CN101855132A - 航空器组装品 - Google Patents

航空器组装品 Download PDF

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Publication number
CN101855132A
CN101855132A CN200980100974A CN200980100974A CN101855132A CN 101855132 A CN101855132 A CN 101855132A CN 200980100974 A CN200980100974 A CN 200980100974A CN 200980100974 A CN200980100974 A CN 200980100974A CN 101855132 A CN101855132 A CN 101855132A
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fastener
structural materials
outside plate
aircraft assembly
outside
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CN101855132B (zh
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神纳祐一郎
小栗和幸
中村康一
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Mitsubishi Heavy Industries Ltd
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Mitsubishi Heavy Industries Ltd
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • B29C65/562—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts to be joined
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • B29C65/562—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts to be joined
    • B29C65/564—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts to be joined hidden in the joint, e.g. dowels or Z-pins
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
    • B29C66/112—Single lapped joints
    • B29C66/1122—Single lap to lap joints, i.e. overlap joints
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
    • B29C66/41—Joining substantially flat articles ; Making flat seams in tubular or hollow articles
    • B29C66/43—Joining a relatively small portion of the surface of said articles
    • B29C66/434—Joining substantially flat articles for forming corner connections, fork connections or cross connections
    • B29C66/4344—Joining substantially flat articles for forming fork connections, e.g. for making Y-shaped pieces
    • B29C66/43441—Joining substantially flat articles for forming fork connections, e.g. for making Y-shaped pieces with two right angles, e.g. for making T-shaped pieces, H-shaped pieces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
    • B29C66/47—Joining single elements to sheets, plates or other substantially flat surfaces
    • B29C66/474—Joining single elements to sheets, plates or other substantially flat surfaces said single elements being substantially non-flat
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/723—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined being multi-layered
    • B29C66/7232—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined being multi-layered comprising a non-plastics layer
    • B29C66/72321—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined being multi-layered comprising a non-plastics layer consisting of metals or their alloys
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/74—Joining plastics material to non-plastics material
    • B29C66/742—Joining plastics material to non-plastics material to metals or their alloys
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B33/00—Features common to bolt and nut
    • F16B33/004—Sealing; Insulation
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/71—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the composition of the plastics material of the parts to be joined
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7212—Fibre-reinforced materials characterised by the composition of the fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/08—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers
    • B29C70/088—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers and with one or more layers of non-plastics material or non-specified material, e.g. supports
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/88—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
    • B29C70/882—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced partly or totally electrically conductive, e.g. for EMI shielding
    • B29C70/885—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced partly or totally electrically conductive, e.g. for EMI shielding with incorporated metallic wires, nets, films or plates
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
    • B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2305/00—Use of metals, their alloys or their compounds, as reinforcement
    • B29K2305/02—Aluminium
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2305/00—Use of metals, their alloys or their compounds, as reinforcement
    • B29K2305/08—Transition metals
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2307/00—Use of elements other than metals as reinforcement
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2309/00—Use of inorganic materials not provided for in groups B29K2303/00 - B29K2307/00, as reinforcement
    • B29K2309/08—Glass
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29K2705/00—Use of metals, their alloys or their compounds, for preformed parts, e.g. for inserts
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2995/00—Properties of moulding materials, reinforcements, fillers, preformed parts or moulds
    • B29K2995/0003—Properties of moulding materials, reinforcements, fillers, preformed parts or moulds having particular electrical or magnetic properties, e.g. piezoelectric
    • B29K2995/0005—Conductive
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • F16B37/14—Cap nuts; Nut caps or bolt caps

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  • Aviation & Aerospace Engineering (AREA)
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Abstract

本发明提供一种不易被雷电流破坏且具备高可信赖性的避雷结构的航空器组装品。其具备：将CFRP层(12)作为主结构的外板(10)、从内侧支承外板(10)的结合件(11)，将这些外板(10)和结合件(11)结合的紧固件(1)，在外板(10)的外表面侧，铜箔(13)及外侧GFRP层(14)以该顺序朝向外侧设置，在外侧GFRP层(14)上设有含有铜粉的铜质漆层(19)。

Description

航空器组装品
技术领域
本发明涉及一种具有避雷结构的航空器的主翼或机身等航空器组装品。
背景技术
要求航空器的机体(外板)材料为轻量且高强度，并具有耐久性，近年来，增加了利用纤维强化了的塑料(复合材料)的使用。
作为该复合材料例如多使用通过环氧树脂等加固了碳纤维的碳纤维强化树脂(CFRP)、通过环氧树脂等加固了玻璃纤维的玻璃纤维强化树脂(GFRP)。
这些复合材料与金属相比存在相对于落雷的抵抗力低的问题。另外，由于将外板固定于内部的构造材料的紧固件为金属制(例如钛合金)，因此，有可能因落雷而产生的电流(雷电流)通过紧固件，并在内部产生火花(电火花)。
因此，在外板使用复合材料时，要求制成考虑了避雷性的结构，尤其要求制成防止雷通过紧固件的结构。
作为这样的避雷性的结构，例如提案有专利文献1及专利文献2中记载的结构。
专利文献1所示的结构在紧固件的头部的外侧端安装有绝缘的帽，这样，提案有多个设计紧固件结构并防止雷的通过的结构。
专利文献2所示的结构在紧固件的周围装配有带(导电层)，且在紧固件的头部的上方设置绝缘层，使落雷导致的雷电流散逸在外板面。
专利文献1：美国专利第4630168号说明书
专利文献2：美国专利第5845872号说明书
但是，专利文献1所示的结构存在如下问题，即，绝缘性的帽位于外板的表面，在雷电流沿外板的表面流动时，雷电流必须绕开这些绝缘性的帽而流动，从而阻碍了雷电流的流动。
另外，专利文献2所示的结构，作为使雷电流散逸的导电层为仅设有一层金属箔的构成，因此，有可能由于雷电流而轻易地被破坏。另外，金属箔中，根据其厚度，也存在不进行破坏地输送雷电流的输送容量小的问题。
发明内容
本发明是鉴于上述情况而完成的，其目的在于提供一种不易被雷电流破坏且具备高可信赖性的避雷结构的航空器组装品。
为了解决上述课题，本发明的航空器组装品采用以下的装置。
即，本发明的航空器组装品的第一方式，其具备：以纤维强化塑料作为主结构的外板、从内侧支承该外板的结构材料、将这些外板和结构材料结合的紧固件，在所述外板的外表面侧设有导电箔，在该导电箔的上方设有含有导电性粉末的导电性树脂层。
航空器组装品被雷击时，由于雷击而产生的电流(以下称为“雷电流”)在位于上层的导电性树脂层中流动。该导电性树脂层为包含导电性粉末的树脂，因此，与导电箔相比，雷电流的输送容量大，且使雷电流散逸的能力高。因此，能够最大限度地抑制雷击导致的损伤。
另外，在导电性树脂层的下方设有导电箔，因此，即使万一由于雷击而破坏了导电性树脂层的情况下，也能够通过该导电箔使雷电流散逸。另外，导电箔不是网格形状而是设为箔即具有规定的剖面积并均匀地展开的面状的片，因此，与网格形状相比，输送雷电流的能力优异。
另外，作为“导电性树脂层”优选相对于酚醛树脂混合了铜粒子。
另外，在上述第一方式中，也可以是，所述紧固件插入贯通所述外板的所述主结构及所述导电箔、以及所述结构材料的插入孔内，位于所述外板的外表面侧的所述紧固件的头部上被覆有所述导电性树脂层。
紧固件插入贯通外板的主结构及导电箔、以及结构材料的插入孔内并配置。而且，紧固件的头部上被覆有导电性树脂层。由此，能够防止雷电流侵入紧固件内。
另外，为了提高紧固件的避雷性，优选紧固件的头部的外侧至少一部分由绝缘物形成。作为该绝缘物，优选热塑性聚酰亚胺树脂、PEEK等。
另外，在上述第一方式中，也可以是，所述紧固件具有从所述结构材料进一步向内侧突出的前端部，在该前端部设有被该前端部插入并将所述外板和所述结构材料固定的固定件，在所述结构材料和所述固定件之间插入有表面被覆了绝缘物的绝缘垫圈，同时，在所述结构材料和所述绝缘垫圈之间插入有绝缘隔片。
在表面被覆了绝缘物的绝缘垫圈的基础上还设置了绝缘隔片，因此，在组装时，增加了由于变形带来的剪切力，即使在绝缘垫圈的被覆绝缘物被剥离的情况下，也能够通过绝缘隔片确保绝缘。这样，通过绝缘垫圈及绝缘隔片双重地进行绝缘，能够提高可信赖性。
另外，雷电流通过紧固件内的情况下，有可能在固定件(例如螺母)和结构材料的微小间隙产生火花。本发明中，通过在固定件和结构材料之间插入被覆了绝缘物的绝缘垫圈和绝缘隔片，防止在微小间隙产生火花。尤其是作为通过结构体和绝缘垫圈而使绝缘隔片压缩变形的构成，能够吸收由紧固件装配时的误差产生的偏斜的微小间隙。
作为绝缘隔片优选聚酰亚胺，更有选的是在施加压缩力的方向层叠了多个片的构成。这是因为通过由多个片构成，假设即使一层片破损了，其它层的片也能有效地发挥作用。
另外，上述第一方式中，也可以在所述紧固件和所述插入孔之间设有绝缘性密封胶。
通过在紧固件和插入孔之间设置绝缘性密封胶，能够进一步提高紧固件和外板之间的绝缘性。
另外，在紧固件和插入孔之间设置绝缘性密封胶时，紧固件插入时，紧固件没有相对于插入孔正确地定位。具体而言，在紧固件涂布了绝缘性密封胶后，将紧固件插入插入孔，并将绝缘性密封胶固化并固定，因此，插入时紧固件不是以与插入孔相抵接的状态定位的。即，紧固件在插入时，相对于插入孔自由配合(即间隙配合)。这样的间隙配合中，没有正确地规定插入孔和紧固件之间的相对位置，因此，在结构材料、紧固件及固定件之间形成非预期的偏斜的微小间隙，而导致火花产生。这时，如果设置通过结构体和绝缘垫圈而压缩的绝缘隔片，则即使在间隙配合的情况下，也能够通过绝缘隔片的压缩变形来抑制微小间隙的偏在，能够防止火花的产生。
另外，本发明的航空器组装品的第二方式，其具备：以纤维强化塑料作为主结构的外板、从内侧支承该外板的结构材料、将这些外板和结构材料结合的紧固件，所述紧固件具有从所述结构材料进一步向内侧突出的前端部，在该前端部，经由表面被覆了绝缘物的绝缘垫圈，设有被该前端部插入并将所述外板和所述结构材料固定的固定件，在所述结构材料和所述绝缘垫圈之间插入有绝缘隔片。
在表面被覆了绝缘物的绝缘垫圈的基础上还设置了绝缘隔片，因此，在组装时，增加了由于变形带来的剪切力，即使在绝缘垫圈的被覆绝缘物被剥离的情况下，也能够通过绝缘隔片确保绝缘。这样，通过绝缘垫圈及绝缘隔片双重地进行绝缘，能够提高可信赖性。
另外，雷电流通过紧固件内的情况下，有可能在固定件(例如螺母)和结构材料的微小间隙产生火花。在上述第二方式中，通过在固定件和结构材料之间插入被覆了绝缘物的绝缘垫圈和绝缘隔片，防止在微小间隙产生火花。尤其是作为通过结构体和绝缘垫圈而使绝缘隔片压缩变形的构成，能够吸收由紧固件装配时的误差产生的偏斜的微小间隙。
作为绝缘隔片优选聚酰亚胺，更有选的是在施加压缩力的方向层叠了多个片的构成。这是因为通过由多个片构成，假设即使一层片破损了，其它层的片也能有效地发挥作用。
通过本发明，能够起到如下的作用效果。
设有导电性树脂层的同时，在其下方设有导电箔，因此，能够得到不易被雷电流破坏且具备高可信赖性的避雷结构的航空器组装品。
另外，通过在固定件和结构材料之间插入绝缘垫圈和绝缘隔片，而双重地进行绝缘，能够提高可信赖性。
附图说明
图1是表示本发明的航空器组装品即主翼的平面图；
图2是概略地表示结合件和外板的位置关系的剖面图；
图3是更详细地表示图2的剖面图；
图4是本实施方式的紧固件，是将其局部作为剖面表示的侧面图；
图5是实施例中作为比较例1使用的铝带的剖面图。
符号说明
1-紧固件
10-外板
11-结合件(结构材料)
13-铜箔(导电箔)
14-外侧GFRP层(绝缘层)
17-辅环(固定件)
18-绝缘性密封胶
19-铜质漆层(导电性树脂层)
21-绝缘垫圈
22-绝缘隔片
具体实施方式
下面，参照附图，对本发明的实施方式进行说明。
图1表示航空器的主翼(航空器组装品)A的平面图。棱线B包含配置后述的结合件(结构材料)11的位置，表示配置后述的铜质漆层(导电性树脂层)19以及铜箔(导电箔)13的区域。
图2概略地表示外板10和结合件(Sea-Tie)11的位置关系。结合件11是结合纵梁、棱等和外板10的部件，设为铝合金或钛合金、或CFRP(碳纤维强化塑料)这样的导电性材料。外板10和结合件11通过紧固件1进行固定。具体而言，通过在紧固件1的前端螺合轴环(螺母)17，将外板10和结合件11紧固并固定。
在轴环17和结合件11之间插入有绝缘垫圈21和绝缘隔片22。
轴环17、绝缘垫圈21、绝缘隔片22如图2的右侧所示，通过树脂等绝缘材料构成的绝缘帽24被覆整体。该绝缘帽24通过相对于结合件11密接并固定，能够兼做燃料(fuel)密封件。
图3更详细地表示图2所示的剖面。另外，图4是紧固件1的侧面图。
如图3及图4所示，紧固件1设置于圆柱形状的轴部(胫：Shank)2、及轴部2的一端侧，其构成为以具有随着远离轴部2而直径扩大的大致圆锥台形状的头部(埋头：flush head)3的紧固件主体4、位于头部3的一端部(图3及图4中位于上侧的顶部)绝缘头部5为主要要素。
紧固件4为轴部2和头部3一体形成的部件，例如，使用钛(Ti-6Al-4V：退火材料)或镍铬铁耐热耐蚀合金等合金制造。
在轴部2的另一端部(图3及图4中为下侧的端部)形成有与后述的轴环(螺母、固定件)的阴螺纹部螺合的阳螺纹部2a。
在头部3的顶部设有卡止绝缘头部5的紧固件侧卡合部7。该紧固件侧卡合部7具备位于轴部2的相反侧(图3及图4中为上侧)并且沿周方向向半径方向外侧突出(直径扩大)的凸部7a、将轴部2和凸部7a连接(连结)并且沿周方向向半径方向内侧凹下(凹陷)的凹部7b。
另外，在头部3的一端面的直径例如为12.7mm(1/2inch)左右。
绝缘头部5设为圆盘状的部件。作为绝缘头部5的材料例如优选耐热性及强度优异的热塑性聚酰亚胺树脂(例如可从三井化学(株)得到的AURUM)。作为除此以外的材料可以例举出其它的热塑性树脂(例如，除了具有耐热性、强度以外绝缘破坏电压高的聚醚酰亚胺(PEI)、除了耐热性、强度优异以外成形性、通用性优异的聚醚醚酮(PEEK)、除了具有耐热性、强度以外成形性、通用性优异的聚苯硫醚(PPS)、耐热性、强度尤其优异的聚酰胺-酰亚胺(PAI))。
在绝缘头部5的周缘部(图3及图4中为下侧的端部)设有与紧固件侧卡合部7卡合的绝缘体层侧卡合部8。该绝缘体层侧卡合部8具备：沿周方向向半径方向内侧凹下(凹陷)，并且与紧固件侧卡合部7的凸部7a吻合的凹部8a；沿周方向向半径方向外侧突出(直径扩大)，并且与紧固件侧卡合部7的凹部7b吻合的凸部8b。
另外，该绝缘部5通过注射成形安装于头部3的紧固件侧卡合部7。由此，紧固件侧卡合部7的外表面、绝缘体层侧卡合部8的内表面遍及整体密接，通过绝缘头部5自身具有的粘接力，绝缘头部5相对于头部3牢固地固定。
另外，绝缘头部5的板厚(顶面(图3及图4中位于上侧的平面)和底面(图3及图4中位于下侧的平面)之间的长度)例如优选设为0.5mm～1.0mm，以使其即使相对于MIL-STD-1757A Zonel的雷击试验电压(约40kV)也具有充分的绝缘耐力。
外板10以具有导电性(铝的1/100～1/1000左右的导电性)的树脂材料即CFRP(碳纤维强化树脂)层12为主结构。在CFRP层12的外表面(组装后位于外侧的面)整体上设置被设为具有绝缘性的GFRP(玻璃纤维固化树脂)的外侧GFRP层14，在CFRP层12的内表面(组装后位于内侧的面)整体上层叠有内侧GFRP层15。
另外，在CFRP层12和外侧GFRP层14之间设有其整体具有导电性的铜箔(导电箔)13。铜箔13的厚度约为70μm。
结合件11例如包含铝合金或钛材料、或者CFRP(碳纤维强化树脂)，配置于内侧GFRP15的背面(组装后位于内侧的面)上的规定位置。
在内侧GFRP15的背面上配置有结合件11的结构物的规定位置形成有插入孔16，其在板厚方向贯通这些外板10及结构物11，并能够收容紧固件1。而且，在各插入孔16收纳紧固件1，在从结合件11的背面向内侧突出的阳螺纹部2a例如螺合连结有使用钛或铬镍铁耐热耐蚀合金等合金制造的轴环17。
在紧固件1和插入孔16之间设有绝缘性密封胶18。作为绝缘性密封胶能够优选使用聚苯硫醚(PPS)。组装时，在紧固件1的轴部2及头部3涂布绝缘性密封胶18后，插入插入孔16内。因此，紧固件1的外形状比插入孔16小，紧固件1相对于插入孔16自由配合(即间隙配合)。
在紧固件1的外表面侧即绝缘头部5上设有铜质漆层(导电性树脂层)19。该铜质漆层19按照被覆紧固件1及其周围的方式设置。
铜质漆层19主要包含酚醛树脂和铜粉。作为铜粉可使用粒径范围为2～10μm、平均值为约5μm的电解铜粉。电解铜粉呈树枝状的尖形状，因此在确保导电性的方面优选。
酚醛树脂和铜粉的混合比以铜粉的体积比计为40～60％，优选约50％。
铜质漆层19通过在外板10的外侧GFRP层14及紧固件1的绝缘头部5的表面涂布后固化而形成。
铜质漆层19的厚度约为150μm。
另外，也可以取代用于铜质漆层19的酚醛树脂，使用环氧系或丙烯酸系的树脂。另外，可以取代铜粉，使用Ni、Au、Ag、Ag包覆Cu(由Ag被覆的Cu粒子)、石墨等导电性粒子。
图3中虽未显示，但在铜质漆层19上层叠有厚度约20μm的环氧系的底漆，进一步在其上层叠厚度约50μm的聚氨酯瓷漆系的外涂层。
在结合件11和轴环17之间插入有绝缘垫圈21和绝缘隔片22。
绝缘垫圈21是在不锈钢等金属材料本体的外表面涂抹了树脂(例如含铝粉树脂)等绝缘材料而形成的。
绝缘隔片22是层叠了多个聚酰亚胺的膜的结构。在通过轴环17紧固时向绝缘隔片22施加压缩力而变形。即使这样发生了变形，绝缘隔片22为层叠了多个绝缘膜的结构，因此，假设即使一张绝缘膜破裂了，该破裂并没有发展到其它绝缘膜上，因此，作为整体是难以破裂的结构。另外，作为绝缘隔片22，可以采用通过进一步层叠纤维而更难以破裂的结构。
将绝缘隔片22设为与绝缘垫圈21大致相等的直径。这是为了防止由于绝缘垫圈的压力而产生裂纹。
另外，可以相对于轴环17的绝缘垫圈21侧的端面上的外周缘及内周缘实施倒角。由此，能够防止绝缘垫圈21的损伤。
进行了上述的本实施方式的构成的航空器组装品的避雷性试验。
下表表示比较例1及2以及本发明的构成。除下表所示的构成以外，比较例1及2以及本发明都是相同的。
【表1】
 试验品   棱顶   棱线   火花的有无
 比较例1   铝带   铜箔   有
 比较例2   铜质漆   铜网   有
 本发明   铜质漆   铜箔   无
表1中，“棱顶”表示图3的铜质漆层19的位置，表示位于紧固件1正上方的部件。
如图5所示，铝带从外表面侧朝向内侧，以厚度为30μm的聚氨酯层31、厚度30μm的粘接层32、厚度20μm的Al层33、以及厚度30μm的粘接层34的顺序进行层叠。
比较例2及本发明中使用的铜质漆层的厚度设为150μm。这是按照使其具有与铝带相等电阻值的方式而选定的。
表1中，“棱顶”表示图3的铜箔13的位置，表示紧固件1周围的区域。铜箔的厚度设为70μm。比较例2中使用的铜网与实心的箔不同，在平面观测为网眼状。
避雷试验根据SAE APR5412A进行。通过利用相当于ASA3000的数码相机检测0.02mJ的火花来评价有无火花产生。从内面侧(图3的结合件11)进行摄影。
分别基于下表所示的条件，对9个试验面板分别进行避雷试验，即使发生了一次火花也评价为有火花，仅对一次也没发生火花的面板评价为无火花。
【表2】
 AppliedZone   Comp D   Comp B   Comp C*   Note
2A+   Peak I＝150KAAl＝1.125×106A2S   Max ChargeTransfer＝10C   Amp＞400ADwell Time＝45ms   50％margin
2A   Peak I＝100KAAl＝0.25×106A2S   Max ChargeTransfer＝10C   Amp＞400ADwell Time＝45ms
3+   Peak I＝60KAAl＝0.18×106A2S   Max ChargeTransfer＝10C   Amp＞400ADwell Time＝45ms   50％margin
表2中，“Applied Zone”表示航空器的避雷对策的区域。“+”表示增加50％雷电流下的评价。
“Comp D”、“Comp B”、“Comp C*”分别表示雷电流的成分。
如表1所示，只有本发明一次也没发现火花的产生。如果与比较例1相比较而言，这是由于铜质漆层19，如果与比较例2相比较而言，这是由于铜箔13。对于该结果，虽然详细的原理还不明确，因此也存在推测，但可知铜质漆层19与铝带相比，雷电流的输送容量及散逸能力优异，另外，铜箔13与铜网相比，雷电流的输送容量及散逸能力优异。
如以上所说明的，根据本实施方式，可以起到以下作用。
在主翼A被雷击时，雷电流在位于上层的铜质漆层19流动。该铜质漆层19为含有铜粉的树脂，因此，与铝带等导电箔相比，雷电流的输送容量大，且使雷电流散逸的能力高。因此，能够将雷击导致的损伤抑制得最小。
另外，在铜质漆层19的下方设有铜箔13，因此，即使万一由于雷击而破坏了铜质漆层19的情况下，也能够通过该铜箔13使雷电流散逸。另外，铜箔13不是网格形状而是设为箔即具有规定的剖面积并均匀地展开的面状的片，因此，与网格形状相比，输送雷电流的能力优异。
通过铜质漆层19被覆了紧固件1的绝缘头部5。由此，能够防止雷电流侵入紧固件1内。
另外，雷电流通过紧固件1内的情况下，有可能在轴环17和结合件11的微小间隙产生火花。本实施方式中，通过在轴环17和结合件11之间插入被覆了绝缘物的绝缘垫圈21和绝缘隔片22，防止在微小间隙产生火花。这样，通过绝缘垫圈21及绝缘隔片22双重地进行绝缘，能够提高可信赖性。尤其是设为通过结合件11和绝缘垫圈21而使绝缘隔片22压缩变形的构成，因此，能够吸收由紧固件1装配时的误差产生的偏斜的微小间隙。
使紧固件1相对于插入孔16间隙配合，因此，没有正确地规定插入孔16和紧固件1的相对位置，有可能在结合件11、紧固件1及轴环17之间形成非预期的偏斜的微小间隙，而导致火花产生。本实施方式中，设置了通过结合件11和绝缘垫圈21而压缩的绝缘隔片22，因此，即使在间隙配合的情况下，也能够通过绝缘隔片22的压缩变形来抑制微小间隙的偏在，能够防止火花的产生。
另外，绝缘隔片22为在施加压缩力的方向层叠了多个片的构成，因此，假设即使一层片破损了，其它层的片也能有效地发挥作用。
另外，上述的实施方式中，举出主翼A作为航空组装品的一例进行了说明，但航空组装品并不限定于此，例如可举出机身、尾翼等。
另外，绝缘隔片22作为层叠了多个层的构成进行了说明，但本发明并不限定于此，也可以是一层的热塑性聚酰亚胺树脂(例如可从三井化学(株)得到的AURUM)。

Claims (5)

1.一种航空器组装品，其具备：以纤维强化塑料为主结构的外板；从内侧支承该外板的结构材料；以及结合这些外板和结构材料的紧固件，其中，
在所述外板的外表面侧设置导电箔，
在该导电箔的上方设置有含有导电性粉末的导电性树脂层。
2.根据权利要求1所述的航空器组装品，其中，
所述紧固件被插入插入孔内，所述插入孔贯通所述外板的所述主结构及所述导电箔、以及所述结构材料，
位于所述外板的外表面侧的所述紧固件的头部上被覆有所述导电性树脂层。
3.根据权利要求2所述的航空器组装品，其中，
所述紧固件具有从所述结构材料更向内侧突出的前端部，
在该前端部设置被该前端部插入而固定所述外板和所述结构材料的固定件，
在所述结构材料和所述固定件之间插入有表面被覆了绝缘物的绝缘垫圈，并且，
在所述结构材料和所述绝缘垫圈之间插入有绝缘隔片。
4.根据权利要求3所述的航空器组装品，其中，
在所述紧固件和所述插入孔之间设置有绝缘性密封胶。
5.一种航空器组装品，其具备：以纤维强化塑料为主结构的外板；从内侧支承该外板的结构材料；以及结合这些外板和结构材料的紧固件，其中，
所述紧固件具有从所述结构材料更向内侧突出的前端部，
在该前端部，经由表面被覆了绝缘物的绝缘垫圈，设置被该前端部插入而固定所述外板和所述结构材料的固定件，
在所述结构材料和所述绝缘垫圈之间插入有绝缘隔片。
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