WO2012041164A1 - 一种密封穿墙件 - Google Patents

一种密封穿墙件 Download PDF

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Publication number
WO2012041164A1
WO2012041164A1 PCT/CN2011/079649 CN2011079649W WO2012041164A1 WO 2012041164 A1 WO2012041164 A1 WO 2012041164A1 CN 2011079649 W CN2011079649 W CN 2011079649W WO 2012041164 A1 WO2012041164 A1 WO 2012041164A1
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Prior art keywords
hole
flange
wall member
groove
glue
Prior art date
Application number
PCT/CN2011/079649
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English (en)
French (fr)
Inventor
徐炯�
单楠
张清
金鑫
王旭
章骏
葛建兵
Original Assignee
中国商用飞机有限责任公司
中国商用飞机有限责任公司上海飞机设计研究院
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Application filed by 中国商用飞机有限责任公司, 中国商用飞机有限责任公司上海飞机设计研究院 filed Critical 中国商用飞机有限责任公司
Publication of WO2012041164A1 publication Critical patent/WO2012041164A1/zh

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Classifications

    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
    • H02G3/00—Installations of electric cables or lines or protective tubing therefor in or on buildings, equivalent structures or vehicles
    • H02G3/22—Installations of cables or lines through walls, floors or ceilings, e.g. into buildings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L5/00—Devices for use where pipes, cables or protective tubing pass through walls or partitions
    • F16L5/02—Sealing

Definitions

  • the present invention is in the field of aircraft electrical harness installation, and in particular, it relates to a sealed wall member for supporting an aircraft electrical harness through an airtight deck. Background technique
  • the present invention provides a sealed through-wall member which allows an aircraft electric harness to easily pass through an airtight partition.
  • the sealing through-wall member of the present invention can also achieve shield grounding of the aircraft electrical harness, thereby overcoming the deficiencies of the prior art and fully satisfying the design requirements of the aircraft electrical harness.
  • the seal wall penetration member of the present invention comprises a cylindrical body and a damper, the body being provided with a central hole for the electrical harness to pass through, and comprising:
  • a fixing portion which is located at one end of the body, and is provided with at least one glue filling hole, and the filling hole communicates with the center hole;
  • a flange which is located on an outer peripheral surface of the body, and is provided with at least one glue hole, the glue hole is in communication with the center hole;
  • a connecting portion located at the other end of the body, and provided with a retaining ring four slots for placing the retaining ring and a shielding four slot for fixing a shielding sleeve of the electric harness, the retaining ring groove being wider than the shielding The groove is closer to the flange.
  • the body is formed by abutting two semicircular hollow thin-walled cylinders, This makes it easy to install.
  • One of the two semi-circular hollow thin-walled cylinders is provided with a convex positioning key on the end face, and the other is provided with a concave positioning key at a corresponding position.
  • the sealing through-wall member is made of a metal material.
  • the sealing through-wall member is made of a metal material plated with nickel.
  • the metal material is an aluminum alloy material.
  • the seal wall penetration member further includes a gasket, the gasket being placed between the flange and the retaining ring.
  • the sealing through-wall member of the present invention adds a groove structure for the connection of the metal sealing through-wall member and the outer sheath of the electric harness to achieve the purpose of shielding grounding.
  • a metal material such as an aluminum alloy material is selected, and nickel is plated on the surface of the device, so that the aluminum alloy nickel-plated device has excellent conductivity. Therefore, the metal sealing through-wall member of the present invention can easily pass the airtight partition of the aircraft, and does not need to disconnect the electric harness, and does not need to pass the electric wire through the sealing through-wall member. Shield grounding requirements for aircraft electrical harnesses. DRAWINGS
  • Figure 1 is a perspective view of a metal seal through-wall member of the present invention
  • Figure 2 is a schematic view showing the structure of an end face of a half-shell of the metal sealing through-wall member of the present invention
  • Figure 3 is a perspective view of a half-shell of the metal sealing through-wall member of the present invention.
  • Figure 4 is a schematic view showing the installation of the metal sealing through-wall member of the present invention. detailed description
  • Figure 1 illustrates a sealed through-wall member 100 of the present invention for supporting an aircraft electrical harness through an airtight barrier and achieving a shielded grounding function.
  • the seal penetration member 100 is made of a metal material, preferably made of a nickel-plated metal material, for example, the metal material may be an aluminum alloy material.
  • the material used is aluminum alloy (GB/T3191-1998 aluminum) And aluminum alloy extruded bar), the surface treatment is nickel plating.
  • the wall penetration member 100 includes a cylindrical body 10 provided with a central bore 15 for electrical harness passing therethrough.
  • the body 10 is formed by abutting two semi-circular hollow thin-walled cylinders or half-shells 1, 1 and 12.
  • One of the half-shells 1 1 is provided with convex positioning keys or projections 13 on the end faces, and the other half-shells 12 are provided with concave positioning keys or grooves 14 at corresponding positions, whereby the two half-shells can be butted together.
  • other connections such as threaded connections, can also be used.
  • the body 10 includes a fixing portion 20, a flange 30, and a connecting portion 40.
  • the fixing portion 20 is located at one end of the body 10 and is provided with at least one glue filling hole 21 communicating with the center hole 15.
  • four filling holes 21 are symmetrically disposed.
  • the flange 30 is located on the outer peripheral surface of the body 10 and is an annular protrusion.
  • the flange 30 is provided with at least one moon crossing hole 3 1 , and the glue hole 3 1 extends in the flange 30 . It is in communication with the center hole 15, and the opening of the glue hole 31 is located at the side of the connecting portion 40.
  • the glue hole 31 can also be set at other positions. Two dispensing holes 31 are shown in FIG.
  • the connecting portion 40 is located at the other end of the body 10, and is provided with a dam groove 41 for placing the dam 50 and a shielding groove 42 for fixing a shield sleeve (not shown) of the electric harness 60, the ring groove 41 It is closer to the flange 30 than the shield groove 42.
  • a circular hole is opened in the airtight partition 200 of the aircraft, and then the electric harness 60 is passed through the circular hole, and the two half-shells 1 1 and 12 are harnessed.
  • a complete metal seal through wall member 100 is formed, and the metal seal through wall member 100 is passed through a circular hole in the airtight partition 200 until the flange 30 abuts against the airtight partition 200.
  • the flange 30 on the metal seal through wall member 100 should be in an airtight region.
  • the retaining ring 50 On the other side (non-hermetic region) of the sealing partition 200, the retaining ring 50 is caught in the retaining ring Hi groove 41 of the metal sealing through-wall member, and the metal sealing through-wall member 100 is fixed by the retaining ring 50. If necessary, a pad (not shown) may be placed between the airtight partition 200 and the retaining ring 50.
  • the outer shield of the electrical harness is secured in the shield recess 42 of the metal seal through-wall member 100 with a stainless steel clip. Then, both ends of the sealing through-wall member 100 are sealed with a tape, and a sealant is injected into the potting hole 2 1 until the sealant is left from the tapping hole 31. After the sealant is solidified, the installation of the metal seal through the wall is completed.
  • the metal sealing through-wall member of the invention does not need to disconnect the electric harness and does not need a By simply passing the wires through the sealed through-wall member, the aircraft electrical harness can easily pass through the airtight partition and meet the shield grounding requirements of the aircraft electrical harness.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Installation Of Indoor Wiring (AREA)
  • Insertion, Bundling And Securing Of Wires For Electric Apparatuses (AREA)

Abstract

一种密封穿墙件（100）包括圆柱形的本体（10）和挡圈（50），本体设有用于电气线束穿过的中心孔（15），并包括固定部（20）、法兰盘（30）和连接部（40）。所述固定部位于本体的一端，并设有至少一个灌胶孔（21），所述灌胶孔与所述中心孔相通。所述法兰盘位于所述本体的外周面上，并设有至少一个出胶孔（31），所述出胶孔与所述中心孔相通。所述连接部位于本体的另一端，并设有用于放置挡圈的挡圈凹槽（41）和用于固定电气线束（60）的屏蔽套的屏蔽凹槽（42），挡圈凹槽比屏蔽凹槽更邻近法兰盘。不需要断开电气线束，也不需要将电气线束一根根穿过密封穿墙件，该密封穿墙件就能够使飞机电气线束方便地穿过气密隔板。

Description

一种密封穿墙件 技术领域
本发明属于飞机电气线束安装领域， 具体地， 其涉及一种用于 支撑飞机电气线束穿过气密舱板的密封穿墙件。 背景技术
飞机电气线束穿越气密隔板时， 通常有以下几种方式： 一种是 用气密型的电连接器， 密封方式是依靠电连接器本身的密封， 因需 要将电气线束断开后靠电连接器重新连接， 所以可靠性差且价格昂 贵； 另一种是电气线束穿过预制的橡胶孔， 密封方式是依靠电线与 橡胶孔的配合， 需要将每根电线都单独穿过一个橡胶孔， 安装使用 不方便。 发明内容
为了解决上述问题， 本发明提供一种密封穿墙件， 其可以使飞 机电气线束方便地穿越气密隔板。 此外， 本发明的密封穿墙件还可 以使飞机电气线束实现屏蔽接地， 从而克服现有技术的不足， 充分 满足飞机电气线束的设计要求。
本发明的密封穿墙件包括圆柱形的本体和挡圏， 所述本体设有 用于电气线束穿过的中心孔， 并包括：
固定部， 其位于所述本体的一端， 并设有至少一个灌胶孔， 所 述灌胶孔与所述中心孔相通；
法兰盘， 其位于所述本体的外周面上， 并设有至少一个出胶孔， 所述出胶孔与所述中心孔相通；
连接部， 其位于所述本体的另一端， 并设有用于放置所述挡圈 的挡圈四槽和用于固定电气线束的屏蔽套的屏蔽四槽， 所述挡圈凹 槽比所述屏蔽凹槽更邻近所述法兰盘。
优选地， 所述本体由两个半圆形的空心薄壁圓柱体对接形成， 这样可以便于安装。 所述两个半圆形的空心薄壁圆柱体中的一个在 端面上设有凸定位键， 而另一个在相应的位置上设有凹定位键。
优选地， 所述密封穿墙件由金属材料制成。
优选地， 所述密封穿墙件由表面镀镍的金属材料制成。
例如， 所述金属材料是铝合金材料。
优选地， 所述密封穿墙件还包括垫圈， 所述垫圏放置在所述法 兰盘和所述挡圈之间。
本发明的有益效果在于：
本发明的密封穿墙件增加一个凹槽结构， 该 槽结构用于金属 密封穿墙件与电气线束外屏蔽套的连接， 从而达到屏蔽接地的目的。 此外， 选用金属材料例如铝合金材料， 并且在器件的表面镀镍， 使 得铝合金镀镍的器件具有极佳的导电性。 因此， 本发明的金属密封 穿墙件， 不需要断开电气线束， 也不需要一根根地将电线穿过密封 穿墙件， 就能够使飞机电气线束方便地穿越气密隔板， 并且满足了 飞机电气线束的屏蔽接地要求。 附图说明
下面结合附图进一步详细描述本发明的优选实施方式， 其中： 图 1是本发明的金属密封穿墙件的透视图；
图 2 是本发明的金属密封穿墙件的一个半壳的端面的结构示意 图；
图 3是本发明的金属密封穿墙件的一个半壳的透视图；
图 4 是本发明的金属密封穿墙件的安装示意图。 具体实施方式
图 1示出了本发明的密封穿墙件 100 ,其用于支撑飞机电气线束 穿越气密隔板且实现屏蔽接地功能。 该密封穿墙件 100 由金属材料 制成， 优选由表面镀镍的金属材料制成， 例如该金属材料可以是铝 合金材料。在本实施例中， 采用的材料为铝合金（GB/T3191-1998 铝 及铝合金挤压棒材） ， 表面处理为镀镍。
结合图 1 - 3 所示， 该穿墙件 100 包括圆柱形的本体 10 , 本体 10设有用于电气线束穿过的中心孔 15。 该本体 10 由两个半圆形的 空心薄壁圆柱体或半壳 1 1、 12对接形成。 一个半壳 1 1在端面上设 有凸定位键或突起 13 ,而另一个半壳 12在相应的位置上设有凹定位 键或凹槽 14 , 由此两个半壳可以对接在一起。 当然， 还可以采用其 它连接方式， 例如螺纹连接等。 本体 10 包括固定部 20、 法兰盘 30 和连接部 40。 固定部 20位于本体 10的一端， 并设有至少一个灌胶 孔 21 , 该灌胶孔 21 与中心孔 15相通， 在本实施例中对称地设有 4 个灌胶孔 21。 法兰盘 30位于本体 10的外周面上， 其为一环形凸起， 该法兰盘 30上设有至少一个出月交孔 3 1， 该出胶孔 3 1 在法兰盘 30 内延伸， 与中心孔 15相通， 出胶孔 3 1的开口位于连接部 40—侧。 当然， 出胶孔 31还可以设置其它位置上。 在图 2中示出了 2个出胶 孔 31。 连接部 40位于本体 10 的另一端， 并设有用于放置挡圏 50 的挡圏凹槽 41 和用于固定电气线束 60的屏蔽套 （未示出） 的屏蔽 凹槽 42， 挡圈凹槽 41比屏蔽凹槽 42更邻近法兰盘 30。
再结合图 4 所示， 在进行飞机电气线束安装时， 首先在飞机的 气密隔板 200上开一圓孔， 再将电气线束 60穿过圓孔， 用两个半壳 1 1、 12在线束外面对合成一个完整的金属密封穿墙件 100 , 将金属 密封穿墙件 100穿过气密隔板 200上的圓孔， 直到法兰盘 30紧贴气 密隔板 200。 金属密封穿墙件 100上的法兰盘 30应在气密区域。 在 密封隔板 200的另一侧 （非气密区） ， 将挡圏 50卡在金属密封穿墙 件的挡圈 Hi槽 41 中， 用挡圈 50将金属密封穿墙件 100 固定住。 如 有必要， 可在气密隔板 200和挡圈 50之间加垫圏 （未示出） 。 电气 线束的外屏蔽套用不锈钢卡带固定在金属密封穿墙件 100 的屏蔽凹 槽 42 中。 然后， 密封穿墙件 100的两端用胶布封住， 在灌胶孔 21 中注入密封胶， 直到密封胶从出胶孔 31 中留出为止。 等密封胶凝固 后， 金属密封穿墙件的安装即告完成。
本发明的金属密封穿墙件， 不需要断开电气线束， 也不需要一 根根地将电线穿过密封穿墙件， 就可以使飞机电气线束方便地穿越 气密隔板， 又满足了飞机电气线束的屏蔽接地要求。
上述具体实施方式只是对本发明的构思和原理进行阐述， 并非 要对本发明的内容进行限制。 本领域的普通技术人员可以意识到， 除了上述首选的具体实施方式之外， 本发明还有很多其他替代的或 者修改的实施方式， 这些替代的或者修改的实施方式仍然在本发明 的范围之内。

Claims

权 利 要 求 书
1. 一种密封穿墙件， 其特征在于， 其包括圆柱形的本体和挡圏， 所述本体设有用于电气线束穿过的中心孔， 并包括：
固定部， 其位于所述本体的一端， 并设有至少一个灌胶孔， 所 述灌胶孔与所述中心孔相通；
法兰盘， 其位于所述本体的外周面上， 并设有至少一个出胶孔， 所述出胶孔与所述中心孔相通；
连接部， 其位于所述本体的另一端， 并设有用于放置所述挡圏 的挡圈凹槽和用于固定电气线束的屏蔽套的屏蔽凹槽， 所述挡圈凹 槽比所述屏蔽凹槽更邻近所述法兰盘。
2. 根据权利要求 1所述的密封穿墙件， 其特征在于， 所述本体 由两个半圆形的空心薄壁圓柱体对接形成。
3. 根据权利要求 2所述的密封穿墙件， 其特征在于， 所述两个 半圓形的空心薄壁圓柱体中的一个在端面上设有凸定位键， 而另一 个在相应的位置上设有凹定位键。
4. 根据权利要求 1所述的密封穿墙件， 其特征在于， 所述密封 穿墙件由金属材料制成。
5. 根据权利要求 1所述的密封穿墙件， 其特征在于， 所述密封 穿墙件由表面镀镍的金属材料制成。
6. 根据权利要求 4或 5所述的密封穿墙件， 其特征在于， 所述 金属材料是铝合金材料。
7. 根据权利要求 1所述的密封穿墙件， 其特征在于， 所述密封 穿墙件还包括垫圈， 所述垫圈放置在所述法兰盘和所述挡圈之间。
PCT/CN2011/079649 2010-09-28 2011-09-14 一种密封穿墙件 WO2012041164A1 (zh)

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CN109309368A (zh) * 2017-07-26 2019-02-05 中国航空工业集团公司西安飞机设计研究所 飞机框板穿线密封装置
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CN110504560B (zh) * 2019-08-26 2020-11-10 中国商用飞机有限责任公司 密封穿墙装置和使用该装置的方法
CN110707631B (zh) * 2019-10-12 2022-01-28 中国商用飞机有限责任公司 一种燃油箱用线束密封穿墙件及其安装方法
CN113970016B (zh) * 2020-07-22 2023-09-15 中国商用飞机有限责任公司 一种密封穿墙件的密封方法
CN113054603B (zh) * 2021-05-31 2021-12-28 成都雷通科技有限公司 防护穿线夹及其安装方法
CN116893315B (zh) * 2023-09-07 2023-12-12 苏州英特模科技股份有限公司 半电波暗室的带载测功机穿墙系统及其安装方法

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