항들은 발명의 설명 및 도면들에 포함되어 있다.Specific details of other embodiments for solving the problem are included in the description and drawings of the invention.
본 발명에 따른 항공기용 날개는, 낙뢰보호장치가 교차보강부를 포함하는 특정한 패턴이 형성되므로, 항공기용 날개가 전자기파를 효과적으로 흡수하면서도 낙뢰 보호 기능을 갖출 수 있는 효과를 제공한다.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.
또한, 전자기파흡수장치가 금속이 코팅된 유전체 섬유로 형성된 전자기파흡수층을 포함하여 복수 개의 전자기파흡수층으로 구성됨으로써, 항공기용 날개가 전자기파를 효과적으로 흡수할 수 있는 효과를 제공한다.In addition, since 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.
도 1은 본 발명의 일 실시예에 따른 항공기용 날개를 구성하는 낙뢰보호장치와 전자기파흡수장치를 도시한 도면,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;
도 2는 도 1의 낙뢰보호장치가 설치된 항공기용 날개를 도시한 도면,2 is a view showing a wing for an aircraft in which the lightning protection device of FIG. 1 is installed;
도 3은 도 1의 낙뢰보호장치의 패턴을 구성하는 제1 평행부 및 제2 평행부를 도시한 도면,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;
도 4는 도 1의 낙뢰보호장치의 제1 평행부 및 제2 평행부가 교차하여 형성하는 셀과 교차보강부를 도시한 도면,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;
도 5는 항공기용 날개의 길이 방향 선분과 제1 평행부가 이루는 각도를 도시한 도면,5 is a view showing an angle formed by a longitudinal line segment of an aircraft wing and a first parallel part;
도 6은 항공기용 날개의 길이 방향 선분과 제2 평행부가 이루는 각도를 도시한 도면,6 is a view showing an angle formed by a longitudinal line segment of an aircraft wing and a second parallel part;
도 7은 항공기용 날개의 길이 방향 선분과 제1 평행부가 이루는 각도에 따른 전자기파 흡수 효율을 도시한 도면이다.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.
※부호의 설명※※Explanation of code※
1 : 항공기용 날개 100 : 낙뢰보호장치1: Aircraft wing 100: Lightning protection device
110 : 제1 평행부 120 : 제2 평행부110: first parallel portion 120: second parallel portion
130 : 셀 140 : 교차보강부130: cell 140: cross reinforcement
200 : 전자기파흡수장치 210 : 제1 전자기파흡수층200: electromagnetic wave absorption device 210: first electromagnetic wave absorption layer
220 : 제2 전자기파흡수층 230 : 제3 전자기파흡수층220: second electromagnetic wave absorbing layer 230: third electromagnetic wave absorbing layer
이하, 첨부한 도면들 및 후술되어 있는 내용을 참조하여 본 발명의 바람직한 실시예들을 상세히 설명한다. 그러나 본 발명은 여기서 설명되는 실시예들에 한정되지 않고 다른 형태로 구체화될 수도 있다. 명세서 전체에 걸쳐서 동일한 참조번호들은 동일한 구성요소들을 나타낸다.Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings and the content to be described later. However, the present invention is not limited to the embodiments described herein and may be embodied in other forms. Like reference numerals refer to like elements throughout.
이하, 본 발명의 실시예에 따른 항공기용 날개(1)에 대하여 설명한다.Hereinafter, an aircraft wing 1 according to an embodiment of the present invention will be described.
도 1은 본 발명의 일 실시예에 따른 항공기용 날개를 구성하는 낙뢰보호장치와 전자기파흡수장치를 도시한 도면이다.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.
도 1을 참조하여 설명하면, 본 발명의 일 실시예에 따른 항공기용 날개(1)는 낙뢰 피격 시 전기 에너지를 주변부나 접지 지점으로 전달하는 낙뢰보호장치(100) 및 항공기가 스텔스 기능을 가지도록 입사되는 전자기파를 흡수하는 전자기파흡수장치(200)를 포함할 수 있다.Referring to FIG. 1 , the wing 1 for an aircraft according to an embodiment of the present invention 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.
예를 들어, 제2 전자기파흡수층(220)으로부터 제3 전자기파흡수층(230)을 향하는 방향을 상방향이라고 하고, 그 반대의 방향을 하방향이라고 했을 때, 낙뢰보호장치(100)는 항공기용 날개(1)의 표면에 가까운 상방향에 설치되고, 전자기파보호장치(200)는 낙뢰보호장치(1)의 상면과 하면에 설치될 수 있다.For example, when the direction from the second electromagnetic wave absorbing layer 220 to the third electromagnetic wave absorbing layer 230 is upward and the opposite direction is downward, 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).
도 2는 도 1의 낙뢰보호장치가 설치된 항공기용 날개를 도시한 도면이다.FIG. 2 is a view showing a wing for an aircraft in which the lightning protection device of FIG. 1 is installed.
먼저, 도 2를 참조하여, 낙뢰보호장치(100)의 구성에 관하여 설명한다.First, with reference to FIG. 2 , the configuration of the lightning protection device 100 will be described.
낙뢰보호장치(100)는 전기 전도도가 높은 얇은 금속판이 특정한 양각의 패턴을 가지도록 형성되어, 항공기용 날개(1)의 표면에 설치될 수 있다.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.
예를 들어, 금속판은 두께가 0.102mm이고, 전기 전도도가 1.25*106 S/m 인 금속으로 형성될 수 있다.For example, 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.
도 2에는 x축, y축, z축의 좌표계가 도시되어 있는데, x축은 항공기용 날개(1)의 시위 방향인 폭 방향, y축은 항공기용 날개(1)의 길이 방향, z축은 상하 방향을 나타낸다. 낙뢰보호장치(100)는 길이 방향을 따라서 항공기용 날개(1)의 특정 부분에 길게 설치될 수 있다. 예를 들어 설명하면, 낙뢰보호장치(100)는 항공기용 날개(1)의 앞전에 길이 방향을 따라서 설치될 수 있다.2, the coordinate system of the x-axis, y-axis, and z-axis is shown, the x-axis represents the width direction, which is the string direction of the aircraft wing 1, the y-axis represents the longitudinal direction of the aircraft wing 1, and the z-axis represents the vertical direction. . The lightning protection device 100 may be installed long in a specific portion of the wing 1 for an aircraft along the longitudinal direction. For example, the lightning protection device 100 may be installed along the longitudinal direction on the leading edge of the wing 1 for an aircraft.
도 3은 도 1의 낙뢰보호장치의 패턴을 구성하는 제1 평행부 및 제2 평행부를 도시한 도면이다.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 .
도 3을 참조하여 설명하면, 낙뢰보호장치(100)는 금속 막에 제1 평행부(110)와 제2 평행부(220)를 포함하는 양각의 패턴이 형성되도록 구성될 수 있다.Referring to FIG. 3 , 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.
구체적으로, 제1 평행부(110)는 복수 개의 평행선을 포함하여 구성될 수 있다(도 3의 (a) 참조). 그리고, 제2 평행부(120)는 제1 평행부(110)와 직교하는 복수 개의 평행선을 포함하여 구성될 수 있다(도 3의 (b) 참조).Specifically, the first parallel portion 110 may be configured to include a plurality of parallel lines (refer to (a) of FIG. 3). In addition, 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 ).
도 4는 도 1의 낙뢰보호장치의 제1 평행부 및 제2 평행부가 교차하여 형성하는 셀과 교차보강부를 도시한 도면이다.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 .
도 4를 참조하여 설명하면, 셀(130)은 제1 평행부(110)와 제2 평행부(120)가 직교함으로써 낙뢰보호장치(100)에 복수 개가 형성될 수 있으며, 각 꼭지점에 교차보강부(140)가 형성된 네 변의 길이가 동일한 정사각형 형상을 가질 수 있다.Referring to FIG. 4 , 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.
구체적으로, 셀(130)은 각 변의 길이(l)가 25mm 이상 35mm 이하이고, 각 변의 두께(d)가 0.5mm 이상 1mm 이하인 네 개의 변으로 이루어진 정사각형 형상을 가질 수 있다. Specifically, 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.
이처럼 셀(130)을 구성하는 변의 길이(l)가 종래의 낙뢰 보호 금속 망에 비하여 길게 형성됨으로써, 낙뢰보호장치(100)에 양각으로 형성되는 전기 전도를 위한 패턴은 낙뢰보호장치(100)의 표면적을 적게 차지하게 된다. 그러므로, 낙뢰보호장치(100)는 레이더 반사 면적(RCS)이 스텔스 기능이 저하될 정도로 증가되지 않아, 낙뢰보호장치(100)의 하부에 설치된 전자기파흡수장치(200)가 전자기파를 효과적으로 흡수할 수 있다.As such, 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. .
교차보강부(140)는 제1 평행부(110)와 제2 평행부(120)가 교차하는 셀(130)의 꼭지점에 해당되는 부분에 형성되며, 낙뢰의 전기 에너지를 주변으로 효과적으로 전달하는 기능을 수행한다.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. carry out
낙뢰보호장치(100)에 형성되는 전기 전도를 위한 패턴의 표면적이 작으면, 낙뢰 피격 시 전기 에너지를 주변으로 효과적으로 전달할 수 없게 되어 항공기용 날개(1)가 파손될 수 있다. 본 발명의 일 실시예에 따른 항공기용 날개(1)는 낙뢰보호장치(100)가 교차보강부(140)를 구비함으로써, 제1 평행부(110)와 제2 평행부(120)에 의해서 낙뢰보호장치(100)에 양각으로 형성되는 패턴이 작은 표면적을 가져도, 전기 에너지가 주변으로 효과적으로 전달되도록 할 수 있다.If the surface area of the pattern for electric conduction formed in the lightning protection device 100 is small, it is impossible to effectively transmit electric energy to the surroundings when being struck by lightning, and thus the aircraft wing 1 may be damaged. In the aircraft wing 1 according to an embodiment of the present invention, 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.
구체적으로, 교차보강부(140)는 제1 평행부(110)와 제2 평행부(120)가 교차하는 부분을 포함하도록 구성될 수 있다. 예를 들어 설명하면, 교차보강부(140)는 곡률 반지름이 0.05mm 이상 1.5mm 이하인 곡선으로 절단된 테두리 4개를 가지는 도형으로 이루어질 수 있다. Specifically, 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. For example, 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.
즉, 교차보강부(140)가 제1 평행부(110)와 제2 평행부(120)가 교차하는 부분을 포함하며 충분한 표면적을 가지는 도형으로 형성됨으로써, 낙뢰보호장치(100)는 낙뢰 피격 시 전기 에너지를 주변으로 효과적으로 전달할 수 있게 된다.That is, 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.
한편, 전술한 낙뢰보호장치(100)에 형성되는 제1 평행부(110) 및 제2 평행부(120)는 항공기용 날개(1)에 특정한 각도를 가지도록 배치됨으로써, 낙뢰 피격 시 전기 에너지를 주변으로 효과적으로 전달할 수 있다.On the other hand, the 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.
도 5는 항공기용 날개의 길이 방향 선분과 제1 평행부가 이루는 각도를 도시한 도면이고, 도 6은 항공기용 날개의 길이 방향 선분과 제2 평행부가 이루는 각도를 도시한 도면이다.5 is a view illustrating an angle formed by a longitudinal line segment of an aircraft wing and a first parallel portion, and FIG. 6 is a view illustrating an angle formed by a longitudinal line segment of an aircraft wing and a second parallel portion.
예를 들어, 도 5를 참조하여 설명하면, 제1 평행부(110)를 구성하는 복수 개의 평행선이 항공기용 날개(1)의 길이 방향 선분(y축 선분)과 이루는 각도(θ1)가 5도 이상 85도 이하가 되도록, 낙뢰보호장치(100)가 항공기용 날개(1)에 설치될 수 있다.For example, when described with reference to FIG. 5 , the angle (θ 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.
다른 예를 들어, 도 6을 참조하여 설명하면, 제2 평행부(120)를 구성하는 복수 개의 평행선이 항공기용 날개(1)의 길이 방향 선분(y축 선분)과 이루는 각도(θ2)가 5도 이상 85도 이하가 되도록, 낙뢰보호장치(100)가 항공기용 날개(1)에 설치될 수도 있다.For another example, referring to FIG. 6 , the angle (θ 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.
도 7은 항공기용 날개의 길이 방향 선분과 제1 평행부가 이루는 각도에 따른 전자기파 흡수 효율을 도시한 도면이다.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.
도 7을 참조하여 설명하면, 제1 평행부(110) 또는 제2 평행부(120)가 항공기용 날개(1)의 길이 방향 선분(y축 선분)과 이루는 각도가 5도 이상 85도 이하일 때, 외부에서 유입되는 전자기파를 효과적으로 흡수할 수 있음을 알 수 있다.7, when the angle between the first parallel part 110 or the second parallel part 120 and the longitudinal line segment (y-axis line segment) of the aircraft wing 1 is 5 degrees or more and 85 degrees or less , it can be seen that the electromagnetic wave introduced from the outside can be effectively absorbed.
이처럼, 제1 평행부(110) 또는 제2 평행부(120)가 항공기용 날개(1)의 길이 방향 선분과 특정한 각도를 이루도록 낙뢰보호장치(100)가 항공기용 날개(1)에 설치되면, 낙뢰보호장치(100)는 낙뢰 피격 시 전기 에너지를 주변으로 보다 효과적으로 전달할 수 있다.As such, 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.
이어서, 도 1을 참조하여, 전자기파흡수장치(200)의 구성에 관하여 설명한다.Next, with reference to FIG. 1 , the configuration of the electromagnetic wave absorption device 200 will be described.
전자기파흡수장치(200)는 복수 개의 전자기파흡수층이 조합되어 구성될 수 있다. 예를 들어 설명하면, 전자기파흡수장치(200)는 금속이 코팅된 유전체 섬유로 형성되며 낙뢰보호장치(100)의 하부에 설치되는 제1 전자기파흡수층(210), 제1 전자기파흡수층(210) 하부에 설치되며 유전체 섬유로 형성된 제2 전자기파흡수층(220), 낙뢰보호장치(100)의 상부에 설치되는 제3 전자기파흡수층(230)을 포함할 수 있다.The electromagnetic wave absorbing device 200 may be configured by combining a plurality of electromagnetic wave absorbing layers. For example, 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 .
이처럼, 전자기파흡수장치(200)는 제1 전자기파흡수층(210)과 제2 전자기파흡수층(220)을 구비함으로써, 외부에서 유입되는 전자기파를 효과적으로 흡수할 수 있다.As such, 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.
그리고, 전자기파흡수장치(200)가 낙뢰보호장치(100)의 상부에 제3 전자기파흡수층(230)을 구비함으로써, 전자기파가 효과적으로 흡수됨과 동시에 낙뢰보호장치(100)가 손상되지 않도록 보호될 수 있다.In addition, since 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.
이하, 본 발명의 항공기용 날개의 작용 및 효과를 구체적으로 설명한다.Hereinafter, the action and effect of the wing for an aircraft of the present invention will be described in detail.
특정한 패턴이 형성된 낙뢰보호장치(100) 및 전자기파흡수장치(200)가 설치된 항공기용 날개(1)가 낙뢰에 피격되면, 낙뢰보호장치(100)는 낙뢰에 의한 전기 에너지를 주변부 또는 접지 부분으로 전달하여 항공기용 날개(1)가 파손되는 것을 방지한다.When the wing 1 for an aircraft in which the lightning protection device 100 and the electromagnetic wave absorption device 200 are installed with a specific pattern are struck by lightning, 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.
이때, 낙뢰보호장치(100)에 형성된 전기 전도를 위한 패턴은 표면적이 작게 형성되지만, 교차보강부(140)가 충분한 표면적을 가지도록 형성되어 있어 낙뢰에 의한 전기 에너지를 주변부 또는 접지 부분으로 효과적으로 전달할 수 있다.At this time, 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. can
한편, 낙뢰보호장치(100)에 형성된 전기 전도를 위한 패턴은 표면적이 작게 형성되므로, 외부에서 유입되는 전자기파가 낙뢰보호장치(100) 하부에 설치된 전자기파흡수장치(200)로 효과적으로 유입되어 흡수될 수 있다.On the other hand, since 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.
그리고 전자기파흡수장치(200)는 금속이 코팅된 유전체 섬유를 포함하는 복수 개의 전자기파흡수층의 조합으로 형성되므로, 유입되는 전자기파를 효과적으로 흡수할 수 있다.And, since 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.
또한, 낙뢰보호장치(100)의 상부에도 전자기파흡수층이 설치될 수 있는데, 이처럼 설치된 전자기파흡수층은 낙뢰보호장치(100)가 파손되지 않도록 낙뢰보호장치(100)를 보호할 수 있다.In addition, 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.
이처럼, 본 발명에 따른 항공기용 날개는, 낙뢰보호장치가 교차보강부를 포함하는 특정한 패턴이 형성되므로, 항공기용 날개가 전자기파를 효과적으로 흡수하면서도 낙뢰 보호 기능을 갖출 수 있는 효과를 제공한다.As such, 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.
또한, 전자기파흡수장치가 금속이 코팅된 유전체 섬유로 형성된 전자기파흡수층을 포함하여 복수 개의 전자기파흡수층으로 구성됨으로써, 항공기용 날개가 전자기파를 효과적으로 흡수할 수 있는 효과를 제공한다.In addition, since 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.
이상에서 대표적인 실시예를 통하여 본 발명에 대하여 상세하게 설명하였으나, 본 발명이 속하는 기술 분야에서 통상의 지식을 가진 자는 상술한 실시예에 대하여 본 발명의 범주에서 벗어나지 않는 한도 내에서 다양한 변형이 가능함을 이해할 것이다. 그러므로 본 발명의 권리 범위는 설명된 실시예에 국한되어 정해져서는 안되며, 후술하는 청구범위뿐만 아니라 이 청구범위와 균등 개념으로부터 도출되는 모든 변경 또는 변형된 형태에 의하여 정해져야 한다.Although the present invention has been described in detail through representative embodiments above, those of ordinary skill in the art to which the present invention pertains can make various modifications to the above-described embodiments without departing from the scope of the present invention. will understand Therefore, the scope of the present invention should not be limited to the described embodiments and should be defined by all changes or modifications derived from the following claims as well as the claims and equivalent concepts.

Claims (9)

  1. 항공기용 날개 표면에 설치되어 낙뢰 피격 시 낙뢰의 전기 에너지를 주변으로 전달하며, 금속판에 양각으로 패턴이 형성된 낙뢰보호장치; 및a lightning protection device installed on the surface of an aircraft wing to transmit electrical energy of lightning to the surroundings when struck by lightning, and a embossed pattern formed on a metal plate; and
    상기 낙뢰보호장치와 접촉하도록 설치되어 전자기파를 흡수하며, 유전체 섬유로 형성된 전자기파흡수층을 포함하는 전자기파흡수장치를 포함하고,It is installed to contact the lightning protection device and absorbs electromagnetic waves, and includes an electromagnetic wave absorption device comprising an electromagnetic wave absorption layer formed of a dielectric fiber,
    상기 낙뢰보호장치의 상기 패턴은,The pattern of the lightning protection device,
    복수 개의 평행선을 포함하는 제1 평행부;a first parallel portion including a plurality of parallel lines;
    상기 제1 평행부와 교차하여 복수 개의 셀을 형성하는, 복수 개의 평행선을 포함하는 제2 평행부; 및a second parallel portion including a plurality of parallel lines intersecting the first parallel portion to form a plurality of cells; and
    상기 제1 평행부와 상기 제2 평행부가 교차하는 부분에 설치되는 교차보강부를 포함하는, 항공기용 날개.An aircraft wing comprising a cross reinforcement provided at a portion where the first parallel portion and the second parallel portion intersect.
  2. 제1항에 있어서,According to claim 1,
    상기 제1 평행부와 상기 제2 평행부는 직교하여 복수 개의 정사각형 형상의 셀을 형성하는, 항공기용 날개.The first parallel portion and the second parallel portion are orthogonal to form a plurality of square-shaped cells, aircraft wings.
  3. 제1항에 있어서,According to claim 1,
    상기 금속판은 전기 전도도가 1.25*106 S/m 인 금속으로 형성된 판이고,The metal plate is a plate formed of a metal having an electrical conductivity of 1.25*10 6 S/m,
    상기 셀의 한 변의 길이는 25mm 이상 30mm 이하이고, 상기 변의 두께는 0.5mm 이상 1mm 이하인, 항공기용 날개. The length of one side of the cell is 25mm or more and 30mm or less, and the thickness of the side is 0.5mm or more and 1mm or less, an aircraft wing.
  4. 제1항에 있어서,According to claim 1,
    상기 교차보강부는 곡률 반지름이 0.05mm 이상 1.5mm 이하인 테두리 4개를 가지는 도형으로 형성되는, 항공기용 날개.The cross-reinforcement portion is formed in a figure having four rims having a radius of curvature of 0.05 mm or more and 1.5 mm or less, an aircraft wing.
  5. 제1항에 있어서,According to claim 1,
    상기 제1 평행부를 구성하는 복수 개의 평행선이 상기 항공기용 날개의 길이 방향 선분과 이루는 각도가 5도 이상 85도 이하이거나,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,
    상기 제2 평행부를 구성하는 복수 개의 평행선이 상기 길이 방향 선분과 이루는 각도가 5도 이상 85도 이하인, 항공기용 날개.The angle formed by the plurality of parallel lines constituting the second parallel portion with the longitudinal line segment is 5 degrees or more and 85 degrees or less, an aircraft wing.
  6. 제1항에 있어서,According to claim 1,
    상기 전자기파흡수장치는,The electromagnetic wave absorption device,
    상기 낙뢰보호장치 하부에 설치되며, 금속으로 코팅된 유전체 섬유로 형성되는 제1 전자기파흡수층; 및a first electromagnetic wave absorbing layer installed under the lightning protection device and formed of a metal-coated dielectric fiber; and
    상기 제1 전자기파흡수층 하부에 설치되며, 유전체 섬유로 형성되는 제2 전자기파흡수층을 포함하는, 항공기용 날개.Installed under the first electromagnetic wave absorption layer, and comprising a second electromagnetic wave absorption layer formed of a dielectric fiber, aircraft wings.
  7. 제6항에 있어서,7. The method of claim 6,
    상기 전자기파흡수장치는,The electromagnetic wave absorption device,
    상기 낙뢰보호장치의 표면을 덮도록 설치되며, 유전체 섬유로 형성되는 제3 전자기파흡수층을 포함하는, 항공기용 날개.Installed to cover the surface of the lightning protection device, comprising a third electromagnetic wave absorption layer formed of a dielectric fiber, aircraft wings.
  8. 제1항에 있어서,The method of claim 1,
    상기 낙뢰보호장치는 상기 항공기용 날개의 앞전에 설치되는, 항공기용 날개.The lightning protection device is installed on the leading edge of the aircraft wing, aircraft wing.
  9. 제1항에 있어서,The method of claim 1,
    상기 유전체 섬유는 유리섬유(Glass fabric) 또는 케블라(Kevlar fabric)으로 형성되는, 항공기용 날개.The dielectric fiber is formed of glass fiber (Glass fabric) or Kevlar (Kevlar fabric), aircraft wings.
PCT/KR2021/007259 2020-08-27 2021-06-10 Aircraft wing having lightning protection function and electromagnetic wave absorption function WO2022045539A1 (en)

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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 (en) * 2016-08-16 2018-02-21 The Boeing Company Integrated current return network in composite structures
KR20180100348A (en) * 2015-12-30 2018-09-10 사이텍 인더스트리스 인코포레이티드 Multifunctional surface material with adaptive resistance
KR20180113120A (en) * 2017-04-05 2018-10-15 한국과학기술원 Wing airfoil structure including metal-coated fiber to absorb electromagnetic wave
KR20200059363A (en) * 2018-11-20 2020-05-29 국방과학연구소 Composite material layer, structural integrated fuel tank and aircraft comprising same

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 (en) * 2015-12-30 2018-09-10 사이텍 인더스트리스 인코포레이티드 Multifunctional surface material with adaptive resistance
EP3284680A1 (en) * 2016-08-16 2018-02-21 The Boeing Company Integrated current return network in composite structures
KR20180113120A (en) * 2017-04-05 2018-10-15 한국과학기술원 Wing airfoil structure including metal-coated fiber to absorb electromagnetic wave
KR20200059363A (en) * 2018-11-20 2020-05-29 국방과학연구소 Composite material layer, structural integrated fuel tank and aircraft comprising same

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