CN112399916A - 并入有自动着陆辅助系统的天线的层压玻璃窗单元 - Google Patents

并入有自动着陆辅助系统的天线的层压玻璃窗单元 Download PDF

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CN112399916A
CN112399916A CN202080002514.4A CN202080002514A CN112399916A CN 112399916 A CN112399916 A CN 112399916A CN 202080002514 A CN202080002514 A CN 202080002514A CN 112399916 A CN112399916 A CN 112399916A
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glazing unit
laminated glazing
antenna
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glass
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V·勒戈瓦
V·拉谢
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Saint Gobain Glass France SAS
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  • Engineering & Computer Science (AREA)
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  • Physics & Mathematics (AREA)
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  • Joining Of Glass To Other Materials (AREA)

Abstract

并入有自动着陆辅助系统的天线的层压玻璃窗单元。本发明涉及：‑一种层压玻璃窗单元，其包括至少一个第一玻璃板（1）和经由第一粘合性中间层（2）彼此粘合的第二玻璃板（3），所述第一玻璃板（1）旨在构成层压玻璃窗单元的与外部大气接触的表面，其中所述层压玻璃窗单元在所述第一玻璃板（1）和所述第二玻璃板（3）之间包括在100和120 MHz之间接收的LOC（定位器）天线和在320和340 MHz之间接收的GLIDE（倾斜）天线，每个天线的尺寸都足够小以至于不会妨碍视线，甚至实际上穿过层压玻璃窗单元不可见；‑一种该层压玻璃窗单元的应用，其应用于具有固定或旋转机翼的加压或非加压飞行器的玻璃窗单元。

Description

并入有自动着陆辅助系统的天线的层压玻璃窗单元
技术领域
本发明涉及具有固定或旋转机翼的加压或不加压飞行器的领域，例如商用飞机、民用飞机（空中客车A320或波音737型）或军用飞行器、直升机、航天飞机，其如今使用自动着陆辅助系统或仪表着陆系统ILS，即使在恶劣的天气条件下也可以进行精确进近（竖直平面和水平平面引导）。这些天线通常放在飞机机头中，放在天线罩后面。它们通过同轴电缆连接到飞行计算机。
背景技术
该系统基于两个天线：
- 在VHF频段内以接近110 MHz（108.10 MHz和111.95 MHz之间）的频率接收的LOC（定位器）天线；
- 使用328.65 MHz和335.40 MHz之间的UHF频率的GLIDE（倾斜）天线。
由两个天线组成的该系统从地面接收竖直平面和水平平面中的引导信息，并将该信息传输到飞行计算机，以特别地用于最终进近（着陆）。它可以由单个天线（以下称为ILS天线）组成。
ILS天线也可以安装在前起落架的门上，如申请EP 0 706 722 A1中所描述的。然后，它利用与由石墨/环氧树脂复合材料制成的前起落架的门相关联的固有电气特性。
飞机还可以配备其他天线（GPS、WIFI），其位置可以对飞机的空气动力和/或重量产生显著的反响。通过将薄平面天线并入玻璃窗单元（挡风玻璃、驾驶舱侧窗、乘客舷窗）中，可以通过减少要安装在机身上的元件（天线，电缆等）的数量来减轻重量。
如今，飞机驾驶舱的玻璃窗中未并入有任何类型的天线（ILS、GPS）。现在，发明人已经意识到了将某些天线并入机载交通工具（特别是飞机、直升机）中，特别是在交通工具前部处的玻璃窗单元中以确保信号的良好接收的显著益处。因此，将天线并入到交通工具前部处的玻璃窗单元（特别是驾驶舱玻璃窗单元）中，具有减小用于将天线链接到飞行计算机的电缆的长度（因此重量减轻）的优点。
这些天线需要连接器，该连接器必须并入在玻璃窗单元中。因此，这必须在良好的工程实践中完成，以免产生脆化区，并且以免降低玻璃窗单元对老化（水分渗透，连接器腐蚀等）的耐性。
信号则必须通过数字/模拟转换来转换，以便能够被飞行计算机读取。因此，转换系统必须被添加和并入玻璃窗单元附近（可用空间很小）或计算机附近。
发明内容
因此，发明人创造了本发明，为此目的，本发明的主题是一种层压玻璃窗单元，其包括至少一个第一玻璃板和经由第一粘合性中间层彼此粘合的第二玻璃板，第一玻璃板旨在构成层压玻璃窗单元的与外部大气接触的表面，其特征在于，所述层压玻璃窗单元在第一玻璃板和第二玻璃板之间包括在100和120 MHz之间接收的LOC（定位器）天线和在320和340 MHz之间接收的GLIDE（倾斜）天线，每个天线的尺寸都足够小以至于不会妨碍视线，甚至实际上穿过层压玻璃窗单元不可见。
两个天线中的每个天线可以彼此独立地嵌入第一粘合性中间层中，或者相反地，与第一或第二玻璃板的朝向该层的面接触。
优选地，将LOC（定位器）天线和GLIDE（倾斜）天线组合在单个天线中，该天线由直径在10到500 µm之间的以F形几何形状成双绞延伸的导电金属线构成。在此以及下文中，导体应理解为是指电导体。
按照优选的升序，导电金属线的直径至多等于300、200和100µm。
在优选的构造中，特别是在先前述及的商用飞机中，第一玻璃板的边缘相对于第二玻璃板的边缘向后退进，第一玻璃板的自由表面的外围部分、第一玻璃板的外缘、第一粘合性中间层的外缘和第二玻璃板的表面的延伸超过第一玻璃板的部分形成阶梯状连续轮廓，由阶梯状元件利用胶的添入而覆盖该阶梯状连续轮廓。
在该构造中，阶梯状元件有利地是导电的并且接地，F的两个平行分支指向层压玻璃窗单元的边缘且与之相距一小段距离，并且这两个分支中的位于F的端部处的一个分支链接到阶梯状元件，而位于F的中间部分中的另一个分支则经由信号的数字/模拟转换装置将来自LOC（定位器）天线和GLIDE（倾斜）天线的这些信号传输到飞行计算机。
根据本发明的层压玻璃窗单元的优选特征，第一玻璃板的朝向第一粘合性中间层的面在其边缘之一的紧邻附近具有导电透明氧化物涂层，该涂层以鱼钩形式该边缘上呈现，并构成GPS天线。该天线设计用于接收大约1300至1800 MHz之间的频率。
第一玻璃板的朝向第一粘合性中间层的面也可以具有与GPS天线的材料具有相同性质的加热导电透明氧化物涂层，但是与之区分开并且相隔适当的距离，以便不打扰其信号的接收。众所周知，这种加热涂层位于层压结构中尽可能靠近外部大气的地方，具有防冰功能。加热涂层和GPS天线可以由薄层组成，例如由金、多层银、掺锡氧化铟（ITO，即indiumtin oxide）、ZnO:Al、 SnO2:F等。
GPS天线可以通过化学或激光蚀刻形成具有鱼钩形式的薄的加热层。因此它是透明的，且其局部透光率与加热区域中挡风玻璃的透光率相同，并且实际上从驾驶舱内部是不可见的。被安装在玻璃窗单元的边缘，它可以位于飞行员视野范围之外，这取决于玻璃窗单元的形式/尺寸。
优选地，天线输出由绝缘的编织物（电绝缘护套）和/或诸如同轴电缆的电缆和/或诸如接触柱的扁平连接器和/或通过任何其他适当的方式制成。该实现方式可以与已经并入在层压件中的温度探头的输出相同。
优选地，与传送信号的每个天线输出相对，所述阶梯状元件在2 X 20mm，优选地2X 30 mm的最小宽度上不存在；这构成用于天线输出的通道，该通道足够宽，以使阶梯状元件的导电材料不会干扰来自天线的信号传输。
优选地，阶梯状元件被气密性和水密性密封件覆盖，并且该密封件防止太阳辐射和流体。
优选地，阶梯状元件被珠（bead）覆盖，该珠赋予层压玻璃窗单元在玻璃窗单元和诸如飞机结构的安装结构之间的空气动力学连续性，以及对于诸如航空流体、清洁产品、脱脂剂、用于地面除冰的乙二醇等的处理流体的良好惰性。
优选地，层压玻璃窗单元包括通过第二粘合性中间层链接到第二玻璃板的至少一个第三玻璃板。
优选地，第一玻璃板由厚度在0.5至5mm之间，优选地在2至4mm之间的矿物玻璃制成，或者由诸如厚度在0.5至5mm之间的聚甲基丙烯酸甲酯（PMMA）的聚合物材料制成。
优选地，第二玻璃板（以及如果合适的话第三玻璃板，甚至随后的玻璃板）由厚度在4至10mm之间的矿物玻璃制成，或者由诸如厚度在5到30mm之间，优选不超过20mm的聚（甲基丙烯酸甲酯）（PMMA）的聚合物材料制成。
优选地，粘合性中间层由聚氨酯（PU）、聚乙烯醇缩丁醛（PVB）、乙烯-乙酸乙烯酯（EVA）或等同物制成，第一粘合性中间层的厚度在3至10mm之间，优选为4至8mm，第二粘合性中间层（以及如果合适的话随后的粘合性中间层）的厚度在0.5至4mm之间，优选至多等于2mm。
本发明的另一个目的是将如上所述的层压玻璃窗单元应用于具有固定或旋转机翼的加压或非加压飞行器的玻璃窗单元，特别是应用于民用商用或军用飞机、直升机或航天飞机的玻璃窗单元，并以绝对优先的方式应用于飞机驾驶舱的前端玻璃窗单元，其中天线输出在天线所定位至的非常靠近的地方穿过玻璃窗单元的的后边缘。
附图说明
附图说明了本发明：
图1是根据本发明的民用商用飞机驾驶舱的前端挡风玻璃的前视示意图。
图2是这样的前端挡风玻璃的横截面示意图，示出了组合在单个天线中的LOC（定位器）天线和GLIDE（倾斜）天线。
图3是示出了GPS天线的这种前端挡风玻璃的横截面示意图。
具体实施方式
参照图1，民用商用飞机驾驶舱的前端挡风玻璃配备有：阶梯状外围元件7，加热导电透明氧化物涂层12，组合在单个天线100中的LOC（定位器）天线和GLIDE（倾斜）天线，以及GPS天线200。
阶梯状元件7是导电的并且接地。它包括40毫米（可能为60毫米）宽的储备区（reserves）71、72，一方面传递来自LOC（定位器）和GLIDE（倾斜）天线的信号的天线输出101通过该储备区，且另一方面传递来自GPS的信号的天线输出201通过该储备区。因此，不存在由于阶梯状元件7引起的天线信号的干扰。
天线100由直径在10到500µm之间的导电金属线构成，该金属线以F形几何形状成双绞延伸。构成位于F的端部处的分支102的双绞线链接到阶梯状元件7，也就是说接地；为此，提供了阶梯状元件7的在附图中未示出的局部切口。
以与加热层12的材料相同的导电材料蚀刻GPS天线200，其与加热层12充分隔离，以使加热层12不会干扰GPS天线200的接收。
在下文中，在这些示例中，玻璃板是指化学回火的铝硅酸盐玻璃板，由圣戈班·苏利公司以注册商标Solidion®出售。
参考图2，图1的层压玻璃窗单元包括构成玻璃窗单元的外部面的第一玻璃板1，厚3 mm，并通过5.76 mm厚的聚氨酯（PU）的第一粘合性中间层2粘合到8 mm厚的第二玻璃板3。
8mm厚的第三玻璃板5通过2mm厚的聚乙烯醇缩丁醛（PVB）的第二粘合性中间层4粘合到第二玻璃板3。
第二和第三玻璃板3、5的外缘被相对坚硬的弹性体板31、51保护免受冲击。
第一玻璃板1的边缘相对于第二玻璃板3的边缘向后退进，第一玻璃板1的自由表面的外围部分、第一玻璃板1的外缘、第一粘合性中间层2的外缘和第二玻璃板3的表面的延伸超过第一玻璃板1的部分形成阶梯状连续轮廓，该轮廓由阶梯状元件7覆盖，阶梯状元件7由导电金属制成。阶梯状金属元件7接地。
由阶梯状元件7利用厚度为100µm的聚硫化物胶6的添入而覆盖所述阶梯状连续轮廓。
阶梯状元件7被由硅树脂制成的气密性和水密性密封件8覆盖，并且由聚硫化物的珠9覆盖，该珠9为层压玻璃窗单元提供了在玻璃窗单元和诸如飞机结构的安装结构之间的空气动力学连续性以及对处理流体的良好惰性，如已经解释的。
硅树脂密封件8的外部面具有密封唇缘81。此外，在硅树脂密封件8的底部中插入了比硅树脂更硬的材料的垫片10，以通过施加一定的压力（例如缩紧，pinching）而确保层压玻璃窗单元良好地保持在其安装位置中。垫片10是实心的，但是包括如图2所示的空隙11，其功能将在下面说明。
玻璃板1的朝向层压结构内部的面带有加热层12，该加热层12的边缘可见，该加热层12由掺锡氧化铟（ITO，即indium tin oxide）或诸如金、多层银、ZnO:Al、 SnO2:F等的等同物组成。加热层12对玻璃板1的外部表面的除冰是有效的。
如参照图1所解释的，LOC（定位器）天线和GLIDE（倾斜）天线被组合在单一天线100中，该天线由直径在10到500 µm之间的以F形几何形状成双绞延伸的导电金属线构成。然而，图2示意性地示出了在选定的横截面平面中天线100的两条线的分离。
天线100由直径为31 µm、导电率等于5.76×107 S/m的铜线组成。玻璃的相对电容率或介电常数Er为6.7，且Δ切线或介电耗散因数（限定介电材料的损耗）Tan d为0.03。对于聚氨酯，Er为2.9，而Tan d为0.2。
天线100示出在第一玻璃板1和第一粘合性中间层2之间的界面处。或者，可以通过例如在层压开始时将天线插入两层聚氨酯之间而将其嵌入到聚氨酯2中。
天线100的金属线在第二和第三玻璃板3和5的外缘的前面延伸到硅树脂密封件8中，然后延伸到垫片10中为此目的而形成的空隙11中。天线100的天线输出101从硅树脂密封件8出来，靠近层压玻璃窗单元的旨在朝向飞机驾驶舱的面。天线输出101经由未示出的用于来自LOC（定位器）/ GLIDE（倾斜）天线100的信号的数字/模拟转换的装置链接到飞行计算机。天线输出101由绝缘的编织物（电绝缘护套）或电缆（例如DR24）制成，尤其是同轴电缆，如对于已经并入在层压件中的温度探头的输出可以完成的。
参照图3，图1的层压玻璃窗单元的GPS天线200放置在第一玻璃板1和第一粘合性中间层2之间的界面处。它由与上面参考图2描述的加热层12相同的材料构成。它是ITO层，厚度为800 nm，电导率为5.5×105 S/m。
两个天线100、200完美地发挥功能。

Claims (20)

1.一种层压玻璃窗单元，其包括至少一个第一玻璃板（1）和经由第一粘合性中间层（2）彼此粘合的第二玻璃板（3），所述第一玻璃板（1）旨在构成层压玻璃窗单元的与外部大气接触的表面，其特征在于，所述层压玻璃窗单元在所述第一玻璃板（1）和所述第二玻璃板（3）之间包括在100和120 MHz之间接收的LOC定位器天线和在320和340 MHz之间接收的GLIDE倾斜天线，每个天线的尺寸都足够小以至于不会妨碍视线，甚至实际上穿过层压玻璃窗单元不可见。
2.根据权利要求1所述的层压玻璃窗单元，其特征在于，所述LOC定位器天线和GLIDE倾斜天线组合在单个天线（100）中，所述天线（100）由直径在10到500 µm之间的以F形几何形状成双绞延伸的导电金属线构成。
3.根据权利要求2所述的层压玻璃窗单元，其特征在于，所述导电金属线的直径最大等于300µm。
4.根据权利要求3所述的层压玻璃窗单元，其特征在于，所述导电金属线的直径最大等于200µm。
5.根据权利要求4所述的层压玻璃窗单元，其特征在于，所述导电金属线的直径最大等于100µm。
6.根据前述权利要求中的任一项所述的层压玻璃窗单元，其特征在于，所述第一玻璃板（1）的边缘相对于所述第二玻璃板（3）的边缘向后退进，所述第二玻璃板（1）的自由表面的外围部分、第一玻璃板（1）的外缘、第一粘合性中间层（2）的外缘和第二玻璃板（3）的表面的延伸超过第一玻璃板（1）的部分形成阶梯状连续轮廓，由阶梯状元件（7）利用胶（6）的添入而覆盖所述阶梯状连续轮廓。
7.根据权利要求6所述的层压玻璃窗单元，其特征在于，所述阶梯状元件（7）是导电的并且接地，在于，F的两个平行分支指向层压玻璃窗单元的边缘且与之相距一小段距离，并且在于，这两个分支中的位于F的端部处的一个分支（102）链接到所述阶梯状元件（7），而位于F的中间部分中的另一个分支（101）则经由信号的数字/模拟转换装置将来自LOC定位器天线和来自GLIDE倾斜天线的这些信号传输到飞行计算机。
8.根据前述权利要求中的任一项所述的层压玻璃窗单元，其特征在于，所述第一玻璃板（1）的朝向所述第一粘合性中间层（2）的面在其边缘中的一个的非常靠近的地方具有导电透明氧化物涂层，所述涂层以鱼钩形式呈现在该边缘上，并构成GPS天线（200）。
9.根据权利要求8所述的层压玻璃窗单元，其特征在于，所述第一玻璃板（1）的朝向所述第一粘合性中间层（2）的面具有与GPS天线（200）的涂层具有相同性质的加热导电透明氧化物涂层（12），但是与之区分开并且相隔适当的距离，以便不打扰其信号的接收。
10.根据权利要求7和8中的任一项所述的层压玻璃窗单元，其特征在于，所述天线输出（101、201）是由绝缘的编织物（电绝缘护套）和/或诸如同轴电缆的电缆和/或诸如接触柱的扁平连接器制成。
11.根据结合权利要求6的权利要求7至10中的任一项所述的层压玻璃窗，其特征在于，与传递信号的每个天线输出（101、201）相对，所述阶梯状元件（7）在2 X 20mm，优选地2 X30 mm的最小宽度（71、72）上不存在。
12.根据结合权利要求6的前述权利要求中的任一项所述的层压玻璃窗单元，其特征在于，所述阶梯状元件（7）被气密性和水密性密封件（8）覆盖，并且该密封件（8）防止太阳辐射和流体。
13.根据结合权利要求6的前述权利要求中的任一项所述的层压玻璃窗单元，其特征在于，所述阶梯状元件（7）被珠（9）覆盖，所述珠赋予所述层压玻璃窗单元在玻璃窗单元和诸如飞机结构的安装结构之间的空气动力学连续性，以及对于诸如航空流体、清洁产品、脱脂剂、用于地面除冰的乙二醇等的处理流体的良好惰性。
14.根据前述权利要求中的任一项所述的层压玻璃窗单元，其特征在于，所述层压玻璃窗单元包括通过第二粘合性中间层（4）链接到第二玻璃板（3）的至少一个第三玻璃板（5）。
15.根据前述权利要求中的任一项所述的层压玻璃窗单元，其特征在于，所述第一玻璃板（1）由厚度在0.5至5mm之间，优选地在2至4mm之间的矿物玻璃制成，或者由诸如厚度在0.5至5mm之间的聚甲基丙烯酸甲酯PMMA的聚合物材料制成。
16.根据前述权利要求中的任一项所述的层压玻璃窗单元，其特征在于，所述第二玻璃板（3）以及如果合适的话第三玻璃板（5）、甚至随后的玻璃板由厚度在4至10mm之间的矿物玻璃制成，或者由诸如厚度在5到30mm之间，优选至多20mm的聚甲基丙烯酸甲酯PMMA的聚合物材料制成。
17.根据结合权利要求14的前述权利要求中的任一项所述的层压玻璃窗，其特征在于，粘合性中间层（2；4）由聚氨酯PU、聚乙烯醇缩丁醛PVB、乙烯-乙酸乙烯酯EVA或等同物制成，在于，第一粘合性中间层（2）的厚度在3至10mm之间，优选为4至8mm，且在于，第二粘合性中间层（4）以及如果合适的话随后的粘合性中间层的厚度在0.5至4mm之间，优选至多等于2mm。
18.根据前述权利要求中任一项所述的层压玻璃窗单元的应用，其应用于具有固定或旋转机翼的加压或非加压飞行器的玻璃窗单元。
19.根据权利要求18所述的应用，其应用于民用商用或军用飞机，直升机或航天飞机的玻璃窗单元。
20.根据权利要求19所述的应用，其应用于飞机驾驶舱前端玻璃窗单元，其中，天线输出在天线所定位至的非常靠近的地方穿过玻璃窗单元的的后边缘。
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KR20220021924A (ko) 2022-02-22
EP3983220B1 (fr) 2023-09-06
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FR3097163B1 (fr) 2021-06-18
BR112021023544A2 (pt) 2022-01-18
CN112399916B (zh) 2023-07-07
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FR3097163A1 (fr) 2020-12-18
IL288890A (en) 2022-02-01

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