CN111216870A - 具有呈夹层板结构的加热层的衬板元件 - Google Patents

具有呈夹层板结构的加热层的衬板元件 Download PDF

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CN111216870A
CN111216870A CN201911154557.XA CN201911154557A CN111216870A CN 111216870 A CN111216870 A CN 111216870A CN 201911154557 A CN201911154557 A CN 201911154557A CN 111216870 A CN111216870 A CN 111216870A
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layer
heating
preparation
lining
lining element
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雷纳·穆勒
安德烈亚斯·巴茨
迪特马尔·弗尔克勒
弗洛里安·黑塞尔巴赫
托比亚斯·莱希纳
诺贝特·施陶迪格尔
本杰明·约曼
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Airbus Operations GmbH
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Airbus Operations GmbH
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Abstract

在用于飞机的内部空间(16)的呈夹层板结构的衬板元件(14)中，所述衬板元件包括芯层(40)和第一覆盖层(34)，其中第一覆盖层(34)形成衬板元件(14)的可视侧(36)，在芯层(40)和第一覆盖层(34)之间设置有电加热层(20)，所述电加热层至少在第一覆盖层(34)的子面之上延伸，并且所述电加热层用于产生通过第一覆盖层(34)放射的热量。

Description

具有呈夹层板结构的加热层的衬板元件
技术领域
本发明涉及一种用于飞机的内部空间的具有呈夹层板结构的衬板元件，所述衬板元件包含芯层和第一覆盖层，其中第一覆盖层在衬板元件在内部空间中的常规的安装状态中形成衬板元件的朝向所述内部空间的可视侧。
背景技术
在飞机、尤其载客飞机的内部空间、尤其客舱中，关于温度方面期望舒适的室内气候。在此常见的是，为了相对于飞机的冷的外部蒙皮隔热，在所述外部蒙皮和内壁或其可视侧(衬板元件，嵌板，衬层)之间引入绝缘材料。
通过边界条件(对于经由玻璃棉包装、热桥、过堂风效应等的足够的绝缘而言不够的结构空间)在此可能出现损害。因此，例如通过改变飞机结构和从中得出的在衬板元件处的热桥，在飞行状态中得出不可接受地低的表面温度。由于小的结构空间，例如不再可能引入足够的绝缘材料。
发明内容
本发明的目的是，在该区域中改进乘客和机组人员的热舒适性。
所述目的通过一种用于飞机的内部空间的衬板元件(也称作为嵌板或衬层)来实现。衬板元件呈夹层板结构，即通过将不同层彼此面状的贴靠来构造。衬板元件包含至少一个芯层和第一覆盖层。
第一覆盖层在衬板元件在内部空间中的常规的安装状态下形成衬板元件的可视侧。因此，在衬板元件在常规的飞机中常规地安装之后，可视侧朝向内部空间并且例如可以由乘客观察到。在最靠近覆盖层的芯层和覆盖层之间设置有电加热层。加热层至少在第一覆盖层的子面之上延伸。加热层用于产生热量并且通过第一覆盖层放射热量，在安装状态中即朝向飞机的内部空间放射热量。在运行中，也就是说在用电能供应时，加热层因此升温。因此，那么热量从衬板元件在其可视侧朝向内部空间或客舱散发。因为加热层(从可视侧起观察)位于芯层上方——或在多个芯层的情况下：位于最上部的芯层上方——所以加热层的散热不受任何其他的芯层损害。覆盖层因此既不包括完整的(其他)芯层也不包括(其他)芯层的一部分。
根据本发明，因此得出具有嵌入的面状的加热层(尤其加热元件、加热纸、加热织物等)的夹层板结构/构造，用于在内部空间的区域中(尤其在机舱中)使用。根据本发明，得出用于面状地加热夹层板结构的技术。本发明能够实现具有尽可能小的系统重量和能量消耗(低的功率吸收)的成本效益高的解决方案。
根据本发明，可以满足关于机械性能、防火要求和防潮和介质抗性的相关要求。
根据本发明得出有源加热系统，所述有源加热系统尤其通过将加热层(加热纸)嵌入到器件(衬板元件)的纤维复合夹层板构造中实现。
根据本发明，因此加热层(面状的加热元件，优选加热纸或加热织物)嵌入到单夹层板、双夹层板或多夹层板构造(中间层，参见下文，优选具有纤维复合材料)。在此，加热层(例如加热组织)不直接位于可视侧、尤其对于乘客可见的表面上，而是处于至少一个层、第一覆盖层和可能中间层、尤其玻璃纤维增强的预浸料之下。由此，加热元件抵御机械影响。可视侧的覆盖层(第一覆盖层)尤其被磨削、刮抹和涂漆。嵌入的元件(加热层、导线、端子，参见下文)对于乘客而言不可见，此外存在防穿透的足够的电绝缘。
在一个优选的实施方式中，衬板元件包含至少一个中间层和/或与第一覆盖层相对置的第二覆盖层。第二覆盖层因此处于可视侧的相对侧，所述第二覆盖层因此在安装状态中朝向飞机的外壁。通过相应的其他层，衬板元件尤其继续稳定化。尤其地，因此面状的加热层或加热元件嵌入到多层的(整个)覆盖层(覆盖层和中间层)中，以便防止通过撞击造成的机械损坏。加热层或加热纸尤其在可视侧上嵌入到器件的纤维复合结构中。因此，热源(加热层)一方面靠近要加热的表面(第一覆盖层，可视侧)嵌入，另一方面其通过玻璃纤维增强的预浸料的尤其三个层(第一覆盖层和两个中间层)防止机械损坏。这尤其涉及撞击事件，其中必须防止：通电的加热层(加热纸)可能对乘客或机上人员造成危险。通过嵌入乘客侧的(整个)覆盖层(尤其构造：第一覆盖层和两个中间层/加热层/中间层/芯层)，系统是非常有能效的，因为可靠近表面提供热量。同时，被加热的表面在背侧上通过芯层、尤其夹层板蜂窝结构相对于冷的外部结构(飞机外罩)热绝缘。
在一个优选的实施方式中，芯层包含蜂窝芯或芯层是蜂窝芯。蜂窝芯尤其是Nomex蜂窝芯，尤其具有3mm至25.4mm的厚度。替选地，芯层也可以由泡沫制成。由此，可以实现尤其稳定的衬板元件。
在一个优选的实施方式中，至少一个覆盖层(第一和/或——如果存在——第二覆盖层)和/或——如果存在——中间层是由纤维复合材料构成的单层的或多层的(整个)层。尤其地，层或子层在此由预浸材料(预浸纤维)形成。基于相应材料的衬板元件在实践中已创建。
在该实施方式的一个优选的变型形式中，纤维复合材料因此是预浸料。
在一个优选的实施方式中，加热层是穿孔的。加热层因此具有沿延伸面的横向方向的穿通开口或穿透部，以便实现在与加热层相邻的层之间的自由的穿通部。尤其在预浸料的情况下，在最终完成的状态中，因此预浸料的结合剂(尤其树脂)穿透穿通开口并且形成在相邻的层之间的连接柱。因此，得出具有柱状的连接部的稳定的预浸料双平面。在层之间的其余的(空)腔那么由加热层的材料填充。
在一个优选的实施方式中，加热层包含面状地延伸的加热元件或者加热层是这种元件。加热元件尤其是加热织物，尤其加热纸。这种加热元件可符合商业需要地提供。作为加热元件尤其使用基于嵌入到PEEK基质中的碳纤维的加热纸。碳纤维在此无序地在纸中定向并且具有多个短路。由此，也可以实现在加热纸中切口(穿孔的穿透部或较大的切口)，而不完全地中断通过流。这也能够实现，将加热纸穿孔，以便实现在纤维复合结构中的更好的或在上文中提到的更好的嵌入。表面电阻从而加热功率尤其可以经由嵌入的碳纤维的份额的改变而改变。
在一个优选的实施方式中，衬板元件包含至少一个温度传感器和/或至少一个热保险装置。温度传感器和保险装置在此分别与加热层热耦联。保险装置尤其是可逆的或不可逆的保险装置。由此，得出如下可行性，经由嵌入的传感器结合调节系统来调节表面温度(第一覆盖层)，并且防止过热。尤其地，因此可以将衬板元件的表面温度在飞行状态中调整到19℃的期望值上，其中精度为+/-2℃。
因此，至少一个温度传感器尤其直接在加热层(加热纸)的附近嵌入，经由所述温度传感器尤其调节加热层(加热纸)。传感器优选构成为PT100传感器。因此，为了防止嵌板的过热，附加地可以嵌入可逆的和/或不可逆的热保险装置。
在一个优选的实施方式中，温度传感器——如果存在——通过中间层、尤其纤维复合材料层与加热层分开。中间层尤其是预浸料层。因此，在良好的热耦合的情况下确保在加热层和温度传感器之间的可靠的分开。
在一个优选的实施方式中，衬板元件包含至少一个电连接元件，用于电连接加热层和/或——如果存在——导线和/或——如果存在——温度传感器和/或——如果存在——热保险装置。连接元件尤其是电导线或接触元件。接触元件尤其是插头、插座、接线柱、焊接部位等。加热层(加热纸)的接触因此尤其经由适当的导线进行。导线在此尤其同样嵌入到夹层板复合件中并且尤其经由插头/插座等连接。
加热层(加热纸)的接触尤其经由铜带进行，所述铜带集成在衬板元件的纤维复合构造中。温度传感器尤其同样经由嵌入的铜带接触。在器件的相关侧上焊接线缆的导线，经由所述线缆供应器件。加热纸(加热层)因此在所述侧上尤其设有铜电极，经由所述铜电极可以连接加热纸。
在该实施方式的一个优选的变型形式中，衬板元件具有至少一个、从其背侧起沿横向方向引导至至少一个连接元件的盲孔状的留空部，所述留空部在连接元件的电连接之后被封闭。电连接尤其通过线缆的端子进行，封闭通过灌封进行。经由嵌板(衬板元件)上的开口(留空部)，因此经由导线接触加热纸(加热层)，可能的(温度)传感器以及热保险装置。开口在连接线缆之后被灌封，以便防止湿气和介质的进入。
在一个优选的实施方式中，加热层因此在两个相对置的边缘区域上电接触。“边缘”在此应关于面状的延伸方向进行理解。因此将加热层面状地端到端地穿流。电接触尤其通过导线带进行，所述导线带沿着边缘伸展。
在一个优选的实施方式中，加热层在边缘区域之间具有至少两个部段(例如中间部段，侧部部段)，所述部段电地串联连接，其中部段的区别在于至少一个参数。根据衬板元件的几何形状，部段可以调整成，在每单位面积至少近似相同的加热功率的情况下实现尽可能完整的面覆盖。尤其地，串联电路通过导电的横向带(连接元件)进行，所述横向带在加热层的整个宽度之上延伸。在横向带上于是可以进行电流密度在两侧的均匀化。
该实施方式基于，在加热层的通电的横截面的较大改变的情况下，例如在铣切的情况下，局部地由于较高的局部电流而可能出现局部较高的加热功率(热点)。因此，必要时为了实现均匀的表面温度，将具有匹配的热阻的多个部段(尤其加热纸的切段)串联连接。
在该实施方式的一个优选的变型形式中，参数是加热层的宽度和/或厚度和/或电特性和/或穿孔参数。电特性尤其是总电阻，材料的表面电阻(局部的，无穷小的，导电纤维的份额)。穿孔参数尤其是穿孔的数量、大小、形状、分布图案或面积份额。因此，可以设定用于部段的个体化的电阻、加热功率等。
在一个优选的实施方式中，衬板元件通常是用于飞机中的如下部位的衬板元件，在所述部位处不存在用于内部空间的足够的无源热绝缘的足够的结构空间。衬板元件尤其是壁衬板、底部衬板(地板)。飞机中的该部位尤其是门区域、紧急出口的区域。如果在常规运行中可以确保大于最小温度的表面温度，那么热绝缘是“足够的”。衬板元件尤其是用于覆盖飞机的紧急出口门的开启机械机构的衬板元件。将“门”在此也理解成活门，壁元件等。机械机构尤其是关节和/或钩结构，门在其上锚固或可运动地和/或可移开地支承。
根据本发明，因此在客机的紧急出口的区域中得到被加热的衬板元件，在客机的门/门框衬板的区域中的被加热的衬板元件，或者用于机舱的被加热的地板。
本发明基于如下知识、观察或考虑并且还具有下述实施方式。实施方式在此部分简化地也称为“本发明”。实施方式在此也可以包含上述实施方式的一部分或组合或者对应于此和/或可能也包括迄今为止未提到的实施方式。
本发明基于如下构思，寻找用于在机舱的区域中的被加热的衬层的解决方案。
本发明基于如下构思，面状的加热元件嵌入夹层板构造中，所述夹层板构造包括电导线、保险装置和传感器在内。因此，加热层(加热纸)以防止机械影响(尤其防止撞击事件)的方式位于夹层板构造中。在此可以考虑不同的夹层板构造(不同的覆盖层和不同的芯材料，根据静态要求)。
根据本发明，在质量相对小的同时在结构空间最小化的情况下可以实现乘客的热舒适性。这尤其在如下区域中是非常令人感兴趣的，在所述区域中，如门区域中或在紧急出口的区域中，为用于衬板部件的背侧的(无源热)绝缘提供少量体积。通过根据本发明的构造，实现鲁棒的集成解决方案，所述解决方案承受住在机舱的区域中的大的负载(乘客负载，撞击事件，滥用负载等)，而不损失功能性或危害乘务员和乘客的安全性(例如短路或敞开的通电的导线)。此外，所述集成解决方案在相对于侵蚀介质、如例如液压油或清洁剂的抗性方面是有利的，并且具有良好的防火性能。
附图说明
本发明的其他的特征、作用和优点从下面对本发明的优选的实施例的描述以及所附的附图中得出。在此分别以示意性的原理简图示出：
图1示出飞机的具有衬板元件的结构部件的立体图，
图2示出具有电极的电加热层的a)立体图和b)细节的俯视图，
图3示出图1中的衬板元件的层剖面，
图4示出图1中的衬板元件的层构造的横截面，
图5示出在最终制成之前的图1中的结构部件的部分构造的立体图，
图6示出图1中的电连接的结构部件的细节的立体图。
具体实施方式
图1示出飞机的结构部件1，在此是用于紧急出口的未详细阐述的活门机械机构。结构部件2主要包含呈铰接的承载结构的形式的金属框架4，在所述金属框架上机械稳定地固定有支架6以及连接板8。在结构方面可能的位置处安置有呈绝缘泡沫的形式的绝缘部10。然而在常规的安装状态下，没有足够的结构空间可用，以便安置足够多或足够面状的绝缘部10。因此在结构部件2没有内部空间16的足够的无源热绝缘。结构部件2部分地由硅树脂密封件12包围。在图1中背离观察者的一侧上，结构部件2由衬板元件14覆盖。
在安装状态中，衬板元件14朝向飞机的内部空间16。包括衬板元件14在内的结构部件2由总计四个可视窗18穿透，以便在安装状态下在需要时能够实现从内部空间16起看到紧急出口的未示出的、关键的结构部件。
图2示出电加热层20，在此呈加热纸的形式。在此所述加热层是具有嵌入的碳纤维22的PEEK基质。图2b在此示出图2a中的圈出的细节。加热层20具有呈多个穿透部24的形式的穿孔。在两个相对置的边缘侧或边缘区域23上，加热层20分别具有呈铜电极的形式的电连接元件26。穿透部24或穿孔也延续到铜电极中。加热纸具有85g/qm的单位面积重量，10-600Ohm/sqr的表面电阻和90微米的厚度。相应的铜电极宽为20mm并且厚为20微米。穿孔的表面占据18％的面积份额。加热层20是衬板元件14的多个层中的一个层，所述衬板元件以夹层板结构制成。
图3示出在加热层20的高度上沿图1中的箭头III的观察方向贯穿衬板元件14的纵剖面。为了实现用于设置有可视窗18的区域28的空间，呈加热层20的中间部段30的形式的第一部段相对于其呈侧部部段32的第二部段和第三部段以减小的宽度构成。呈上述铜电极的形式的连接元件26a、b分别在端侧处于加热层20上。
在加热层20运行时，经由连接元件26a将电流导入到所述加热层中并且经由连接元件26b将其再次导出(或者相反)。
在具有一致的局部的表面电阻的均匀地穿过的加热层的情况下，在运行中由于在中间部段30的区域中的电流密度的局部升高，得出中间部段30的相对于侧部部段32的局部升高的加热。出于所述原因，加热层20三件式地构成，其中在此由于侧部部段32的对称性总电阻R1＝R3，并且中间部段30的电阻R2＜R1相对更小地构成。因此，在整个加热层20的通过流中得到均匀的温度分布。
加热层20因此由三个子部段30、32组成，所述子部段分别在一侧上经由连接元件26连接。分别彼此邻接的连接元件26在此彼此电连接。因此，得出部段的电串联连接32-30-32。
图4示出沿着图3中的用符号表示的线IV-IV贯穿整个连接元件14的横截面。朝向内部空间16(常规的安装状态)，衬板元件14具有覆盖层34，所述覆盖层形成衬板元件14的可视侧36。连同两个中间层38a、b，因此得出三层构造。覆盖层34和中间层38a、b都是玻璃纤维预浸料层。
作为下一层跟随有加热层20以及另一中间层38c。随后跟随有芯层40，在此是呈蜂窝或蜂窝芯的形式的Nomex蜂窝芯。另一中间层38d以及第二覆盖层42，同样还有玻璃纤维预浸料将构造封闭。
层构造因此可以如下组成：在可视侧设有厚度分别为0.25mm的三个玻璃纤维预浸料层。在这三个层之下存在呈加热层20的形式的加热纸并且存在又一玻璃纤维预浸料层。在此之下存在芯层40和最后在背侧上再次存在两个玻璃纤维预浸料层。预浸料是PHG600-68-37类型。在本发明的范围内，由第一覆盖层台34和两个中间层38构成的三层的层也可以理解成由纤维复合材料构成的三层的(单个覆盖)层。同样内容适用于中间层38d和作为两层的(单个覆盖)层的第二覆盖层42。
图4此外示出用于连接元件26a的连接的电导线44，所述电导线与其通过相应的中间层38c间隔开并且电绝缘地在连接元件14的内部伸展。导线44也称作为“return copperstrip”。
图4在替选的实施方案中虚线地示出，沿衬板元件14的横向方向，为了从衬板元件14的背侧56起电接触器件，所述器件在此为导线44，如何将盲孔状的留空部58引入到所述衬板元件中，以便到达相应的器件。在同样虚线表明的接触之后，随后将留空部58相对于环境影响密闭地灌封或封闭。
图5示出中间层38c连同位于其下的、在此通过虚线表明的、不可见的加热层20的俯视图。中间层38c的相应的边缘区域在最终安装时分别在边缘侧还卷边，使得最后得出衬板元件14的形状。为了电接触加热层20，将切口46(也参见图4)引入到中间层38c中，从其可见在图中还未接触的连接层26b。而连接元件26a已经接触并且随后由绝缘薄膜48贴盖。
在中间层38c上此外设置有具有相应的连接导线44的温度传感器50并且同样通过绝缘薄膜48粘贴或固定。由此，始终可以检测衬板元件14或加热层20的当前的温度。在一个替选的实施方式中，还可以将在此未示出的热保险装置54(在图中表明示例性的使用地点)装入结构部件2(器件)中。这种热保险装置附加地引向温度传感器50，以便确保附加的安全性。
图6最后示出电接触的结构部件2，其中(在附图中不可见)温度传感器50和连接元件26a、b或引向所述元件的导线44借助于示出的连接线缆52接触。
附图标记列表：
2 结构部件
4 框架
6 支架
8 连接板
10 绝缘泡沫
12 硅树脂密封件
14 衬板元件
16 内部空间
18 可视窗
20 加热层
22 碳纤维
23 边缘区域
24 穿透部
26，26a，b 连接元件
28 区域
30 中间部段
32 侧部部段
34 第一覆盖层
36 可视侧
38，38a-d 中间层
40 芯层
42 第二覆盖层
44 导线
46 切口
48 绝缘薄膜
50 温度传感器
52 连接线缆
54 热保险装置
56 背侧
58 留空部
R1-3 总电阻

Claims (15)

1.一种用于飞机的内部空间(16)的呈夹层板结构的衬板元件(14)，所述衬板元件包含至少一个芯层(40)和第一覆盖层(34)，其中所述第一覆盖层(34)形成所述衬板元件(14)的可视侧(36)，其中在最靠近所述覆盖层(34)的芯层(40)和所述第一覆盖层(34)之间设置有电的加热层(20)，所述电的加热层至少在所述第一覆盖层(34)的子面之上延伸，并且所述电的加热层用于产生通过所述第一覆盖层(34)放射的热量。
2.根据权利要求1所述的衬板元件(14)，
其特征在于，
所述衬板元件(14)包含至少一个中间层(38)和/或与所述第一覆盖层(34)相对置的第二覆盖层(42)。
3.根据上述权利要求中任一项所述的衬板元件(14)，
其特征在于，
所述芯层(40)包含蜂窝芯或者这种蜂窝芯或所述芯层(40)由泡沫制成。
4.根据上述权利要求中任一项所述的衬板元件(14)，
其特征在于，
所述覆盖层(34，42)和/或所述中间层(38)中的至少一个是由纤维复合材料构成的单层的或多层的层。
5.根据权利要求4所述的衬板元件(14)，
其特征在于，
所述纤维复合材料是预浸料。
6.根据上述权利要求中任一项所述的衬板元件(14)，
其特征在于，
所述加热层(20)是穿孔的。
7.根据上述权利要求中任一项所述的衬板元件(14)，
其特征在于，
所述加热层(20)包含面状延伸的加热元件或是面状延伸的加热元件。
8.根据上述权利要求中任一项所述的衬板元件(14)，
其特征在于，
所述衬板元件(14)包含至少一个温度传感器(50)和/或至少一个热保险装置(54)，所述热保险装置与所述加热层(20)热耦联。
9.根据权利要求8所述的衬板元件(14)，
其特征在于，
所述温度传感器(50)通过中间层(38c)与所述加热层(20)分开。
10.根据上述权利要求中任一项所述的衬板元件(14)，
其特征在于，
所述衬板元件(14)包含至少一个电连接元件(26)，用于电连接所述加热层(20)和/或所述导线(44)和/或所述温度传感器(50)和/或所述热保险装置(54)。
11.根据权利要求10所述的衬板元件(14)，
其特征在于，
所述衬板元件(14)具有至少一个从其背侧(56)起沿横向方向引导至所述连接元件(26)中的至少一个的盲孔状的留空部(58)，所述留空部在电连接所述连接元件(26)之后被封闭。
12.根据上述权利要求中任一项所述的衬板元件(14)，
其特征在于，
所述加热层(20)在两个相对置的边缘区域(23)处电接触。
13.根据权利要求12所述的衬板元件(14)，
其特征在于，
所述加热层(20)在所述边缘区域(23)之间具有至少两个部段(30，32)，所述部段电地串联连接，其中这些部段(30，32)的区别在于至少一个参数。
14.根据权利要求13所述的衬板元件(14)，
其特征在于，
所述参数是所述加热层(20)的宽度和/或厚度和/或电特性和/或穿孔参数。
15.根据上述权利要求中任一项所述的衬板元件(14)，
其特征在于，
所述衬板元件(14)通常是用于飞机中的如下部位的衬板元件，在所述部位处不存在用于所述内部空间(16)的足够的无源热绝缘(10)的足够的结构空间。
CN201911154557.XA 2018-11-23 2019-11-22 具有呈夹层板结构的加热层的衬板元件 Pending CN111216870A (zh)

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