CN104416280A - 用于接合零件的层压制件以及用于接合零件的方法和系统 - Google Patents

用于接合零件的层压制件以及用于接合零件的方法和系统 Download PDF

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Publication number
CN104416280A
CN104416280A CN201410432225.4A CN201410432225A CN104416280A CN 104416280 A CN104416280 A CN 104416280A CN 201410432225 A CN201410432225 A CN 201410432225A CN 104416280 A CN104416280 A CN 104416280A
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CN
China
Prior art keywords
parts
laminate
layer
composite
solidified
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201410432225.4A
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English (en)
Inventor
帕布洛·塞沃利亚加罗费
卡洛斯·罗蒙巴诺贡
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations GmbH
Airbus Operations SL
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Airbus Operations GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations GmbH filed Critical Airbus Operations GmbH
Publication of CN104416280A publication Critical patent/CN104416280A/zh
Pending legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/12—Construction or attachment of skin panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B32B5/12—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer characterised by the relative arrangement of fibres or filaments of different layers, e.g. the fibres or filaments being parallel or perpendicular to each other
    • 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
    • B29C65/02—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure
    • B29C65/18—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated tools
    • 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
    • B29C65/4805—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the type of adhesives
    • B29C65/483—Reactive adhesives, e.g. chemically curing adhesives
    • B29C65/4835—Heat curing adhesives
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • 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
    • B29C65/5007—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 characterised by the structure of said adhesive tape, threads or the like
    • B29C65/5014—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 characterised by the structure of said adhesive tape, threads or the like being fibre-reinforced
    • 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
    • B29C65/5007—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 characterised by the structure of said adhesive tape, threads or the like
    • B29C65/5021—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 characterised by the structure of said adhesive tape, threads or the like being multi-layered
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • 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
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    • 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
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    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
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    • 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
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    • 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
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    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/12—Joint cross-sections combining only two joint-segments; Tongue and groove joints; Tenon and mortise joints; Stepped joint cross-sections
    • B29C66/128—Stepped joint cross-sections
    • B29C66/1282—Stepped joint cross-sections comprising at least one overlap joint-segment
    • B29C66/12821—Stepped joint cross-sections comprising at least one overlap joint-segment comprising at least two overlap joint-segments
    • 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
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    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/12—Joint cross-sections combining only two joint-segments; Tongue and groove joints; Tenon and mortise joints; Stepped joint cross-sections
    • B29C66/128—Stepped joint cross-sections
    • B29C66/1286—Stepped joint cross-sections comprising at least one bevelled joint-segment
    • 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
    • B29C66/301—Three-dimensional joints, i.e. the joined area being substantially non-flat
    • 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
    • B29C66/41—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
    • 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
    • B29C66/41—Joining substantially flat articles ; Making flat seams in tubular or hollow articles
    • B29C66/45—Joining of substantially the whole surface of the articles
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    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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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
    • B29C66/737—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 characterised by the state of the material of the parts to be joined
    • B29C66/7375—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 characterised by the state of the material of the parts to be joined uncured, partially cured or fully cured
    • B29C66/73755—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 characterised by the state of the material of the parts to be joined uncured, partially cured or fully cured the to-be-joined area of at least one of the parts to be joined being fully cured, i.e. fully cross-linked, fully vulcanized
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    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
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    • B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
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    • C—CHEMISTRY; METALLURGY
    • C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
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    • C—CHEMISTRY; METALLURGY
    • C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
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    • C—CHEMISTRY; METALLURGY
    • C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
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Abstract

提供一种用于接合由复合材料制成的零件(1、2)的层压制件(3)以及一种用于将由复合材料制成的至少两个零件(1、2)与根据本发明的层压制件(3)接合的方法，该层压制件(3)包括：由粘合材料制成的第一层(3.1)，与第一层(3.1)相邻的由预浸渍的复合材料制成的第二层(3.2)，以及与第二层(3.2)相邻的由粘合材料制成的第三层(3.3)；该方法包括下述步骤：提供已固化的复合材料零件(1、2)，将用于接合的层压制件(3)定位在两个固化的零件(1、2)之间，将压力和温度施加至包括至少两个零件(1、2)和层压制件(3)的整个结构，以使层压制件(3)被固化并且使至少两个零件(1、2)在所获得的结构中被接合在一起。

Description

用于接合零件的层压制件以及用于接合零件的方法和系统
技术领域
本发明涉及一种用于接合一对飞行器零件的方法。接合部在由包括树脂基体和增强纤维的复合材料制成的第一固化零件与第二固化零件之间形成。
背景技术
飞机已大部分或完全由金属部件构建，金属部件在机械特性方面提供了良好的性能，但是，其缺点是还提供了太多的重量。
随着航空公司之间竞争的增加，飞行器机架制造商探索改善特定的性能的新途径，即，增加或保持结构特性并且针对金属构造降低重量。
在本文中，措辞“复合材料”应理解为任何类型的材料，例如CFRP(碳纤维增强聚合物)，其包括两个或更多个物理地可辨别的且机械地可分开的部分，这两个或更多个部分不能溶解在彼此中。CFRP用于主要结构零件的优点在于实现了重要的重量减轻以及运营成本的降低。具有较大CFRP成分的第一飞行器为空客A320，其CFRP成分多于20％。
已经提出了在经济上有竞争力的制造复合零件的方法，诸如过程的自动化，如预浸渍层合(ATL(自动铺带机)、AFP(自动铺丝机))、切割、修整、NDT(非破坏性测试)以及其他。不同的CFRP制造方法(预浸渍、树脂传递模塑、干燥纤维等)、新型聚合物材料等改善了复合材料的收益性。
总之，复合材料已经被证明满足以下要求：
-重量减轻；
-成本有效；
-在飞行器条件下满足结构需求；
-受益的成本/重量关系。
用于接合固化的复合材料零件的常规方法为特别地借助于铆钉的机械结合。在现有技术中要解决的技术问题是如何避免在具有不同的固化零件的组件中使用铆钉以在整个结构中减轻重量。
使用机械结合来接合两个固化零件的另一缺点在于在要被接合的零件的表面之间由于其制造公差可能产生的任何间隙将必须通过垫片来填充，而垫片增加重量且使组件操作复杂化。因此需要提供一种能够吸收将要被接合的零件的所述制造公差的接合部。
在本说明书中的以下术语定义为：
·共固化：通过单个的固化周期将提供的处于新鲜状态(fresh state)的两个复合层压制件接合的工艺。所获得的接合部被验证用于一级结构。
·共结合：通过固化周期和沿着层压制件的接合表面施加粘合剂将提供的处于新鲜状态的复合层压制件接合至固化的复合层压制件的工艺。所获得的接合部被验证用于一级结构。
·结合：通过粘合材料接合两个固化的复合零件的工艺。该工艺未被验证用于接合一级结构。
·机械结合：借助于诸如铆钉或螺栓之类的紧固装置接合两个零件的工艺。所获得的接合部被验证用于一级结构。
在本说明书中，“一级结构”应被理解为这些结构的失效或者破坏将意味着飞行器在飞行时的灾难性后果。因此，根据需求，这种结构的验证比二级结构的验证要求更高，二级结构的失效或破坏将不意味着飞行器在飞行时的灾难性后果。
通过本发明要解决的另一技术问题是如何在避免使用铆钉且仍然遵循一级结构的验证的情况下接合一级结构。
发明内容
本发明提供了一种通过根据本发明的第一方面的层压制件解决前述问题的解决方案，一种根据本发明的第二方面的用于接合两个零件的方法，以及一种根据本发明的第三方面的系统。
在本发明的第一方面中提供了一种用于接合由复合材料制成的零件的层压制件，该层压制件包括：
·由粘合材料制成的第一层；
·与第一层相邻的包括预浸渍的复合材料的第二层；以及
·与第二层相邻的由粘合材料制成的第三层。
在本发明中，由预浸渍的复合材料制成的层将包括至少一层嵌入在树脂基体中的增强纤维。
在层压制件的第二层内的纤维的定向将根据将要施加至所获得的零件的载荷来确定。
层压制件适于接合零件，特别是已固化的由复合材料制成的零件。
在本发明的第二方面中提供了一种用于将由复合材料制成的至少两个零件与根据本发明的第一方面的层压制件接合的方法，该方法包括以下步骤：
·提供已固化的由复合材料制成的零件；
·将用于接合的层压制件定位在两个固化的零件之间，
·将压力和温度施加至包括至少两个零件和层压制件的整个结构，以使层压制件被固化并且使至少两个零件在所获得的结构中被接合在一起。
两个零件在对整个结构施加压力和温度以及接合层压制件的第二层中的树脂被聚合的步骤期间被接合在一起。
要接合的零件已固化的事实意味着零件具有足够的刚度以能够将施加至整个结构的压力从外部均匀地分布至结合区域。
温度在两个零件的接合部的结合区域中局部地升高以执行接合层压制件的第二层的固化周期。这涉及能量的有效利用，因为仅在需要的地方提供热量并且减少浪费。这种方法还利用了如下事实：固化的复合材料支持进一步的固化周期而不损失其特性。
当温度在固化周期期间升高时，层压制件的第二层中的树脂转变为液体。有利地，这允许树脂沿着两个固化的表面分布以及在层压制件的纤维之间分布。这连同通过要被接合的固化零件施加在接合层压制件上的均匀压力意味着树脂填充可能由两个固化的零件因其制造公差在固化周期之前的定位造成的任何间隙。一旦树脂被聚合，则零件的定位和施加给零件的压力将提供具有所期望的几何形状的接合部结构。
因此，在固化周期期间施加压力允许：
·达到良好的压实，消除孔隙度，以及
·获得目标的厚度，同时吸收要被接合的零件的制造公差。
三个零件的定位必须精确以吸收：
·当要被接合的零件的表面不完全平坦时在定位中的公差，或者
·当零件具有不规则区域时由于制造工艺而在制造中的公差。
该发明能够借助于可以在高压釜外部执行的固化周期将简单的零件(先前验证的)通过结合集成为复杂结构，因此在工业化中具有主要的优点。
有利地，由于复合零件已通过NTD验证且在“双共结合”之前被修整至最终的形状的事实，对所得的结构的NDT和修整被最小化。仅需要接合部区域的小检查，从而允许在低成本下的高集成。
该工艺在本发明范围内被命名为双共结合。换言之，双共结合工艺进行一类结合但用以下“夹层”代替粘合剂：
·粘合剂，其可以为在共结合的现有技术中所使用的任何类型的粘合剂。
·预浸渍体，以及
·粘合剂。
本发明基于共结合技术。正如所解释的，共结合的接合部通过中间粘合剂以及随后的固化周期被用在两个部件(一个固化的部件以及一个新鲜的部件)之间。最终在零件之间形成共接合的结构。还通过在接合层压制件中包括由预浸渍的复合材料制成的层以及通过共结合整个结构，在两个未固化的零件之间提供了具有共接合的接合部特性的接合部。因此，本方法可以用于接合一级结构。
产生的优点为：
·避免使用铆钉接合两个固化的零件，并且因此减轻重量，
·具有确保在固化的零件之间垫补间隙的结构接合部。
在本发明的第三方面中提供了用于接合由复合材料制成的两个零件的系统，其特征在于，该系统包括：
·至少两个热板，所述至少两个热板适用于施加压力和温度；
·定位装置，所述定位装置适用于以使两个零件利用根据本发明的第一方面的层压制件接合的方式定位两个零件；以及
·控制装置，该控制装置适用于实施根据本发明的第二方面的方法的步骤。
在本发明的第四方面中提供了一种飞行器，该飞行器包括至少一个结构，所述至少一个结构的零件已利用根据本发明的用于接合由复合材料制成的至少两个零件的方法接合。
附图说明
参照附图，本发明根据仅作为示例给出且不局限于此的本发明的优选实施方式变得明显，本发明的这些及其他特征和优点鉴于本发明的详细描述将被清楚地理解。
图1：该图示出了根据本发明的层压制件(3)。示出了三层，因此可以观察到各层(3.1、3.2、3.3)。
图2：该图示出了待使用根据本发明的层压制件(3)被接合的两个零件(1、2)。温度和压力例如通过使用热板压力机施加在第一零件(1)的基部中和第二零件(2)上，由于仅局部施加温度，因此节省能量。
图3a：该图示出了使用根据本发明的层压制件(3)接合的两个零件(1、2)，其中，定位公差和制造公差被吸收。
图3b：该图示出了使用根据本发明的层压制件(3)接合的两个零件(1、2)，其中，树脂和纤维层(3.2)和粘合剂层(3.1、3.2)适于由零件(1、2)所施加的波动。
图4：该图示出了定位成将压力和温度施加在由复合材料制成的两个零件(1、2)上的热板压力机(9)的图示。
具体实施方式
一旦概述了本发明的目的，则将在下文中描述具体的非限制性实施方式。
在本说明书(包括权利要求、说明书以及附图)中描述的所有特征可以以除互相排斥的特征的组合之外的任何组合方式组合。
用于接合至少两个零件(1、2)的层压制件(3)
如图1所示，层压制件(3)包括：
·由粘合材料形成的第一层(3.1)，
·与第一层(3.1)相邻的由预浸渍复合材料形成的第二层(3.2)，以及
·与第二层(3.2)相邻的由粘合材料形成的第三层(3.3)。
层压制件3允许载荷在两个零件(1、2)之间传输。载荷由要被接合的零件(1、2)承受但不由层压制件(3)承受。
第二层(3.2)中的纤维的作用不被规定为承受载荷或在两个零件(1、2)之间传输载荷。载荷通过第二层(3.2)的树脂基体来传输，并且所述第二层(3.2)中的纤维的作用是将树脂基体保持在一起。在具体的示例中，纤维的数目被最小化以使解决方案的重量不利最小化。
在具体的实施方式中，第二层(3.2)的总厚度被最小化。有利地，该事实减小了由于在要被接合的零件中的一个零件上施加剪切力而在另一零件中产生的动量。
层压制件包括由至少一层新鲜纤维制成的第二层(3.2)。第二层(3.2)可以包括处于被认为对于所考虑的每种情况更适当的定向的由树脂和纤维制成的若干层。
在例如用于飞行器的双共结合纵梁的层压制件(3)的具体实施方式中，在纵梁端部处的第二层(3.2)的由树脂和纤维制成的若干层的定向为0°。
在例如用于飞行器的双共结合纵梁的层压制件(3)的具体的实施方式中，在纵梁端部处的第二层(3.2)的由树脂和纤维制成的若干层的定向为45°。
来源于使用层压制件(3)接合零件(1、2)的优点之一为层压制件(3)在被固化之前可以适用于不同的形状，例如在制造和/或定位中精度不足的那些零件(1、2)，如在图3a中示出的一个例子。在图3a中示出了使用根据本发明的层压制件(3)接合的两个零件(1、2)，其中，在定位和制造中的公差被吸收。第二层(3.2)中的纤维分布在层压制件(3)的中央以占据位于要被共结合的两个零件(1、2)之间的整个空间。
图3b中示出了有利的适用性的另一示例。在图3b中示出了使用根据本发明的层压制件(3)接合的两个零件(1、2)，其中，第二层(3.2)和粘合层(3.1、3.3)适用于由零件(1、2)所施加的波动。
用于将至少两个零件(1、2)与层压制件(3)接合的方法
要被接合的零件(1、2)由复合材料制成且零件(1、2)已经通过固化工艺固化。
该方法包括以下步骤：
·提供已固化的零件(1、2)，
·将用于接合的层压制件(3)定位在两个固化的零件(1、2)之间，
·将压力和温度施加至包括至少两个零件(1、2)和层压制件(3)的整个结构，以使层压制件(3)被固化并且至少两个零件1、2在所获得的结构中被接合在一起。
在具体的实施方式中，方法中所描述的三个步骤在单个机器中完成。
如图3a和图3b所示，通过施加均匀的压力，树脂沿着零件(1、2)在定位期间的波动或非对称性分布。
在具体的实施方式中，定位通过实现所需的公差的定位装置进行。公差取决于要被接合的部件及其形状。
在图2中示出了待使用根据本发明的层压制件(3)被接合的两个零件(1、2)。温度和压力仅局部地施加于：
·第一零件(1)的基部上，该第一零件(1)例如可以是纵梁，以及
·第二零件(2)上，
无需高压釜。
在图2中示出的实例中，该方法允许仅在纵梁(1)的基部上以及在第二零件(2)上施加温度，这因此允许在无需高压釜的情况下执行固化周期，从而使能量消耗最优化。因此，固化周期在本发明的背景下没有构思为高成本的固化周期，而是构思为可以通过使用例如热板压力机(9)来执行的简单的固化周期。这与需要使用高压釜的解决方案相比表现出在工业化中的优点。
如上所述，在固化辅助层压制件(3)的具体实施方式中，通过热板压力机(9)施加压力和温度，如图4所示，在图4中示出了将压力和温度施加在定位在根据本发明的层压制件(3)的外部层(3.1、3.3)二者上的两个零件(1、2)上的热板压力机(9)的图示。该图还示出了层压制件(3)的边缘上的密封件(8)。有利地，该密封件避免了在施加压力时树脂被排出。
在具体的实施方式中，热板压力机(9)为可能的解决方案之一，但许多其他可能的解决方案可以适用于这些提议。
有利地，由复合材料制成的零件(1、2)允许热量通过所述零件(1、2)朝向通过待使用热压板(9)固化的层压制件(3)传输。
在具体的实施方式中，温度在160℃至190℃的范围内以用于改善纤维的聚合。
在具体的实施方式中，至少两个零件(1、2)的固化表面以及层压制件(3)的新鲜表面的预处理通过如现有技术的共固化中的剥离层或表面预处理来执行。
用于接合由复合材料制成的两个零件(1、2)的系统
根据本发明的用于接合由复合材料制成的两个零件(1、2)的系统的特征在于，其包括：
·至少一个热板压力机(9)，所述至少一个热板压力机(9)适用于施加压力和温度，
·定位装置，该定位装置适用于以使两个零件利用层压制件(3)接合的方式定位两个零件，以及
·控制装置，该控制装置适用于实施根据本发明的方法的步骤。

Claims (10)

1.一种用于接合由复合材料制成的零件(1、2)的层压制件(3)，所述层压制件(3)包括：
·由粘合材料制成的第一层(3.1)；
·与所述第一层(3.1)相邻的由至少预浸渍的复合材料制成的第二层(3.2)；以及
·与所述第二层(3.2)相邻的由粘合材料制成的第三层(3.3)。
2.根据权利要求1所述的用于接合零件(1、2)的层压制件(3)，其特征在于，所述第二层(3.2)包括至少两层呈0°铺设的新鲜纤维。
3.根据权利要求1所述的用于接合零件(1、2)的层压制件(3)，其特征在于，所述第二层包括至少两层呈45°铺设的新鲜纤维。
4.一种用于将由复合材料制成的至少两个零件(1、2)与根据权利要求1至3中的任一项所述的层压制件(3)接合的方法，所述方法包括以下步骤：
·提供已固化的复合材料零件(1、2)，
·将用于接合的所述层压制件(3)定位在两个固化的零件(1、2)之间，
·将压力和温度施加至包括所述至少两个零件(1、2)和所述层压制件(3)的整个结构，以使所述层压制件(3)被固化并且使所述至少两个零件(1、2)在所获得的结构中被接合在一起。
5.根据权利要求4所述的方法，其特征在于，定位利用定位装置进行。
6.根据权利要求4或5所述的方法，其特征在于，利用热板压力机(9)施加压力和温度，而无需高压釜工艺。
7.根据权利要求4至5中的任一项所述的方法，其特征在于，所述零件(1、2)包括通过剥离层或表面预处理执行的固化表面。
8.根据权利要求6所述的方法，其特征在于，所述零件(1、2)包括通过剥离层或表面预处理执行的固化表面。
9.一种用于接合由复合材料制成的两个零件(1、2)的系统，其特征在于，所述系统包括：
·至少一个热板压力机(9)，所述至少一个热板压力机(9)适用于施加压力和温度；
·定位装置，所述定位装置适用于以使所述两个零件利用根据权利1至3中的任一项所述的层压制件(3)接合的方式定位所述两个零件；以及
·控制装置，所述控制装置适用于实施根据权利要求4至8中的任一项所述的方法的步骤。
10.一种飞行器，所述飞行器包括至少一个结构，所述至少一个结构的零件已利用根据权利要求4至8中的任一项所述的方法接合。
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