CN218104067U

CN218104067U - Lightning-stroke-resistant and anti-static protection device and aircraft

Info

Publication number: CN218104067U
Application number: CN202222299903.7U
Authority: CN
Inventors: 胡华智; 肖启伟
Original assignee: Ehang Intelligent Equipment Guangzhou Co Ltd
Current assignee: Ehang Intelligent Equipment Guangzhou Co Ltd
Priority date: 2022-08-31
Filing date: 2022-08-31
Publication date: 2022-12-20
Anticipated expiration: 2032-08-31
Also published as: WO2024046057A1

Abstract

The utility model provides an anti-lightning and anti-static protection device, including casing and conductive part, the casing has head end and tail end, the surface of casing is scribbled and is equipped with the conductive paint layer, the conductive part includes connecting portion and the conductive part that are the conductor, connecting portion and conductive part all locate on the conductive paint layer, connecting portion are located the head end of casing, connecting portion are used for connecting the ground structure of airborne vehicle, the one end fixed connection of conductive part is in connecting portion, the other end of conductive part extends to the tail end of casing; the electrically conductive lacquer layer on casing surface can prevent the electrical equipment in the electrostatic interference casing, and the electrically conductive part that sets up on the electrically conductive lacquer layer can pass through the quick ground structure that transmits to the aircraft on of connecting portion with the thunderbolt that suffers outside the casing to the lightning release.

Description

Lightning stroke resistance and anti-static protection device and aircraft

Technical Field

The utility model relates to an unmanned airborne vehicle technical field especially relates to an anti thunder hits and prevents protection device and airborne vehicle of static.

Background

With the continuous research and development and innovation of composite materials, particularly carbon fiber composite materials, the application range of the carbon fiber composite materials in the field of aviation is wider and wider. The composite material has low conductive performance, and the protection of the composite material against static electricity and lightning stroke is far higher than that of the conventional aircraft with a metal shell, however, in order to reduce the weight of the conventional electric aircraft, the aircraft body shell is made of the composite material, so that the aircraft is easily interfered by the static electricity or the lightning stroke, and the static electricity or the lightning stroke easily damages electrical equipment in the aircraft, so that the flight safety is influenced. At present, the above problems can be solved only by restricting the flight according to weather conditions or flying after discharging static electricity as much as possible on the ground.

SUMMERY OF THE UTILITY MODEL

The utility model provides an anti thunderbolt and prevent electrostatic protection device and airborne vehicle to solve present airborne vehicle can't prevent thunderbolt or antistatic problem when the operation.

Based on this, the utility model provides an anti-lightning and prevent protection device of static, including casing and conductive parts, the casing has head end and tail end;

the outer surface of the shell is coated with a conductive paint layer, the conductive part comprises a connecting part and a conductive part which are both conductors, and the connecting part and the conductive part are both arranged on the conductive paint layer; the connecting portion is located at the head end of the shell and used for being connected with a grounding structure of an aircraft, one end of the conductive portion is fixedly connected with the connecting portion, and the other end of the conductive portion extends to the tail end of the shell.

In some optional embodiments, the conductive part includes a first conductive member and a second conductive member arranged in parallel, an end of the first conductive member and an end of the second conductive member are both connected to the connection part, and the first conductive member and the second conductive member are respectively located on two sides of the housing.

In some optional embodiments, the conductive part further includes a conductive connecting part, a middle part of the conductive connecting part is fixedly connected to the connecting part, two ends of the conductive connecting part respectively extend to two sides of the housing to respectively connect the first conductive piece and the second conductive piece, and the first conductive piece and the second conductive piece are both connected to the connecting part through the conductive connecting part.

In some optional embodiments, the conductive part further comprises 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 is connected to the connecting part.

In certain alternative embodiments, the third conductive member is positioned on a plane of symmetry of the first and second conductive members.

In some optional embodiments, the first and second conductive members have a circular cross-section.

In some optional embodiments, the cross-section of the third conductive member is circular.

In certain optional embodiments, the connecting portion has a rectangular parallelepiped structure.

In some optional embodiments, a conductive adhesive for connecting the conductive part and the conductive paint layer is arranged between the conductive part and the conductive paint layer.

In order to solve the same technical problem, the utility model also provides an aircraft, including foretell lightning protection and prevent electrostatic protection device.

The utility model discloses an anti thunderbolt reaches protection device who prevents static, the electric equipment in its housing surface's conductive paint layer can prevent the static interference casing, and the conductive part that sets up on the conductive paint layer can pass through the lightning stroke that the casing suffered outside to the grounding structure on the aircraft through connecting portion fast transfer to the release thunder and lightning, and small part of thunder and lightning can be followed on the conductive paint layer and dispersed gradually and conduct to other fuselage of aircraft on, with the electric equipment in the protective housing.

Drawings

The advantages and the manner of realisation of the invention will become more apparent hereinafter by describing in detail, by way of example, with reference to the accompanying drawings, wherein the content shown in the drawings is only intended for the purpose of illustrating the invention, and does not constitute any significant limitation thereof, in which:

fig. 1 is a schematic structural diagram of a protection device for lightning protection and electrostatic protection according to an embodiment of the present invention;

fig. 2 is a second schematic structural diagram of the protection device for lightning protection and electrostatic protection according to the embodiment of the present invention.

10, a shell; 11. a conductive paint layer; 20. a connecting portion; 30. a conductive portion; 31. a first conductive member; 32. a second conductive member; 33. a third conductive member; 34. a conductive connection member.

Detailed Description

In the description of the present invention, "a plurality" means two or more unless otherwise specified; the terms "upper", "lower", "inner", "outer", "top", "bottom", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience in describing the present invention and simplifying the description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "connected" and "connected" should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.

To facilitate an understanding of the present application, the present application will now be described more fully with reference to the accompanying drawings. Preferred embodiments of the present application are given in the accompanying drawings. This application may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete.

Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein in the description of the present application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application.

Referring to fig. 1 and 2, the protection device for lightning strike resistance and static electricity resistance of the present invention is schematically shown.

A lightning strike and static protection device comprises a housing 10 and electrically conductive components, the housing 10 being for protecting a radar and/or antenna on the roof of an aircraft, the housing 10 being formed from plastics or other known composite material, the housing 10 having a head end and a tail end.

The outer surface of the shell 10 is coated with a conductive paint layer 11, the conductive paint layer 11 can be made of the existing conductive paint material, the conductive paint is a paint capable of being sprayed by adding conductive metal powder into a specific resin raw material, and the paint film formed after drying can play a role of conductivity, so that the function of shielding electromagnetic wave interference is achieved.

The conductive member includes a connecting portion 20 and a conductive portion 30, both of which are conductors, and the connecting portion 20 and the conductive portion 30 are optionally made of steel. The connecting portion 20 and the conductive portion 30 are both disposed on the conductive paint layer 11, that is, the connecting portion 20 and the conductive paint layer 11 can conduct electricity, and the conductive portion 30 and the conductive paint layer 11 can conduct electricity. The connecting portion 20 is located at the head end of the housing 10, the connecting portion 20 is used for connecting a grounding structure of the aircraft, that is, the top of the aircraft is provided with a clamping groove, the clamping groove is electrically connected with the grounding structure of the aircraft, and the connecting portion 20 is embedded in the clamping groove.

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 tail end of the shell 10, so that the conductive part 30 under the structure can protect the whole shell 10, transmit the thunder hitting the shell 10 to the connecting part 20, and further release the thunder hitting other parts of the aircraft fuselage to protect the electrical equipment in the shell 10.

Specifically, the conductive part 30 includes a first conductive member 31 and a second conductive member 32 that are arranged parallel to each other, an end of the first conductive member 31 and an end of the second conductive member 32 are both connected to the connection part 20, and the first conductive member 31 and the second conductive member 32 are respectively located on both sides of the casing 10, so that the area protected by the conductive part 30 is larger. Wherein, in order to connect the first and second

conductive members

31 and 32 to the connection part 20, the conductive part 30 further includes a conductive connection member 34, the conductive connection member 34 extending in a width direction of the case 10, and the first and second

conductive members

31 and 32 extending in a length direction of the case 10. The middle portion of the conductive connecting member 34 is fixedly connected to the connecting portion 20, both ends of the conductive connecting member 34 extend to both sides of the housing 10 to connect the first conductive member 31 and the second conductive member 32, respectively, and both the first conductive member 31 and the second conductive member 32 are connected to the connecting portion 20 through the conductive connecting member 34.

To further enhance the conductive performance of the conductive portion 30, the conductive portion 30 further 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, and an end of the third conductive member 33 is connected to the connecting portion 20. Wherein the third conductive member 33 is located on a symmetrical plane of the first conductive member 31 and the second conductive member 32.

In some alternative embodiments, the cross-sections of the first conductive member 31 and the second conductive member 32 are circular.

In some alternative embodiments, the cross-section of the third conductive member 33 is circular.

In certain alternative embodiments the connecting portion 20 is a rectangular parallelepiped structure.

In order to connect the conductive part 30 and the conductive paint layer 11, a conductive adhesive is disposed between the conductive part 30 and the conductive paint layer 11 for connecting the conductive part and the conductive paint layer, and the conductive adhesive is an adhesive which has certain conductivity after being cured or dried. It can connect multiple conductive materials together to form an electrical path between the connected materials.

In order to solve the same technical problem, the utility model also provides an aircraft, include the protection device who reaches antistatic as above-mentioned lightning protection.

The utility model discloses an anti thunder hits and prevent protection device of static, the electrical equipment in the electrostatic interference casing 10 can be prevented to the conducting paint layer 11 on its casing 10 surface, the conducting part 30 that sets up on the conducting paint layer 11 can pass through the lightning stroke that the casing 10 suffered outside to the ground structure on the aircraft through connecting portion 20 fast transfer, in order to release the thunder and lightning, few part thunder and lightning can be followed on the conducting paint layer 11 and dispersed gradually and conduct to other fuselage of aircraft, in order to protect the electrical equipment in the casing 10.

The preferred embodiments of the present invention have been described with reference to the accompanying drawings, and those skilled in the art can implement the present invention in various modifications without departing from the scope and spirit of the present invention. For instance, features illustrated or described as part of one embodiment, can be used with another embodiment to yield a still further embodiment. The above description is only a preferred and practical embodiment of the present invention, and not intended to limit the scope of the present invention, and all equivalent changes made by using the contents of the specification and the drawings of the present invention are included in the scope of the present invention.

Claims

1. A lightning-resistant and antistatic protection device is characterized by comprising a shell and a conductive component, wherein the shell is provided with a head end and a tail end;

2. The lightning and static electricity resistant protection device of claim 1, wherein said conductive part comprises a first conductive member and a second conductive member disposed in parallel with each other, an end of said first conductive member and an end of said second conductive member are both connected to said connecting part, and said first conductive member and said second conductive member are respectively disposed at two sides of said housing.

3. The lightning and static electricity protection device of claim 2, wherein the conductive part further comprises a conductive connecting member, a middle portion of the conductive connecting member is fixedly connected to the connecting part, two ends of the conductive connecting member extend to two sides of the housing respectively to connect the first conductive member and the second conductive member, and the first conductive member and the second conductive member are connected to the connecting part through the conductive connecting member.

4. The lightning and static protection device of claim 2, wherein the conductive part further comprises 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 is connected to the connecting part.

5. The device of claim 4, wherein the third conductive member is located on a plane of symmetry of the first and second conductive members.

6. The lightning strike and static electricity protection device of claim 2, wherein the first conductive member and the second conductive member have a circular cross-section.

7. The device of claim 4, wherein the cross-section of the third conductive member is circular.

8. The device of claim 7, wherein the connecting portion is a rectangular parallelepiped.

9. The lightning strike and static electricity prevention protection device according to claim 1, wherein a conductive adhesive is provided between the conductive portion and the conductive paint layer for connecting the conductive portion and the conductive paint layer.

10. An aircraft comprising a lightning protection and antistatic protection device according to any one of claims 1 to 9.