CN113306170A - 复合结构、制造该复合结构的方法以及混合式复合结构 - Google Patents

复合结构、制造该复合结构的方法以及混合式复合结构 Download PDF

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CN113306170A
CN113306170A CN202110637091.XA CN202110637091A CN113306170A CN 113306170 A CN113306170 A CN 113306170A CN 202110637091 A CN202110637091 A CN 202110637091A CN 113306170 A CN113306170 A CN 113306170A
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China
Prior art keywords
flange
thermoplastic
web
fiber
reinforced
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CN202110637091.XA
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E·M·小费舍尔
A·W·布卢姆
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Boeing Co
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Boeing Co
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Publication of CN113306170A publication Critical patent/CN113306170A/zh
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    • B29C65/16—Laser beams
    • B29C65/1629—Laser beams characterised by the way of heating the interface
    • B29C65/1632—Laser beams characterised by the way of heating the interface direct heating the surfaces to be joined
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Abstract

本发明涉及复合结构、制造该复合结构的方法以及混合式复合结构。混合式复合结构包括共焊接在一起的模制的热塑性复合部件和层压物热塑性复合部件。模制的部件由不连续的纤维加强，并且层压物部件由连续的纤维加强。

Description

复合结构、制造该复合结构的方法以及混合式复合结构
本申请是申请日为2014年12月1日、申请号为201410718019.X、发明名称为“复合结构、制造该复合结构的方法以及混合式复合结构”的发明专利申请的分案申请。
技术领域
本发明涉及复合结构、制造该复合结构的方法以及混合式复合结构。
背景技术
在飞机和其它行业中，使用热固性预浸带铺放技术(thermoset prepreg tapelayup technique)和高压蒸汽养护构造诸如梁和加强杆的复合结构。预浸带或丝束的带宽并排铺放，以形成被真空袋装并且被高压蒸汽养护的多层层压物。在结构需要在负载输入位置连接的一些应用中，定制的金属配件被分别加工，接着被紧固于层压物结构。诸如梁的层压物结构是通过组装两个或更多个复合层压物部件而形成的。由于这些部件的几何形状，在部件之间的接合处可能会存在间隙或腔体。为了加强这些接合处，必须将填料(有时被称为“面条(noodle)”)安装在接合处中。
上述的复合层压物构造过程是耗时、劳动密集的并且需要诸如自动化纤维放置机的昂贵资本设备。在一些情况下，这些复合层压物结构可能会比期望的情况重，因为在一些部件的某些区域中需要用层加强件。此外，需要填料，这增加了制造成本并且对于一些应用而言不能充分地加强接合处。
因此，需要一种制造复合结构的方法，该方法能减少对预浸带铺放的需要并且在结构中不存在需要填料的接合处。还需要可更容易且经济地制造同时保持所需的强度并且允许配件或其它特定特征一体化的复合结构。
本申请涉及2013年12月3日提交的美国专利申请序列号14/095,531(代理人案卷号No.12-1660-US-NP)和2013年12月3日与之同时提交的美国专利申请序列号14/095,711(代理人案卷号No.13-0763-US-NP)。
发明内容
所公开的实施方式提供了一种快速容易地制造混合式复合结构并且减少对铺放叠层的需要的方法。该混合式复合结构包括被共焊接的第一热塑性部件和第二热塑性部件。第一热塑性部件被随机取向的、不连续的纤维加强，并且可通过压缩模制制造。第一部件的压缩模制允许集成一个或多个一体的配件并且形成复杂或特定的结构特征。压缩模制的使用还使结构中不存在需要填料的接合处。第二热塑性部件是被连续纤维加强的层压物，以便提供具有具体应用所需的整体强度和刚性的结构。
根据一个公开的实施方式，提供了一种制造复合结构的方法。模制被不连续的纤维加强的热塑性树脂第一部件。铺放被大体连续的纤维加强的热塑性树脂第二部件。第一部件和第二部件被共焊接。
根据另一个公开的实施方式，提供了一种制造复合结构的方法。模制具有腹板和与腹板成一体的至少一个凸缘的被纤维加强的热塑性部件。将被纤维加强的热塑性盖铺放并且放置在凸缘上。将热塑性盖与凸缘连接。
根据另一个实施方式，提供了一种制造复合梁的方法。使用热塑性预浸片模制梁，并且使用热塑性预浸带制造至少一个盖。盖和梁被共焊接。
根据其它实施方式，混合式复合结构包括第一热塑性树脂部件和第二热塑性树脂部件。第一热塑性树脂部件被不连续的纤维加强，并且第二热塑性树脂部件被连续的纤维加强并且连接到第一热塑性树脂部件。
根据另一个实施方式，一种复合结构包括由被随机取向的、不连续的纤维加强的热塑性树脂形成的复合梁。梁包括腹板和与腹板成一体的一对凸缘。复合结构还包括与凸缘之一连接的至少一个复合盖。复合盖由被连续的纤维加强的热塑性树脂形成。
特征、功能和优点可独立地在本公开的各种实施方式中实现，或者可组合在其它实施方式中，在所述其它实施方式中，可参照下面的描述和附图发现其它细节。
附图说明
表征示例性实施方式的新颖特征在随附的权利要求书中阐述。然而，当结合附图阅读时，将通过下面参照本公开的示例性实施方式的详细描述最佳地理解示例性实施方式以及这些实施方式的优选使用模式、其它目的和优点，其中：
图1是根据所公开的方法制造的具有一体配件的混合式复合结构的立体图的图示。
图2是图1的混合式结构的分解立体图的图示。
图3是沿着图1中的3-3线截取的剖视图的图示。
图4是图3中的被指定为图4的区域的图示。
图5是热塑性预浸料片的平面图的图示。
图6是将盖铺放在模制的复合凸缘上的自动化纤维放置机的立体图的图示。
图7是连续压缩模制机的图解侧视图的图示。
图8是根据所公开的方法制造的波状外形的混合式复合帽纵梁的立体图的图示。
图9是根据所公开的方法制造的波状外形的混合式复合框架构件的立体图的图示。
图10是制造混合式复合结构的方法的流程图的图示。
图11是示出所公开的方法的另外细节的流程图的图示。
图12是飞机制造和维修方法的流程图的图示。
图13是飞机的框图的图示。
具体实施方式
首先，参照图1和图2，混合式复合结构20大体上包括模制的第一复合部件22和用于加强并且硬化第一部件22的层压的第二部件36。在范例中，第一部件22包括由模制的热塑性复合物(TPC)材料形成的整体梁22，然而，如随后将讨论的，第一部件22可具有适于针对特定应用传递负载的各种形状和构造中的任一个，包括沿着其长度具有一个或多个弯曲或轮廓的形状。第二部件36包括接合梁22的TPC盖36。
梁22包括由中心腹板24连接从而形成I形横截面的一对凸缘26。腹板24可包括一个或多个减重孔34，以减轻梁22的重量。梁22还包括位于其相对两端的一对配件30。在图示的示例中，配件30包括与腹板24和凸缘26形成一体的TPC凸耳32。然而，示例性的凸耳32只是可使用下述模制技术与梁22形成一体的各种配件和特征的示例。此外，配件30可包括与TPC腹板24和TPC凸缘26共模制的金属配件。TPC盖36是覆盖各凸缘26并且共焊至各凸缘26的层压物。TPC层压物盖36用于硬化并且加强模制的TPC梁22。
现在，还参照图3，整体梁22的各凸缘26与腹板24和凸耳32形成一体。凸缘26和腹板24形成不存在需要填料的腔体或间隙的连续T形横截面。如图4中所示，梁22由模制的热塑性树脂42形成，该模制的热塑性树脂被分散的、随机取向、不连续的纤维44加强。TPC层压物盖36中的每个由包括热塑性树脂42的多个薄层形成，热塑性树脂42被具有任何所需取向或取向的组合的连续纤维40根据预定的铺层结构(未示出)加强。第一部件22和第二部件36(即，梁22和盖36)沿着对应的接合表面28、38被共焊接。可使用以下将更详细讨论的许多技术中的任一种来实施共焊接。
参照图4和图5，可通过诸如压缩模制的任何合适的模制技术来制造梁22，在压缩模制中，将一定装载量的热塑性预浸纤维片25(未示出)引入具有梁22的形状的模腔(未示出)中。将所述装载量的热塑性预浸纤维片加热至热塑性树脂的熔融温度，直到纤维片25中的树脂熔融并变得可流动，从而形成热塑性树脂和不连续的随机取向的纤维的可流动混合物。可流动混合物被压缩，以填充模腔，接着快速冷却并且被从模具中取出。如本文使用的，“片”、“TPC片”和“纤维片”是指包含适于加强梁22的纤维的热塑性树脂的个体片、碎片、切片、层或块。
在图5中示出的实施方式中，纤维片25中的每个纤维片具有大体矩形的长薄形形状，在该形状中，加强用纤维44具有基本相同的长度L和宽度W。然而，在其它实施方式中，纤维片25可具有其它形状，并且加强用纤维44的长度L可变化。具有不同长度的纤维44的存在可有助于实现纤维片25在梁22中更均匀地分布，同时提升各向同性机械性质和/或加强梁22。在一些实施方式中，模具的装载可包括装载具有不同尺寸和/或形状的TPC片25的混合物。纤维片25可以是通过将大块预浸带切成所需尺寸和形状而制造的“新”片。另选地，纤维片25可以是通过将废弃的预浸TPC材料切成所需尺寸和形状而制造的“回收”片。
形成片25的部分的热塑性树脂可包括相对高粘性的热塑性树脂，诸如(而不限于)PEI(聚醚酰亚胺)、PPS(聚苯硫醚)、PES(聚醚砜)、PEEK(聚醚醚酮)、PEKK(聚醚酮酮)和PEKK-FC(聚醚酮酮-fc级)，等等。片25中的加强用纤维44可以是诸如(而不限于)碳、金属、陶瓷和/或玻璃纤维的各种高强度纤维中的任一种。
可使用各种技术中的任一种来制造TPC层压物盖36。例如，可通过根据预定的铺层结构堆叠具有所需纤维取向的纤维预浸层，用手来铺放盖36。在一个实施方式中，铺层堆叠可被加固、裁切成所需尺寸，然后被置于凸缘26上，之后可将盖36与凸缘26共焊接。可用手或者使用取放机(未示出)来将加固的铺层堆叠放置在凸缘26上。在另一个实施方式中，铺层堆叠可直接形成在凸缘26上，然后通过将结构20放置在模具中并且将凸缘26和盖36压缩在一起并且将铺层堆叠加热至树脂的熔融温度来进行加固。可使用自加热模具或通过将模具放置在烤炉内来实现必要的加热。铺层堆叠和凸缘26二者的同时加热导致接合表面28、38(图4)处的树脂熔融，从而共焊接盖36和凸缘26。这里，应该注意，可使用各种其它技术中的任一种技术来熔融接合表面28、38处的热塑性树脂，从而共焊接盖36和凸缘26，包括(但不限于)激光焊接、超声焊接、感应焊接和电阻焊接，等等。
还可以使用自动化纤维放置(AFP)设备在原位来铺放盖36，以要么在铺放工具(未示出)上或直接在凸缘26上形成盖36的叠层(复合层)。在图6中示出了适于铺放盖36的典型AFP机68。在图示的示例中，使用AFP机68作为操纵器(未示出)上的末端执行器，以将盖36的叠层直接铺放在凸缘26上。
AFP机68是计算机数字控制的并且包括梳80，梳80引导进入的预浸丝束78(或条带)进入织带机82中，织带机82将丝束78并排布置成预浸纤维材料的带宽86。丝束切割器84将带宽86切割成所需长度。带宽86经过下面的依从辊(compliant roller)88，该辊88将带宽86施加并压实到凸缘26上或下面的已经被放置在凸缘26上的叠层上。将带宽86放在热塑性预浸带或预浸丝束78的平行行(parallel course)76中，以形成盖36的各个层或叠层。根据预定的铺层结构，在纤维取向是相对于参考方向的预选角度的情况下，放置这些行76。在图示的示例中，正形成的叠层的行76具有0度的纤维取向。可选地，可在AFP机68上安装激光器90或诸如热气体火炬、超声电筒或红外源的类似热源，用于加热或熔融凸缘26和盖36的接合表面28、38(图4)。激光器90将撞击凸缘26和丝束78的带宽86的光束92投射到其中带宽86正被放置到凸缘72上的区域94中。光束92熔融丝束78和凸缘26下面的层二者中的树脂，从而“在传输过程中(on-the-fly)”共焊接盖36和凸缘26。
在另一个实施方式中，可使用图7中示出的连续压缩模制(CCM)机制造包含连续纤维加固的TPC层压物盖70。CCM机90大体包括预形成区102和加固区108。在预形成区102中，纤维加固的热塑性材料的叠层98以它们的正确取向被加载到叠层堆叠中，并且与工具100组合。
叠层98的堆叠连同工具100一起被供应到预形成区102中，在预形成区102中，它们在升高的温度下被预形成为盖36的大体形状。预形成的盖36接着退出预形成区102并且进入加固区108，在加固区108中，盖被加固以形成单个一体的TPC层压物盖36。用于预形成盖36的升高温度高得足以造成层98软化，使得在预形成过程期间，叠层98可根据需要弯曲。
预形成的盖36进入加固区108内的单独或连接的加固结构104。加固结构104包括大体用114指示的多个标准化加工模具，这些模具单独与工具100相配合。加固结构104具有脉动结构116，脉动结构116逐渐将预形成的盖36在加固区108内向前移动并且远离预形成区102。当盖36向前移动时，盖36首先进入加热区106，加热区106将盖36加热至允许叠层98的基质树脂的聚合物成分自由流动。
接下来，盖36向前移动到加压区110，其中，使标准化模具114共同或单独地处于足以将叠层98加固(即，允许基质树脂自由流动)成其所需形状和厚度的预定力(压力)下。可用绝缘体形成具有多个不同温度区的各模具114。打开模具114，并且将盖36推入加固结构104内，远离预形成区102。然后，再关闭模具114，允许预形成的盖36的一部分在不同温度区内的力下被施压。当预形成的盖36逐渐被推向冷却区112时，对模具114的各温度区，重复这个过程。
在冷却区112中，可使形成且成形的盖36的温度低于叠层98的基质树脂的自由流动温度，从而造成熔融或加固的盖36硬化成它最终的受压形状。完全形成且加固的盖36接着退出加固结构104，其中，在118收集加工构件100。
上述CCM机96可特别适于制造盖36或者沿着它们的长度具有一个或多个弯曲或轮廓的类似的部件，然而，可使用其它技术制造带有连续纤维加强件的TPC层压物盖36，所述其它技术包括(但不限于)拉挤成型或辊压成形。
如之前提到的，根据所公开的方法制造的混合式复合结构20可包括一个或多个弯曲或轮廓。例如，参照图8，复合结构20可以是帽纵梁20a。帽纵梁20a包括：第一部件22a，其由被不连续的、随机取向的纤维加强的热塑性树脂形成；以及第二部件36a，其由被连续纤维加强的热塑性树脂形成。第一部件22a包括帽成形部分48和向外延伸的凸缘52。第二部件36a的横截面是帽子形状。帽子形状的第二部件36a覆盖帽子形状的部分48并且与它一起被共焊接。第一部件22a和第二部件36a二者具有沿着半径R弯曲的公共纵轴56。
图9示出根据所公开的方法制造的混合式复合结构20b的另一个示例。在这个示例中，复合结构20b包括均沿着半径R弯曲的第一模制TPC部件22b和第二TPC层压物部件36b。具有T形横截面的第一部件22b由被随机取向的、不连续纤维加强的热塑性树脂形成，并且包括与中心腹板64形成一体的凸缘62。复合结构20b的第二部件36b是由被所需取向的连续纤维加强的热塑性树脂形成的层压物，并且包括与凸缘62共焊接的盖66。
图10大体示出制造之前描述的类型的混合式复合结构20的方法的整体步骤。在步骤95中，模制具有连续加强用纤维的TPC第一部件22。在步骤97中，铺放具有连续加强用纤维的TPC第二部件36。在步骤99中，通过将TPC第一部件22和第二部件36沿着它们各自的接合表面28、38熔融来共焊接这两个部件22、36。
图11大体示出制造混合式复合结构20(诸如，图1和图2中示出的复合梁)的方法的整体步骤。从102开始，通过从大块卷上切下TPC带来制造热塑性纤维预浸片25。在104中，可选地，可通过加热和压缩TPC纤维片25来预先加固它们。在106中，将一定装载量的TPC纤维片25引入模具中。在108中，将装载的TPC纤维加热至片25中的热塑性树脂的熔融温度，从而导致树脂变得可流动并且填充模具。在110中，模具中的装载物被压缩并且模制为TPC第一部件22。在112中，使用之前讨论的技术中的任一种铺放被连续纤维加强用的TPC第二部件36。在114中，使TPC第一部件22和第二部件36沿着它们各自的接合表面38、28接触。在116中，将TPC第一部件22和第二部件36沿着它们各自的接合表面38、28共焊接。
本公开的实施方式可在各种潜在的应用中进行使用，特别是在运输行业中，包括(例如，航空、海事、汽车应用和可使用诸如梁、纵梁和加强杆的复合式结构构件的其它应用)。因此，现在参照图12和图13，本公开的实施方式可用于如图12中所示的飞机制造和维修方法118和如图13中所示的飞机120的背景。所公开的实施方式的飞机应用可包括例如(而不限于)底梁、翼梁、肋、机身部分、加强杆和其它复合式结构构件。在预制造期间，示例性方法118可包括飞机120的规格和设计122以及材料采购124。在制造期间，发生部件和子组件制造126以及飞机120的系统整合128。此后，飞机120可经过合格审定和运输130，以进入运行132。当由顾客进行运行时，安排对飞机120进行常规维护和维修134(还可包括改装、重构、翻新等等)。
可由系统整合商、第三方和/或运营商(例如，顾客)执行或进行方法118中的各过程。出于进行此描述的目的，系统整合商可包括(而不限于)任何数量的飞机制造商和主系统分包商；第三方可包括(而不限于)任何数量的售卖方、分包商和供应商；并且运营商可以是航空公司、租赁公司、军事单位、服务组织等。
如图13中所示，通过示例性方法118制造的飞机120可包括带有多个系统138和内部140的机身136。高级系统138的示例包括推进系统142、电子系统144、液压系统146和环境系统148中的一个或多个。可以包括任何数量的其它系统。尽管示出了飞机示例，但本公开的原理可应用于其它行业(诸如，海事和汽车行业)。
可在制造和维修方法118的阶段中的任一个或多个期间采用本文中实施的系统和方法。例如，可用运行飞机120时制造的部件或子部件类似的方式构造或制造对应于制造过程126的部件或子部件。另外，例如，通过相当大程度地迅速完成组装飞机120或降低飞机120的成本，在制造阶段126和128期间可以利用一个或更多个设备实施方式、方法实施方式或其组合。类似地，当飞机1100例如在运行期间并且不限制于维护和维修134时，可以利用一个或多个设备实施方式、方法实施方式或者其组合。
已经出于例示和描述的目的提供了对不同示例性实施方式的描述，该描述不旨在是排他性的或者限于所公开形式的实施方式。对应本领域的普通技术人员而言，许多修改形式和变形形式将是明显的。另外，相比于其它示例性实施方式，不同示例性实施方式可提供不同优点。选择描述所选择的一个或多个实施方式，以最佳地说明这些实施方式、实际应用的原理，并且使本领域的其它普通技术人员能够理解进行了各种适于预期实际使用的修改的各种实施方式的公开。另外，本公开包括根据以下条款的实施方式：
条款1.一种制造复合结构的方法，该方法包括：
模制热塑性树脂第一部件，该热塑性树脂第一部件由不连续的纤维加强；
铺放热塑性树脂第二部件，该热塑性树脂第二部件由大体连续的纤维加强；以及
共焊接所述热塑性树脂第一部件和所述热塑性树脂第二部件。
条款2、根据条款1所述的方法，其中，模制热塑性树脂第一部件是通过压缩模制热塑性树脂和不连续的、随机取向的纤维的可流动混合物来执行的。
条款3、根据条款2所述的方法，其中，所述压缩模制包括：
将一定装载量的热塑性预浸片放置在模具中；
通过熔融所述预浸片中的热塑性树脂来形成树脂和纤维的可流动混合物；以及
压缩所述模具内的所述可流动混合物。
条款4、根据条款3所述的方法，其中：
所述压缩模制包括：在所述热塑性树脂第一部件已被模制之后冷却该热塑性树脂第一部件；并且
共焊接所述热塑性树脂第一部件和所述热塑性树脂第二部件包括：将所述热塑性树脂第一部件和所述热塑性树脂第二部件加热至所述热塑性树脂第一部件和所述热塑性树脂第二部件中的热塑性树脂的熔融温度。
条款5、根据条款1所述的方法，其中，所述共焊接是通过以下步骤来执行的：
沿着所述热塑性树脂第一部件和所述热塑性树脂第二部件的接合表面将所述热塑性树脂第一部件和所述热塑性树脂第二部件组装在一起；以及
熔融所述接合表面。
条款6、根据条款5所述的方法，其中，熔融所述接合表面是通过将组装的所述热塑性树脂第一部件和所述热塑性树脂第二部件放置于烤炉中来执行的。
条款7、根据条款1所述的方法，该方法还包括：
在执行共焊接之前，加固所述热塑性树脂第二部件。
条款8、根据条款1所述的方法，其中：
铺放所述热塑性树脂第二部件是通过将叠层铺放在所述热塑性树脂第一部件的表面上来执行的；并且
所述共焊接是在将所述热塑性树脂第二部件铺放在所述热塑性树脂第一部件的表面上的同时执行的。
条款9、根据条款8所述的方法，其中，所述共焊接是在将所述热塑性树脂第二部件铺放在所述热塑性树脂第一部件的表面上的同时通过局部熔融所述热塑性树脂第一部件和所述热塑性树脂第二部件的接合表面来执行的。
条款10、一种通过条款1所述的方法制造的复合结构。
条款11、一种制造复合结构的方法，该方法包括：
压缩模制具有腹板和与所述腹板成一体的至少一个凸缘的由纤维加强的热塑性部件；
铺放由纤维加强的热塑性盖；
将所述热塑性盖放置在所述凸缘上；以及
将所述热塑性盖与所述凸缘连接。
条款12、根据条款11所述的方法，其中，所述压缩模制包括：
将一定装载量的热塑性预浸片引入具有模腔的模具中，所述模腔对应于所述腹板和所述凸缘的形状；
加热所述模具，直到所述热塑性预浸片中的树脂熔融并且变得可流动；以及
压缩所述模具内的可流动树脂。
条款13、根据条款11所述的方法，其中，铺放由纤维加强的热塑性盖是通过将成行的热塑性预浸带铺放在所述凸缘上来执行的。
条款14、根据条款13所述的方法，其中，将所述热塑性盖与所述凸缘连接是通过在铺放成行的热塑性预浸带的同时局部熔融所述预浸带和所述凸缘的接合表面来执行的。
条款15、根据条款11所述的方法，其中，铺放由纤维加强的热塑性盖是使用自动化纤维放置机铺放多个复合叠层来执行的。
条款16、根据条款11所述的方法，其中，将所述热塑性盖与所述凸缘连接是通过共焊接所述热塑性盖和所述凸缘来执行的。
条款17、一种制造复合梁的方法，该方法包括：
使用热塑性预浸片模制梁；
使用热塑性预浸带制造至少一个盖；以及
共焊接所述盖和所述梁。
条款18、一种混合式复合结构，该混合式复合结构包括：
第一热塑性树脂部件，该被第一热塑性树脂部件由不连续的纤维加强；
第二热塑性树脂部件，该被第二热塑性树脂部件由连续的纤维加强并且被连接到所述第一热塑性树脂部件。
条款19、根据条款18所述的混合式复合结构，其中，所述第一热塑性树脂部件包括腹板和与所述腹板成一体的至少一个凸缘。
条款20、根据条款19所述的混合式复合结构，其中，所述第二热塑性树脂部件包括与所述凸缘共焊接的盖。
条款21、根据条款19所述的混合式复合结构，其中，所述第一热塑性树脂部件包括与所述腹板和所述凸缘中的至少一者形成一体的至少一个配件。
条款22、根据条款18所述的混合式复合结构，其中，所述第二热塑性树脂部件包括热塑性树脂的多个层压的叠层，所述热塑性树脂由连续的纤维加强。
条款23、一种复合结构，所述复合结构包括：
复合梁，该复合梁由被随机取向的、不连续的纤维加强的热塑性树脂形成，所述梁包括腹板和与所述腹板成一体的一对凸缘；以及
至少一个复合盖，所述至少一个复合盖被连接到所述凸缘中的一个，所述复合盖由被连续的纤维加强的热塑性树脂形成。
条款24、根据条款23所述的复合结构，其中，所述复合梁和所述复合盖中的每个均具有沿着其长度的至少一个轮廓。
条款25、根据条款23所述的复合结构，其中：
所述至少一个复合盖和所述至少一个凸缘均具有接合表面；并且
所述至少一个复合盖和所述至少一个凸缘沿着所述接合表面被共焊接。

Claims (13)

1.一种制造复合结构的方法，该方法包括：
压缩模制具有腹板和与所述腹板成一体的至少一个凸缘的由纤维加强的热塑性部件；
铺放由纤维加强的热塑性盖；
将所述热塑性盖放置在所述凸缘上；以及
将所述热塑性盖与所述凸缘连接。
2.根据权利要求1所述的方法，其中，所述压缩模制包括：
将一定装载量的热塑性预浸片引入具有模腔的模具中，所述模腔对应于所述腹板和所述凸缘的形状；
加热所述模具，直到所述热塑性预浸片中的树脂熔融并且变得可流动；以及
压缩所述模具内的可流动树脂。
3.根据权利要求1所述的方法，其中，铺放由纤维加强的热塑性盖是通过将成行的热塑性预浸带铺放在所述凸缘上来执行的。
4.根据权利要求3所述的方法，其中，将所述热塑性盖与所述凸缘连接是通过在铺放成行的热塑性预浸带的同时局部熔融所述预浸带和所述凸缘的接合表面来执行的。
5.根据权利要求1所述的方法，其中，铺放由纤维加强的热塑性盖是使用自动化纤维放置机铺放多个复合叠层来执行的。
6.根据权利要求1所述的方法，其中，将所述热塑性盖与所述凸缘连接是通过共焊接所述热塑性盖和所述凸缘来执行的。
7.根据权利要求1所述的方法，其中，铺放由纤维加强的热塑性盖包括铺放具有大致连续纤维的由纤维加强的热塑性盖。
8.根据权利要求1所述的方法，其中，压缩模制所述由纤维加强的热塑性部件包括；压缩模制具有所述腹板、与所述腹板成一体的所述凸缘、和与所述腹板成一体的配件的由纤维加强的热塑性部件。
9.根据权利要求8所述的方法，其中，所述配件包括从所述腹板纵向延伸的凸耳。
10.根据权利要求1所述的方法，其中，压缩模制所述由纤维加强的热塑性部件包括；压缩模制具有所述腹板、与所述腹板成一体的所述凸缘、和与所述腹板或所述凸缘成一体的复杂结构特征的由纤维加强的热塑性部件。
11.根据权利要求10所述的方法，其中，所述复杂结构特征包括模制穿过所述腹板的减重孔。
12.根据权利要求10所述的方法，其中，所述复杂结构特征包括沿所述由纤维加强的热塑性部件的纵向长度的至少一个弯曲。
13.一种通过权利要求1-12中任一项所述的方法制造的复合结构。
CN202110637091.XA 2013-12-03 2014-12-01 复合结构、制造该复合结构的方法以及混合式复合结构 Pending CN113306170A (zh)

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