An electric aircraft grounding support and an electric aircraft

Abstract

The utility model provides an electric aircraft ground support and electric aircraft relates to aviation ground field, and electric aircraft ground support includes: ground support main part, including a plurality of first support and a plurality of second support, a plurality of first support is arranged at interval in first direction, and each first support includes straight section main body along second direction extension and two bending sections respectively connected in straight section main body both ends, and second direction is perpendicular to first direction, and a plurality of second support is arranged at interval in second direction, and each second support extends along first direction and is connected with a plurality of first support, a plurality of fixed support is installed on ground support main part, is used for with the fuselage structure connection of electric aircraft. The electric aircraft ground support has simple structure, and the characteristics such as convenient installation and removal, maintenance is convenient, is installed on the fuselage structure of electric aircraft, can increase the ground area of electric aircraft, reduce ground resistance, and ensure the continuity and stability of ground loop.

Description

Technical Field

[0001] This application relates to the field of aviation grounding technology, specifically to a grounding bracket for an electric aircraft and an electric aircraft. Background Technology

[0002] Traditional aircraft fuselages are made of metal materials such as aluminum alloys, which can naturally form a grounding loop through the metal fuselage structure. However, electric aircraft such as eVTOL (Electric Vertical Takeoff and Landing) use a large amount of non-metallic materials such as carbon fiber composites and glass fiber composites in order to reduce the weight of the fuselage while ensuring structural performance. The conductive metal area on the fuselage that can be used for grounding is very limited, resulting in problems such as insufficient grounding area, excessive grounding resistance, and discontinuous grounding loop. Therefore, electric aircraft need to be designed with an independent grounding network to ensure flight safety and normal equipment operation. Utility Model Content

[0003] In view of the above, the purpose of this application is to provide a grounding bracket for an electric aircraft and an electric aircraft to solve at least one of the above technical problems.

[0004] In a first aspect, this application provides a grounding bracket for an electric aircraft, comprising: a grounding bracket body, including a plurality of first brackets and a plurality of second brackets, wherein the plurality of first brackets are spaced apart in a first direction, each first bracket including a straight section body extending along a second direction and two bent sections respectively connected to both ends of the straight section body, the second direction being perpendicular to the first direction, the plurality of second brackets being spaced apart in the second direction, each second bracket extending along the first direction and connected to the plurality of first brackets; and a plurality of fixed brackets, mounted on the grounding bracket body, for connecting to the fuselage structure of the electric aircraft.

[0005] In conjunction with the first aspect, in some optional embodiments, each bending segment includes a first bending portion and a second bending portion, the first bending portion extending along a third direction and having one end connected to the straight segment body, the third direction being perpendicular to the first and second directions, the second bending portion extending along the second direction and having one end connected to the other end of the first bending portion; the first bending portions of the two bending segments extend in the same direction, and the second bending portions of the two bending segments extend in opposite directions.

[0006] In conjunction with the first aspect, in some alternative embodiments, each first bracket has a plurality of first connection holes distributed along the extension direction, the plurality of first connection holes being used to connect fasteners to the second bracket, the fixed bracket, and the grounding wire of the equipment on the electric aircraft.

[0007] In conjunction with the first aspect, in some alternative embodiments, the plurality of first connecting holes include at least one of circular through holes and oblong holes.

[0008] In conjunction with the first aspect, in some alternative embodiments, each second bracket has a plurality of second connection holes distributed along the extension direction, the plurality of second connection holes being used to engage fasteners for connection with the grounding wires of the first bracket and the equipment on the electric aircraft.

[0009] In conjunction with the first aspect, in some alternative embodiments, the plurality of second connecting holes include at least one of circular through holes and oblong holes.

[0010] In conjunction with the first aspect, in some alternative embodiments, each fixed bracket includes a bracket connecting part and a fuselage connecting part, the bracket connecting part and the fuselage connecting part being vertically connected to form an L-shaped structure, the bracket connecting part being provided with a third connecting hole for connecting with the grounding bracket body with a fastener, and the fuselage connecting part being provided with a fourth connecting hole for connecting with the fuselage structure of the electric aircraft with a fastener.

[0011] In conjunction with the first aspect, in some optional embodiments, the thickness of the first bracket, the second bracket, and the fixed bracket is 1.5mm-2.5mm.

[0012] In conjunction with the first aspect, in some alternative embodiments, the first bracket, the second bracket, and the fixed bracket are all made of aluminum alloy.

[0013] Secondly, this application provides an electric aircraft, including the electric aircraft grounding bracket in any of the embodiments of the first aspect described above.

[0014] Based on the above technical solutions, the electric aircraft grounding bracket and electric aircraft provided in this application have a stable frame structure formed by multiple first brackets and multiple second brackets. The grounding bracket is installed on the fuselage structure of the electric aircraft by a fixed bracket, which can increase the grounding area of ​​the electric aircraft, reduce the grounding resistance, and ensure the continuity and stability of the grounding circuit. The number of first brackets, second brackets, and fixed brackets can be adjusted according to actual needs, which has good flexibility and adaptability in installation and use. The design of the bent sections at both ends of the first bracket can raise the position of the second bracket connected to the bent section, which is convenient for operators to perform wiring operations on the electric aircraft. The electric aircraft grounding bracket has the characteristics of simple structure, convenient installation and disassembly, and convenient maintenance. Attached Figure Description

[0015] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a schematic diagram of the structure of a grounding bracket for an electric aircraft provided in an embodiment of this application.

[0017] Figure 2 This is an exploded structural diagram of a grounding bracket for an electric aircraft provided in an embodiment of this application.

[0018] Figure 3 This is a schematic diagram of the connection between a grounding bracket and a grounding wire for an electric aircraft, provided as an embodiment of this application.

[0019] Reference numerals: 1. Grounding wire; 100. Grounding bracket for electric aircraft; 10. Grounding bracket body 10; 11. First bracket 11; 111. Straight section body 111; 112. Bending section 112; 1121. First bending part 1121; 1122. Second bending part 1122; 113. First connecting hole 113; 12. Second bracket 12; 121. Second connecting hole 121; 20. Fixed bracket 20; 21. Bracket connecting part 21; 211. Third connecting hole 211; 22. Fuselage connecting part 22; 221. Fourth connecting hole 221. Detailed Implementation

[0020] The specific embodiments of this application will now be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are merely a part of the embodiments of this application, and not all of them. Based on the description of this application, all other embodiments obtained by those skilled in the art without inventive effort are within the scope of protection of this application.

[0021] In the description of this application, unless otherwise expressly specified and limited, the terms "connection," "setup," "installation," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0022] The terms “upper,” “lower,” “left,” “right,” “front,” “back,” “center,” “top,” “bottom,” “inner,” “outer,” “vertical,” “horizontal,” “clockwise,” “counterclockwise,” “axial,” “radial,” and “circumferential” indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product is in use. They are used only for the convenience of description and simplification, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0023] The terms “first,” “second,” “third,” etc., are used only to distinguish elements with similar properties, and do not indicate or imply relative importance or a specific order, unless otherwise explicitly stated or limited.

[0024] The terms “comprising,” “including,” “having,” or any other variations thereof are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitation, an element defined by the phrase “comprising one…” does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element.

[0025] The term "multiple" means two or more (including two).

[0026] The term "and / or" describes the relationship between related objects, indicating that there can be three relationships. For example, A and / or B can represent three cases: A exists alone, A and B exist simultaneously, and B exists alone.

[0027] The terms "an embodiment," "as an example," and "in one implementation" refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which may be included in at least one embodiment or example of this application. These illustrative expressions do not necessarily refer to the same embodiment, nor are they independent or alternative embodiments mutually exclusive with other embodiments. Where there is no conflict, the embodiments and features described in these embodiments can be combined in a suitable manner.

[0028] Figure 1 This is a schematic diagram of the structure of a grounding bracket 100 for an electric aircraft provided in an embodiment of this application. Figure 2 This is an exploded structural diagram of an electric aircraft grounding bracket 100 provided in an embodiment of this application, as shown below. Figure 1 and Figure 2As shown in the figure, this application embodiment provides an electric aircraft grounding bracket 100, including a grounding bracket body 10 and a plurality of fixed brackets 20.

[0029] The grounding support body 10 includes multiple first supports 11 and multiple second supports 12.

[0030] Multiple first supports 11 are arranged at intervals in a first direction. Each first support 11 includes a straight main body 111 and two bent sections 112 respectively connected to both ends of the straight main body 111. The straight main body 111 extends along a second direction perpendicular to the first direction. Each bent section 112 includes a first bent portion 1121 and a second bent portion 1122. The first bent portion 1121 extends along a third direction and one end of it is connected to the straight main body 111. The third direction is perpendicular to the first and second directions. The second bent portion 1122 extends along the second direction and one end of it is connected to the other end of the first bent portion 1121. The first bent portions 1121 of the two bent sections 112 extend in the same direction, and the second bent portions 1122 of the two bent sections 112 extend in opposite directions.

[0031] Each first bracket 11 has a plurality of first connecting holes 113 distributed along its extending direction. The plurality of first connecting holes 113 are used to mate fasteners with the second bracket 12, the fixed bracket 20, and the grounding wire 1 of the equipment on the electric aircraft (see...). Figure 3 The multiple first connection holes 113 include at least one of circular through holes and oblong holes, wherein the oblong holes facilitate position adjustment during connection.

[0032] As an example, in each first bracket 11, the straight section body 111 has multiple circular through holes and multiple waist-shaped holes distributed along the extension direction, the first bending portion 1121 of the two bending sections 112 has multiple circular through holes distributed along the extension direction, and the second bending portion 1122 of the two bending sections 112 is provided with a waist-shaped hole.

[0033] The thickness of the first bracket 11 is determined based on the current carrying capacity of the grounding network design of the electric aircraft, and can be 1.5mm-2.5mm, preferably 1.5mm, 2mm, or 2.5mm. The diameter of the circular through-hole of the first bracket 11 is determined based on the current released by the equipment on the electric aircraft, and can be 3mm-6mm, preferably 3mm, 4mm, 5mm, or 6mm. The width of the oblong hole of the first bracket 11 can be consistent with the diameter of the circular through-hole.

[0034] The second bracket 12 has a long, straight structure. Multiple second brackets 12 are arranged at intervals in the second direction. Each second bracket 12 extends along the first direction and is detachably connected to multiple first brackets 11. Each second bracket 12 has multiple second connection holes 121 distributed along its extending direction. The multiple second connection holes 121 are used to connect with fasteners to the first brackets 11 and the grounding wire 1 of the equipment on the electric aircraft. The multiple second connection holes 121 include at least one of circular through holes and oblong holes, wherein the oblong holes facilitate position adjustment during connection.

[0035] As an example, each second bracket 12 has multiple circular through holes distributed along its extension direction. These circular through holes are used to connect with the grounding wire 1 of the equipment on the electric aircraft using fasteners. Each second bracket 12 has a waist-shaped hole at both ends, which is used to connect with the first bracket 11 using fasteners. There are two first brackets 11 and five second brackets 12. The two ends of three second brackets 12 are connected to the straight sections 111 of two first brackets 11 respectively by fasteners, and the two ends of the other two second brackets 12 are connected to the second bent portions 1122 of two first brackets 11 respectively by fasteners.

[0036] The thickness of the second bracket 12 is determined based on the current carrying capacity of the electric aircraft's grounding network design. The thickness of the second bracket 12 can be 1.5mm-2.5mm, preferably 1.5mm, 2mm, or 2.5mm, and can be consistent with the thickness of the first bracket 11. The diameter of the circular through-hole in the second bracket 12 is determined based on the current released by the equipment on the electric aircraft. The diameter can be 3mm-6mm, preferably 3mm, 4mm, 5mm, or 6mm, and can be consistent with the diameter of the circular through-hole in the first bracket 11. The width of the oblong hole in the second bracket 12 can be consistent with the diameter of the circular through-hole.

[0037] Multiple fixed brackets 20 are distributed and installed on the grounding bracket body 10. Each fixed bracket 20 is detachably connected to the grounding bracket body 10 and is used to connect with the fuselage structure with fasteners. Each fixed bracket 20 includes a bracket connecting part 21 and a fuselage connecting part 22. The bracket connecting part 21 and the fuselage connecting part 22 are vertically connected to form an L-shaped structure. The bracket connecting part 21 is provided with one or more third connecting holes 211 for connecting with the grounding bracket body 10 with fasteners. The fuselage connecting part 22 is provided with one or more fourth connecting holes 221 for connecting with the fuselage structure with fasteners.

[0038] As an example, in each fixed bracket 20, the bracket connecting part 21 is provided with a third connecting hole 211, which is a threaded hole, and the body connecting part 22 is provided with two fourth connecting holes 221, which are both circular through holes; there are four fixed brackets 20, and there are two first brackets 11, with two fixed brackets 20 installed on each first bracket 11.

[0039] The thickness of the fixing bracket 20 is mainly determined based on mechanical strength requirements, while also taking into account electrical conductivity requirements. The thickness of the fixing bracket 20 can be 1.5mm-2.5mm, preferably 1.5mm, 2mm, or 2.5mm, and can be consistent with the thickness of the first bracket 11.

[0040] The materials of the first bracket 11, the second bracket 12, and the fixed bracket 20 should be metal materials with advantages such as light weight, high strength, and good electrical and thermal conductivity. For example, the first bracket 11, the second bracket 12, and the fixed bracket 20 are all made of aluminum alloy. More specifically, the first bracket 11, the second bracket 12, and the fixed bracket 20 are all made of 6061 aluminum alloy.

[0041] The electric aircraft grounding bracket 100 is installed on the fuselage structure below the fuselage base plate during use. As an example, the installation process of the electric aircraft grounding bracket 100 involves first fixing the required number of fixed brackets 20 to the fuselage structure below the fuselage base plate using fasteners. Then, the first bracket 11 and the second bracket 12 are assembled into the grounding bracket body 10 using fasteners according to the actual required quantity. Finally, the grounding bracket body 10 is connected to each fixed bracket 20 using fasteners, thus completing the installation. This installation method allows for flexible and convenient adjustment of the position of the grounding bracket body 10, improving installation efficiency. Alternatively, the first bracket 11, the second bracket 12, and the fixed brackets 20 can be assembled into the electric aircraft grounding bracket 100 before being connected to the fuselage structure.

[0042] The first bracket 11 and the second bracket 12 can be adjusted in position, distance, and engagement with other brackets via oblong holes during assembly, facilitating the assembly process. The number of the first bracket 11, second bracket 12, and fixed bracket 20 shown in the diagram is illustrative and can be adjusted according to actual needs. The number of grounding bracket bodies 10 can also be adjusted as needed. For example, when more than two grounding bracket bodies 10 need to be installed on the fuselage structure, these grounding bracket bodies 10 can be assembled in the first and / or second directions and then connected to the fuselage structure via the fixed bracket 20.

[0043] In addition, it should be noted that the two bent sections 112 of the first bracket 11 have a lifting effect. Specifically, the straight section body 111 of each first bracket 11 is parallel to the base plate of the machine body, and the first bent part 1121 of the two bent sections 112 bends relative to the straight section body 111 toward the base plate of the machine body, so that the second bracket 12 installed on the second bent part 1122 of the two bent sections 112 achieves the lifting effect, which facilitates the operator to perform wiring operations.

[0044] When using, such as Figure 3 As shown, the electric aircraft grounding bracket 100 serves as the grounding connection point on the electric aircraft. The grounding wire 1 of the equipment on the electric aircraft is connected to the first bracket 11 and the second bracket 12. The electric aircraft grounding bracket 100 realizes the grounding protection function for the equipment on the electric aircraft, enabling the electric aircraft, which uses a large number of composite materials, to achieve good and reliable grounding.

[0045] This application embodiment also provides an electric aircraft, which includes the above-described electric aircraft grounding bracket 100.

[0046] In summary, the electric aircraft grounding bracket and electric aircraft provided in this application embodiment form a stable frame structure by connecting multiple first brackets and multiple second brackets. The grounding bracket is then mounted on the fuselage structure of the electric aircraft via fixed brackets. This increases the grounding area of ​​the electric aircraft, reduces grounding resistance, and ensures the continuity and stability of the grounding circuit. The number of first brackets, second brackets, and fixed brackets can be adjusted according to actual needs, providing good flexibility and adaptability in installation and use. The bent sections at both ends of the first brackets raise the position of the second brackets connected to the bent sections, facilitating wiring operations on the electric aircraft. The electric aircraft grounding bracket features a simple structure, convenient installation and disassembly, and easy maintenance.

[0047] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any person skilled in the art can easily conceive of various variations or substitutions within the technical scope disclosed in this application, and these should all be included within the scope of protection of this application.

Claims

1. A grounding bracket for an electric aircraft, characterized in that, include: The grounding support body includes a plurality of first supports and a plurality of second supports. The plurality of first supports are arranged at intervals in a first direction. Each first support includes a straight section body extending along a second direction and two bent sections respectively connected to both ends of the straight section body. The second direction is perpendicular to the first direction. The plurality of second supports are arranged at intervals in the second direction. Each second support extends along the first direction and is connected to the plurality of first supports. as well as Multiple fixed brackets are installed on the grounding bracket body for connection to the fuselage structure of the electric aircraft.

2. The electric aircraft grounding bracket according to claim 1, characterized in that, Each of the bending segments includes a first bending portion and a second bending portion, the first bending portion extending along a third direction and having one end connected to the straight segment body, the third direction being perpendicular to the first direction and the second direction, and the second bending portion extending along the second direction and having one end connected to the other end of the first bending portion; The first bends of the two bends extend in the same direction, and the second bends of the two bends extend in opposite directions.

3. The electric aircraft grounding bracket according to claim 1, characterized in that, Each of the first brackets has a plurality of first connection holes distributed along the extending direction. The plurality of first connection holes are used to connect with fasteners to the second bracket, the fixed bracket, and the grounding wire of the equipment on the electric aircraft.

4. The electric aircraft grounding bracket according to claim 3, characterized in that, The plurality of first connecting holes include at least one of circular through holes and oblong holes.

5. The electric aircraft grounding bracket according to claim 1, characterized in that, Each of the second brackets has a plurality of second connection holes distributed along the extending direction. The plurality of second connection holes are used to connect fasteners to the grounding wires of the first bracket and the equipment on the electric aircraft.

6. The electric aircraft grounding bracket according to claim 5, characterized in that, The plurality of second connecting holes include at least one of circular through holes and oblong holes.

7. The electric aircraft grounding bracket according to claim 1, characterized in that, Each of the fixed brackets includes a bracket connecting part and a fuselage connecting part, the bracket connecting part and the fuselage connecting part are vertically connected to form an L-shaped structure, the bracket connecting part is provided with a third connecting hole, the third connecting hole is used to cooperate with fasteners to connect with the grounding bracket body, and the fuselage connecting part is provided with a fourth connecting hole, the fourth connecting hole is used to cooperate with fasteners to connect with the fuselage structure of the electric aircraft.

8. The electric aircraft grounding bracket according to claim 1, characterized in that, The thickness of the first bracket, the second bracket, and the fixed bracket is 1.5mm-2.5mm.

9. The electric aircraft grounding bracket according to claim 1, characterized in that, The first bracket, the second bracket, and the fixed bracket are all made of aluminum alloy.

10. An electric aircraft, characterized in that, Including the electric aircraft grounding bracket as described in any one of claims 1-9.

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