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    Electrically heated transparent laminated glazing unit
    2.
    发明授权
    Electrically heated transparent laminated glazing unit 失效
    电加热透明层压玻璃单元

    公开(公告)号：US3974359A

    公开(公告)日：1976-08-10

    申请号：US585417

    申请日：1975-06-09

    申请人： Dee R. Orcutt ,  Kenneth C. Collier

    发明人： Dee R. Orcutt ,  Kenneth C. Collier

    IPC分类号： B32B17/10 ,  B64C1/14 ,  H05B3/86 ,  H05B3/06

    CPC分类号： B32B17/10761 ,  B32B17/10036 ,  B32B17/10174 ,  B32B17/10366 ,  B32B17/1077 ,  B64C1/1484 ,  H05B3/86 ,  H05B2203/014

    摘要： A laminated glass-plastic glazing unit suitable for aircraft is disclosed. The unit comprises a pair of sheets of rigid transparent material such as glass and an interlayer of thermoplastic material that is susceptible to crack at low temperatures and that has a higher coefficient of thermal expansion than the sheets of rigid transparent material. Electrical resistance material preferably in the form of thin metal wire, is embedded within the interlayer and disposed locally in areas along a pair of opposite marginal edges of the interlayer and electrically energized to heat the interlayer portion adjacent thereto sufficiently to overcome the tendency of the interlayer to pull chips from the marginal portion of one or both of the rigid sheets when the unit is subjected to extremely low temperature conditions in a high-flying aircraft. The electroconductive material is embedded within the interlayer in spaced relation to a transparent electroconductive coating on one of the glass sheets for heating the glazing unit to dissipate mist or frost and is located relative to the thickness of the interlayer in a plane that is closer to the rigid sheet more likely to become damaged when the unit is exposed to the aforesaid low temperature conditions. The interlayer may also include a metal reinforcement frame in heat exchanging relation to the electroconductive material that extends to the edge of the interlayer to conduct heat received from the electroconductive material to the edge of the interlayer, thereby retarding the cooling of the edge of the interlayer to a temperature at which it cracks.

    摘要翻译： 公开了一种适用于飞机的夹层玻璃塑料玻璃装置。 该单元包括一对刚性透明材料如玻璃和热塑性材料的中间层，其在低温下易于裂纹，并且具有比刚性透明材料片材更高的热膨胀系数。 优选以细金属丝的形式的电阻材料嵌入在中间层内并且局部地设置在沿着中间层的一对相对的边缘边缘的区域中，并被电通电以加热与其相邻的中间层部分，足以克服中间层的趋势 当高速飞行器中的单元受到极低温度条件时，从一个或两个刚性片材的边缘部分拉出芯片。 导电材料以与玻璃板之一上的透明导电涂层间隔开的方式嵌入在中间层内，用于加热玻璃窗单元以消散雾或霜，并且相对于中间层的厚度位于更靠近 当单元暴露于上述低温条件下时，刚性片更容易损坏。 中间层还可以包括与导电材料热交换的金属增强框架，该金属增强框架延伸到中间层的边缘以将从导电材料接收的热量传导到中间层的边缘，从而延缓中间层边缘的冷却 达到其破裂的温度。