CN102781651A - 利用中间部件的用于两个复合材料箱的连接布置及用于制造该中间部件的方法 - Google Patents

利用中间部件的用于两个复合材料箱的连接布置及用于制造该中间部件的方法 Download PDF

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CN102781651A
CN102781651A CN2011800115298A CN201180011529A CN102781651A CN 102781651 A CN102781651 A CN 102781651A CN 2011800115298 A CN2011800115298 A CN 2011800115298A CN 201180011529 A CN201180011529 A CN 201180011529A CN 102781651 A CN102781651 A CN 102781651A
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安东尼奥·德朱利安阿瓜多
洛雷托·马第尼斯费尔南德斯
奥斯卡·德拉库兹加西亚
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    • 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
    • B29C65/5064—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 of particular form, e.g. being C-shaped, T-shaped
    • B29C65/5078—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 of particular form, e.g. being C-shaped, T-shaped and being composed by several elements
    • 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
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    • 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
    • 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
    • B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
    • B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
    • B29C66/54—Joining several hollow-preforms, e.g. half-shells, to form hollow articles, e.g. for making balls, containers; Joining several hollow-preforms, e.g. half-cylinders, to form tubular articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
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    • 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
    • B29C66/725—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 hollow-walled or honeycombs
    • B29C66/7252—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 hollow-walled or honeycombs hollow-walled
    • B29C66/72523—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 hollow-walled or honeycombs hollow-walled multi-channelled or multi-tubular
    • 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
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/302—Details of the edges of fibre composites, e.g. edge finishing or means to avoid delamination
    • 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
    • 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
    • B29C66/13—Single flanged joints; Fin-type joints; Single hem joints; Edge joints; Interpenetrating fingered joints; Other specific particular designs of joint cross-sections not provided for in groups B29C66/11 - B29C66/12
    • B29C66/131—Single flanged joints, i.e. one of the parts to be joined being rigid and flanged in the joint area
    • 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
    • B29C66/72—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
    • B29C66/7214—Fibre-reinforced materials characterised by the length of the fibres
    • B29C66/72141—Fibres of continuous length
    • 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
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
    • B29C70/48—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
    • 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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    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/4998—Combined manufacture including applying or shaping of fluent material
    • 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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Abstract

一种利用中间部件（31）的用于两个复合材料箱（11、11’）的连接布置，以及一种制造所述中间部件（31）的方法。所述连接通过在所述箱（11、11’）的外壳（15，15’；17、17’）与所述T形部件（31）的上和下凸缘（33、35）之间使用铆钉来实现。所述制造方法包括以下步骤：a）提供两个C形预成形件（41、41’），所述C形预成形件被构造成使得它们的腹板（43、43’）彼此平行，它们的上和下凸缘（55、55’；57、57’）大致平行于所述外壳（15、15’；7’、15’）的末端区域；b）提供两个平坦的预成形件（45、47），以加强凸缘（35、37）；c）使用RTM方法来形成和固化由所述预成形件（41、41’、45、47）制成的部件（31）。

Description

利用中间部件的用于两个复合材料箱的连接布置及用于制造该中间部件的方法
技术领域
本发明涉及利用中间部件的用于两个复合材料箱的连接布置以及所述中间部件的制造方法，更具体地涉及利用双T形中间部件的用于飞行器的水平稳定器的侧箱的连接布置。
背景技术
当前尤其在航空工业中，具有有机基体和连续纤维（主要基于环氧树脂和碳纤维）的复合材料被大量地用于各种各样的结构元件中。
众所周知地，航空结构需要将各种结构元件集成起来。例如，机身需要集成外壳与不同的结构元件（诸如横梁、框架和纵梁）。与使用金属材料的情形不同，在使用机械连接是实际应用中用于将构件的不同结构元件集成起来的唯一选择时，还可以使用化学物连接集成复合材料。
在特定的航空结构中，两个构件必须以确保两个构件之间具有有效负载传递的方式被连接。这通常需要使用中间部件。这尤其在连接飞行器的水平稳定器的侧箱时发生，因为水平尾部稳定器必须如一结构单元那样运转（behave）。此外，连接既经受空气动力负载、又经受由用于配平水平稳定器的机构所产生的负载。
因为它是存在问题的连接，因此，对于剪切连接和牵引连接以及使用由金属材料、复合材料或混合材料制成的中间部件，已经有多种建议。
在这些建议中的一个建议中，如在US2009159742中描述的，使用由复合材料制成的双T形中间部件。
对于侧箱的特定构造，在该文献中描述的双T形中间部件的使用可能存在问题。本发明旨在解决这些问题。
发明内容
本发明的一个目的在于提供一种使用双T形中间部件的在两个抗扭箱（诸如飞行器的水平尾部稳定器的侧箱）之间的连接布置，该连接布置便于组装部件以实施所述连接。
本发明的另一目的在于提供一种用于制造所述中间部件的方法，以赋予所述中间部件优化的构造，使其用作所述侧箱的中间连接部件。
在第一方面中，通过一种制造双T形部件的方法来实现这些和其他目的，其中所述双T形部件具有中心部分以及上凸缘和下凸缘，所述双T形部件用作两个箱形结构构件的中间连接部件，其中两个箱形结构构件包括上外壳和下外壳，所述连接形成在所述构件的上外壳和下外壳与所述部件的上凸缘和下凸缘之间，所述部件和所述箱两者由复合材料制成，所述方法包括以下步骤：
a）提供两个C形预成形件，所述C形预成形件被构造成使得它们的中心部分彼此平行，它们的上凸缘和下凸缘大致平行于所述外壳的末端区域；
b）提供两个平坦的预成形件，以加强凸缘；
c）使用RTM方法来形成和固化由所述预成形件制成的部件。
在优选实施例中，所述平坦的预成形件被布置在双T形中间部件的凸缘的中心区域中，而不覆盖其的整个宽度，其中两个或多个区段朝向它的纵向轴线是台阶状的。这导致了用于制造双T形中间部件的有效方法，其便于在箱之间逐步传递负载。
在其他优选实施例中，所述平坦的预成形件包括在它们的末端中的一个末端处的局部加强区域。这样产生用于制造双T形中间部件的有效方法，其中所述双T形中间部件被适当配置用于接收局部负载，诸如由水平尾部稳定器的配平机构所产生的负载。
在其他优选实施例中，中间连接部件被应用于具有或不具有二面角的箱，或者应用于多肋箱或多加强杆箱。这样产生用于制造双T形中间部件的有效方法，其中所述双T形中间部件被适当配置用于飞行器的水平尾部稳定器的基本类型的侧箱。
在第二方面中，通过提供用于两个箱形结构构件的连接布置来实现上述目的，其中所述两个箱形结构构件包括上外壳和下外壳，所述连接布置使用双T形中间连接部件并且使用铆钉连接所述构件的外壳与所述部件的上凸缘和下凸缘，所述部件和所述构件两者由复合材料制成，其中所述部件通过使用上述方法制造。
在优选实施例中，所述连接布置在部件的上凸缘和下凸缘的具有不同厚度的每个区域中使用至少两排铆钉。这样产生在箱之间非常有效地传递负载的连接布置。
本发明的其他特征和优点在以下对实施例的详细描述中被说明，其中所述实施例关于附图解释了本发明的目的。
附图说明
图1示出用于飞行器的水平尾部稳定器的两个侧箱的连接布置，其中所述连接布置利用现有技术中己知的T形中间部件。
图2示出根据本发明的T形中间部件，以及图3示出用于制造根据本发明的所述中间部件的方法的预成形件。
图4示出用于飞行器的水平尾部稳定器的、具有二面角（dihedral）的两个侧箱的连接布置的横截面视图，其中所述连接布置利用根据本发明的T形中间部件。
图5示出用于飞行器的水平尾部稳定器的、不具有二面角的两个侧箱的连接布置的横截面视图，其中所述连接布置利用根据本发明的T形中间部件。
具体实施方式
下面的描述涵盖用于飞行器的水平尾部稳定器的两个侧箱11、11’的连接布置的本发明实施例，其中所述连接布置利用双T形中间部件。侧箱11、11’和中间部件两者由碳纤维增强塑料（CFRP）的复合材料制成。
在US2009159742中描述的连接布置的情况中，图1示出所述连接布置基于双T形部件21的凸缘25、27与侧箱11、11’的外壳15、17；15’、17’的末端区域的重叠，以便于它们之间的铆接。并且，这种连接布置使得能够通过将侧箱11、11’定位在它们的适当位置、并且随后将部件21插入它们之间而将所述结构组装起来。
这种连接布置需要外壳15、17；15’、17’的末端区域被平坦化，使得它们能够被附连至所述部件的平坦的凸缘25、27。
根据本发明的优选实施例，如在图2中示出的利用双T形中间部件31（该双T形中间部件31具有中心部分33和两个凸缘35、37）的用于飞行器的尾部稳定器的两个侧箱11、11’的连接布置基于利用树脂转移模制（RTM）方法（即，闭式模制工艺）进行的部件的制造，其中利用如图3中示出的预成形件进行树脂注塑：具有中心部分43、43’以及凸缘55、57；55’、57’的两个C形预成形件41、41’；两个平坦的预成形件45、47（如对于本领域技术人员来说是熟知的，术语“平坦的”不应该被以严格的几何意义理解）。
如图4和5所示，使用适当的模具、根据所述方法制造的、分别用于具有和不具有二面角的几个箱11、11’的中间部件31具有几个凸缘35、37，通过用平坦的预成形件45、47连接C形预成形件的凸缘55、55’；57、57’而形成所述几个凸缘35、37，其中所述平坦的预成形件45、47一方面被具体构造用于适应箱11、11’的末端的具体构造，另一方面便于在连接中的负载的逐步传递。
部件31对于箱11、11’的末端的构造的上述适应性使得本发明能够被应用于具有二面角或不具有二面角的箱，并且能够应用于多肋或多加强杆（multi-spar）的箱。
并且，具体参考附图3和4，可以看到，预成形件45、47可以由沿纵向和横向具有不同厚度的区段构造而成。
并且，图3示出上预成形件45包括基础区段61，在基础区段61上具有区段63，所述区段63沿纵向覆盖整个上凸缘、但是比区段61窄。在所述区段63上，区段65和67又位于区段63的末端的一个末端上。一方面，得益于区段61、63的台阶形式，使得这个构造便于在箱11、11’之间逐步传递负载；而另一方面，这个构造通过区段65、67提供局部加强（这可能是需要的）。
在图4中，上预成形件45包括基础区段61，所述基础区段61不覆盖部件31的上凸缘的全部，这意味着：第一排铆钉被应用于外壳15、15’与来自C形预成形件的标记55、55’处的区域的连接，并且被宽度逐渐减小的台阶式区段63、65和67覆盖。这种台阶式构造便于通过部件31在箱11、11’之间逐步地传递负载。图4示出在不同厚度的每个区域中具有两排铆钉的优选实施例。
本发明包括以下优点：
-在连接所述箱11、11’时使用的部件的数量显著减小。
-利用适当的工具使得中间部件31的与侧箱的外壳15、15’、17、17’相接触的内部表面55、55’；57、57’具有优化的光洁度（finish），这便于对制造和组装过程中的公差要求的顺应性；一旦侧箱11、11’处于其适当的位置而没有箱11、11’的任何后续的移动，则这种顺应性将通过移动中间部件31来实现。
虽然已经关于优选实施例完整地描述了本发明，然而，可以清楚地知道，本发明可以包括在其范围内任何修改，该范围不受前述的实施例的限制，而是由以下权利要求的内容限定。

Claims (12)

1.一种用于制造双T形部件（31）的方法，其中所述双T形部件具有中心部分（33）以及上凸缘和下凸缘（35、37），所述双T形部件用作两个箱形结构构件（11、11’）的中间连接部件，其中两个箱形结构构件包括上外壳（15、15’）和下外壳（17、17’），所述连接形成在所述构件（11、11’）的上外壳和下外壳（15、15’；17、17’）与所述部件（31）的上凸缘和下凸缘（35、37）之间，所述部件（31）和所述箱（11、11’）两者由复合材料制成，
其特征在于，所述方法包括以下步骤：
a）提供两个C形预成形件（41、41’），所述C形预成形件被构造成使得它们的中心部分（43、43’）彼此平行，它们的上凸缘和下凸缘（55、55’；57、57’）大致平行于所述外壳（15、15’；17、15’）的末端区域；
b）提供两个平坦的预成形件（45、47），以加强凸缘（35、37）；
c）使用RTM方法来形成和固化由所述预成形件（41、41’、45、47）制成的部件（31）。
2.根据权利要求1所述的用于制造双T形部件（31）的方法，其特征在于，所述平坦的预成形件（45、47）被布置在部件（31）的凸缘（35、37）的中心区域中，而不覆盖它们的整个宽度。
3.根据权利要求2所述的用于制造双T形部件（31）的方法，其特征在于，所述平坦的预成形件（45、47）包括具有不同厚度的至少两个区段（61、63；71、73），较厚的区段（63、73）比较薄的区段（61、71）窄。
4.根据权利要求3所述的用于制造双T形部件（31）的方法，其特征在于，所述平坦的预成形件（45、47）包括在它们的末端中的一个末端处的局部加强区域。
5.根据权利要求1-4中任一项所述的用于制造双T形部件（31）的方法，其特征在于，所述箱（11、11’）的外壳（15、17；15’、17’）的末端区域彼此不平行。
6.根据权利要求1-4中任一项所述的用于制造双T形部件（31）的方法，其特征在于，所述箱（11、11’）的外壳（15、17；15’、17’）的末端区域彼此平行。
7.根据权利要求6所述的用于制造双T形部件（31）的方法，其特征在于，所述箱（11、11’）的上外壳（15、15’）和下外壳（17、17’）的末端区域彼此不对齐。
8.根据权利要求1-7中任一项所述的用于制造双T形部件（31）的方法，其特征在于，所述箱（11、11’）是多肋箱。
9.根据权利要求1-7中任一项所述的用于制造双T形部件（31）的方法，其特征在于，所述箱（11、11’）是多加强杆（Spar）箱。
10.根据权利要求1-9中任一项所述的用于制造双T形部件（31）的方法，其特征在于，所述箱（11、11’）是飞行器的水平尾部稳定器的侧箱。
11.一种用于两个箱形结构构件（11、11’）的连接布置，其中所述两个箱形结构构件包括上外壳（15、15’）和下外壳（17、17’），所述连接布置使用双T形中间连接部件（31）并且使用铆钉在所述构件（11、11’）的外壳（15、15’；17、17’）与所述部件（31）的上凸缘和下凸缘（33、35）之间实现连接，所述部件（31）和所述构件（11、11’）两者由复合材料制成，
其特征在于，所述部件（31）由根据权利要求1-10中任一项所述的方法制造。
12.根据权利要求11所述的连接布置，其特征在于，在部件（31）的上凸缘和下凸缘（33、35）的具有不同厚度的每个区域中使用至少两排铆钉（81）。
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