CN111405983B - 由结构塑料制成的加热窗玻璃 - Google Patents

由结构塑料制成的加热窗玻璃 Download PDF

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CN111405983B
CN111405983B CN201880078220.2A CN201880078220A CN111405983B CN 111405983 B CN111405983 B CN 111405983B CN 201880078220 A CN201880078220 A CN 201880078220A CN 111405983 B CN111405983 B CN 111405983B
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T.通迪
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Abstract

本发明涉及一种加热窗玻璃(1)，其包括至少一个塑料结构基材和加热装置(4)，加热装置(4)优选包括至少一个透明且导电的薄层，其特征在于，它以层压形式包括至少一个第一塑料结构基材(30)，至少一个配备有加热层(4)的玻璃板(5)和至少一个第二塑料结构基材(31)。这样的窗玻璃特别地旨在形成飞机的侧窗。

Description

由结构塑料制成的加热窗玻璃
本发明涉及一种基于结构塑料的加热窗玻璃。
本发明将更具体地描述用于在航空领域中使用的加热窗玻璃，但是不限于此。
飞机窗玻璃可包括加热装置，以防止外表面结冰或内表面起雾现象。加热装置用于通过非常细的线网或通过透明的导电层通过焦耳效应进行加热。
飞机的侧窗玻璃通常由塑料制成，具有多个塑料片，并且将加热装置结合在塑料中。
在由塑料制成的窗玻璃中使用加热丝不是最佳的。事实上，经受周期性机械应力(例如窗玻璃的膨胀或飞机的加压)的电热丝易于断裂，这限制了窗玻璃的寿命。此外，由于由塑料制成的窗玻璃的低导热性，每根加热丝散发的热量难以排出，这导致加热时出现光雾现象。
至于沉积在塑料上的加热层，由于必须在金属层的沉积(金属化)之前沉积清漆以允许使层的沉积表面光滑并提高该金属化的附着力，因此它们的制造在工业上很繁琐。此外，清漆的沉积需要非常干净的环境，以及需要热交联步骤，该步骤是控制复杂的。
加热层还可以在真空下沉积。但是，在塑料上的真空沉积仅限于低温。金通常被选作在塑料上的加热层，因为它可以低温沉积，并且由于其自然延展性而不会很脆；然而，金基层降低了穿过窗玻璃的透光率并产生黄色外观。此外，使用真空沉积的窗玻璃的制造周期由于塑料的脱气而被延长。
最后，在层压各种塑料片材之前，由于金属化片材相对较脆并且易于刮擦，因此施加了剧烈的处理和组装条件。
因此，本发明的目的是提供一种加热窗玻璃，该窗玻璃虽然由结构塑料制成，但是没有上述缺点。
根据本发明，基于结构硬质塑料的加热窗玻璃包括至少一个塑料结构基材和旨在通过焦耳效应提供加热以使窗玻璃除冰和/或除雾的加热装置，其特征在于，其以层压形式包括至少一个第一塑料结构基材，至少一个配备有加热装置的玻璃板和至少一个第二塑料结构基材。
因此，窗玻璃具有在结构上由塑料制成的优点，而没有将加热装置与塑料结合制造的上述缺点，这是由于加热装置预先沉积在玻璃上，然后将该玻璃层压在两个塑料基材之间。玻璃板形成窗玻璃的加热支撑。
根据一个特征，玻璃板的表面尺寸小于两个塑料结构基材的表面尺寸。
根据另一特征，两个结构基材彼此间隔开并且通过透明的塑料中间层(例如由聚乙烯醇缩丁醛(PVB)或TPU(热塑性聚氨酯)制成)接合。玻璃板特别地通过所述塑料中间层接合。因此，它被封装在将结构基材接合在一起的塑料中，特别地所述塑料中间层的厚度在1.2至5mm之间，优选在2.5至4mm之间。
所述玻璃板经由例如由PVB或TPU制成的单层或多层塑料膜被接合至每个塑料结构基材。
优选地，每个塑料结构基材的厚度在5至25mm之间。
塑料结构基材例如由PMMA(聚甲基丙烯酸甲酯)或PU(聚氨酯)或PC(聚碳酸酯)制成。
有利地，玻璃板是薄的，其厚度在0.5mm至1.6mm之间，优选地在0.5mm至0.7mm之间。
有利地，加热装置包括至少一个透明且导电的薄层。与金属线相比，使用加热层允许更好地分配加热，提供完美的透明性并防止任何浑浊效果，并最终提供增长的窗玻璃的使用寿命。导电层例如基于氧化锡，或者基于掺杂有铟或氟的氧化锡，或者基于金属尤其金和/或银类型金属。该层的厚度特别地在50至500nm之间。
优选地，加热层基于ITO，这允许通过高温沉积或通过承受这些温度的玻璃的随后退火来获得最佳的电导率。
在一个特定的实施方案中，窗玻璃包括两个由两个塑料结构基材组成的片材，和在它们之间夹有玻璃板，和至少一个第三片材，特别地打算用作窗玻璃的最外面片材并在其最终用途中窗玻璃的使用/组装位置时面向外部环境，所述第三片材要么由塑料制成，特别地厚度在1至3mm之间，要么构成玻璃基材，该玻璃基材优选地由增强玻璃制成(通过热或化学钢化)，特别地厚度在0.5至5mm之间，优选在1.5至3mm之间。特别地，第三片材经由由PU型塑料制成的接合中间层添加/接合至结构基材之一。优选地，所述第三片材的表面尺寸小于与之结合的结构基材的表面尺寸。
优选地，窗玻璃包括至少一个温度探针，该温度探针布置在两个塑料结构基材之间，或者通过接合到玻璃板上(在与配备有导电层的面相对的面上)，或者布置在分隔两个塑料结构基材的中间层材料的厚度中。
薄玻璃的使用有利地允许将可变电阻型的温度传感器抵靠玻璃放置在加热层的相反面上。这时，玻璃既作为电绝缘体，又作为良好的导热体。这允许精确控制加热层的温度，同时防止发生短路的风险。
根据本发明的窗玻璃还可以包括除加热层以外的至少一个薄功能层，例如用于太阳保护的层或电致变色层，这些薄功能层中的多个可以呈层堆叠体形式。可以将功能层施加在薄玻璃的非加热面上，但是在这种情况下，温度探针将更好地位于塑料中间层中并且不与功能层结合。作为变体，窗玻璃可以包括第二玻璃板，该第二玻璃板与第一玻璃板层压在两个塑料结构基材之间，并设有功能层。
根据一个特定特征，根据所述窗玻璃的厚度，窗玻璃的整个外围形成仅由塑料组成的扩展框架，该框架允许如同任何需要在厚度上穿孔的由塑料制成的通常窗玻璃一样地固定窗玻璃。
优选地，窗玻璃包括最外层的片材，其被设计为制成旨在容纳该接纳窗玻璃的结构的一部分的外围肩部。
窗玻璃可以在飞行器中使用，特别地用作侧窗，特别地用作飞机驾驶舱侧窗。
在本说明书的其余部分中，限定词“外部”和“内部”用于在驾驶舱中正常安装窗玻璃的情况下，其中一个面朝向驾驶舱的外部环境，一个面朝向驾驶舱的内部。
本发明现在借助于实施例并使用附图图示进行描述，所述实施例仅仅是说明性的，绝不限制本发明的范围，其中：
-图1表示根据本发明的加热窗玻璃的示意性剖视图；
-图2和3是图1的窗玻璃的两个分别的实施方案变型的示意性剖视图；
-图4是固定在如飞机结构的驾驶舱内的图2的窗玻璃的示意性剖视图。
在图1至图3中所示的本发明的加热窗玻璃1旨在固定至飞机驾驶舱的结构2，如图4所示，以特别形成侧窗。
根据本发明，加热窗玻璃1包括至少两个透明的塑料结构基材30和31，连接两个结构基材的透明热塑性塑料中间层32，有利地包括透明导电层的加热装置4以及用于所述加热装置的支撑件5，所述支撑件5被嵌入中间层32中，并且根据本发明由薄玻璃板形成。
飞机的结构2具有面向飞机外部环境的被称为外表面的面20。
两个透明的塑料结构基材30和31例如由PMMA制成。结构基材30，由于朝向飞机的外侧因此被称为外部基材，优选地具有例如14mm的厚度，该厚度大于结构基材31(由于它朝向内部，被称为内部基材的)的厚度，例如具有为6毫米的厚度。
能够接合两个结构基材的中间层32例如由PVB或TPU制成。例如，其具有为3.1mm的厚度。它是至少两个PVB膜类型的膜，以将薄玻璃板5结合到窗玻璃中并使其接合。
因此，玻璃板5借助于中间层32被层压在两个结构基材30和31之间。玻璃板5通过其表面之一50经由单层或多层PVB膜32A与外部结构基材30接合，并通过相反的面51经由第二单层或多层PVB膜32B与外部结构基材31接合。
根据本发明，薄玻璃板5形成用于沉积加热层4的支撑装置。
薄玻璃板具有例如0.7mm的厚度。
透明导电层4是例如通过PVD(物理气相沉积)或CVD(化学气相沉积)以已知方式沉积在玻璃上的薄层。优选地，该层基于掺杂的氧化物，例如ITO。例如，其厚度在50至800nm之间。
加热层覆盖玻璃板的一个面50的全部或一部分。具有加热层4的玻璃板5位于窗玻璃中，使得加热层4面向外部结构基材30。
加热层4连接到供电集电器或条带(在这里未示出)，该供电集电器或条带旨在连接到在窗玻璃外部的电流源。
有利地，窗玻璃包括至少一个温度探针6，该温度探针优选布置在玻璃板5上，特别地布置在玻璃板的与承载加热层4的面50相反的面51上。温度探针例如以已知的方式包括具有可变电阻的细线。作为变型，可以将温度探针放置在中间层32的厚度中。
在图2所示的实施例中，窗玻璃1在窗玻璃的外侧并且因此在飞机的外侧包括第三片材7。该片材由第三刚性基材形成，例如按照在1-3mm之间的厚度，或者由刚性塑料如PMMA制成，或者由增强玻璃(通过热或化学钢化)制成。该第三片材7经由透明塑料例如PU按照例如为5mm的厚度制成的中间层70接合至外部结构基材31的外表面。因此，与图1的实施例相比，该实施例的窗玻璃具有更多的片材，并且其厚度也更大。
在图3的实施例中，窗玻璃1仅包括两个片材，其对应于塑料结构基材30和31，但是特别地由18mm的PMMA制成的外部基材30的厚度相对于图1中的实施例的玻璃基材的厚度得到增大。
为了制造窗玻璃，将每个结构基材30和31，薄玻璃5(在沉积加热层4之前)，附加基材7和中间层70制造成期望的尺寸和形状，然后将窗玻璃的每个构成元件，结构基材，覆盖有加热层的薄玻璃5，任选的附加基材及其中间层，以及接合元件(尤其是薄膜32A和32B)，以层压材料的形式相互沉积，最后组件被传递到高压釜中。作为变型，可以在高压釜之后通过将塑料结构基材30和31切割成期望的尺寸来进行最终的尺寸确定。
为了确保将本发明的窗玻璃1固定在飞机的结构中(图4)，在窗玻璃的厚度内的玻璃板5(图1至图3)以及第三片材7及其中间层70(对于图2的实施例)具有小于塑料结构基材30和31的表面尺寸以提供在窗玻璃的整个厚度上完全由塑料制成的扩展外围框架8，以使其仅仅在固定装置80塑料中穿过，如图4所示。
此外，为了将窗玻璃结合到飞机的结构中，使得窗玻璃1的外表面10与飞机结构的外表面20共面(图4)，图2的实施例的第三片材7及其中间层70具有的表面尺寸小于外部结构基材30的表面尺寸，并且图3的外部结构基材30本身具有合适的形状以提供外周肩部9(飞机的机舱2厚度被安置在其中)。
当然，在窗玻璃和飞机的结构之间设置有这里未示出的密封件。

Claims (16)

1.一种加热窗玻璃(1)，其包括至少一个塑料结构基材和加热装置(4)，其特征在于，其以层压形式包括至少一个第一塑料结构基材(30)，至少一个装备有加热装置(4)的玻璃板(5)和至少一个第二塑料结构基材(31)，其中玻璃板被层压在第一塑料结构基材(30)和第二塑料结构基材(31)之间，并且所述第一塑料结构基材(30)和第二塑料结构基材(31)各自具有在5mm与25mm之间的厚度。
2.根据权利要求1所述的窗玻璃，其特征在于，玻璃板(5)具有的表面尺寸小于第一塑料结构基材(30)和第二塑料结构基材(31)的表面尺寸。
3.根据权利要求1或2所述的窗玻璃，其特征在于，所述第一塑料结构基材(30)和第二塑料结构基材(31)彼此间隔开并且通过为1.2至5mm的透明塑料中间层(32)接合。
4.根据权利要求3所述的窗玻璃，其特征在于，所述塑料中间层的厚度在2.5至4mm之间。
5.根据权利要求1-2中任一项所述的窗玻璃，其特征在于，所述玻璃板(5)经由单层或多层塑料膜(32A，32B)与每个塑料结构基材接合。
6.根据权利要求3所述的窗玻璃，其特征在于，所述透明塑料中间层(32)由PVB或PU制成。
7.根据权利要求1-2中任一项所述的窗玻璃，其特征在于，所述第一塑料结构基材(30)和第二塑料结构基材(31)由PMMA或PU或PC制成。
8.根据权利要求1-2中任一项所述的窗玻璃，其特征在于，所述玻璃板(5)具有在0.5至1.6mm之间的厚度。
9.根据权利要求1-2中任一项所述的窗玻璃，其特征在于，所述加热装置(4)包括至少一个透明且导电的薄层。
10.根据权利要求9所述的窗玻璃，其特征在于，所述透明且导电的薄层基于氧化锡或基于用铟或氟掺杂的氧化锡或基于金属。
11.根据权利要求1-2中任一项所述的窗玻璃，其特征在于，所述窗玻璃包括由第一塑料结构基材(30)和第二塑料结构基材(31)组成的两个片材并且在其间层压有玻璃板(5)，和至少一个第三片材(7)，其用于为在窗玻璃的片材的最外侧，并且在窗玻璃最终目的地中的窗玻璃使用位置中面向外部环境，所述第三片材由塑料制成，或构成玻璃基材，将所述第三片材(7)通过由PU型塑料制成的接合中间层(70)接合到所述结构基材中一个。
12.根据权利要求11所述的窗玻璃，其特征在于，所述第三片材(7)的表面尺寸小于与其结合的第一塑料结构基材(30)的表面尺寸。
13.根据权利要求1-2中任一项所述的窗玻璃，其特征在于，所述窗玻璃包括至少一个温度探针(6)，所述温度探针通过在与配备有加热装置(4)的面相反的面(51)上与玻璃板(5)接合而被布置在第一塑料结构基材(30)和第二塑料结构基材(31)之间，或被布置在分隔第一塑料结构基材(30)和第二塑料结构基材(31)的透明塑料中间层(32)的厚度中。
14.根据权利要求1-2中任一项所述的窗玻璃，其特征在于，根据所述窗玻璃的厚度，所述窗玻璃的整个周边形成仅由塑料构成的扩展框架(8)。
15.根据权利要求1-2中任一项所述的窗玻璃，其特征在于，所述窗玻璃包括第一塑料结构基材(30)和第三片材(7)作为最外侧的片材，该最外侧的片材进行设计以设置外围肩部(9)，该外围肩部旨在接纳用于容纳窗玻璃的结构(2)的一部分。
16.根据权利要求1-2中任一项所述的窗玻璃，其特征在于，其被用在飞行器中。
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