CN101730618B - 热塑性材料与纤维复合材料的接合方法 - Google Patents

热塑性材料与纤维复合材料的接合方法 Download PDF

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CN101730618B
CN101730618B CN2008800086965A CN200880008696A CN101730618B CN 101730618 B CN101730618 B CN 101730618B CN 2008800086965 A CN2008800086965 A CN 2008800086965A CN 200880008696 A CN200880008696 A CN 200880008696A CN 101730618 B CN101730618 B CN 101730618B
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fibrous composite
thermoplastic
support
airborne vehicle
sidewall paneling
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CN101730618A (zh
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萨宾·沃洛奇
约根·申克
乔治·华盛戈尔
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Airbus Operations Ltd
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Airbus Operations GmbH
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    • 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
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/04—Layered products comprising a layer of synthetic resin as impregnant, bonding, or embedding substance
    • 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
    • B29C65/02—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure
    • B29C65/06—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using friction, e.g. spin welding
    • 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
    • B29C65/02—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure
    • B29C65/06—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using friction, e.g. spin welding
    • B29C65/0672—Spin welding
    • 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
    • B29C65/02—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure
    • B29C65/34—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement"
    • B29C65/36—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction
    • B29C65/3604—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction characterised by the type of elements heated by induction which remain in the joint
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    • B29C65/3612—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction characterised by the type of elements heated by induction which remain in the joint comprising single particles, e.g. fillers or discontinuous fibre-reinforcements comprising fillers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • 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
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    • B29C65/368—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated elements which remain in the joint, e.g. "verlorenes Schweisselement" heated by induction characterised by the composition of the elements heated by induction which remain in the joint being metallic with a polymer coating
    • 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
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    • B29C66/47—Joining single elements to sheets, plates or other substantially flat surfaces
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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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    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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Abstract

本发明涉及一种将热塑性材料(10)和纤维复合材料(11)接合的方法，所述热塑性材料(10)焊接至所述纤维复合材料(11)，其中所述纤维复合材料为纤维增强基体材料或包括纤维增强基体材料，其中所述基体材料为热固性材料或包括热固性材料。优选地，所述热塑性材料(10)和所述纤维复合材料(11)通过运动焊接和/或感应焊接在一起。另外，优选地，对于感应焊接，在热塑性材料和纤维复合材料之间的接合区域设置导电材料，从而在导电材料中产生感应热，使热塑性材料开始熔化而纤维复合材料被加热。

Description

热塑性材料与纤维复合材料的接合方法
技术领域
本发明涉及一种热塑性材料和纤维复合材料的接合方法。此外，本发明也涉及一种包含热塑性材料和纤维复合材料的装置。
背景技术
在航空器中，热塑性材料通常利用机械构件将热塑性材料与纤维复合材料连接，例如利用螺丝钉或利用粘合剂。例如，包含热塑性材料的塑料支架通常依附加在加压区域的元件例如侧壁板或帽架箱，这些元件包含纤维复合材料，例如在航空器的舱室区域。
含有热塑性塑料的塑料支架和含有纤维复合材料元件之间的粘接需要对塑料支架的粘附表面预处理。这些表面首先需要进行表面粗糙处理，然后用涂底漆进行预处理。只有在预处理之后，塑料支架才可以粘接至含纤维复合材料的元件。然后，需要等待一段时间，一般5至8小时，直至粘合剂固化，并表现出所需的粘接强度。通常使用热固性的粘合剂。当采用这种粘合剂时，粘接在一起的热塑性支架和元件必须在烤箱中固化48小时。所以，粘接过程很复杂，且很费时间。此外，粘合剂包括对健康有害的成分。
作为选择或者在此基础上，含有热塑性塑料的塑料支架常常通过螺丝钉连接至含有纤维复合材料的元件上。但是，这有缺点，螺丝钉的孔的大小和位置必须在塑料支架和元件的制造过程中就已经知道，如果元件和/或塑料支架的连接位置改变，必须增加新的孔。这对于整个生产过程将是不利的。
发明内容
本发明的目的在于，提供一种将热塑性材料和纤维复合材料接合的方法，该方法与现有方法相比较简单且消耗的时间较少，同时不采用对健康有害的物质，并且与使用机械连接方法例如采用螺丝钉相比，热塑性材料和纤维复合材料的连接位置更容易改变。
本发明的上述目的通过一种将热塑性材料和纤维复合材料接合的方法来完成，其中热塑性材料焊接至纤维复合材料，所述纤维复合材料为纤维增强的基体材料，或者包括纤维增强的基体材料，其中该基体材料为热固性材料或者包含有热固性材料。
通过将热塑性材料焊接至纤维复合材料，两材料之间接合所需的时间大大减少。总共只需要几秒钟。此外，通常材料不需要预处理，也不需要另外的有害物质。此外，元件和塑料支架之间不需要形成有孔，从而更容易改变热塑性材料和纤维复合材料之间的接合位置。
优选地，通过“运动焊接”将热塑性材料焊接至纤维复合材料。术语“运动焊接”包括热塑性材料和纤维复合材料之间的任何相对运动，在接合区域产生运动热足以使热塑性塑料和纤维复合材料之间焊接在一起。此外，优选地，在运动焊接过程中，热塑性材料和纤维复合材料之间彼此相对运动，热塑性材料开始熔化而纤维复合材料被加热。更优选地，在运动焊接过程中，热塑性材料和纤维复合材料之间彼此相对运动的方式是，热塑性材料相对于纤维复合材料运动，且热塑性材料和纤维复合材料彼此相互挤压，热塑性材料开始熔化而纤维符合材料被加热。
简单地，运动焊接允许在热塑性材料和纤维复合材料之间的接合区域产生运动热，尤其是摩擦热，该运动热足以焊接两种材料焊接在一起。
同样，运动的能量也可以用于热塑性材料的目标去除。
相对运动可以通过例如热塑性材料和纤维复合材料彼此之间的相对转动和/或振动。当利用振动时，纤维复合材料和热塑性材料优选通过振动焊接彼此相互连接。在振动焊接中，摩擦热由在热塑性材料和纤维复合材料之间的接合区域中的振动产生，并足以将两种材料焊接在一起。
此外，优选地，热塑性材料通过感应焊接与纤维符合材料接合。为此目的，在热塑性材料和纤维复合材料之间的接合区域设置导电材料，在导电材料中产生感应热，以足够使热塑性材料开始熔化，并加热纤维复合材料。在感应焊接中，优选将导电材料通电，以通过电阻效应和/或磁滞现象产生感应热。优选地，为了产生感应热，在热塑性材料和纤维复合材料之间的接合区域设置金属颗粒和/或金属层。
此外，导电材料为开槽、绷紧的金属箔，例如商品名为Astrostrike的金属箔。导电材料优选由铝和/或铜制成，或者包含铝和/或铜。优选地，导电材料为金属编织材料和/或金属层。优选地，导电材料包括或由金属纳米颗粒构成。导电材料尤其是金属层优选通过一种或多种金属粉的热喷涂方法产生，这些金属粉可以包括一种或多种金属，或者通过利用一种或多种金属的烧结技术，或者通过熔融一种或多种金属箔和/或一种或多种焊接材料，尤其是使之形成在热塑性材料上。
优选地，通过中频或高频产生感应热。在优选的实施方式中，采用频率范围10～50kHz，尤其是功率在2～5kW。在另一个优选实施方式中，采用频率范围400kHz～1MHz，尤其是功率小于25kW。
在另一个实施方式中，纤维复合材料包括碳纤维增强塑料(CFRP)，在碳纤维增强塑料内产生感应热，尤其是没有采用另外的导电材料。感应热优选产生在接近碳纤维增强塑料的表面上。
纤维复合材料为纤维增强基体材料或包括纤维增强基体材料。基体材料为热固性材料或包括热固性材料。优选地，纤维复合材料的纤维为单向的，或形成编织物。因此，纤维复合材料优选为纤维增强塑料(FRP)，即增强的、热塑性和/或热固性的基体材料，并设置有单向纤维或形成编织物的纤维。此外，纤维复合材料也可以利用树脂尤其是加聚树脂和/或缩聚树脂。纤维复合材料优选设置在蜂窝结构，尤其是Nomex蜂窝结构。在这种情况下，蜂窝结构为层的形式，纤维复合材料设置在蜂窝结构的两个对边。
热塑性材料由一种或多种工程热塑性塑料制成或包含一种或多种工程热塑性塑料组成。热塑性材料还可以由聚酰胺组成或包括聚酰胺此外，热塑性材料可以由聚醚酰亚胺(PEI)和/或聚醚醚酮(PEEK)组成或者包括聚醚酰亚胺(PEI)和/或聚醚醚酮(PEEK)。在优选实施方式中，热塑性材料包括纤维增强件，尤其是短的纤维增强件，其中纤维可以为碳纤维和/或玻璃纤维。在另一个优选实施方式中，热塑性材料没有包含纤维增强件。
通过利用纤维复合材料和热塑性材料，可以根据本发明的方法在这些材料之间产生良好的接合。
此外，热塑性材料优选为支架的成分，或者支架由热塑性材料构成，纤维复合材料优选为元件的成分或者元件由纤维复合材料构成，从而支架的热塑性材料与元件的纤维复合材料焊接在一起，使支架和元件接合形成支架结构。这样，支架可以简单快捷地与元件接合。
如果纤维复合材料通过运动焊接连接至热塑性材料，热塑性材料的支架优选设置为运动的，同时待接合的元件的纤维复合材料为不动的。
元件可以为航空器中的侧壁板，尤其是在航空器的操作时可加压的空间内，特别是航空器的舱室空间内，和/或航空器的帽架箱或者侧壁板的一部分和/或帽架箱的一部分。此外，所述方法优选应用在航空器，优选航空器中在操作时可加压的空间内，尤其是在舱室空间内。因此，根据本发明的方法使之可以简单、快捷和可靠地在热塑性材料和纤维复合材料之间产生焊接接合。
所述支架的结构优选可以制成所需的物体。
本发明还涉及包含热塑性材料和纤维复合材料的装置，其中热塑性材料和纤维复合材料包括根据本发明方法形成的接合处。
所述装置的优选结构记载在权利要求20至24中。
附图说明
下面结合附图，对本发明的优选实施方式作进一步描述，其中：
图1为根据本发明实施例的装置的示意图；
图2为纤维增强塑料和热塑性材料之间接合的层结构；
图3为带纤维增强塑料的夹层结构；
图4为带舱室空间的航空器，其中设置有支架结构；
图5为含有热塑性材料的支架的示意图。
具体实施方式
图1展示了将热塑性材料和纤维复合材料接合的装置1，其中纤维复合材料为纤维增强的基体材料或包含纤维增强的基体材料，其中基体材料为热固性材料或包含热固性材料。装置1包含转动和提升单元2和控制单元3，该控制单元3连接至转动和提升单元2，并控制该转动和提升单元。装置1还包括支架支座4，支架5可拆卸地连接至该支架支座4。支架支座4可转动地和高度可调节地支撑在转动和提升单元中，从而转动和提升单元2可以通过支架支座转动支架5，并可以改变其高度位置。装置1还包括纤维复合材料支座6，该纤维复合材料支座6上支撑有纤维复合材料7，在该实施例中为纤维增强塑料。
通过装置1，支架5，例如处于图1所示的高度位置，可以被嵌入支架支座4。此外，纤维复合材料7，尤其是纤维增强塑料，可以被嵌入纤维复合材料支座6中。一旦支架5和纤维复合材料7被嵌入相应的支座4、6中，支架支座4沿纤维复合材料7的方向移动，从而支架5与纤维复合材料7接触，并有预定的压力。支架5和纤维复合材料7之间的预定压力形成之前、期间或之后，由于支架支座4，支架5开始以预定频率转动。作为转动的结果，由热塑性材料构成的或者包含热塑性材料的支架5的表面，和纤维复合材料的表面相互摩擦，从而产生运动热。维持该运动过程，直至产生足够的运动热量，以将两个表面相互接合。随后，该运动停止，表面冷却。加热过程和冷却过程都只持续了几秒钟，具体地，每个过程持续少于5秒钟。
图4展示了航行器30的示意图，该航行器具有当操作时可加压的舱室区域31。在每个舱室区域31中，设置有元件32，该元件包含纤维复合材料，尤其是纤维增强塑料，或者其结合。元件32与包含热塑性材料或由热塑性材料构成的支架33接合。元件32和支架33之间的接合可以通过根据本发明的上述方法实现。
纤维复合材料和热塑性材料之间的接合与其他材料之间的焊接接合不同。特别是，根据本发明方法，热塑性材料和纤维复合材料之间的接合处的显微结构与其他材料(例如两种金属材料)之间的焊接接合处的显微结构不同。
在图1中，纤维复合材料7由纤维复合材料支座6支撑。但是，根据本发明，纤维复合材料7也可以为较大元件的一部分，例如侧壁板或帽架箱，该较大元件的一部分可以由相应的支座支撑，或者已经固定在航空器的舱室区域中。在后者情况中，无须支座来支撑纤维复合材料或支撑元件。
转动和提升单元2和控制单元3可以采取例如美国专利US 5,160,393所述的固定装置。作为选择，转动和提升单元2、控制单元3和支架支座4也可以为手持结构。
支架5至少在纤维复合材料的接合区域包含有热塑性材料，该热塑性材料以据本发明的方式与纤维复合材料接合。在接合区域所获得的层如图2所示。热塑性材料10焊接至纤维复合材料11。在此实施例中，纤维复合材料11应用在蜂窝结构12中，尤其是Nomex蜂窝。优选地，蜂窝结构12依次应用在纤维复合材料的第二层13。
热塑性材料10优选为工程热塑性塑料并更优选为聚酰胺。但是，根据本发明，热塑性材料也可以为标准的热塑性塑料或高性能的热塑性塑料。所用的工程热塑性塑料可以优选为PA66(带有或不带有玻璃纤维)，尤其是PA66-GF30和PA60-GF30，PA12，PC(聚碳酸脂)或PMMA。材料PA66、PA12和PC优选具有阻燃剂，并因此具有良好的防火性能。
所使用的高性能热塑性塑料可以为聚醚酰亚胺(PEI)，带有或不带有玻璃纤维，以及其玻璃纤维改性。此外，高性能的热塑性材料可以是，例如：聚芳醚酮(PAEK，aromaticpolyetherketones)、聚苯砜(PPSU，polyphenylsulfone)和聚酰胺-酰亚胺(polyamideimides)。
纤维复合材料11(优选纤维增强塑料)可以包含有碳纤维和/或玻璃纤维，尤其是碳纤维增强塑料和/或玻璃纤维增强塑料(GRP)。纤维复合材料优选利用树脂制成，尤其是加聚树脂和/或缩聚树脂。一系列层包括纤维复合材料层11、13和穿插的蜂窝结构12，同样是夹层结构。泡沫结构也可以被用来取代或加入所述的蜂窝结构12。
图3为夹层结构的示意图，图中该夹层结构的顶面为纤维复合材料层11，底面为纤维复合材料层13，这些层围住蜂窝结构15或泡沫结构16。为了清晰的原因，图3中，部分的纤维复合材料11已经被去除。优选地，纤维复合材料层11完全覆盖层14。为了清晰的原因，图3中蜂窝结构15和泡沫结构16均展示出。但是，优选地，对于夹层架构，在纤维复合材料层11、13之间，只包含蜂窝结构15或泡沫结构16。蜂窝结构优选为Nomex蜂窝。
纤维复合材料层11、13优选具有厚度0.1～0.2mm，并更优选厚度0.15mm。
接合过程的微观顺序将在下文描述。
在焊接过程中，热塑性材料的表面进入高粘性状态，该状态下材料的温度高于玻璃化转变温度而低于熔点。这意味着热塑性材料只是开始熔化。同时，纤维复合材料的表面被加热，并与热塑性材料的高粘性部分进行准化学结合。如果纤维复合材料包括树脂，尤其是加聚和/或缩聚树脂，那么未固化的树脂可以与热塑性材料的高粘性部分发生准化学结合，即：所述树脂可能没有完全固化，例如超过50％的树脂固化，尤其是超过80％的树脂固化，其中未固化的树脂可以与热塑性材料的高粘性部分发生准化学结合。此外，支架的高粘性的热塑性材料穿过纤维复合材料的微孔，从而热塑性材料穿透纤维复合材料，从而产生连接。此外，高粘性的热塑性材料可以进入纤维复合材料并穿过纤维物和材料，从而锚定在远离热塑性材料的纤维复合材料一侧，从而产生接合。当纤维复合材料采用蜂窝结构中如图2所示时，热塑性材料的高粘性部分可以穿过纤维复合材料。由于多孔性的纤维复合材料，在蜂窝结构的方向上可以发生毛细效应，这可以至少导致高粘性热塑性材料被引入纤维复合材料中。
在另一个实施例中，热塑性材料通过感应焊接被焊接在纤维复合材料，其中在热塑性材料和纤维复合材料之间的接合区域设置有导电材料。优选地，导电材料为开槽、绷紧的金属箔，例如商品名称为Astrostrike的金属箔。导电材料优选由铝和/或铜制成或包含铝和/或铜。在另一个优选实施方式中，导电材料为金属编制材料和/或金属层。在另一个优选实施方式中，导电材料包括或由金属纳米颗粒组成。导电材料，尤其是金属层，优选通过一种或多种金属粉末的热喷涂方法产生，或者利用一种或多种金属的烧结技术，或者利用一种或多种金属箔和/或一种或多种焊接材料的熔化产生，特别是在热塑性材料上。
在优选实施例中，感应热可以利用中频或高频产生。优选地，采用的频率在10～50kHz，尤其是功率在2～5kW。在另一个优选实施例中，采用频率400kHz～1MHz，尤其是功率小于25kW。
在另一个优选实施例中，纤维复合材料包括碳纤维增强塑料(CFRP)，感应热在碳纤维增强塑料中产生，尤其是不利用额外的导电材料。感应热优选在碳纤维增强塑料的表面附近产生。
根据本发明的将热塑性材料和纤维复合材料接合的方法的例子如下所述。
实施例1
根据实施例1，包含热塑性材料的支架展示在图5中，该支架与纤维复合材料接合，在本实施例中，纤维复合材料为纤维增强塑料。
在该实施例中，支架33包括盘状连接部分34和支座35，所述盘状连接部分与纤维增强塑料连接。连接部分34和支座35具有聚酰胺PA66含量70％和玻璃纤维含量30％。支座35用于支撑物体，例如电导线或更重的物体。连接部分的厚度在此实施例中为2.2mm，连接部分的直径在此实施例中为24mm。
在此实施例中，纤维增强塑料为玻璃增强塑料薄片，支架33的表面36将连接的薄片的顶部外层为40％树脂和60％玻璃纤维编织物。薄片的厚度总计为2mm。
支架固定在装置1的支架支座4，如图1所示。此外，玻璃增强塑料薄片，即纤维增强塑料，固定在装置1的支座6。然后，支架被转动和提升单元2和支架支座4压在玻璃增强塑料薄片上，并相对玻璃增强塑料薄片转动，以产生运动热，使玻璃增强塑料薄片和支架接合。
在焊接过程中，热塑性材料和纤维增强塑料之间的压力在本实施例中为0.5、1.0和1.5巴。对应于每个压力，含有热塑性材料的支架与纤维增强材料之间根据本发明产生接合。在焊接过程中，含有热塑性材料的支架相对于纤维增强材料转动，角频率为120Hz。在本实施例中，焊接深度为0.35mm。在本实施例中，焊接过程通过焊接深度控制，即焊接过程在达到预定焊接深度时就结束。
为了检查热塑性材料和纤维增强塑料之间的接合，确定其拉伸剪切强度。根据本发明产生的接合具有非常好的拉伸剪切强度。这些拉伸剪切强度足以使用于支撑重物的支架连接至纤维增强塑料元件。
实施例2
在本实施例中，同样采用实施例1所示的支架。在该实施例中，纤维增强塑料为碳纤维增强塑料薄片，支架连接的薄片顶部外层为45％树脂和55％碳纤维编织物。薄片的厚度为2mm。
根据本发明的用于将热塑性材料(支架)连接至纤维增强材料(碳纤维增强塑料薄片)的方法通过利用图1所示装置1来实现。
在本实施例中，角频率为160Hz，焊接时间为3秒。焊接时间为支架相对纤维增强塑料运动的时间，热塑性材料和纤维增强塑料之间的预定压力在此实施例中为1.0巴。焊接过程在此实施例中通过焊接时间来调节，即焊接过程每次为3秒。在这些实施例中，确定拉伸剪切强度。
通过实施例2的参数获得的，热塑性材料和纤维增强塑料之间的接合，具有非常好的拉伸剪切强度，足以使用于支撑重物的热塑性材料支架连接至纤维增强塑料元件。
虽然上述实施例中描述的是运动焊接，但是本发明并不限于运动焊接。根据本发明，可以采用任何类型的焊接，以产生足够的热量使根据本发明的接合可以实现。例如，热也可以通过辐射，尤其是红外线焊接或激光焊接。作为选择或在此基础上，热也可以通过对流产生，尤其是热气焊接或挤压焊接或利用热空气的非接触焊接。
另外，热塑性材料可以通过感应焊接与纤维复合材料焊接在一起。为此目的，在热塑性材料和纤维复合材料之间的接合区域设置导电材料，导电材料中产生足够的热量，以使热塑性材料开始熔化而纤维复合材料被加热。在感应焊接中，导电材料通电，通过电阻效应和/或磁滞现象产生感应热。优选地，为了产生感应热，可以在热塑性材料和纤维复合材料之间的接合区域设置金属颗粒和/或金属层。
虽然本发明已经通过支架与纤维增强塑料接合的实施例进行描述，但是本发明并不限于将支架和纤维增强材料接合。根据本发明，含有热塑性材料的其他物体也可以与纤维复合材料接合，尤其是纤维增强塑料。本发明并不局限于特定支架的形状。
此外，本发明并不局限在热塑性材料和纤维复合材料之间的圆周运动。根据本发明，在纤维复合材料和热塑性材料接触期间，两种材料之间的任何相对运动均可以采用，以产生焊接过程所需的运动热。另外，相对运动也可以是直线运动。
本发明不局限于实施例中的压力、焊接时间、焊接深度或频率。如上所述，根据本发明，热塑性材料和纤维复合材料之间的任何所需相对运动均可以采用，纤维复合材料和热塑性材料之间任何所需的压力均可以采用，只要产生足够的运动热，以将两种材料焊接在一起。

Claims (21)

1.一种将航空器的热塑性材料(10)和纤维复合材料(11)接合的方法，其特征在于：将所述热塑性材料(10)焊接至所述纤维复合材料(11)，其中所述纤维复合材料为纤维增强基体材料或包括纤维增强基体材料，其中所述基体材料为热固性材料或包括热固性材料，其中，通过运动焊接将所述热塑性材料(10)与所述纤维复合材料(11)焊接在一起，所述热塑性材料和所述纤维复合材料之间的相对运动由所述热塑性材料和所述纤维复合材料之间的相对转动和振动产生，其中所述热塑性材料(10)为支架(33)的组成成分，或者说所述支架(33)由所述热塑性材料(10)构成，所述纤维复合材料(11)为元件(32)的组成成分，或者说所述元件(32)由所述纤维复合材料(11)构成，这样，所述支架(33)的所述热塑性材料(10)与所述元件(32)的所述纤维复合材料(11)被焊接在一起，使所述支架(33)和所述元件(32)接合，以形成支架结构。
2.根据权利要求1所述的方法，其特征在于：所述纤维复合材料的纤维为单向取向或形成编织物。
3.根据权利要求1或2所述的方法，其特征在于：所述纤维复合材料(11)包括碳纤维和/或玻璃纤维。
4.根据权利要求3所述的方法，其特征在于：所述纤维复合材料(11)包括碳纤维增强材料和/或玻璃纤维增强材料。
5.根据权利要求1或2所述的方法，其特征在于：利用树脂制造所述纤维复合材料(11)。
6.根据权利要求5所述的方法，其特征在于：利用加聚和/或缩聚树脂制造所述纤维复合材料(11)。
7.根据权利要求1或2所述的方法，其特征在于：所述纤维复合材料(11)设置在蜂窝结构(15)上。
8.根据权利要求7所述的方法，其特征在于：所述纤维复合材料(11)设置在Nomex蜂窝上。
9.根据权利要求7所述的方法，其特征在于：所述蜂窝结构(15)被形成为一层，所述纤维复合材料(11)设置在所述蜂窝结构(15)的相对的两侧。 
10.根据权利要求1或2所述的方法，其特征在于：所述热塑性材料(10)由一种或多种工程热塑性塑料组成或包括一种或多种工程热塑性塑料。
11.根据权利要求1或2所述的方法，其特征在于：所述热塑性材料(10)由聚酰胺组成或包括聚酰胺。
12.根据权利要求1或2所述的方法，其特征在于：所述元件为航空器(30)内的侧壁板，和/或所述航空器的帽架箱或者所述侧壁板的一部分和/或所述帽架箱的一部分。
13.根据权利要求12所述的方法，其特征在于：所述侧壁板为位于所述航空器内的空间(31)中的侧壁板，所述空间(31)为在操作时可加压的空间。
14.一种包含航空器的热塑性材料(10)和纤维复合材料(11)的装置，其特征在于：所述热塑性材料(10)和所述纤维复合材料(11)具有接合处，其中所述纤维复合材料为纤维增强基体材料或包含纤维增强基体材料，其中所述基体材料为热固性材料或包含热塑性材料，其中所述装置包括具有支架(33)和元件(32)的支架结构，所述热塑性材料(10)为所述支架(33)的一种组成成分，或者说所述支架(33)包含所述热塑性材料(10)，所述纤维复合材料(11)为所述元件(32)的一种组成成分，或者说所述元件(32)包含所述纤维复合材料(11)，所述支架(33)与所述元件(32)通过所述接合处接合，所述接合处是用根据权利要求1至9任意一项所述的方法获得的。
15.根据权利要求14所述的装置，其特征在于：所述装置包括一系列的层，第一层包含热塑性材料(10)或由热塑性材料(10)组成，第二层与所述第一层通过所述接合处接合，该第二层包含纤维复合材料(11)或由纤维复合材料(11)组成，第三层(12)设置在所述第二层远离所述接合处的一侧、并包含蜂窝结构和/或泡沫结构或者由蜂窝结构和/或泡沫结构组成。
16.根据权利要求14所述的装置，其特征在于：所述元件为航空器(30)的侧壁板，和/或所述航空器(30)的帽架箱或者所述侧壁板的一部分和/或所述帽架箱的一部分。
17.根据权利要求16所述的装置，其特征在于：所述侧壁板为位于所述航空器中的操作时可加压的空间(31)内的侧壁板。
18.根据权利要求17所述的装置，其特征在于：所述侧壁板为位于航空器中的操作时可加压的舱室空间内的侧壁板。
19.根据权利要求14所述的装置，其特征在于：所述支架结构设置在航空器(30)中。 
20.根据权利要求19所述的装置，其特征在于：所述支架结构设置在所述航空器(30)中的操作时可加压的空间内。
21.根据权利要求14-16和19中任意一项所述的装置，其特征在于：所述装置为航空器(30)。 
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