• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    COVERAGE, FIXING STRUCTURE USING THE SAME, AND AIRCRAFT INCLUDING THE FIXING STRUCTURE. A cover is provided that is able to obtain increased security by inhibiting the occurrence of sparks within it even if a lightning current has flowed through a fastener, a fastening structure using it, and an aircraft including the fastening structure. A cover (27) according to the present invention is fixed so as to cover a portion of a fastener (15) that couples an upper metallic lining (3) of an aircraft and a beam (11) located inside the upper metallic lining (3), the portion projecting through the beam (11), in which an outer surface (33) of the roof that comes into contact with an interior space of the upper metallic lining (3) is a curved surface, and the roof is made of conductive material.
    公开号:BR112012023333B1
    申请号:R112012023333-5
    申请日:2011-03-22
    公开日:2020-12-29
    发明作者:Kazuo Yamamoto；Nobuyuki Kamihara；Koichi Murakami
    申请人:Mitsubishi Heavy Industries, Ltd.；
    IPC主号:
    专利说明:

    Technical field
    [001] The present invention relates to a cover, a fixation structure using the same, and an aircraft including the fixation structure. Background art
    [002] A coating constituting an aircraft body is reinforced from the inside with a structural element that is a frame element formed in a grid configuration.
    [003] The coating and the structural element located inside the coating are connected with a fastener. Since the fixer is made of metal (for example, a titanium alloy), there is the possibility of a ray of lightning that can pass through the fixer and generate sparks internally.
    [004] For this reason, a structure to inhibit a ray of lightning from passing through the fixer has been proposed, for example, as revealed in the patent literature 1.
    [005] In the structure revealed in patent literature 1, an insulating cover is mounted on the outer end of a fixer's head, and many structures have been proposed that inhibit the passage of a lightning bolt by idealizing the fixer's structure in this way. Citation list PTL patent literature 1 Japanese unexamined patent application, publication no. 2007-126119 Summary of the invention Technical problem
    [006] With conventional structures in which a coating and a structural element are coupled to a fastener, a corner is present in a portion of the fastener that projects from the structural element. Therefore, when a current flows through the fastener, the electric field tends to be concentrated in the corner. In the case where an aircraft was struck by lightning, after a current flowed through the fixer, concentration of the electric field occurs in the corner even if inhibition measurements were taken, and thus sparks tend to occur. For example, when sparks occur in a fuel tank containing a flammable as a fuel inside, there is the possibility of an explosion due to ignition of the fuel.
    [007] In view of such circumstances, it is an objective of the present invention to provide a cover capable of obtaining increased safety by inhibiting the occurrence of sparks inside even if a lightning current has flowed through a fastener, a fastening structure using the same and an aircraft including the fastening structure. Solution to the problem
    [008] To solve the problem described above, the present invention adopts the following means.
    [009] That is, a first aspect of the present invention is a cover that is fixed so as to cover a portion of a fastener that engages an aircraft jacket and a structural element located within the jacket, the portion projecting through the element structural, where an outer surface of the roof that comes into contact with an interior space of the roof is a curved surface, and the roof is made of a conductive material.
    [010] The cover according to the first aspect of the present invention is made of a conductive material and is fixed so as to cover a portion of a fastener that couples an aircraft jacket and a structural element located inside the jacket, to basement projecting through the structural element. Therefore, the discharge current that passes through the fastener flows through the interior of the cover. This makes it possible to inhibit concentrations of the electric field in a corner of the fastener that is located in the portion described above.
    [011] Since the outer surface of the cover that comes into contact with the interior space of the cover, for example, the exposed surface inside a tank is a curved surface, there is no corner on the outer surface of the cover that comes in contact with the interior space of the coating. Therefore, a portion where the electric field is concentrated is not present on the outer surface of the roof, and therefore it is possible to inhibit the occurrence of sparks caused by the concentration of the electric field.
    [012] For example, the use of this cover for a fuel tank containing a flammable as a fuel inside can suppress the possibility of explosion due to the ignition of the fuel caused by the occurrence of sparks, and therefore it is possible to obtain increased security.
    [013] In the first aspect described above, it is preferable that the cover includes a contact surface coming into contact with the structural element.
    [014] This allows the current flowing from the fastener to the cover to flow through the contact surface to the structural element and, therefore, the resistance of the current flowing from the fastener to the structural element is effectively decreased. When the resistance of the current flowing from the fastener to the structural element is decreased, the current value is decreased, and therefore it is possible to further inhibit the occurrence of sparks.
    [015] The contact surface is in contact with the structural element and therefore does not correspond to the external surface that comes in contact with the interior space of the coating and, therefore, a corner may be present.
    [016] A second aspect of the present invention is a cover which is fixed in such a way as to cover a portion of a fastener that engages an aircraft jacket and a structural element located within the jacket, the portion projecting through the structural element, wherein the cover includes a contact surface contacting the structural element and is made of a conductive material.
    [017] The cover according to the second aspect of the present invention is made of a conductive material and is fixed so as to cover a portion of a fastener that couples an aircraft jacket and a structural element located within the jacket, the portion projecting through the structural element. Therefore, the discharge current that passes through the fastener flows through the interior of the cover. This makes it possible to inhibit the concentration of the electric field in a corner of the fastener that is located in the portion described above.
    [018] In addition, since the current flowing from the fastener to the cover flows through the contact surface to the structural element, the resistance of the current flowing from the fastener to the structural element is effectively decreased. When the resistance of the current flowing from the fastener to the structural element is decreased, the current value is decreased and therefore it is possible to further inhibit the occurrence of sparks.
    [019] For example, the use of this cover for a fuel tank containing a fuel as a fuel inside can suppress the possibility of an explosion due to fuel ignition caused by the occurrence of sparks, and therefore it is possible to obtain increased security.
    [020] The contact surface is in contact with the structural element and therefore does not correspond to the outer surface coming into contact with the interior space of the coating, and therefore a corner may be present.
    [021] A third aspect of the present invention is a fastening structure in which an aircraft jacket and a structural element located inside the jacket are coupled by a fastener, in which a portion of the fastener that projects through the structural element is covered by coverage according to the first or second aspect.
    [022] With the fastening structure according to the third aspect of the present invention, the portion of the fastener that protrudes through the structural element is covered by the cover according to the first or second aspect, and it is therefore possible to inhibit sparks occur even if a discharge current flows through the fastener.
    [023] For example, the use of this fixation structure as a fixation structure for a fuel tank containing a flammable as a fuel inside can suppress the possibility of explosion due to fuel ignition caused by the occurrence of sparks. , and therefore it is possible to obtain increased security.
    [024] A fourth aspect of the present invention is an aircraft in which a liner and a structural element located within the liner are at least partially fixed by the fixing structure according to the third aspect.
    [025] With the aircraft according to the fourth aspect of the present invention, a lining and a structural element located inside the lining are at least partially fixed by the fixation structure capable of inhibiting the occurrence of sparks. Therefore, for example, the use of this fixation structure as a fixation structure for a fuel tank containing an inflammable as a fuel inside can suppress the possibility of explosion due to fuel ignition caused by the occurrence of sparks, and, therefore, it is possible to obtain increased security. Advantageous effects of the invention
    [026] According to the present invention, the cover is made of a conductive material and is fixed in such a way as to cover a portion of a fastener that couples an aircraft jacket and a structural element located inside the jacket. , the portion projecting through the structural element. Therefore, the discharge current that passes through the fastener flows through the interior of the cover. This makes it possible to inhibit the concentration of the electric field in a corner of the fastener that is located in the portion described above.
    [027] The outer surface of the cover that comes into contact with the interior space of the liner, for example, the exposed surface inside a tank is a curved surface, and / or the cover includes a contact surface coming into contact with the element structural, and therefore it is possible to inhibit the occurrence of sparks caused by concentration of electric field.
    [028] For example, the use of this cover for a fuel tank containing a flammable as a fuel in the interior can suppress the possibility of explosion due to the ignition of the fuel caused by the occurrence of sparks, and therefore it is possible to obtain increased security. Brief description of the drawings Figure 1
    [029] Figure 1 is a perspective view illustrating the configuration of a main wing equipped with a fuel tank using a fastening structure according to an embodiment of the present invention. Figure 2
    [030] Figure 2 is a cross-sectional view that illustrates the fuel tank configuration shown in figure 1 taken along the arrow X-X. Figure 3
    [031] Figure 3 is a cross-sectional view that illustrates the configuration of a fixing portion between an upper cladding and a beam shown in figure 2. Description of modalities
    [032] In the following, a fixation structure according to an embodiment of the present invention will be described in detail with reference to figures 1 to 3.
    [033] Figure 1 is a perspective view that illustrates the configuration of a main wing equipped with a fuel tank using a fastening structure in accordance with the present modality. Figure 2 is a cross-sectional view that illustrates the fuel tank configuration shown in Figure 1 taken along the arrows X-X.
    [034] As shown in figures 1 and 2, a main wing 1 is mainly provided with an upper lining (lining) 3, a lower lining (lining) 5, stringers (structural elements) 7, ribs (structural elements) ) 9 and beams (structural elements) 11.
    [035] In addition, a fuel tank 13 is provided integrally with the main wing 1 inside, or in other words, the interior space of the main wing 1.
    [036] The upper lining 3 and the lower lining 5 are thin plates that form the external shape of the main wing 1, and serve to support a portion of the traction load and compression load that act on the main wing 1, together with side members 7, ribs 9 and beams 11.
    [037] The upper lining 3 is a thin plate that forms the upper face of the main wing 1, and the lower lining 5 is a thin plate constituting the lower face of the main wing 1.
    [038] The top 3 and bottom 5 are made of, for example, a carbon fiber reinforced plastic (CFRP) that uses an epoxy based resin as the base material and also uses carbon fiber as the fiber reinforcement. The top coating 3 and the bottom coating 5 can also be made of, for example, a metal such as an aluminum alloy.
    [039] As shown in figures 1 and 2, the stringers 7 are structural elements that extend in the span direction of the main wing 1 (the direction perpendicular to the paper plane in figure 2), and are arranged extending between the top coat 3 and bottom coat 5.
    [040] In the present modality, a description will be given of an example in which the side members 7 are respectively arranged on the leading edge LE and the leading edge TE side of the main wing 1.
    [041] As shown in figures 1 and 2, beams 11 are structural elements extending between a pair of stringers 7 in the span of the main wing 1 (the direction perpendicular to the paper plane in figure 2), and serve to assist the stringers 7 in the resistance.
    [042] The side members 7 and beams 11 are used to transmit, to the aircraft fuselage (not shown) to which the main wing 1 is attached, the bending and torsional forces exerted on the main wing 1 acting in the front-rear direction. and in the up-down direction.
    [043] As shown in figures 1 and 2, the ribs 9 are structural elements extending in the rope direction of the main wing 1 (the right-left direction in figure 2) and arranged extending between the top 3 and bottom 5 In other words, the ribs 9 are structural elements extending in a substantially orthogonal direction to the stringers 7 and beams 11, and are elements similar to the plate molded to have the shape in cross section of the main wing 1.
    [044] The side members 7, the ribs 9 and the beams 11 are made, for example, of a metal such as an aluminum alloy. Alternatively, they can be partially made of metal, or they can be made entirely of fiber-reinforced plastic, such as CFRP.
    [045] Fuel tank 13 is a tank in which an aircraft fuel (fuel) is stored, and its storage space is formed by the interior of the main wing 1 divided by the upper shell 3, the lower shell 5, a pair of stringers 7 and a plurality of ribs 9 as shown in figures 1 and 2. The fuel tank 13 is an integral tank that is integrally formed with the main wing 1.
    [046] Installed inside the fuel tank 13 are fuel tubes (omitted in the drawing) for receiving and supplying fuel and wiring (omitted in the drawing) for a metering system to measure the amount of fuel.
    [047] The side members 7, the beams 11, and the ribs 9 are attached to the top cladding 3 and the bottom cladding 5 with fasteners 15 made of a metal. The fasteners 15 can be made, for example, from an aluminum or titanium alloy.
    [048] Figure 3 is a cross-sectional view illustrating the configuration of a fixing structure 17 between the top cladding 3 and a beam 11 shown in figure 2.
    [049] A fastener 15 includes a cylindrically extended stem portion 19 and a head portion 21 arranged at one end of the stem portion 19.
    [050] The head portion 21 is shaped like a truncated cone. A small diameter portion of the head portion is configured to connect to the stem portion 19 having a diameter substantially the same as that of the small diameter portion of the head portion. An external thread 23 is notched on the other end (the side opposite the head portion 21) of the stem portion 19.
    [051] The fastener 15 is arranged in such a way that the stem portion 19 is inserted into a direct hole formed in the upper cladding 3 and beam 11 and head portion 21 are incorporated in the upper cladding 3.
    [052] The stem portion 19 is configured to project from the beam 11 into the interior space of the fuel tank 13. The fastener 15 fixes the upper casing 3 and the beam 11 by a nut 25 being engaged threaded with the external thread 23 of the stem portion 19 and thus being moved towards the beams 11.
    [053] A cover 27 is provided that covers the portion of the fastener 15 that is located inside the fuel tank 13, or in other words, the portion that protrudes from the beam 11 through the interior of the fuel tank 13, and because 25.
    [054] The cover 27 is shaped like a substantially spherical body that is cut by a plane. This section plane constitutes a contact surface 29 coming into contact with beam 11 serving as a structural element.
    [055] A housing space 31 for housing the portion of the fastener 15 projecting from the beam 11 and the entire nut 25 is formed in the central portion of the contact surface 29. The cover 27 is mounted in a state in which the housing space 31 houses the portion of the fastener 15 that protrudes from the beam 11 and the entire nut 25 and that the contact surface 29 is in contact with the beam 11. In other words, the cover 27 is fixed so as to cover the portion of the fastener 15 projecting through the beam 11 and the entire nut 25.
    [056] The outer surface 33 of the cover 27, excluding the contact surface 29, faces the interior space of the top liner 3, in other words, the interior space of the fuel tank 13. During assembly of the cover 27, the outer surface 33 comes into contact with the interior space of the top cladding 3. On the other hand, the contact surface 29 is in contact with the beam 11, and thus will not be in contact with the interior space of the top coating 3.
    [057] The eternal surface 33 forms a part of a substantially spherical body, and therefore is a curved surface. The shape of the outer surface 33 is not limited to a part of a spherical body, and can be any suitable shape that constitutes a curved surface.
    [058] Although a corner is formed at the boundary between the contact surface 29 and the outer surface 33, that corner does not correspond to the outer surface 33 coming into contact with the inner space of the top lining 3 because the contact surface 29 is in contact with beam 11.
    [059] The cover 27 is made, for example, of an aluminum alloy. The material that forms the cover 27 is not limited to an aluminum alloy, and can be any suitable conductive material.
    [060] In this case, it is preferable, when inhibiting the occurrence of electrolytic corrosion, to use a material having an electrical resistance substantially equal to that of the materials of the fastener 15 and beam 11.
    [061] The cover 27 can also be fixed by notching an internal thread in the housing space 31 and screwing the internal thread into thread with the external thread 25 of the fastener 15 such that the contact surface 29 is in firm contact with beam 11.
    [062] When a gap is created between the contact surface 29 and the beam 11, a conductive grease can be disposed between the contact surface 29 and the beam 11 in order to ensure conductivity.
    [063] Alternatively, a seal can be arranged between the contact surface 29 and the beam 11 in order to obtain increased adhesive capacity. In this case, for example, it is preferable to provide the contact surface 29 with a projection and firmly push the contact surface 29 in order to be incorporated on the side of the beam 11, thereby ensuring conductivity.
    [064] The fastening structure provided by the fastener 15 between the top cladding 3 and the bottom cladding 5, and the side members 7 and the ribs 9 includes the cover 27 described above.
    [065] An operation of the fixture structure 17 according to the present embodiment configured as described above will now be described.
    [066] When lightning strikes near the fastener 15, the discharge current flows through the fastener 15. The discharge current flowing through the fastener 15 flows from the fastener 15 to the beam 11, while flowing from the fastener 15 through the interior of the cover 27 to the beam 11 via contact surface 29.
    [067] In this way, the discharge current flows from the fastener 15 through the interior of the cover 27 to the beam 11, and therefore it is possible to inhibit the concentration of the electric field in a corner of the fastener 15 located in that portion, for example , the distal end of the external thread 23 or the end of the fastener 15.
    [068] Since the outer surface 33 of the cover 27 is a curved surface, there is no corner. Therefore, the outer surface 33 of the cover 27 has no portion where the electric field is concentrated, and therefore it is possible to inhibit the occurrence of sparks caused by the concentration of the electric field.
    [069] Furthermore, since the discharge current that flowed from the fastener 15 to the roof 27 flows through the contact surface 29 to the beam 11, the area in which the current is transmitted is increased in comparison with a structure including only one path in which the current flows from the fastener 15 directly to the beam 11. Consequently, the resistance of the current flowing from the fastener 15 to the beam 11 is effectively decreased. When the resistance of the current flowing from the fastener 15 to the beam 11 is decreased, the current value is decreased, and therefore it is possible to further inhibit the occurrence of sparks.
    [070] Therefore, it is possible to sufficiently suppress the possibility of explosion due to the ignition of the fuel caused by the occurrence of sparks inside the fuel tank 13, thereby increasing the safety of the aircraft. In addition, since the lightning protection structure for the fastener 15 and the like can be made simple and more workable, it is possible to reduce the manufacturing costs.
    [071] It must be recognized that the present invention is not limited to the modalities described above, and several modifications can be made without departing from the essence of the present invention.
    [072] For example, in the case where a wide contact surface 29 can be ensured and the resistance of the chain flowing from the fastener 15 to the beam 11 can be sufficiently decreased, the outer surface 33 can have a corner. List of reference signs 1 main wing 3 top cladding 5 bottom cladding 7 stringer 9 rib 11 beam 15 fastener 17 fastening structure 27 cover 29 contact surface 33 outer surface
    权利要求:
    Claims (2)
    [0001]
    1. A fixing structure (17) comprising: an aircraft jacket (3); a structural element (11) located within the liner (3); a fastener (15) that couples the liner (3) and the structural element (11); a nut (25) engaged with a portion of the fastener, the portion projecting through the structural element and towards the interior of the liner (3); and a cover (27) covering the portion of the fastener (15) and the nut (25), the portion projecting through the structural element (11) and towards the interior of the coating (3), FEATURED by the fact that the cover (27) is fixed so as to cover the portion of the fastener (15) that penetrates the beam and the entire nut (25), the cover (27) includes a contact surface (29) that comes into contact contact with the structural element (11) and is made of a conductive material, and an entire outer surface (33) of the cover (27) that comes into contact with an interior space of the coating (3) is a curved surface.
    [0002]
    2. Aircraft CHARACTERIZED by the fact that a lining (3) and a structural element (11) located inside the lining (3) are at least partially fixed by the fixing structure (17) as defined in claim 1.
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    同族专利:
    公开号 | 公开日
    RU2531113C2|2014-10-20|
    CA2792105C|2014-05-06|
    US20130043351A1|2013-02-21|
    CN105129100A|2015-12-09|
    EP2551187B1|2020-06-17|
    WO2011118558A1|2011-09-29|
    CN102883949A|2013-01-16|
    EP2551187A1|2013-01-30|
    US9108743B2|2015-08-18|
    CA2792105A1|2011-09-29|
    EP2551187A4|2016-11-23|
    JP5619446B2|2014-11-05|
    CN102883949B|2015-09-16|
    CN105129100B|2018-03-23|
    RU2012138584A|2014-04-27|
    BR112012023333A2|2016-05-24|
    JP2011195114A|2011-10-06|
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    法律状态:
    2019-01-08| B06F| Objections, documents and/or translations needed after an examination request according art. 34 industrial property law|
    2019-10-29| B06U| Preliminary requirement: requests with searches performed by other patent offices: suspension of the patent application procedure|
    2020-07-07| B06A| Notification to applicant to reply to the report for non-patentability or inadequacy of the application according art. 36 industrial patent law|
    2020-10-20| B09A| Decision: intention to grant|
    2020-12-29| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 22/03/2011, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    JP2010066927A|JP5619446B2|2010-03-23|2010-03-23|Cap, fastening structure using the cap, and aircraft having the fastening structure|
    JP2010-066927|2010-03-23|
    PCT/JP2011/056744|WO2011118558A1|2010-03-23|2011-03-22|Cap, fastened structure using same, and aircraft having said fastened structure|
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