WO2024046057A1 - 一种抗雷击及防静电的保护装置及航空器 - Google Patents

一种抗雷击及防静电的保护装置及航空器 Download PDF

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Publication number
WO2024046057A1
WO2024046057A1 PCT/CN2023/111774 CN2023111774W WO2024046057A1 WO 2024046057 A1 WO2024046057 A1 WO 2024046057A1 CN 2023111774 W CN2023111774 W CN 2023111774W WO 2024046057 A1 WO2024046057 A1 WO 2024046057A1
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Prior art keywords
conductive
conductive member
protection device
lightning strike
connecting portion
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PCT/CN2023/111774
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English (en)
French (fr)
Inventor
胡华智
肖启伟
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亿航智能设备（广州）有限公司
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Publication of WO2024046057A1 publication Critical patent/WO2024046057A1/zh

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Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
    • H01R4/00—Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one another; Means for effecting or maintaining such contact; Electrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation
    • H01R4/58—Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one another; Means for effecting or maintaining such contact; Electrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation characterised by the form or material of the contacting members
    • H01R4/64—Connections between or with conductive parts having primarily a non-electric function, e.g. frame, casing, rail
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05F—STATIC ELECTRICITY; NATURALLY-OCCURRING ELECTRICITY
    • H05F3/00—Carrying-off electrostatic charges
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K5/00—Casings, cabinets or drawers for electric apparatus
    • H05K5/02—Details
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K5/00—Casings, cabinets or drawers for electric apparatus
    • H05K5/04—Metal casings
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K9/00—Screening of apparatus or components against electric or magnetic fields

Definitions

  • the present invention relates to the technical field of unmanned aircraft, and in particular to an anti-lightning strike and anti-static protection device and an aircraft.
  • the present invention provides an anti-lightning strike and anti-static protection device and an aircraft to solve the problem that the current aircraft cannot prevent lightning strikes or anti-static electricity during operation.
  • the invention provides an anti-lightning strike and anti-static protection device, which includes a shell and a conductive component.
  • the shell has a head end and a tail end;
  • the outer surface of the housing is coated with a conductive paint layer, and the conductive component includes a connecting portion and a conductive portion that are both conductors, and the connecting portion and the conductive portion are both provided on the conductive paint layer; the connecting portion Located at the head end of the casing, the connecting portion is used to connect to the grounding structure of the aircraft. One end of the conductive portion is fixedly connected to the connecting portion, and the other end of the conductive portion extends to the tail of the casing. end.
  • the conductive part includes a first conductive member and a second conductive member arranged parallel to each other, and the ends of the first conductive member and the second conductive member are both connected to the In the connection part, the first conductive member and the second conductive member are respectively located on both sides of the housing.
  • the conductive part further includes a conductive connector, the middle part of the conductive connector is fixedly connected to the connection part, and both ends of the conductive connector extend to the housing respectively. Both sides of the first conductive member and the second conductive member are connected to the connecting part through the conductive connecting member respectively.
  • the conductive part further includes a third conductive member, the third conductive member is located between the first conductive member and the second conductive member, and an end of the third conductive member part is connected to the connecting part.
  • the third conductive member is located on the symmetry plane of the first conductive member and the second conductive member.
  • the first conductive member and the second conductive member have a circular cross-section.
  • the third conductive member has a circular cross-section.
  • the connecting portion is a rectangular parallelepiped structure.
  • a conductive glue is provided between the conductive part and the conductive paint layer for connecting the two.
  • the present invention also provides an aircraft including the above-mentioned anti-lightning strike and anti-static protection device.
  • the conductive paint layer on the surface of the casing can prevent static electricity from interfering with the electrical equipment in the casing, and the conductive portion provided on the conductive paint layer can quickly transmit lightning strikes outside the casing through the connecting portion. to the grounding structure on the aircraft to release lightning. A small amount of lightning can gradually disperse from the conductive paint layer and be conducted to other fuselages of the aircraft to protect the electrical equipment inside the casing.
  • FIG. 1 is a schematic structural diagram of an anti-lightning strike and anti-static protection device according to an embodiment of the present invention.
  • FIG. 2 is a second structural schematic diagram of an anti-lightning strike and anti-static protection device according to an embodiment of the present invention.
  • connection should be understood in a broad sense.
  • it can be a fixed connection, a detachable connection, or an integrated connection.
  • Ground connection can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium.
  • specific meanings of the above terms in the present invention can be understood according to specific circumstances.
  • FIG. 1 and FIG. 2 the anti-lightning strike and anti-static protection device of the present invention is schematically shown.
  • the anti-lightning strike and anti-static protection device includes a casing 10 and conductive components.
  • the casing 10 is used to protect the radar and/or antenna on the top of the aircraft.
  • the casing 10 can be made of plastic or other existing composite materials.
  • the casing 10 10 has a leading end and a trailing end.
  • the outer surface of the housing 10 is coated with a conductive paint layer 11.
  • the conductive paint layer 11 can be made of existing conductive paint materials. Conductive paint is made by adding conductive metal powder to specific resin raw materials to make a paint that can be sprayed. After drying, the paint film formed can play a conductive role, thereby shielding electromagnetic wave interference.
  • the conductive component includes a connecting portion 20 and a conductive portion 30 that are both conductors.
  • the connecting portion 20 and the conductive portion 30 are optionally made of steel.
  • the connecting part 20 and the conductive part 30 are both disposed on the conductive paint layer 11 , that is, the connection part 20 and the conductive paint layer 11 can conduct electricity, and the conductive part 30 and the conductive paint layer 11 can conduct electricity.
  • the connecting part 20 is located at the front end of the casing 10.
  • the connecting part 20 is used to connect to the grounding structure of the aircraft. That is, a snap-in slot is provided on the top of the aircraft.
  • the snap-in slot is electrically connected to the grounding structure of the aircraft.
  • the connecting part 20 is embedded in the ground structure of the aircraft. Located in the snap slot.
  • One end of the conductive part 30 is fixedly connected to the connecting part 20, and the other end of the conductive part 30 extends to the rear end of the casing 10.
  • the conductive part 30 under this structure can protect the entire casing 10 from any objects that hit the casing 10.
  • the lightning is conducted to the connecting part 20 and then released to other parts of the aircraft fuselage to protect the electrical equipment in the casing 10 .
  • the conductive part 30 includes a first conductive member 31 and a second conductive member 32 arranged parallel to each other. The ends of the first conductive member 31 and the end of the second conductive member 32 are both connected to the connecting portion 20 . The member 31 and the second conductive member 32 are respectively located on both sides of the housing 10 so that the area protected by the conductive part 30 is larger.
  • the conductive part 30 in order to connect the first conductive member 31 and the second conductive member 32 to the connection part 20 , the conductive part 30 also includes a conductive connection member 34 , the conductive connection member 34 extends along the width direction of the housing 10 , and the first conductive member 31 and the second conductive member 32 extends along the length direction of the housing 10 .
  • the middle part of the conductive connector 34 is fixedly connected to the connecting part 20 . Both ends of the conductive connector 34 extend to both sides of the housing 10 to connect the first conductive member 31 and the second conductive member 32 respectively. The first conductive member 31 and The second conductive members 32 are connected to the connecting portion 20 through the conductive connecting members 34 .
  • the conductive part 30 also includes a third conductive member 33.
  • the third conductive member 33 is located between the first conductive member 31 and the second conductive member 32. The end of the third conductive member 33 is connected to at the connection part 20.
  • the third conductive member 33 is located on the symmetry plane of the first conductive member 31 and the second conductive member 32 .
  • the cross-sections of the first conductive member 31 and the second conductive member 32 are circular.
  • the third conductive member 33 has a circular cross-section.
  • the connecting portion 20 has a rectangular parallelepiped structure.
  • a conductive adhesive is provided between the conductive part 30 and the conductive paint layer 11 for connecting the two.
  • the conductive adhesive is an adhesive that has a certain conductivity after curing or drying. . It can connect a variety of conductive materials together to form an electrical path between the connected materials.
  • the present invention also provides an aircraft, including the above-mentioned anti-lightning strike and anti-static protection device.
  • the conductive paint layer 11 on the surface of the casing 10 can prevent static electricity from interfering with the electrical equipment in the casing 10 , and the conductive portion 30 provided on the conductive paint layer 11 can protect the outside of the casing 10 .
  • the lightning strike is quickly transmitted to the grounding structure on the aircraft through the connecting part 20 to release the lightning.
  • a small part of the lightning can gradually disperse from the conductive paint layer 11 and be conducted to other fuselages of the aircraft to protect the components inside the casing 10 Electrical Equipment.
  • the anti-lightning strike and anti-static protection device can prevent static electricity from interfering with the electrical equipment in the casing through the conductive paint layer on the surface of the casing.
  • the conductive portion provided on the conductive paint layer can connect lightning strikes outside the casing. Part of the lightning is quickly transmitted to the grounding structure on the aircraft to release lightning. A small amount of lightning can gradually disperse from the conductive paint layer and be conducted to other parts of the aircraft to protect the electrical equipment inside the casing. Therefore, it has industrial practicality.

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  • Engineering & Computer Science (AREA)
  • Microelectronics & Electronic Packaging (AREA)
  • Elimination Of Static Electricity (AREA)

Abstract

一种抗雷击及防静电的保护装置及航空器，包括壳体（10）和导电部件，壳体（10）具有首端和尾端，壳体（10）的外表面涂设有导电漆层（11），导电部件包括均为导体且均设于导电漆层（11）上的连接部（20）和导电部（30），连接部（20）位于壳体（10）的首端，连接部（20）用于连接航空器的接地结构，导电部（30）的一端固定连接于连接部（20），导电部（30）的另一端延伸至壳体（10）的尾端；壳体（10）表面的导电漆层（11）能够防止静电干扰壳体（10）内的电气设备，导电漆层（11）上设置的导电部（30）能够将壳体（10）外遭受的雷击通过连接部（20）快速传递至航空器上的接地结构，以释放雷电。

Description

一种抗雷击及防静电的保护装置及航空器 技术领域
本发明涉及无人驾驶航空器技术领域，尤其涉及一种抗雷击及防静电的保护装置及航空器。
 背景技术
随着复合材料的不断研发创新，尤其是碳纤维复合材料，其在航空领域应用的范围越来越广。复合材料的导电性能低，其对静电和雷击的防护远没有传统的金属外壳的航空器高，然而，目前的电动航空器为了减轻重量，其机身外壳均为复合材料，导致航空器容易受到静电或雷击干扰，静电或雷击极易损伤航空器内部的电气设备，影响飞行安全。目前，只能够通过根据天气情况限制飞行或在地面尽可能地释放静电后再飞行来解决上述问题。
 技术问题
有鉴于此，本发明提供了一种抗雷击及防静电的保护装置及航空器，以解决目前航空器在运行时无法防雷击或抗静电的问题。
 技术解决方案
本发明为解决上述技术问题所采用的技术方案如下：
本发明提供了一种抗雷击及防静电的保护装置，包括壳体和导电部件，所述壳体具有首端和尾端；
所述壳体的外表面涂设有导电漆层，所述导电部件包括均为导体的连接部和导电部，所述连接部和导电部均设于所述导电漆层上；所述连接部位于所述壳体的首端，所述连接部用于连接航空器的接地结构，所述导电部的一端固定连接于所述连接部，所述导电部的另一端延伸至所述壳体的尾端。
在某些可选地实施例中，所述导电部包括相互平行设置的第一导电件和第二导电件，所述第一导电件的端部和第二导电件的端部均连接于所述连接部，所述第一导电件和第二导电件分别位于所述壳体的两侧。
在某些可选地实施例中，所述导电部还包括导电连接件，所述导电连接件的中部固定连接于所述连接部，所述导电连接件的两端分别延伸至所述壳体的两侧以分别连接所述第一导电件和第二导电件，所述第一导电件和第二导电件均通过所述导电连接件连接所述连接部。
在某些可选地实施例中，所述导电部还包括第三导电件，所述第三导电件位于所述第一导电件和第二导电件之间，所述第三导电件的端部连接于所述连接部。
在某些可选地实施例中，所述第三导电件位于所述第一导电件和第二导电件的对称面上。
在某些可选地实施例中，所述第一导电件和第二导电件的横截面呈圆形。
在某些可选地实施例中，所述第三导电件的横截面呈圆形。
在某些可选地实施例中，所述连接部为长方体结构。
在某些可选地实施例中，所述导电部和导电漆层之间设有用于将二者相连接的导电胶。
为了解决相同的技术问题，本发明还提供了一种航空器，包括上述的抗雷击及防静电的保护装置。
 有益效果
本发明的抗雷击及防静电的保护装置，其壳体表面的导电漆层能够防止静电干扰壳体内的电气设备，导电漆层上设置的导电部能够将壳体外遭受的雷击通过连接部快速传递至航空器上的接地结构，以释放雷电，少部分雷电可从导电漆层上逐渐散开并传导至航空器的其他机身上，以保护壳体内的电气设备。
 附图说明
下面通过参考附图并结合实例具体地描述本发明，本发明的优点和实现方式将会更加明显，其中附图所示内容仅用于对本发明的解释说明，而不构成对本发明的任何意义上的限制，在附图中：
图1为本发明实施例的抗雷击及防静电的保护装置的结构示意图之一。
图2为本发明实施例的抗雷击及防静电的保护装置的结构示意图之二。
其中，10、壳体；11、导电漆层；20、连接部；30、导电部；31、第一导电件；32、第二导电件；33、第三导电件；34、导电连接件。
 本发明的实施方式
在本发明的描述中，除非另有说明，“多个”的含义是两个或两个以上；术语“上”、“下”、“内”、“外”、“顶部”、“底部”等指示的方位或位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本发明和简化描述，而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本发明的限制。此外，术语“第一”、“第二”等仅用于描述目的，而不能理解为指示或暗示相对重要性。
在本发明的描述中，需要说明的是，除非另有明确的规定和限定，术语“相连”、“连接”应做广义理解，例如，可以是固定连接，也可以是可拆卸连接，或一体地连接；可以是机械连接，也可以是电连接；可以是直接相连，也可以通过中间媒介间接相连。对于本领域的普通技术人员而言，可以根据具体情况理解上述术语在本发明中的具体含义。
为了便于理解本申请，下面将参照相关附图对本申请进行更全面的描述。附图中给出了本申请的较佳实施方式。但是，本申请可以以许多不同的形式来实现，并不限于本文所描述的实施方式。相反地，提供这些实施方式的目的是使对本申请的公开内容理解的更加透彻全面。
除非另有定义，本文所使用的所有的技术和科学术语与属于本申请的技术领域的技术人员通常理解的含义相同。本文中在本申请的说明书中所使用的术语只是为了描述具体的实施方式的目的，不是旨在于限制本申请。
结合图1和图2所示，示意性地显示了本发明的抗雷击及防静电的保护装置。
抗雷击及防静电的保护装置包括壳体10和导电部件，该壳体10用于保护航空器顶部的雷达和/或天线，壳体10可采用塑料或其他现有的复合材料制成，壳体10具有首端和尾端。
壳体10的外表面涂设有导电漆层11，导电漆层11可采用现有的导电漆材料，导电漆是用导电金属粉末添加于特定的树脂原料中以制成能够喷涂的油漆涂料，干燥后形成漆膜后能起到导电的作用，从而屏蔽电磁波干扰的功能。
导电部件包括均为导体的连接部20和导电部30，连接部20和导电部30可选的为钢制材料。连接部20和导电部30均设于导电漆层11上，即连接部20与导电漆层11之间能够导电，导电部30与导电漆层11之间能够导电。连接部20位于壳体10的首端，连接部20用于连接航空器的接地结构，即航空器的顶部设置有一卡接槽，该卡接槽与航空器的接地结构是电连接的，连接部20嵌设于卡接槽内。
导电部30的一端固定连接于连接部20，导电部30的另一端延伸至壳体10的尾端，该结构下的导电部30能够对整个壳体10进行防护，将击中壳体10的雷电传导至连接部20，进而释放到航空器机身的其他部位，以保护壳体10内的电气设备。
具体地，导电部30包括相互平行设置的第一导电件31和第二导电件32，第一导电件31的端部和第二导电件32的端部均连接于连接部20，第一导电件31和第二导电件32分别位于壳体10的两侧，以使导电部30所防护的面积更大。其中，为了将第一导电件31和第二导电件32连接至连接部20，导电部30还包括导电连接件34，导电连接件34沿壳体10的宽度方向延伸，而第一导电件31和第二导电件32沿壳体10的长度方向延伸。导电连接件34的中部固定连接于连接部20，导电连接件34的两端分别延伸至壳体10的两侧以分别连接第一导电件31和第二导电件32，第一导电件31和第二导电件32均通过导电连接件34与连接部20相连接。
为进一步增强导电部30的导电性能，导电部30还包括第三导电件33，第三导电件33位于第一导电件31和第二导电件32之间，第三导电件33的端部连接于连接部20。其中，第三导电件33位于第一导电件31和第二导电件32的对称面上。
在某些可选地实施例中，第一导电件31和第二导电件32的横截面呈圆形。
在某些可选地实施例中，第三导电件33的横截面呈圆形。
在某些可选地实施例中连接部20为长方体结构。
为了将导电部30与导电漆层11相连接，导电部30和导电漆层11之间设有用于将二者相连接的导电胶，导电胶是一种固化或干燥后具有一定导电性的胶粘剂。它可以将多种导电材料连接在一起，使被连接材料间形成电的通路。
为了解决相同的技术问题，本发明还提供了一种航空器，包括如上述的抗雷击及防静电的保护装置。
本发明的抗雷击及防静电的保护装置，其壳体10表面的导电漆层11能够防止静电干扰壳体10内的电气设备，导电漆层11上设置的导电部30能够将壳体10外遭受的雷击通过连接部20快速传递至航空器上的接地结构，以释放雷电，少部分雷电可从导电漆层11上逐渐散开并传导至航空器的其他机身上，以保护壳体10内的电气设备。
以上参照附图说明了本发明的优选实施例，本领域技术人员不脱离本发明的范围和实质，可以有多种变型方案实现本发明。举例而言，作为一个实施例的部分示出或描述的特征可用于另一实施例以得到又一实施例。以上仅为本发明较佳可行的实施例而已，并非因此局限本发明的权利范围，凡运用本发明说明书及附图内容所作的等效变化，均包含于本发明的权利范围之内。
 工业实用性
本发明实施例的抗雷击及防静电的保护装置，通过其壳体表面的导电漆层能够防止静电干扰壳体内的电气设备，导电漆层上设置的导电部能够将壳体外遭受的雷击通过连接部快速传递至航空器上的接地结构，以释放雷电，少部分雷电可从导电漆层上逐渐散开并传导至航空器的其他机身上，以保护壳体内的电气设备。因此，具有工业实用性。

Claims (10)

  1. 一种抗雷击及防静电的保护装置，包括壳体和导电部件，所述壳体具有首端和尾端；
    所述壳体的外表面涂设有导电漆层，所述导电部件包括均为导体的连接部和导电部，所述连接部和导电部均设于所述导电漆层上；所述连接部位于所述壳体的首端，所述连接部用于连接航空器的接地结构，所述导电部的一端固定连接于所述连接部，所述导电部的另一端延伸至所述壳体的尾端。
  2. 根据权利要求1所述的抗雷击及防静电的保护装置，其中，所述导电部包括相互平行设置的第一导电件和第二导电件，所述第一导电件的端部和第二导电件的端部均连接于所述连接部，所述第一导电件和第二导电件分别位于所述壳体的两侧。
  3. 根据权利要求2所述的抗雷击及防静电的保护装置，其中，所述导电部还包括导电连接件，所述导电连接件的中部固定连接于所述连接部，所述导电连接件的两端分别延伸至所述壳体的两侧以分别连接所述第一导电件和第二导电件，所述第一导电件和第二导电件均通过所述导电连接件连接所述连接部。
  4. 根据权利要求2所述的抗雷击及防静电的保护装置，其中，所述导电部还包括第三导电件，所述第三导电件位于所述第一导电件和第二导电件之间，所述第三导电件的端部连接于所述连接部。
  5. 根据权利要求4所述的抗雷击及防静电的保护装置，其中，所述第三导电件位于所述第一导电件和第二导电件的对称面上。
  6. 根据权利要求2所述的抗雷击及防静电的保护装置，其中，所述第一导电件和第二导电件的横截面呈圆形。
  7. 根据权利要求4所述的抗雷击及防静电的保护装置，其中，所述第三导电件的横截面呈圆形。
  8. 根据权利要求7所述的抗雷击及防静电的保护装置，其中，所述连接部为长方体结构。
  9. 根据权利要求1所述的抗雷击及防静电的保护装置，其中，所述导电部和导电漆层之间设有用于将二者相连接的导电胶。
  10. 一种航空器，包括如权利要求1至9任一所述的抗雷击及防静电的保护装置。
PCT/CN2023/111774 2022-08-31 2023-08-08 一种抗雷击及防静电的保护装置及航空器 WO2024046057A1 (zh)

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