CN1044265A - 飞机挡风板 - Google Patents
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Abstract
一种玻璃/聚碳酸酯层压板装备一种边缘附件,可使层压板的轮廓挠曲减少,并可使作用在聚碳酸酯层压板上的载荷降低。
Description
本发明涉及飞机机窗,更具体地说是涉及重量轻的、玻璃和聚碳酸脂层压板的飞机挡风板,这种层压板可降低由于机舱内部压力作用而造成的挡风板挠曲和降低在挡风板聚碳酸脂层上的载荷。
当一架飞机飞向高空,机舱内的空气增压,结果,随着飞机高度的变化,飞机的内部压力也改变时,飞机机窗就受到交变载荷的影响,而作用在聚碳酸脂窗板上的交变载荷,可以导致窗板由于疲劳过早的损坏。因为聚碳酸脂的刚性同其它常用透明体材料比较起来相对地要低,交变载荷使聚碳酸脂板向外挠曲,从而改变了飞机机窗以及整架飞机的表面轮廓,为减少这种挠曲,在层压透明板中加入更硬的层,例如玻璃外板,然而,聚碳酸脂板的周边通过附件夹固在飞机构架上的,而受压时在聚碳酸脂板的中央则发生挠曲,但由于刚性较好的玻璃在其周边产生较少量的挠曲,因此在玻璃板和剩下的透明聚碳酸脂板之间的层板周边,引起该机窗透明体发生分层。
透明体对于一架飞机来说甚有用处,尤其是采用聚碳酸脂和玻璃板的飞机挡风板,这种挡风板能避免上述有害的分层现象,同时经得住对飞机的挡风板来说常遇到的巨大冲击力,而能保持透明体结构完好更是如此。
Stefanik发明的美国专利第3,919,022号和第4,004,388号公开了一种玻璃层板窗户板的周边结构,它包括模制的,用玻璃纤维增强的,热固的树脂嵌条,粘附並搭接在视野边缘区,外侧层板的玻璃板的两面,当层压时,嵌条固化形成刚性地固定到窗户玻璃板和其它边缘材料上的刚性联接件。
Roberts等人发明的美国专利第3,953,630号刊载出一种层压透明体组件,该组件包括一玻璃层压板,具有聚乙稀醇缩丁醛夹层和一高抗拉强度柔性嵌入物,它沿四周延伸並有一部分嵌置在夹层周边边缘内。嵌入物的一部分延伸到透明体的周边上用来把透明体安装到飞行器上。
美国Stefanik发明的第4,046,399号专利,介绍了一种层压透明体窗户,它用一浸渍了硅酮合成橡胶粘结剂的柔性纤维带来把至少其中一块窗户层压板或加强件粘结到窗户的另一构件上。
按照本发明,提供了一种经受在内部反复加压的飞行器,例如飞机的窗板,包括一外侧刚性板固定到一内侧刚性板上。外侧板要比内侧板刚性好,在本发明的一个具体实施例中,外侧板是玻璃而内侧板是聚碳酸脂层压板。内侧板的周边边缘延伸超出外侧板的周边边缘,嵌条件固定到围绕外侧板周边边缘的主表面並遍布内侧板的周边边缘。在本发明的最佳实施例里,有一对嵌条件固定到外侧板的相对两主表面上,一刚性边缘附件固定到内侧板的边缘和嵌条的延伸部分,以使外侧板设置在由边缘附件限定的周边内。
在本发明里,当窗板受到加压载荷时,因为玻璃板比内侧聚碳酸脂层压板刚性更强,并且嵌条固定住它的周边,于是外侧玻璃层限制住窗板向外挠曲。其结果,施加在内侧聚碳酸层压板的交变载荷较小,因此疲劳应力也较小。此外,鉴于内侧聚碳酸脂层压板被限止同外侧玻璃层受到等量的挠曲,机窗就不会在它周边产生分层。
图1是体现本发明新特征的一种飞机窗户组件的局部截面视图。
图2是玻璃层和聚碳酸脂层的相对挠曲的示意说明图。
图1表示一架飞机窗户组件10的局部截面视图,它是本发明的主题。应当理解组件10可以是平面形状的,稍微弯曲的或者成型成飞机座舱盖的明显弯曲形状的。外侧玻璃层12通过夹层14固定到一个内侧聚碳酸脂层压件16上,但应当理解组件10的内侧制件也可以是,例如一单独的聚碳酸脂层或者其它的单层或多层的透明塑料组件。在图1中示出本发明的具体实施例里,固定嵌条18和20用一种高强度粘合剂如一种改进成与玻璃相容的结构环氧树脂。沿外侧玻璃层12周边边缘22与该玻璃层的两相对主表面固定在一起,並遍布到组件10的边界边缘24,嵌条18和20可以是一金属制品,例如钛合金,不锈钢或织造品,诸如玻璃纤维。虽然在本发明中没有限制,但固定嵌条18和20最好是浸渍热固树脂胶的玻璃纤维,与美国Stefanik发明的专利号3,919,022公开的相似,这里只引用作为参考。如果需要,玻璃层12的外侧周边可以通入相当于外侧嵌条和粘合剂的厚度的深度,因此当组件10层压成整体结构形式时,它就会有一个齐平的外侧表面。楔块26是一个填充剂材料,用来充填从玻璃层12延伸过来的在嵌条18和20之间的空隙。充填材料最好是予固化的,这样在组装时,充入充填材料后它们就不会流淌开来。组件10的周边边缘24是支撑在一固定装置上,它包括一对轻质的最好是铝的夹板28和30,组件10上的每一块板都分别有一孔32或33,它们大体上对准层板16上的穿入螺栓36的孔34,螺栓36把夹板28和30固定到组件10上去。衬套38装在孔34中,其作用是使夹板28和30间保持一定的距离。
缓冲垫挡块40充填外侧嵌条18和外侧夹板28之间的空隙。密封层42和44分别用来密封夹板28和30的内侧表面,把它们分别对着外侧镶装嵌条18和层板16密封。设置边缘密封件46围绕组件10的周边边缘48,以阻止潮气或溶剂进入组件10,这些潮气和溶剂可能引起在组件内的电气系统短路以及造成分层或其它的材料剥蚀。
如果需要,机窗外侧玻璃层12的外表面50可以涂上透明导电涂层(未示出)並接地,例如接到飞机框架(未示出)上,以收集聚集在组件10上的静电电荷。此外,由于组件10的多层设计会产生重象现象,组件10的内层表面可以涂覆上一种抗反射涂层(未示出)。聚碳酸脂层压板16的内侧表面52可涂覆上耐磨涂层(未示出)以增加它的使用寿命。嵌条18的窗外侧表面可应用耐磨涂层(未示出)以增加它的使用寿命。
当机舱增压时,组件10向外挠曲。作用在组件10上的内压载荷通过夹板28和30传递到飞机构架(未示出)上。参考图2可见由于玻璃板12是比聚碳酸脂层压板16刚性好,在相同载荷下层压板16比玻璃板12往外挠曲更大,如果玻璃层12的周边缘22设有用组件10的边缘附件钳制夹在夹板28和30之间,在加载时由于层压板16的抗弯曲力较小,层压板就有可能挠曲较大,而玻璃板12则抵抗挠曲,这将势必使玻璃板12的边缘22与装在下面的层压板16边界边缘54脱开,其结果在组件10的玻璃/层压板交界面的边界区域周围产生应力。随载荷增加,这种应力也随之增加,于是组件10就可能在它的周边周围开始分层脱开。
在图1所示本发明的具体实施例中,层压板16固定在外侧玻璃板12和纤维玻璃嵌条18和20上,嵌条18和20固定在外侧玻璃12的边界边缘22上和延伸到组件10的周边24,並夹在夹板28和30当中。组件10的挠曲是由刚性较强的外层玻璃12控制,因此宁可层压板16挠曲较小,而不使玻璃板12被迫挠曲更大以及造成在玻璃板边界区22发生分层脱开。此外,层压板16挠曲将比其不是与玻璃板12固定在一起时小,那么当受到增压载荷时,由于它在交变载荷下而遭受的疲劳应力也较小,这就能增加层压板的寿命而不致层间脱开。
虽然本发明的最佳实施例包括一对嵌条18、20如图1所示,对于一个熟练的技术人员将明显地看到,基于这种公开的启示,组件10可以只包含一单独的嵌条。特殊地,外侧嵌条18能够用来抑制外侧玻璃板12的变形而并不用内部嵌条20,而相反地也可不用外侧嵌条18而单用内侧嵌条20。
本说明书中所描述的发明形式系代表一种示例性的最佳实施例。显然;可以作各种变化而并不偏离如下列的权利要求书所限定的本发明的精神。
Claims (14)
1、一种窗板组件,它包括:
第一板,有一周边边缘相对的主表面;
第二板,固定在所述第一板的一主表面並有周边边缘延伸超过所述第一板的周边边缘,所述第二板的刚性比所述第一板的刚性小些;
一嵌条件,粘附于所述第一板的一主表面的边界边缘,所述嵌条件有一部分从所述第一板的周边边缘向外延伸到所述第二板外露的边界边缘的表层;以及
把所述嵌条件的延伸部分和所述第二板的边界边缘固定到一刚性的边缘附件上去的装置。
2、根据权利要求1的窗板组件,其特征为:上述板的第一板是玻璃板,上述板的第二板是塑料板。
3、根据权利要求2的窗板组件,其特征为:上述的塑料板至少包含一层聚碳酸脂。
4、根据权利要求2的窗板组件,其特征为:上述嵌条件是用一种热固性树脂浸渍的纤维玻璃材料。
5、根据权利要求2的窗板组件,其特征为:上述嵌条件是一金属嵌条。
6、根据权利要求5的窗板组件,其特征为:所述嵌条件是一钛合金嵌条。
7、根据权利要求1的窗板组件,其特征为:所述嵌条件是一粘附于所述第一板的第一主表面的第一嵌条件,另外还包含粘附于所述第一板的相对主表面的边界边缘的第二嵌条件,所述第二嵌条件有一部分从所述第一板的边界边缘向外延伸到所述第二板的外露边界边缘的表层,以及把所述第二嵌条件的延伸部分固定到所述刚性边缘附件的装置。
8、根据权利要求7的窗板组件,其特征为:所述的第一和第二板的边界边缘是弧形的,而其边缘附件的轮廓大体与所述第二板的边界边缘的弧形外表面相匹配。
9、根据权利要求8的窗板组件,其特征为:所述边缘附件包括在飞机机身开口上固定所述窗板组件的装置。
10、根据权利要求9的窗板组件,其特征为:所述窗板组件是一飞机挡风板。
11、根据权利要求1的窗板组件,其特征为:所述嵌条件是粘附于所述第一板的第一主表面的第一嵌条件,並进一步包括粘附于所述第一板相对主表面的边界边缘的第二嵌条件,所述第二嵌条件有一部分从所述第一板的周边边缘向外延伸到与所述第二板外露的边界边缘交叠,以及把所述的第二嵌条件的延伸部分固定到所述的刚性边缘附件上的装置。
12、根据权利要求11的窗板组件,其特征为:所述的嵌条件是一种用热固性树脂浸渍的纤维玻璃材料。
13、根据权利要求12的窗板组件,其特征为:所述的第一板是一在外侧的玻璃板,而所述的第二板是一在内侧的塑料层压板。
14、根据权利要求13的窗板组件,其特征为:所述板的边界边缘是弧形的,而且其边缘附件的轮廓大体与所述第二板的边界边缘的弧形外表面相匹配。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US292,057 | 1988-12-30 | ||
US07/292,057 US4933227A (en) | 1988-12-30 | 1988-12-30 | Aircraft windshield |
Publications (2)
Publication Number | Publication Date |
---|---|
CN1044265A true CN1044265A (zh) | 1990-08-01 |
CN1034488C CN1034488C (zh) | 1997-04-09 |
Family
ID=23123005
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN89109568A Expired - Fee Related CN1034488C (zh) | 1988-12-30 | 1989-12-25 | 窗板组件 |
Country Status (6)
Country | Link |
---|---|
US (1) | US4933227A (zh) |
EP (1) | EP0376190B1 (zh) |
JP (1) | JPH0825517B2 (zh) |
CN (1) | CN1034488C (zh) |
BR (1) | BR8906501A (zh) |
DE (1) | DE68915261T2 (zh) |
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-
1988
- 1988-12-30 US US07/292,057 patent/US4933227A/en not_active Expired - Lifetime
-
1989
- 1989-12-01 JP JP1313105A patent/JPH0825517B2/ja not_active Expired - Fee Related
- 1989-12-15 BR BR898906501A patent/BR8906501A/pt unknown
- 1989-12-22 DE DE68915261T patent/DE68915261T2/de not_active Expired - Fee Related
- 1989-12-22 EP EP89123747A patent/EP0376190B1/en not_active Expired - Lifetime
- 1989-12-25 CN CN89109568A patent/CN1034488C/zh not_active Expired - Fee Related
Cited By (3)
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CN104647165B (zh) * | 2014-12-16 | 2017-04-26 | 中国航空工业集团公司北京航空材料研究院 | 一种纤维金属层板疲劳分层扩展试验缺口的加工方法 |
CN107428419A (zh) * | 2015-03-31 | 2017-12-01 | 三菱重工业株式会社 | 结构体制造装置以及结构体制造方法 |
CN112061371A (zh) * | 2020-08-27 | 2020-12-11 | 北京航玻新材料技术有限公司 | 一种飞机风挡玻璃 |
Also Published As
Publication number | Publication date |
---|---|
JPH0825517B2 (ja) | 1996-03-13 |
EP0376190B1 (en) | 1994-05-11 |
US4933227A (en) | 1990-06-12 |
DE68915261T2 (de) | 1994-12-08 |
EP0376190A3 (en) | 1991-01-30 |
CN1034488C (zh) | 1997-04-09 |
DE68915261D1 (de) | 1994-06-16 |
EP0376190A2 (en) | 1990-07-04 |
JPH02204197A (ja) | 1990-08-14 |
BR8906501A (pt) | 1990-08-28 |
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