CN111075810A - 用于连接两个构件的方法和系统 - Google Patents

用于连接两个构件的方法和系统 Download PDF

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CN111075810A
CN111075810A CN201910972908.1A CN201910972908A CN111075810A CN 111075810 A CN111075810 A CN 111075810A CN 201910972908 A CN201910972908 A CN 201910972908A CN 111075810 A CN111075810 A CN 111075810A
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component
auxiliary body
vacuum
adhesive
actuator
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沃尔夫冈·舒尔策
马丁·埃伯利
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Airbus Operations GmbH
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B11/00—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding
    • F16B11/006—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding by gluing
    • B—PERFORMING OPERATIONS; TRANSPORTING
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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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
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    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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Abstract

本发明提出一种用于连接两个构件的方法，其中作用在粘合剂上的、两个接合配件之间的压力由辅助体支持，所述辅助体放置在所述构件之一的切口上。两个有待彼此连接的构件和所述辅助体被真空膜覆盖并且在吸出所述真空膜下方的空气之后产生压缩力。

Description

用于连接两个构件的方法和系统
技术领域
本发明涉及一种用于连接两个构件的方法以及一种用于连接两个构件的系统。
背景技术
在现代载具结构中，使用各种连接方法来连接两个构件。连接类型通常取决于所使用的材料、待连接的构件的尺寸、其形状和指定的荷载。虽然在使用金属接合配件时经常使用焊接方法或铆接方法，但是通常粘合由塑料制成的大面积的构件。如果使用不同的材料(比如塑料和金属)，那么也可以在那里进行粘合。为了额外的安全性，可以使用铆接，然而这需要对接合配件进行更高耗费的加工。
已知的是，为了产生精确的粘合，接合配件和粘合剂承受压力。由此可以实现多个优点。在缩聚粘合剂中，可以将裂解产物以及尤其水从粘合缝隙中排出。在溶剂粘合剂中可以从粘合缝隙中移除溶剂残留物。也可以改善粘合剂与两个接合配件之间的粘着性和湿润性，这可以使荷载能力提高。例如可以将压力施加到高压釜中。粘合剂不会从粘合缝隙逸出，并且粘合层厚度很大程度上保持恒定。有待彼此粘合的构件越坚硬或者越厚，所需要的压力就越高，以便补偿粘合缝隙中的表面的尺寸公差。
发明内容
然而，尤其在非常大的、有待彼此连接的构件中，高压釜的使用是非常高耗费并且昂贵的。本发明的目的在于提出一种用于连接两个构件的方法，其中在无需高压釜的情况下，可以尽可能简单地将压力引入到两个接合配件之间的粘合剂上。
该目的通过根据本发明的方法来实现。有利的实施方式和改进方案可以自以下说明书中得知。
提出一种用于连接两个构件的方法，所述方法具有以下步骤：将第一构件布置在模具表面上，将具有切口的第二构件布置在所述第一构件连同粘合剂上，将覆盖所述切口的辅助体放置到所述第二构件上，以真空膜覆盖所述第二构件、所述辅助体、以及所述第一构件的包围所述第二构件的至少一个闭合区域，对由所述第一构件和所述真空膜包围的空间抽真空，并且在所述粘合剂固化后移除所述真空膜。
将第一构件布置在模具表面上应理解为如下含义：将所述第一构件放置在所述模具表面上，使得能够正好从外部到达位于其上的、所提供的接合面。因此，于是所述接合面优选布置在与所述模具表面背向的侧面上。
此外，所述模具表面不一定必须由连续地闭合的表面形成，而是可以设想，也存在用于放置所述第一构件的单独的支撑面。尤其如飞行器的机身壳等较大的构件可以布置在由支撑面或保持元件构成的系统上。
所述第二构件具有切口，所述切口例如用于形成窗户框架。将所述第二构件放置在所述第一构件上，使得所述第二构件的接合面位于所述第一构件的接合面上。所述第二构件的接合面可以例如布置在所述切口周围的边缘上。
此外，将所述粘合剂引入所述第一构件与所述第二构件之间。这可以通过将粘合剂施加到所述第一接合面或所述第二接合面上来进行。还可以有利的是，将所述粘合剂施加到两个接合面上。可以设想的是，所述粘合剂藉由输出装置以计量的方式(例如通过机器人引导)被施加到相关接合面上。另一方面也可以在小规模生产中进行手动施加所述粘合剂。此外，可以设想的是，将所述粘合剂用作粘合剂膜，所述粘合剂膜在室温下是固态的并且通过加热才变为液态并且以涂覆构件的方式固化。
特别有利之处在于：将覆盖所述切口的辅助体放置在所述第二构件上。这个辅助体可以超过所述切口的尺寸并且齐平地被放置在所述第二构件上。施加在所述辅助体上的力可以通过在所述辅助体与所述第二构件之间的接触面作用到所述第二构件上。
如果所述辅助体放置在所述第二构件上并且这个辅助体覆盖所述切口，那么以真空膜覆盖所述第二构件、所述辅助体、以及所述第一构件的包围所述第二构件的至少一个闭合区域。由此，在所述真空膜下方因此产生密封空间，所述密封空间能够被抽真空。因此，通过对这个空间抽真空，环境压力藉由辅助体而作用于第二构件，所述第二构件因而给所述第一构件与所述第二构件之间的粘合剂提供压缩力。在这个状态下可以使所述粘合剂固化。固化后移除所述真空膜。
根据本发明的方法的特别有利之处在于：不需要在高压釜中进行固化，然而无需放弃施加比仅由真空可实现的压力更高的压力(即例如0.9巴的压力)。尽管存在所述第二构件的切口，仍可以通过所施加的辅助体来实现用于产生所期望的粘合的更高压力。因此，可以实现这两个构件彼此之间的明显更容易并且更成本有效的粘合，因为可以仅通过真空并且必要时利用加热来在高压釜外部的正常制造环境中实现所述粘合，而无需对所述两个接合配件的中间运输或其他处理。
所述第一构件可以为纤维复合材料或金属材料。独立于此，所述第二构件同样可以为纤维复合材料或金属材料。在更下文中提到的可能的强化元件同样可以独立于此由纤维复合材料或金属材料制成。
所述方法优选具有以下步骤：加热所述第一构件与所述第二构件之间的间隙，所述粘合剂位于所述间隙中。所述加热可以通过对模具表面、所述第一构件和/或所述第二构件加热来进行。示例性地，可以对所述模具表面加热，使得位于其上的第一构件或所述粘合剂变热。替代于此，所述第二构件也可以通过放置加热元件或通过热辐射来加热。可以设想的是，使用加热垫、炉、贯通炉等。此外，可以设想的是，使用粘合剂系统，所述粘合剂系统需要100℃至450℃的温度来进行固化。已知例如用于粘合纤维复合材料的粘合系统，所述粘合系统在180℃的温度下固化。还已知另外的粘合系统，所述粘合系统在明显更低的温度下固化，或者暴露于更高的温度以进行激活，例如在具有热塑性基质的纤维复合材料的情况下。
在有利的实施方式中，所述方法还具有以下步骤：在所述第一构件与所述第二构件之间引入强化元件，其中在所述第一构件与所述强化元件之间并且在所述强化元件与所述第二构件之间包含粘合剂。所述强化元件可以用于增厚承载所述第二构件的所述第一构件的区域。由于所述第二构件具有切口，因此可以有意义的是，使用强化元件来加厚所述切口周围的环绕的边缘面，从而存在更高的强度。
在有利的实施方式中，所述第一构件具有第一切口，并且所述第二构件具有第二切口，其中将所述第二构件这样放置到所述第一构件上，使得所述第一切口与所述第二切口彼此对准地定向。因此，所述接合面可以是所述第一切口周围的边缘面，所述第二构件的对应区段可以放置在该边缘面上。例如可以在交通飞行器的机身壳上实现这种布置，其中所述第一切口为窗户开口并且所述第二构件为窗户框架。特别优选的是，然后在所述两个构件之间引入以上所提到的强化元件。
有利的实施方式还可以具有以下步骤：借助于施加拉力或压缩力的元件将辅助体张紧在成型模具上。如果在粘合层中所需的压力无法通过仅使真空作用于所述辅助体而产生，那么可以张紧所述辅助体以获得额外的支持。所述张紧可以通过沿所述成型模具的方向施加拉力来实现或可以通过借助压力挤压所述辅助体的与所述成型模具背向的侧面来实现。根据所需压力可以控制额外的、作用在所述辅助体上的力。
有利的是，所述张紧包括：穿过布置在所述辅助体中的开口拧入螺栓。针对这个目的，所述成型模具例如可以具有螺纹孔，螺栓能够被拧入所述螺纹孔中。针对这个目的，所述第一构件也应具有切口，所述螺栓可以穿过该切口延伸到所述成型模具中。由此，通过例如调节所述螺栓的拧紧扭矩，可以很容易地控制所述额外的、作用在所述辅助体上的力。
然而，所述张紧可以包括：利用致动器将所述辅助体压紧到所述第二构件上。所述致动器可以压靠到所述辅助体上并且为此提供适合的接触面。所述致动器被布置在所述辅助体的与所述成型模具背向的侧面上并且例如保持在刚性框架上。这个框架可以与所述成型模具刚性地连接。所述致动器可以为液压致动器或气动式致动器。为了精确地控制所述力，可以设想的是，使用力测量单元，所述力测量单元与控制单元联接，所述控制单元进而驱动所述致动器。尤其在使用液压致动器时，这可能对于避免过度的力作用是有意义的。当然，还可以使用主轴驱动器或者类似的线性驱动器，它们并非基于被施加压力的流体。在这里可以监测扭矩，以便限制作用在所述辅助体上的压缩力。
如果使用气动式致动器，那么可以将这个制动器与用于抽真空的真空源联接。由此获得更小的结构耗费，因为不需要单独的压力源来使致动器运动。除此之外，还可以明显限制在所述辅助体上产生的压缩力，因为通过所述真空源可以达到最高大约0.95巴的压力，所述压力作用于所述致动器的有效区域。
所述第二构件具有至少局部地围绕所述切口的凸缘，所述凸缘从所述第二构件沿与所述第一构件背向的方向延伸，其中所述辅助体被放置到所述凸缘上。这种布置(所述布置例如针对交通飞行器的窗户框架来实现)允许从所述辅助体向所述第二构件中的很好的力引入。所述辅助体可以具有与所述凸缘适配的、环绕的凹槽，所述凹槽能够与所述凸缘的外边缘产生接触。
本发明还涉及一种用于连接两个构件的系统，所述系统具有成型模具、辅助体、真空膜、真空源、以及粘合剂，其中所述成型模具有用于接收第一构件的模具表面，其中所述辅助体设计成用于放置到第二构件上并且在此覆盖所述第二构件的切口，其中所述真空膜设计成用于覆盖放置到所述第一构件上的所述第二构件连同所述粘合剂、放置到所述第二构件上的辅助体、以及所述第一构件的包围所述第二构件的至少一个闭合区域，并且其中所述真空源能够与所述真空膜或所述成型模具中的至少一个开口联接，使得能够对由所述第一构件和所述真空膜包围的空间抽真空。能够设想的是，根据本发明的系统可以实施上述方法。
所述模具表面可以由连续的、部分地间断的或者仅由单独的支撑面组成并且设计成使得所述第一构件可以放置在所述模具表面上。
所述辅助体可以由足够稳固的材料制成，所述材料适用于所述使用目的。由于所述辅助体仅用作模具，因此这个模具可以是由木材、木纤维、塑料、金属或其他材料制成的板。
所述真空源尤其可以以抽风机的形式来实施。穿过所述真空膜中的开口，可以形成与真空源的连接，从而使得空气从由所述真空膜包围的空间被吸出并且因此环境压力作用在位于所述真空膜下方的部件上。
所述辅助体优选具有能够滑动的涂层。示例性地，这个涂层可以具有聚四氟乙烯。由此，可以确保：所述真空膜也能够在加热后容易地与所述辅助体分离，并且因此所述辅助体能够被多次使用。
在有利的实施方式中，所述模具表面具有螺纹孔，其中所述辅助体具有开口，所述开口在所述第一构件、所述第二构件、以及所述辅助体的所提供的位置中与所述螺纹孔对准，并且其中所述系统还具有带有与所述螺纹孔相对应的螺纹的螺栓，其用于将所述辅助体张紧在所述成型模具上。
如以上所实施地，所述系统还可以具有用于将所述辅助体按压到所述第二构件上的致动器。还如上所述，所述致动器可以为气动式致动器、液压致动器或线性驱动器。可以提出的是，在使用气动式致动器时与所述真空源的联接，从而可以降低所述系统的复杂性。
所述系统还可以具有与所述致动器所联接的力控制单元，所述力控制单元设计成用于检测由所述致动器作用到所述辅助体上的力并将其调节至预先确定的值。作用在所述辅助体上的力可以由所述力控制单元限制，从而精确地调节作用在所述粘合层上的压缩力。
附图说明
本发明的其他特征、优点和应用可能性由以下对实施例和附图的说明得出。在此，所有所描述的和/或图示的特征自身和以任意组合构成本发明的主题，而与其在单独权利要求中或其所引用的权利要求中的关系无关。在附图中相同的附图标记代表相同或相似的物体。
图1示出根据本发明的、用于连接构件的系统的截面图示。
图2示出修改的、用于连接构件的系统的截面图示。
图3示出另一修改的、用于连接构件的系统的截面图示。
图4示出了用于连接构件的方法的基于框的示意性图示。
具体实施方式
图1示出用于连接第一构件4与第二构件6的系统2的截面图示。成型模具8具有模具表面10，第一构件4放置在所述模具表面上。在这个图示中，模具表面10是连续地(即不间断地)地实施的。然而，这还可以是修改了的，只要确保位于其上的组件是气密并且能够被抽真空的。
示例性地，第一构件4为交通飞行器的机身壳，所述机身壳在所示出的位置具有第一切口12。示例性地，这个切口为窗户切口并且是圆形、椭圆形或者很大程度上具有修圆的拐角的方形的。第二构件6为稍后位于完成制造的飞行器机身内部的窗户框架，所述窗户框架具有第二切口14，该第二切口与第一切口12对准。
第二构件6还具有围绕所述第二切口14的凸缘16，所述凸缘从第二构件6沿与第一构件4背向的方向延伸。凸缘16大致沿第一切口12的边缘延伸，并且由此可以是空心柱体或空心锥体的罩面的区段。
为了连接第一构件4与第二构件6，第二构件6具有支撑面18，所述支撑面示例性地位于凸缘16的径向外部。支撑面18用于产生第二构件6与所述接合配件之间的表面接触。在此示例性地，这个接合配件以强化元件20的形式示出，所述强化元件被用于加厚第一构件4的围绕第一切口12的边缘面21。因此，支撑面18被粘合到强化元件20上，而所述强化元件被粘合到边缘面21上。然而如果不需要加厚，也可以省去强化元件20。于是因此，支撑面18被粘合到边缘面21上。
在所示实例中，在第一构件4与强化元件20之间以及在强化元件20与第二构件6之间分别存在一层粘合剂。所述粘合剂可以实施为能够热固化的粘合剂。
为了依次按压构件4和6，使用真空膜22，所述真空膜可以被粘合到第一构件4上并且在此完全覆盖第二构件6。在抽真空后，给粘合剂施加压力，以优化粘合品质。然而，由于第二构件6具有第二切口14，通过单纯地放置真空膜22由于受限的支撑面而无法预期可以引起足够的压缩力。
为了增大这个压缩力，提供辅助体24，所述辅助体被放置在凸缘16上并且在此完全覆盖第二切口14。示例性地，所述辅助体24具有环绕的凹槽25，所述凹槽适配于凸缘16的形状。凹槽25可以齐平地放置在凸缘16上。
由成型模具8、第一构件4、第二构件6和辅助体24构成的整个组件由真空膜22覆盖。这个真空膜延伸直到明显位于第二构件6外部的闭合区域23。在对位于真空膜下方的空间抽真空之后，由第二构件6的外轮廓确定的整个表面用于产生沿成型模具8的方向的压缩力。辅助体24使得向凸缘16上引入相对大的压缩力，从而使得位于径向外部的粘合剂承载预先确定的压缩力并且因此承受所期望的压力。
真空源26(所述真空源是示意性地作为方框展示的)可以与真空膜22的开口28联接并且将空气从真空膜22下方的内部空间30中吸出。开口28可以与辅助体24的穿孔32对准。替代性地，这种开口也可以集成在成型模具8中。通过抽真空，真空膜22贴靠所有位于其下的部件并且沿模具表面10的方向挤压这些部件。所述粘合剂因此承受所期望的压力。
因此，可以在高压釜外部进行对这两个构件4和6的连接。可以以这种系统来加工尤其较大的构件。
然而，如果通过系统2所获得的压力仍然不足，那么可以额外地张紧辅助体24。为此，可以使用在图2中所示出的经修改的系统34，其中除了图1中的部件外还提供示意性示出的致动器36。这个致动器作用在辅助体24上。致动器36可以为液压致动器或气动式致动器，并且供应有被施加压力的流体。可以通过控制施加到致动器36上的压力来调节由致动器36施加的力。替代于此，致动器36还可以具有与电动机联接的主轴驱动器。为了简单起见，没有示出为运行致动器36所必需的流体线路和电气线路。
此外，可以设想的是，致动器36与力控制单元38联接，所述力控制单元限制由致动器36施加在辅助体24上的力。为此，可以提供力测量装置，所述力测量装置测量施加在辅助体24上的力并且取决于此来驱动致动器36。
如在图3中借助另一修改的系统40也可以使用螺栓42，所述螺栓向成型模具8的螺纹孔44中延伸并且被引导穿过辅助体24的对应开口46。通过穿过开口46将螺栓42拧入螺纹孔44中，可以调节额外的、作用到第二构件6上的压缩力。特别优选地，可以通过在螺栓42的螺钉头部48使用扭矩扳手来精确地调节额外的压缩力。
最后，图4示出用于连接两个构件4和6的方法50的基于框的示意性图示。方法50具有以下步骤：将第一构件4布置52在模具表面10上。随后，将具有切口14的第二构件6放置54在所述第一构件4连同粘合剂上。将覆盖第二切口14的辅助体24放置56在第二构件6上。此外，以真空膜22覆盖58第二构件6、辅助体24、以及第一构件4的包围第二构件6的至少一个闭合区域。随后，对由第一构件4和真空膜22包围的空间30抽真空60。在粘合剂固化后移除62真空膜22。任选地，在覆盖58之前还可以张紧64所述辅助体。此外，在覆盖58之后，可以加热66所述第一构件4与所述第二构件6之间的间隙，所述粘合剂位于所述间隙中。同样任选地，可以在第一构件4与第二构件6之间引入68强化元件20，从而尤其对第一切口12周围的边缘区域进行强化。
补充性地可以指出，“具有”并不排除其他的元件或步骤，并且“一个”或“一种”不排除多数。此外还可以指出，可以使用已经参照上述实施例之一描述的特征还有与上文描述的另外实施例的其他特征的组合。权利要求书中的附图标记不应视为限制。
附图标记清单
2 系统
4 第一构件
6 第二构件
8 成型模具
10 模具表面
12 第一切口
14 第二切口
16 凸缘
18 支撑面
20 强化元件
21 边缘面
22 真空膜
23 闭合区域
24 辅助体
25 凹槽
26 真空源
28 开口
30 内部空间
32 穿孔
34 系统
36 致动器
38 力控制单元
40 系统
42 螺栓
44 螺纹孔
46 开口
48 螺钉头部
50 方法
52 布置第一构件
54 布置第二构件
56 放置辅助体
58 以真空膜覆盖
60 抽真空
62 移除真空膜
64 张紧辅助体
66 加热
68 引入强化元件

Claims (14)

1.一种用于连接两个构件的方法(50)，所述方法具有以下步骤：
-将第一构件(4)布置(52)在模具表面(10)上，
-将具有切口(14)的第二构件(6)布置(54)在所述第一构件(4)连同粘合剂上，
-将覆盖所述切口(14)的辅助体(24)放置(56)到所述第二构件(6)上，
-以真空膜(22)覆盖(58)所述第二构件(6)、所述辅助体(24)、以及所述第一构件(4)的包围所述第二构件(6)的至少一个闭合区域(23)，
-对由所述第一构件(4)和所述真空膜(22)包围的空间(30)抽真空(60)，并且
-在所述粘合剂固化后移除所述真空膜(22)。
2.根据权利要求1所述的方法(50)，
还具有以下步骤：加热(66)所述第一构件(4)与所述第二构件(6)之间的间隙，所述粘合剂位于所述间隙中。
3.根据权利要求1或2所述的方法(50)，
还具有以下步骤：将强化元件(20)引入(68)所述第一构件(4)与所述第二构件(6)之间，其中在所述第一构件(4)与所述强化元件(20)之间并且在所述强化元件(20)与所述第二构件(6)之间包含粘合剂。
4.根据以上权利要求之一所述的方法(50)，
其中所述第一构件(4)具有第一切口(12)，其中所述第二构件(6)具有第二切口(14)，并且其中将所述第二构件(6)这样放置到所述第一构件(4)上，使得所述第一切口(12)与所述第二切口(14)彼此对准地定向。
5.根据以上权利要求之一所述的方法(50)，
还具有以下步骤：借助于施加拉力或压缩力的元件将辅助体(24)张紧(64)在所述成型模具(8)上。
6.根据权利要求5所述的方法(50)，
其中所述张紧(64)包括：穿过布置在所述辅助体(24)中的开口(46)拧入螺栓(42)。
7.根据以上权利要求之一所述的方法(50)，
其中所述张紧(64)包括：利用致动器(36)将所述辅助体(24)压紧到所述第二构件(6)上。
8.根据权利要求7所述的方法(50)，
其中所述致动器(36)与真空源(26)联接，所述真空源用于抽真空(60)。
9.根据以上权利要求之一所述的方法(50)，
其中所述第二构件(6)具有至少局部地围绕所述切口(14)的凸缘(16)，所述凸缘从所述第二构件(6)沿与所述第一构件(4)背向的方向延伸，其中所述辅助体(24)被放置到所述凸缘(16)上。
10.一种用于连接两个构件的系统(2，34，40)，所述系统具有：
-成型模具(8)，
-辅助体(24)，
-真空膜(22)，
-真空源(26)，以及
-粘合剂，
其中所述成型模具(8)具有用于接收第一构件(4)的模具表面(10)，
其中所述辅助体(24)设计成用于放置到第二构件(6)上并且在此覆盖所述第二构件(6)的切口(14)，
其中所述真空膜(22)设计成用于覆盖放置到所述第一构件(4)上的所述第二构件(6)连同所述粘合剂、放置到所述第二构件(6)上的辅助体(24)、以及所述第一构件(4)的包围所述第二构件(6)的至少一个闭合区域，并且
其中所述真空源(26)能够与所述真空膜(22)或所述成型模具(8)中的至少一个开口(28)联接，使得能够对由所述第一构件(4)和所述真空膜(22)包围的空间抽真空。
11.根据权利要求10所述的系统(2，34，40)，
其中所述辅助体(24)具有能够滑动的涂层。
12.根据权利要求10或11所述的系统(2，34，40)，
其中所述模具表面(10)具有螺纹孔(44)，
其中所述辅助体(24)具有开口(46)，所述开口在所述第一构件(4)、所述第二构件(6)、以及所述辅助体(24)的所提供的位置中与所述螺纹孔(44)对准，并且
其中所述系统(2，34，40)还具有带有与所述螺纹孔(44)相对应的螺纹的螺栓(42)，其用于将所述辅助体(24)张紧在所述成型模具(8)上。
13.根据权利要求10至12之一所述的系统(2，34，40)，
还具有用于将所述辅助体(24)压靠到所述第二构件(6)上的致动器(36)。
14.根据权利要求13所述的系统(2，34，40)，
还具有与所述致动器(36)所联接的力控制单元(38)，所述力控制单元设计成用于检测由所述致动器(36)作用在所述辅助体(24)上的力并将其调节至预先确定的值。
CN201910972908.1A 2018-10-19 2019-10-14 用于连接两个构件的方法和系统 Pending CN111075810A (zh)

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