CN102653316A - 损坏的结构的维修部件和方法,以及用于实施的维修工具 - Google Patents

损坏的结构的维修部件和方法,以及用于实施的维修工具 Download PDF

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CN102653316A
CN102653316A CN2012100119454A CN201210011945A CN102653316A CN 102653316 A CN102653316 A CN 102653316A CN 2012100119454 A CN2012100119454 A CN 2012100119454A CN 201210011945 A CN201210011945 A CN 201210011945A CN 102653316 A CN102653316 A CN 102653316A
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N·布勒
O·肖姆
F·谢兰
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Airbus Operations SAS
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Abstract

本发明涉及损坏的结构的维修部件和方法，以及用于实施的维修工具，具体而言，本发明旨在允许快速并有效地维修损坏的金属结构、尤其是飞行器机身的蒙皮，而不需要不利于波的传输的厚度余量。为此，本发明提出由特殊材料构成的内部/外部双板。根据一个实施例，损坏的结构具有外表面和内表面，部件具有大致平面地延伸的内部/外部双板和中央芯，该双板能够分别地固定在金属结构的内表面和外表面上，中央芯连接内部板和外部板。由此在板之间构成槽。该部件由复合材料的单个块以及玻璃褶皱构成，玻璃褶皱覆盖在槽上，可定位在板和结构之间。芯可以被至少一个开孔穿过，开孔能够让穿过结构的连接件通过。

Description

损坏的结构的维修部件和方法,以及用于实施的维修工具
技术领域
本发明涉及损坏的金属结构、尤其是飞行器的机身蒙皮的维修部件，以及使用这种部件的维修方法。本发明还涉及能够实施该方法的维修工具。 
背景技术
传统上，飞行器具有金属机身，该金属机身主要由铝合金制成，并通过框架、杆和板的组合来安装。在机身的板中切开探测器区域、门区域、其他开口及等同物。一般地，机身的蒙皮因此通过按照“步长”来局部地增大厚度而在内部围绕切开部分加强。 
当这些具有大的厚度(通常大于4mm)的加强区域由于工作事故、起火、腐蚀等而承受大的损坏时，通常对损坏的蒙皮进行切割，并固定同样具有大的厚度的外部板。 
外部板的使用例如在专利文档US 4517038中进行了描述。在该文档中，提出按照预先选择的开口切割损坏的部分，在该开口中引入组件，并通过铆钉将板固定在损坏的结构的蒙皮上，所述组件由纤维层的堆叠构成，该堆叠的尺寸大致等于开口，并与具有更大尺寸的金属板连接。这种维修不是可靠的，尤其是对于防火，而且这种修复在靠近探测器的时候造成干扰探测器的空气动力学问题。 
还由专利文档EP 0471923已知通过固定外部板来维修不受限制的、损坏的飞行器结构，其中所述外部板防火，并由用热硬化树脂浸透的编织玻璃织物层构成。板通过多个机械夹紧装置来固定。 
在环境限制条件增多的情况下，该类型维修难以实施：由于空气动力学的原因，外部板的厚度在探测器附近必须受到限制，甚至取消， 以免干扰空气的流动，这种干扰会使探测器的测量不准确。 
板人工地或通过厚板材的机械加工来成形。再加工一般是必要的，以减小在板周边上板的外部固定线处的厚度。该方法因此时间长而精细，并造成与制造方法相关的内部机械应力。 
此外，在安装时，还增加了主要与制造公差相关的安装应力。另外，中性纤维的不对齐也在接合部分处造成次生挠应力。 
最后，维修在时间上可能是受限制的，并带有补充的中间检查：最终解决方法始终是替换整块板，这是在成本和固定方面最不利的情况。 
发明内容
本发明旨在解除这些维修应力，尤其是消除安装应力。为此，本发明提出由特殊材料构成的内部/外部双板。 
更具体地，本发明的主题在于一种损坏的结构、尤其是飞行器的机身的维修部件，该损坏的结构具有外表面和内表面。该部件具有大致平面地延伸的内部/外部双板和中央芯，该双板能够被分别固定在金属结构的内表面和外表面上，而中央芯连接内部板和外部板，以在板之间构成槽，该部件由复合材料制成的单一的块构成。 
借助于由双板造成的力平衡，这种维修部件允许消除内部应力，并减少中性纤维的不对齐。 
根据特定的实施例： 
-板具有根据损坏的位置来确定的尺寸和厚度； 
-盖在槽上的玻璃褶皱被布置在板和结构之间； 
-芯被至少一个开口穿过，该开口能够让穿过结构的连接件通过； 
-内部板可以具有多个褶皱，以覆盖和固定在位于邻近环境中的元件上。 
本发明还涉及一种用于使用上述维修部件维修尤其是金属结构 或复合结构的方法。这种方法包括：通过在由复合材料制成的预成形件中切割来形成上述部件的步骤；在结构中形成允许取出损坏的部分的扩大开口的步骤；在金属结构的两侧靠着此结构的内表面和外表面来安装板的步骤，该部件具有因此能够在结构的开口处大致贴合该结构的剖面的剖面；在分别相向的该结构的表面和板的表面之间进行固定的步骤；在至少其中一个板和在这些板之间延伸的金属结构之间横向地机械固定的步骤。 
根据特定的实施例： 
-在要与结构的表面进行固定的板的表面和芯上实施新的覆盖，这种新的覆盖方便部件的成形； 
-覆盖通过玻璃褶皱形成，以使得在维修部件和金属结构的表面之间的固定穿过该褶皱来实施； 
-褶皱的内部板的布置允许根据其他结构的覆盖来调节该板的厚度。 
本发明还涉及一种维修工具，该维修工具能够实施该方法。该工具由上述维修部件构成，该维修部件可干燥成形为褶皱，并优选地伴有树脂块以将部件固定在结构的表面上，或者成形为嵌在热塑性基质中的纤维板。该工具可以有利地包括用于将部件机械地固定在结构上的装置。 
附图说明
通过阅读以下参照附图来描述的示例，本发明的其他数据、特征和优点将变得显而易见。所述附图分别示出了： 
-图1a和图1b示出了被靠近空速管探测器的碰撞损坏的飞机机身部分的、分别为外部和内部的视图； 
-图2示出了根据本发明能够固定在机身的蒙皮上的维修部件的示意剖视图。 
具体实施方式
在详细的说明中，形容词“内”或“内部”和“外”或“外部”分别指的是限定在飞机机身内部的封闭空间和位于该封闭空间之外的空间。 
参照图1b，在所示出的示例中为空速管的速度探测器1被固定在铝合金的飞机机身蒙皮2上。如图1a所示，该固定通过由铆钉4和螺栓5固定的同心金属褶皱3来在内部加强。由碰撞而形成的损坏的部分10位于探测器1的附近。由于过于接近探测器和探测器的加强区域，该部分不能由如上所述的用于添加外部板的传统装置来维修。 
本发明使用一种如在图2的剖视图中所示例性而非限制性地示出的部件20的维修部件。机身损坏的金属部分10的该维修部件20在部分10的两侧延伸，尤其是在机身的蒙皮2的外表面2e和内表面2i上延伸。 
维修部件构成根据扩大的开口6的尺寸来选择的工具的一部分，扩大的开口6由侧表面21来限定，并在蒙皮2中实施，以去除损坏的部分。每个工具都包括：具有在范围内预先确定的尺寸的维修部件；树脂块，用于将部件固定在待维修结构的表面上；以及用于将部件横向地固定在结构上的装置。 
部件20由复合材料的块构成，该块通过在复合材料的预成形件中切割来成形，在示例中，复合材料是基于碳纤维的。 
该部件20由平面地或略微弯曲地(即大致平行于机身蒙皮2)延伸的两个板构成：内部板21和外部板22，它们通过中央芯23相互连接。板21和22朝向机身蒙皮2的、相对的表面21f和22f构成周边槽25，芯23的侧表面231用作槽的底部。在该示例中，芯被至少一个开口7穿过，开口能够让系统连接(例如电缆)在机身蒙皮的外部和内部之间通过。 
板21和22通过铆钉4横向地固定在蒙皮2的内表面2i和外表面2e上。铆钉与机身蒙皮以及两个板21和22、或根据构造与板中的至 少一个关联。 
由于碳和铝之间的电腐蚀，预先在板21和22的表面21f和22f以及芯23的侧表面231上实施槽25的新的覆盖。该覆盖由玻璃褶皱8构成，该玻璃褶皱布置在板和蒙皮之间，以使得在板21、22和机身蒙皮2的相对的表面2i和2e之间的固定穿过此褶皱来实施。内部板2i有利地成形为褶皱，以使厚度适应其环境。因此，其他的周围加强元件或具有多少复杂的形状的部件(例如支撑足30)可以由内部板2i来覆盖，并固定在该板上。 
当安装维修部件20时，板21和22被安装在机身蒙皮2的两侧，顶着该板的内表面2i和外表面2e。部件20具有大致贴合蒙皮2在其开口6处的轮廓的轮廓。分别通过玻璃褶皱8接触的机身蒙皮2的表面2i和2e和板21和22的表面21f和22f通过布置在工具中的树脂来固定。安装通过铆钉4的横向固定来实现。 
本发明不限于所示及所述的示例。例如可以设置围绕中央轴的圆形展开部件或具有其他形状(椭圆、长形等)的部件。此外，维修部件的复合材料可基于碳纤维、玻璃或其他(芳香尼龙、钙的碳化物等)。此外，本发明不限于航空领域，而是可以例如应用于车辆领域。 

Claims (10)

1.一种损坏的结构(2)、尤其是飞行器机身蒙皮的维修部件(20)，所述损坏的结构具有外表面(2e)和内表面(2i)，其中，所述维修部件具有大致平面的内部/外部双板(21、22)和中央芯(23)，所述双板能够分别地固定在所述结构的内表面(2i)和外表面(2e)上，所述中央芯连接所述内部板(21)和外部板(22)，以构成在所述板(21、22)之间的槽(25)，所述部件由复合材料的单个块构成。
2.如权利要求1所述的维修部件，其中，所述板(21、22)具有根据损坏的位置确定的尺寸和厚度。
3.如权利要求1和2中任一项所述的维修部件，其中，覆盖在所述槽(25)上的玻璃褶皱(8)定位在所述板(21、22)和所述结构(2)之间。
4.如权利要求1所述的维修部件，其中，所述芯(23)被至少一个开孔(7)穿过，所述至少一个开孔能够让穿过所述结构(2)的连接件通过。
5.如权利要求1所述的维修部件，其中，所述内部板(2i)具有多个褶皱，以覆盖和固定在位于邻近的环境中的元件上。
6.一种损坏的结构的维修方法，所述维修方法使用如权利要求1所述的维修部件(20)，其特征在于，所述方法包括：通过在复合材料的预成形件中切割来使所述部件(20)成形的步骤；在所述结构(2)中形成扩大的开口(6)的步骤，其中所述开口允许去除所述损坏的部分；在所述金属结构(2)的两侧靠着所述结构的内表面(2i)和外表面(2e)安装所述板(21、22)的步骤，所述部件(20)具有大致贴合所述结构(2)在其开口(6)处的轮廓的轮廓；在分别相向所述结构(2)的表面(2i、2e、21)和所述板的表面(21f、22f、231)之间进行固定的步骤；在至少其中一个板和在所述板(21、22)之间延伸的所述金属结构(2)之间横向地机械固定(4)的步骤。
7.如权利要求6所述的维修方法，其中，在要与所述结构(2)的表面(2i、2e、21)进行固定的所述板(21、22)的表面(21f、22f)和所述芯(23)上实施覆盖。
8.如权利要求6或7所述的维修方法，其中，所述覆盖由玻璃褶皱(8)形成，以使得在所述维修部件(20)和所述金属结构(2)的表面(2i、2e、2l)之间的固定穿过所述褶皱来实施。
9.如权利要求6所述的维修方法，其中，褶皱的所述内部板(21)的布置允许根据其他结构(30)的覆盖来调节所述板(21)的厚度。
10.一种用于根据权利要求6所述的维修方法中使用的维修工具，其中，所述维修工具由如权利要求1至5中任一项所述的维修部件(20)构成，该维修部件被干燥地成形为褶皱，或嵌在热塑性基质中的纤维板。
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