CN103391840B - 用于飞机或航天器的连接器及连接器的制造方法 - Google Patents

用于飞机或航天器的连接器及连接器的制造方法 Download PDF

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CN103391840B
CN103391840B CN201280009925.1A CN201280009925A CN103391840B CN 103391840 B CN103391840 B CN 103391840B CN 201280009925 A CN201280009925 A CN 201280009925A CN 103391840 B CN103391840 B CN 103391840B
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connector
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CN103391840A (zh
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马太依斯·波罗克尔
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Airbus Operations GmbH
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J15/00—Riveting
    • B21J15/02—Riveting procedures
    • 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
    • B29C65/60—Riveting or staking
    • B29C65/601—Riveting or staking using extra riveting elements, i.e. the rivets being non-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
    • 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
    • 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
    • B29C66/40—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
    • B29C66/472—Joining single elements to sheets, plates or other substantially flat surfaces said single elements being substantially 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
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    • 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
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    • B29C66/73—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 intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset
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    • B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
    • B29C73/04—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements
    • B29C73/10—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D using preformed elements using patches sealing on the surface of the article
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/40—Maintaining or repairing aircraft
    • 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
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    • F16B19/00—Bolts without screw-thread; Pins, including deformable elements; Rivets
    • F16B19/04—Rivets; Spigots or the like fastened by riveting
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
    • B29C65/5057—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like positioned between the surfaces 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
    • B29C66/70—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
    • 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
    • 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
    • B29C66/90—Measuring or controlling the joining process
    • B29C66/95—Measuring or controlling the joining process by measuring or controlling specific variables not covered by groups B29C66/91 - B29C66/94
    • B29C66/959—Measuring or controlling the joining process by measuring or controlling specific variables not covered by groups B29C66/91 - B29C66/94 characterised by specific values or ranges of said specific variables
    • B29C66/9592—Measuring or controlling the joining process by measuring or controlling specific variables not covered by groups B29C66/91 - B29C66/94 characterised by specific values or ranges of said specific variables in explicit relation to another variable, e.g. X-Y diagrams
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3076—Aircrafts
    • B29L2031/3082—Fuselages
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3097—Cosmonautical vehicles; Rockets
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
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    • Y10T29/49826—Assembling or joining
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Abstract

本发明提供一种连接器(100)的制造方法，特别是用于航空及航天领域的修复，该方法包含以下步骤：提供一基材层(102)；将具有一第一刚性的纤维复合材料的一第一层(200)贴置在所述基材层(102)上；将具有一第二刚性的纤维复合材料的一第二层(202)贴置在所述第一层(200)上，并由此形成偏移，且所述第二刚性大于所述第一刚性；及将所述第一层(200)铆接至所述基材层(102)上，且将所述第二层(202)铆接至所述第一层(200)及所述基材层(102)上。

Description

用于飞机或航天器的连接器及连接器的制造方法
技术领域
本发明涉及一种飞机或航天器、连接器及连接器的制造方法。
背景技术
图1A为一种公知的修复方法所完成的一连接器100的俯视图。图1B是沿图1A的直线I-I的剖视图。
所述连接器100包含飞机或航天器的一外壳层部102(不详述细节)，其在一个破洞104的形状中具有一损坏区域。所述外壳层部102例如由一种纤维复合材料以碳纤维强化塑料(CFRP)的形式所形成。
为了修复所述外壳层部102，公知的是在所述外壳层部102上设置一补片106，以这种方式将所述补片106覆盖在所述破洞104上。所述补片106也可以由一种纤维复合材料制成，特别是碳纤维强化塑料。
之后，所述补片106铆接至由所述破洞104划界的边缘区域108。在图1A、1B中相应的所述铆钉分别被标记为112、114。为了更清楚地说明，图1A、1B的所述铆钉数目没有匹配。
如图1A所示，如果作用于该连接器100的一负载F与同样设置于该连接器100的铆钉112、114为由左到右的同一方向，如图3的点画线所示，最外边的每一铆钉112承受所述最大负载，例如每一承受量为负载的40％，在此同时，内部的所述铆钉114只能承受一小部分的负载，例如仅为负载的10％。所述铆钉在如图1A的X轴所示，每一铆钉承载的负载FN如Y轴所示。这是一个单纯的定性分析方法以说明现有的问题。
所述外铆钉112承受一相对高负载FN，并且取决于所述外壳层部102的组成物。这意味着所述外壳层部102无法轻易地利用公知的现有技术进行修补，因为这会导致在所述外壳层部102中的所述外铆钉112在相应点被拉出。然而，即使所述外壳层部102以一个适当稳定的方法形成，而所述补片106也以一相应稳定的方法提供，用以使所述负载FN在所述外铆钉112的点可被承受，这从现有技术公知的方法仍然会造成问题，不管如何，都带来关于重量上的缺点。
另外，在现有技术中，德国专利第DE 10 2009 001 075 A1号揭露了公知的一种修复方法。
发明内容
因此，本发明的目的在于提供一种连接器的制造方法，特别是用于修复，用以至少改善所述的缺点。
为实现所述目的，是通过本发明的一种方法所具有的特征，通过本发明的一种连接器所具有的特征及通过本发明的一种飞机或航天器所具有的特征。
根据本发明所提供的如下所示：
一种连接器的制造方法，特别是用于航空及航天领域的修复，包含步骤：提供一基材层；将具有一第一刚性的纤维复合材料的一第一层贴置在所述基材层上；将具有一第二刚性纤维复合材料的一第二层贴置在所述第一层上，并由此形成偏移，且所述第二刚性大于所述第一刚性；及将所述第一层铆接至所述基材层上，且将所述第二层铆接至所述第一层及所述基材层上。
另外，提供一连接器，特别是用于飞机或航天器上，其包含：一基材层；纤维复合材料的一第一层，具有一第一刚性，并贴置在所述基材层上；纤维复合材料的一第二层，具有一第二刚性，并贴置在所述第一层上，由此形成偏移，且所述第二刚性大于所述第一刚性；及多个铆钉，分别连接所述第一层至所述基材层，以及连接所述第二层至所述第一层与所述基材层。
此外，根据本发明提供的一种飞机或航天器，包含所述连接器。
本发明基于以下得到的结果：所述负载可均匀地分布于被连接的所述基材层中的数个铆钉之间(特别是在修复中)，所述基材层铆接于一纤维复合材料的第一层以及设置在所述第一层上的一纤维复合材料的第二层，所述第一层及被设置的第二层会彼此偏移，且所述第二层具有的刚性高于所述第一层。
如果使用这种方式，例如在前言所描述的修复方法，一补片，其包含所述第一层及所述第二层，且被铆接至所述外壳层部。由于所述负载更均匀地分布在所述铆钉之间，较薄的外壳层部可被修复，且所述补片具有较低的稳定性，因而可使用较轻的重量。
本发明提供的较佳形态在从属权利要求中。
特别要说明的是，根据本发明的方法，其不仅可用于修复，也可以用于连接二基材层，例如二桁条(stringer)。
在本文中，「刚性(rigidity)」经常是关于每一层的弹性模量，特别是测量帕斯卡(pascals)。
根据本发明的方法的一种形态，所述第一刚性为所述第二刚性的25％至75％，优选为45％至55％，依这种方式。所述负载可特别均匀地分布在所述铆钉之间。
根据本发明的方法的另一种形态，所述基材层的刚性为所述第二刚性的80％至120％，优选为95％至105％。依这种方式，所述负载可更均匀地分布在所述铆钉之间。
根据本发明的方法的另一种形态，所述第一层及第二层分别提供作为贴补片，并连接至所述基材层的一边缘区域，所述边缘区域包围一损坏区域，特别是一个孔或一条裂痕。因此，所述方法是一种易于配置的修复方法。
根据本发明的方法的另一种形态，所述第一层及第二层分别提供作为连接器，并连接至所述基材层的一个部分，而且从所述基材层的另一部分连接至相隔有一距离的另一基材层。因此，所述方法是一种易于配置的用于二基材层相互连接的方法，例如二桁条。
根据本发明的方法的另一种形态，所述基材层及/或所述另一基材层形成作为一蒙皮(skin)、一桁条或一成型件(former)。所述结构组件可益于相互连接。
根据本发明的方法的另一种形态，所述基材层由纤维复合材料所构成，及/或所述基材层、另一基材层、第一层及/或第二层的纤维复合材料选自于以下群组：玻璃纤维塑料、碳纤维强化塑料或玻璃纤维金属层压板。所述玻璃纤维金属层压板，例如作为一层压板，其包含玻璃纤维材料及铝材料的数个交替层(也称为)。
根据本发明的方法的另一种形态，所述第一刚性、第二刚性及所述基材层的刚性分别对应于相同的预定负载方向。这对于各向异性的纤维材料具有特别重要的意义。
以下将对本发明的实施方式有更详细的描述，参阅附图，其中：
附图说明
图1A是公知现有技术的一种连接器的上视图；
图1B是从图1A的Ⅰ-Ⅰ线的剖视图；
图2A是根据本发明一实施例的连接器的上视图；
图2B是从图2A的Ⅱ-Ⅱ线的剖视图；
图2C是根据图2A的实施例变化的剖视图；及
图3是显示每一铆钉所承受的负载的示意图。
具体实施方式
在附图中，除非另有说明，不然相同的标号表示相同或功能等同的元件。
如图2A的上视图，及由图2A的Ⅱ-Ⅱ线的图2B的剖视图所示，为根据本发明的一个实施例的连接器100。
所述连接器100包含一外壳层部(skin portion)102，其具有一损坏区域104，在一个破洞的形状中，所述外壳层部102的形成，可例如由碳纤维强化塑料(CFRP)。所述外壳层部102，可例如为一飞机的组件在操作时损坏而导致形成所述损坏区域104。
为了修复所述损坏区域104，将二补片200、202形成在例如碳纤维强化塑料(CFRP)，其可涂覆在所述损坏区域104。在这种情况下，所述补片202较小于所述补片200(在其主要延伸平面)，以便提供如图2B所示阶梯状排列的补片的剖视图。相应的阶梯如图2B所示，请参阅标号204。
所述补片200、202优选为应用在固化状态的外壳层部102。在这种情况下，所述补片200、202具有一轮廓，其对应至所述外壳层部102的形状，以确保所述补片在使用时没有间隙。任选地，另一种密封胶填入在所述补片200及所述外壳层部102之间，以确保所述损坏区域104的耐压密封。
所述补片200直接位于一边缘区域108以涵盖所述损坏区域104。所述边缘区域108也覆盖有补片202，例如，所述补片202设置在所述边缘区域108上且在所述补片200之间。
所述第一补片200具有例如约40千兆帕斯卡的弹性模量(在本文中也称为第一刚性)。所述第二补片202具有例如约80千兆帕斯卡的弹性模量(在本文中也称为第二刚性)。所述外壳层部102具有例如约73千兆帕斯卡的弹性模量(在本文中也称为基材层的刚性)
从所使用的每根纤维的复合材料，会各自产生刚性，所述刚性被影响特别是在由化学组合物中所使用的矩阵，所使用的纤维强度及其方位。另外，在本文中，所述刚性与所述负载F的方向相关联，且与所述铆钉112、114相应的延伸方向相匹配。
所述补片200、202是利用所述铆钉112、114铆接至所述外壳层部102。在这种情况下，一个或多个以上的铆钉206仅连接所述补片200至所述外壳层部102，及一个或多个以上的铆钉208连接所述补片200、202至所述外壳层部102。
如果所述连接器100有负载，所述负载FN的图表显示于为图3所示的虚线，所述铆钉112、114各自的铆钉延伸方向如图2A所示。由此可知，所述外部铆钉112承载的负载大致相等于所述内部铆钉114。
所述铆钉112、114可例如为钛铆钉。
如图2C所示是根据如图2B的实施例的一种变化。
根据如图2C所示的实施例，形成在所述区域108的外壳层部102包含一阶梯210。所述层212插入至所述阶梯210中。所述层212适合与所述外壳层部102的表面214齐平，以面对所述补片200、202。所述层212可依序由一材料形成，特别是复合纤维材料，其具有不同于所述外壳层部102的刚性。使用所述方式，在所述铆钉112、114之间的负载也可以更均匀的分布，一个或多个铆钉112、114，特别是一内部铆钉114，优选为穿透所述层212。
如图2C所示的虚线，所述层212也可以包含一部分216。所述部分216延伸穿过所述损坏区域104。在这种情况下，所述阶梯210优选地形成在所述损坏区域104周围，所述层212插入所述损坏区域。
根据图中未绘示的一实施例，所述第一、二层200、202可用于连接两基材层102，而取代覆盖所述损坏区域104。虽然已经描述了本发明的优选实施例的方式，但是不限于此，而是可以修改为各种方式。特别应指出的是，根据本发明的方法在本文描述的装置和实施例中，根据本发明的飞机或航天器，可以相应地适用于所述连接器，反之亦然。此外，应指出的是，一或一个不排除本文中的多个。
附图标记列表
100 连接器
102 基材层
104 损坏区域
106 补片
108 边缘区域
112 铆钉
114 铆钉
200 补片
202 补片
204 阶梯
206 铆钉
208 铆钉
210 阶梯
212 层
214 表面
216 部分
F   负载
FN  每铆钉的负载

Claims (13)

1.一种连接器(100)的制造方法，用于航空及航天领域的修复，其特征在于：
包含步骤：
提供一基材层(102)；
将具有一第一刚性的纤维复合材料的一第一层(200)贴置在所述基材层(102)上；
将具有一第二刚性纤维复合材料的一第二层(202)贴置在所述第一层(200)上，并由此形成偏移，且所述第二刚性大于所述第一刚性；及
将所述第一层(200)铆接至所述基材层(102)上，且将所述第二层(202)铆接至所述第一层(200)及所述基材层(102)上。
2.如权利要求1所述的方法，其特征在于：所述第一刚性为所述第二刚性的25％至75％。
3.如权利要求2所述的方法，其特征在于：所述第一刚性为所述第二刚性的45％至55％。
4.如权利要求1所述的方法，其特征在于：所述基材层(102)的刚性为所述第二刚性的80％至120％。
5.如权利要求1所述的方法，其特征在于：所述基材层(102)的刚性为所述第二刚性的95％至105％。
6.如权利要求1所述的方法，其特征在于：所述第一层(200)及第二层(202)分别提供作为贴补片，并连接至所述基材层(102)的一边缘区域(108)，所述边缘区域包围一损坏区域(104)。
7.如权利要求6所述的方法，其特征在于：所述损坏区域(104)是一个孔或一条裂痕。
8.如权利要求1所述的方法，其特征在于：所述第一层(200)及第二层(202)分别提供作为连接器，并连接至所述基材层(102)的一个部分，而且从所述基材层的另一部分连接至相隔有一距离的另一基材层。
9.如权利要求1所述的方法，其特征在于：所述基材层(102)及/或所述另一基材层形成作为一蒙皮、一桁条或一成型件。
10.如权利要求1所述的方法，其特征在于：所述基材层(102)由纤维复合材料所构成，及/或所述基材层(102)、另一基材层、第一层(200)及/或第二层(202)的纤维复合材料选自于以下群组：玻璃纤维塑料、碳纤维强化塑料或玻璃纤维金属层压板。
11.如权利要求1所述的方法，其特征在于：所述第一刚性、第二刚性及所述基材层(102)的刚性分别对应于相同的预定负载方向。
12.一种连接器(100)，其特征在于：包含：
一基材层(102)；
纤维复合材料的一第一层(200)，具有一第一刚性，并贴置在所述基材层(102)上；
纤维复合材料的一第二层(202)，具有一第二刚性，并贴置在所述第一层(200)上，由此形成偏移，且所述第二刚性大于所述第一刚性；及多个铆钉(206、208)，分别连接所述第一层(200)至所述基材层(102)，以及连接所述第二层(202)至所述第一层(200)与所述基材层(102)。
13.一种航天器，包含一如权利要求12所述的连接器(100)。
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