CN103261021A - 多向负载连接系统 - Google Patents
多向负载连接系统 Download PDFInfo
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- CN103261021A CN103261021A CN2010800707173A CN201080070717A CN103261021A CN 103261021 A CN103261021 A CN 103261021A CN 2010800707173 A CN2010800707173 A CN 2010800707173A CN 201080070717 A CN201080070717 A CN 201080070717A CN 103261021 A CN103261021 A CN 103261021A
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- Engineering & Computer Science (AREA)
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Abstract
一种结构连接件包括具有第一基底部分和第一支腿部分的第一元件。该结构连接件还包括具有第二基底部分和第二支腿部分的第二元件。第一基底部分和第二基底部分在重叠部分连接到一起。第一支腿部分和第二支腿部分形成用于结构性连接到结构元件的空腔。
Description
技术领域
本申请的系统涉及结构连接件。具体地,本申请的系统涉及复合结构连接件。
背景技术
一种典型的结构连接件包括机械紧固法兰。例如,图1所示的是现有技术中的机械系统101。第一结构元件103通过紧固件107连接到第二结构元件105。系统101依靠紧固件107在元件103和元件105之间传递负载。由于紧固件孔需要钻孔和修边,因此通常安装紧固件107的工作强度很大。此外,紧固件107典型地围在固件孔周围产生应力集中,由此通常使得元件103和105的尺寸、厚度以及重量增加。紧固件107还可能提高腐蚀的可能性。机械紧固件还需要定期检查以确保它们不会在不经意间变松。
图2示出了另一种传统的系统201。系统201包括通过转接器205连接到一起的第一元件203和第二元件207。转接器205典型地粘着地接合或机械地紧固到第二元件207。第一元件203位于转接器205的狭槽内。在狭槽中使用粘合剂209以在转接器205和第一元件203之间产生粘合。系统201具有多个缺点,包括难以制备用于粘合的狭槽内表面。通常,粘合表面必须通过砂纸打磨和清理过程来彻底清理掉污物。狭槽的形状使得制备用于粘合连接的狭槽变得困难和耗时。此外,转接器205中狭槽的形状通常将粘合剂的类型限定为具有厚的胶层的糊状粘合剂。系统201另一个缺点在于当转换器205为固化过的刚性结构时,公差要求通常规定狭槽必须很大以适应当第一元件203处于公差的高厚度侧的情况。如此,转换器205中较大的狭槽需要更多的粘合剂,由此增加了重量和费用。此外,狭槽的固定形状通常防止在第一元件203和狭槽的两个内表面之间施加正粘合压力。系统201的另一个缺点在于第一元件203必须平移到转换器205的狭槽中,由此需要放置元件203的空间。这在封闭几何结构中尤其成问题,例如当第二元件207为封闭的飞机机身蒙皮,并且第一元件203为飞机的舱壁结构。
尽管结构连接件的开发已经取得了长足的进步,仍然存在许多缺点。
附图说明
被认为是本申请特有的新颖性特征在所附的权利要求中提出。然而,系统本身及其优选的使用方式、以及其他的目标和优点将在参考下面的详细说明并结合附图阅读时获得最好的理解,其中附图标记最左侧的数字表示各个附图标记第一次出现在哪个附图,其中:
图1为现有技术的结构系统的横截面视图;
图2为另一个现有技术的结构系统的横截面视图;
图3为根据本申请的优选实施例的结构系统的透视图;
图4为图3所示的根据本申请的优选实施例的结构系统沿着截面线IV-IV的横截面视图;
图5为根据本申请的另一个实施例的结构系统的横截面视图;
图6为根据本申请的另一个实施例的结构系统的横截面视图;
图7为根据本申请的优选实施例的多结构系统的典范结构的横截面视图;
图8为根据本申请的另一个实施例的结构系统的横截面视图;
图9为根据本申请的另一个实施例的结构系统的横截面视图;
图10为根据本申请的另一个实施例的结构系统的横截面视图;并且
图11为根据本申请的另一个实施例的结构系统的横截面视图。
尽管本申请的系统容许有各种修改和替代形式,其具体实施例已经通过举例方式在图中详细示出并且在文中详细描述。然而应当理解的是文中对具体实施例的描述并不是为了将本发明限定为公开的特定形式,而恰好相反,旨在覆盖落在所附的权利要求所限定的本申请的精神和范围内的全部修改、等同、以及替代方案。
具体实施方式
图示的本申请的系统的各个实施例将在下面进行说明。为了清楚起见,没有在这个说明书中描述实际实现中所有的特征。应当意识到的是在任何这种实际实施方式的开发中,为了实现开发者的具体目标,必须作出多种具体实施决定,例如服从系统相关和商业相关的约束条件,其随不同的实现方式而不同。而且,可以意识到这种开发劳动可能是复杂和耗时的,但只不过是享有本公开的益处的本领域普通技术人员所承担的常规工作。
在说明书中,如在附图中描绘的,参考标记用于标示各种组件之间的空间关系以及组件的各种朝向的空间指向。然而,如本领域技术人员在完整地阅读了本申请之后将认识到的,文中描述的装置、元件、设备等等可以设置成任何期望的指向。由此,用于描述各种组件之间的空间关系或者用于描述这些组件的朝向的空间指向的诸如“上方”、“下方”、“上部”、“下部”这些术语或者其它类似术语的使用应当理解为描述组件之间的相对关系或这些组件的朝向的空间指向,因为文中描述的装置可以指向任何期望的方向。
参照图3和4,根据本申请的优选实施例的连接系统301包括第一元件305和第二元件307。第一元件305和第二元件307配置用于将嵌板309连接到表皮3。表皮303典型地为复合材料,但是表皮303可以是任意材料,例如金属。表皮303优选地为飞机的蒙皮;然而,表皮303可以是多种结构主体的任意结构组件。例如,表皮303可以是结构组件中的面板。进而,表皮303可以是卫星、火车、巴士、汽车、船只、风力涡轮机叶片、百叶箱、活动房屋以及房车上的结构,仅举几例。应该意识到虽然表皮303被描述为相对平坦的表面,表皮303可以具有多种外形和厚度。例如,表皮303可以具有翼型形状。此外,嵌板309优选地包括具有第一面311、第二面313、以及结合在第一面311和第二面313之间的核心315。优选地,嵌板309在安装到系统301之前经过完全固化。应该意识到嵌板309可以是任意类型的结构,包括固体材料。例如,嵌板309可以没有核心材料而仅包括复合材料层。此外,嵌板309可以是多种结构物,例如舱壁、翼梁、肋材、或任意的配置用于承载结构负载的支撑物。
系统301包括第一元件305和第二元件307,它们配置成组合使用将嵌板309连接到表皮303。第一元件305和第二元件307优选地为刚性结构。相应地,第一元件305和第二元件307优选地为复合结构,在安装前对它们进行固化。此外,第一元件305和第二元件307优选地通过模制工艺制造而成以产生在树脂基底上布置多个纤维的复合材料。然而,应该意识到第一元件305和第二元件307还可以为任意能够承载预定负载的材料,例如金属、塑料、木材,仅举几例。第一元件305优选地具有“T”形横截面,横截面具有内部基底部分305a、外部基底部分305b、以及支腿部分305c。内部基底部分305a、外部基底部分305b、以及支腿部分305c中的任意一个可以是锥形以最小化位于毗邻元件之间的粘结层中的应力。第一元件305,优选地通过位于表皮303和基底部分305a和305b之间的粘结层317a,沿着粘结表面D1连接到表皮303。支腿部分305c从基底部分305a和305b开始以与嵌板309的外形一致的角度延伸。应该意识到即使支腿部分305c被描述成与基底部分305a和305b具有近似90度夹角,第一元件305可以配置成支腿部分305c相对于基底部分305a和305b具有0度到180度之间的任意角度。如文中进一步描述的,第一元件305优选地在安装过程中粘合到表皮303。此外,第一元件305以及第二元件307可以包括很多种特征,例如圆角和倒角,仅举几例。
第二元件307优选地具有“T”形横截面,其具有内部基底部分307a、外部基底部分307b以及支腿部分307c。内部基底部分307a、外部基底部分307b以及支腿部分307c中的任意一个可以为锥形以最小化位于毗邻元件之间的粘合层上的应力。内部基底部分307a配置成与第一元件305的内部基底部分305a至少部分重叠。支腿部分307c从基底部分307a和307b开始以与嵌板309的形状相一致的角度延伸。应该意识到即使支腿部分307c被描述为相对于基底部分307a和307b具有近似90度夹角,第二元件307可以配置成支腿部分307c相对于基底部分307a和307b的夹角为0度到180度之间的任意角度。第二元件307的外部基底部分307b通过粘合层317b沿着结合表面D2粘合到表皮303。第二元件307的内部基底部分307a还通过粘合层317b沿着结合表面D3结合到第一元件305的内部基底部分305a。
嵌板309优选地通过粘合层317d沿着结合表面D4结合到第一元件305的支腿部分305c。类似地,嵌板309优选地通过粘合层317c沿着结合表面D5结合到第二元件307的支腿部分307c。
粘合层317a-d优选地由高强度粘合膜构成,例如3M销售的AF-163。然而粘合层317a-d可以由任何适于产生足够的结合强度的粘合剂构成。例如,粘合层317a-d可以由糊状粘合剂构成,例如Magnolia Plastics销售的Magnobond6398。粘合层317a-d需要进行高温固化,或者作为另一选择仅需要进行室温固化。
因为内部基底部分305a和内部基底部分307a重叠并结合在一起,系统301的结构负载能力得到优化。例如,如果嵌板309要经受在一个或多个方向319和321的负载,那么内部基底部分305a和内部基底部分307a起作用以将负载传递给表皮303。没有内部基底部分305a和内部基底部分307a,第一元件305和第二元件307可能会从表皮303分离开来。
简单地参照图6,系统601表示系统301的替换实施例。系统601基本上类似于系统301,除了内部基底部分305a和内部基底部分307a被缩短以允许嵌板309具有更大的容差。在安装过程中,内部基底部分305a和内部基底部分307a被配置成使第一元件305和第二元件307能够选择性地沿着方向603布置以容纳不同嵌板309的厚度。优选的是内部基底部分305a和内部基底部分307a大致上彼此平行;然而,替换实施例中第一元件305和第二元件307可以彼此成一定角度。应该意识到内部基底部分305a和内部基底部分307a可以具有多种长度、厚度和指向。此外,内部基底部分305a和内部基底部分307a可以包括多种特征,例如圆角和倒角,这是几个例子。
简单地参照图5,系统501表示系统301的替换实施例。系统501基本上类似于系统301,除了包括有紧固件。紧固件可以用于为粘合层备用。作为另一选择,紧固件可以用于维修。紧固件503可以用在外部部分305b和表皮303之间。类似地,紧固件505可以用在外部部分307b和表皮303之间。紧固件507优选地为盲孔紧固件,其可以用在内部部分305a、内部部分307a和表皮303之间。进一步,可以在支腿部分305c、支腿部分307c和嵌板309之间安装紧固件509。应该意识到各种紧固件以及各种数量的紧固件可以用在系统501中。一个替换实施例可以采用紧固件代替粘合层。
再参照图3和4,系统301的安装优选地为一个分段的过程,其包括首先将第一元件305布置并结合到表皮303。在该步骤中,结合表面通过将涂料和其它污渍从将要与粘合剂接触的表面除掉而准备好。涂覆粘合剂317a,将第一元件305设置在表皮303上,对粘合剂317a进行固化。在该步骤中,可以对第一元件305施压以确保在第一元件305和表皮303之间具有良好的结合。第一元件305的位置支配性地规定了嵌板309和第二元件307的最终位置。如此,第一元件305的准确位置通过工具被确定。在第一元件305结合到表皮303之后,嵌板309和第二元件307准备进行结合由于第一元件305和第二元件307为分立的部件,因此粘合过程所需的对表面的接触是充分的。施加粘合层317b-d。接着,第二元件307和嵌板309被定位和组装。在施加压力的过程中对粘合层317b-d进行固化。可以采用多种装置施加压力,例如真空袋和泵或者充气内胆,这是几个例子。作为另一选择,可以使用一个或多个紧固件(在图5中示出),或其他机械系统。在固化过程中选择性地向粘合层317a-d施加压力能够提高结合的质量,并且可以根据具体的粘合需要来定制胶层的厚度。在该步骤中,第一元件作用为“止挡”以使得在对粘合层317b-d进行固化的过程中第一元件305、第二元件307和嵌板309保持在期望位置。
仍然参照图3和4,作为另一选择在单个阶段的过程中安装系统301。在单个阶段的过程中,第一元件305、第二元件307和嵌板309全部在单个过程中进行结合。一个或多个工具可以用于定位并组装第一元件305、第二元件307和嵌板309。此外,一个或多个工具可以用于帮助向系统301施加压力。
现在参照图7,多个系统301可以组合使用以向嵌板309提供结构性支撑。此外,表皮303可以为翼盒中的上部和下部机翼蒙皮。翼盒为封闭结构,上部和下部蒙皮303以一定的距离固定在其中。每个系统301被配置成使嵌板309可以通过文中公开的组装次序设置在每个系统301的第一元件305和第二元件307之间。例如,嵌板309可以通过将嵌板沿与表皮303的表面近似平行的方向滑动而定位。这种结构不需要像一些传统系统那样,使嵌板309从垂直于表皮303的方向进行定位。
参照图8,系统801为系统301的替换实施例。系统801包括形状均优选为“T”形的第一元件805和第二元件807。第一元件805包括内部基底部分805a、外部基底部分805b和支腿部分805c。类似地,第二元件807包括内部基底部分807a、外部基底部分807b和支腿部分807c。第一元件805通过位于内部基底部分805a和表皮303之间以及外部基底部分805b和表皮303之间的粘合层结合到表皮303。类似的,第二元件807通过位于内部基底部分807a和表皮303之间以及外部基底部分807b和表皮303之间的粘合层结合到表皮303。在安装过程中,内部基底部分805a和内部基底部分807a被配置成使第一元件805和第二元件807能够选择性地沿着方向803放置以容纳多种嵌板309厚度。第一元件805和第二元件807可以被构型成使第一元件805和第二元件为同样的部件,由此降低了在安装之前需要进货的部件的多样性。应该意识到第一元件805和第二元件807可以具有各种长度、厚度以及指向。
参照图9,系统901为系统301的替代实施例。系统901包括形状均优选为“T”形的第一元件905和第二元件907。第一元件905包括内部基底部分905a、外部基底部分905b和支腿部分905c。类似的,第二元件907包括内部基底部分907a、外部基底部分907b和支腿部分907c。系统901类似于系统301,除了内部基底部分905a和内部基底部分907a在斜接部分部分地重叠。此外,内部基底部分907a结合到内部基底部分905a和表皮303。应该意识到第一元件905和第二元件907可以具有各种长度、厚度和指向。此外,第一元件905和第二元件907可以包括多种特征,例如圆角和倒角,这是几个例子。
参照图10,系统1001为系统301的替换实施例。系统1001包括形状均优选为“T”形的第一元件1005和第二元件1007。第一元件1005包括内部基底部分1005a、外部基底部分1005b和支腿部分1005c。类似地,第二元件1007包括内部基底部分1007a、外部基底部分1007b和支腿部分1007c。第一元件1005通过位于内部基底部分1005a和表皮303之间以及外部基底部分1005b和表皮303之间的粘合层结合到表皮303。第二元件1007通过位于内部基底部分1007a和内部基底部分1005a之间以及外部基底部分1007b和内部基底部分1005a之间的粘合层结合到第一元件1005。在安装过程中,第一元件1005和第二元件1007能够选择性地沿着方向1003布置以容纳多种嵌板309的厚度。可以使用紧固件代替粘合剂或作为粘合剂的补充将表皮303、第一元件1005、第二元件1007以及嵌板309中任意几个连接到一起。应该意识到第一元件1005和第二元件1007可以具有各种长度、厚度和指向。此外,第一元件1005和第二元件1007可以包括多种特征,例如圆角和倒角,这是几个例子。
参照图11,系统1101为系统301的替换实施例。系统1101包括形状均优选为“L”形的第一元件1105和第二元件1107。第一元件1105包括基底部分1105a和支腿部分1105b。类似地,第二元件1107包括基底部分1107a和支腿部分1107b。第一元件1105采用位于基底部分1105a和表皮303之间的粘合层结合到表皮303。第二元件1107通过位于基底部分1107a和基底部分1105a之间的粘合层结合到第一元件1105。在安装过程中,第一元件1105和第二元件1107能够选择性地沿着方向1103布置以容纳多种嵌板309的厚度。可以使用紧固件代替粘合剂或作为粘合剂的补充将表皮303、第一元件1105、第二元件1107以及嵌板309中任意几个连接到一起。应该意识到第一元件1105和第二元件1107可以具有各种长度、厚度和方向。此外,第一元件1105和第二元件1107可以包括多种特征,例如圆角和倒角,这是几个例子。
系统301、501、601、801、901、1001和1101被构型成使粘合层能够定制成最佳的胶层厚度,同时还使嵌板309具有大的容差。定制的胶层厚度很重要,因为在特定的胶层厚度下特定的粘合剂能够提供更好的强度。此外,特定的粘合剂当其在固化的过程中受到压力时会具有更好的性能。系统301、501、601、801、901、1001和1101还被构型成使压力施加到粘合层上。系统301、501、601、801、901、1001和1101还被构型成在安装过程中最小化粘合层的剪切/涂脏。例如,嵌板309能够被安装成使嵌板309在垂直于粘合层的方向上挤压相邻的粘合层,由此防止粘合层发生涂脏。
本申请的系统具有显著的优点,包括:(1)第一元件和第二元件的表面可接触为结合表面作准备;(2)对第一元件和第二元件可接触以便在安装之前进行检查;(3)能够使用多种粘合剂;(4)胶层厚度可以控制和定制;(5)能够在固化过程中对粘合层施加正压力;(6)能够在容纳部件容差的同时维持期望的胶层厚度;以及(7)减少在安装过程中所需的接触。
上面公开的具体实施例仅仅是示例性的,因为本申请可以以不同但是等效的方式修改并且实施,这对于受益于本申请的教导的本领域技术人员来说是显而易见的。进而,除了下面的权利要求书中描述的内容,也对这里示出的结构或设计的细节进行限制。因此,显而易见的是上面描述的具体实施例可以改变或修改并且所有的这些变形都被认为位于本申请的精神和范围之内。相应地,本申请在这里寻求的保护范围在下面的权利要求书中提出。很明显,上面描述和示出了具有显著优点的系统。尽管本申请的系统以有限数量的形式示出,其并不仅限于这些形式,而是可修改成多种变形和改变而不会脱离本申请的精神。
Claims (46)
1.一种将嵌板连接到表皮的连接系统,该系统包括:
具有第一支腿部分、第一内部基底部分、以及第一外部基底部分的第一元件,第一外部基底部分和第一内部基底部分连接到表皮;以及
具有第二支腿部分、第二内部基底部分、以及第二外部基底部分的第二元件,第二外部基底部分连接到表皮,第二元件的第二内部基底部分连接到第一元件的第一内部基底部分;
其中嵌板连接到第一支腿部分和第二支腿部分。
2.根据权利要求1的连接系统,其中第一支腿部分和第二支腿部分中至少一个为锥形。
3.根据权利要求1的连接系统,其中第一内部基底部分、第一外部基底部分、第二内部基底部分、以及第二外部基底部分中至少一个为锥形。
4.根据权利要求1的连接系统,其中第二内部基底部分与第一内部基底部分至少部分地重叠。
5.根据权利要求1的连接系统,其中第二内部基底部分与第一内部基底部分近似平行。
6.根据权利要求1的连接系统,其中第一元件和第二元件通过粘合剂连接到表皮。
7.根据权利要求1的连接系统,其中第一元件和第二元件通过至少一个紧固件连接到表皮。
8.根据权利要求1的连接系统,其中嵌板通过粘合剂连接到第一支腿部分和第二支腿部分。
9.根据权利要求1的连接系统,其中嵌板通过至少一个紧固件连接到第一支腿部分和第二支腿部分。
10.根据权利要求6的连接系统,其中粘合剂为薄膜粘合剂。
11.根据权利要求6的连接系统,其中粘合剂为糊状粘合剂。
12.根据权利要求1的连接系统,其中第一元件和第二元件近似为“T”形。
13.根据权利要求1的连接系统,进一步包括:
至少一个穿过第一内部基底部分、第二内部基底部分和表皮设置的紧固件。
14.根据权利要求1的连接系统,其中嵌板为飞机中的结构元件。
15.根据权利要求1的连接系统,其中表皮为面板结构元件。
16.一种结构连接件包括:
具有第一基底部分和第一支腿部分的第一元件;以及
具有第二基底部分和第二支腿部分的第二元件;
其中第一基底部分和第二基底部分在重叠部分连接到一起;
其中第一支腿部分和第二支腿部分形成用于结构性地连接到结构元件的空腔。
17.根据权利要求16的结构连接件,其中第一基底部分和第二基底部分通过粘合剂连接到一起。
18.根据权利要求16的结构连接件,其中第一基底部分和第二基底部分通过紧固件连接到一起。
19.根据权利要求16的结构连接件,其中第一基底部分和第二基底部分连接到嵌板。
20.根据权利要求19的结构连接件,其中第一基底部分和第二基底部分通过粘合剂连接到嵌板。
21.根据权利要求16的结构连接件,其中结构元件为飞机中的结构件。
22.根据权利要求16的结构连接件,其中第一元件和第二元件为“T”形。
23.根据权利要求16的结构连接件,其中第一元件和第二元件为“L”形。
24.根据权利要求16的结构连接件,其中结构元件为具有第一面、第二面以及位于这两个面之间的核心的嵌板。
25.根据权利要求16的结构连接件,其中第一元件和第二元件为固化后的复合材料。
26.根据权利要求16的结构连接件,其中第一基底部分和第二基底部分在重叠部分为斜接的。
27.根据权利要求16的结构连接件,其中第二元件设置在第一元件的第一基底部分的顶部。
28.一种用于将嵌板连接到表皮的连接系统,该系统包括:
具有第一支腿部分、第一内部基底部分、以及第一外部基底部分的第一元件,第一外部基底部分和第一内部基底部分连接到表皮;以及
具有第二支腿部分、第二内部基底部分、以及第二外部基底部分的第二元件,第二外部基底部分和第二内部基底部分连接到表皮;
其中嵌板连接到第一支腿部分和第二支腿部分。
29.根据权利要求28的连接系统,其中第一支腿部分和第二支腿部分中至少一个为锥形。
30.根据权利要求28的连接系统,其中第一内部基底部分、第一外部基底部分、第二内部基底部分以及第二外部基底部分中至少一个为锥形。
31.根据权利要求28的连接系统,进一步包括:
位于第一内部基底部分和第二内部基底部分之间的间隙。
32.根据权利要求28的连接系统,其中第二内部基底部分大致上平行于第一内部基底部分。
33.根据权利要求28的连接系统,其中第一元件和第二元件通过粘合剂连接到表皮。
34.根据权利要求28的连接系统,其中第一元件和第二元件通过至少一个紧固件连接到表皮。
35.根据权利要求28的连接系统,其中嵌板通过粘合剂连接到第一支腿部分和第二支腿部分。
36.根据权利要求28的连接系统,其中嵌板通过至少一个紧固件连接到第一支腿部分和第二支腿部分。
37.根据权利要求33的连接系统,其中粘合剂为薄膜粘合剂。
38.根据权利要求33的连接系统,其中粘合剂为糊状粘合剂。
39.根据权利要求28的连接系统,其中第一元件和第二元件近似为“T”形。
40.根据权利要求28的连接系统,其中嵌板为飞机中的结构元件。
41.根据权利要求28的连接系统,其中表皮为面板结构元件。
42.一种组装结构连接系统的方法,包括:
将第一元件连接到表皮以使第一元件与表皮刚性连接,第一元件包括:
第一基底部分;
从第一基底部分延伸出来的第一支腿部分;
准备第二元件用于粘合,第二元件包括:
第二基底部分;
从第二基底部分延伸出来的第二支腿部分;
将第二元件结合到表皮以及第一元件以使第二基底部分与第一基底部分至少部分重叠;以及
将结构元件结合在第一支腿部分和第二支腿部分之间。
43.根据权利要求42的方法,其中第一支腿部分和第一基底部分设置成彼此近似成90度夹角。
44.根据权利要求42的方法,其中将第二元件结合到表皮和第一元件的步骤,以及将结构元件结合到第一支腿部分和第二支腿部分之间的步骤大致上在同一过程中发生。
45.根据权利要求42的方法,其中将结构元件结合到第一支腿部分和第二支腿部分之间包括使用粘合膜以及将第二支腿部分向第一支腿移动以防止粘合膜被移位。
46.根据权利要求42的方法,进一步包括:
在第一基底部分和第二基底部分之间的重叠部分使用紧固件以在对设置在这两者之间的粘合剂进行固化的过程中施加压力。
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WO2008150688A1 (en) * | 2007-05-31 | 2008-12-11 | The Boeing Company | Apparatus and methods for securing a first structural member and a second structural member to one another |
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CN106697327B (zh) * | 2016-12-19 | 2019-10-18 | 中航成飞民用飞机有限责任公司 | 飞机壁板对接结构 |
CN113665782A (zh) * | 2021-09-24 | 2021-11-19 | 肇庆市海特复合材料技术研究院 | 一种复合材料无人机粘接结构及其粘接方法 |
Also Published As
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EP2630032A1 (en) | 2013-08-28 |
WO2012091695A1 (en) | 2012-07-05 |
CA2820004A1 (en) | 2012-07-05 |
US9592901B2 (en) | 2017-03-14 |
EP2630032B1 (en) | 2015-06-24 |
US20150147114A1 (en) | 2015-05-28 |
CN103261021B (zh) | 2016-01-20 |
EP2630032A4 (en) | 2013-09-11 |
US20130026297A1 (en) | 2013-01-31 |
US8985515B2 (en) | 2015-03-24 |
CA2820004C (en) | 2016-02-16 |
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