Low voltage power distribution for electric aircraft and electric aircraft

Abstract

The application provides a low-voltage power distribution device for an electric aircraft and an electric aircraft. The low-voltage power distribution device comprises a power distribution device housing and a power distribution structure, and the power distribution device housing and the power distribution structure form a plurality of power distribution modules. The power distribution device housing comprises a main body, a plurality of cover plates and a plurality of electrical connectors, the plurality of cover plates are used for covering the plurality of power distribution modules respectively at least partially, and each cover plate is movably connected with the main body of the power distribution device housing via a movable connection part. The power distribution structure comprises a plurality of circuit breaker groups, bus bars and circuit elements, each circuit breaker group comprises a plurality of circuit breakers, and each cover plate is connected with at least one circuit breaker group, so that the circuit breaker group can move with the cover plate connected with the circuit breaker group. The bus bars comprise first bus bars and second bus bars, the plurality of circuit breakers in one circuit breaker group are connected with one first bus bar, the second bus bars are installed to the inside of the power distribution device housing, and the second bus bars are connected with the electrical connectors and the circuit elements.

Description

Technical Field

[0001] This application relates to the field of electric aircraft technology, and particularly to a low-voltage power distribution device for electric aircraft and an electric aircraft. Background Technology

[0002] With the development of the low-altitude economy, electric vertical takeoff and landing (eVTOL) aircraft are gradually being put into commercial operation, and their application scenarios include, but are not limited to, low-altitude sightseeing, urban passenger transport, cargo transport, emergency medical services, and rescue services.

[0003] Unlike traditional aircraft, eVTOL aircraft heavily rely on electricity as their sole or primary energy source. The reliability, lightweight design, maintainability, and safety of their power distribution system directly determine the overall performance and operational efficiency of the aircraft. However, current low-voltage power distribution devices used in electric aircraft suffer from poor versatility and maintainability, and lack modular design. Therefore, there is an urgent need to improve low-voltage power distribution devices to address at least one of the aforementioned problems and adapt to the power distribution requirements of electric aircraft. Utility Model Content

[0004] This application is made in view of the aforementioned state of the prior art. The purpose of this application is to provide a low-voltage power distribution device for electric aircraft that is versatile and easy to maintain.

[0005] This application also provides an electric aircraft that includes the aforementioned low-voltage power distribution device.

[0006] This application provides a low-voltage power distribution device for an electric aircraft, comprising a power distribution device housing and a power distribution structure, wherein the power distribution device housing and the power distribution structure form a plurality of power distribution modules. The power distribution device housing includes a main body, a plurality of cover plates, and a plurality of electrical connectors. The plurality of cover plates are used to at least partially cover the plurality of power distribution modules, and each of the cover plates is movably connected to the main body of the power distribution device housing via a movable connecting portion. The electrical connectors are used to connect to the power supply or electrical equipment of the electric aircraft.

[0007] The power distribution structure includes multiple circuit breaker groups, busbars, and circuit elements. Each circuit breaker group includes multiple circuit breakers, and each cover plate is connected to at least one circuit breaker group, allowing the circuit breaker group to move with the cover plate to which it is connected. The busbars include a first busbar and a second busbar. Multiple circuit breakers in one circuit breaker group are each connected to a first busbar. The second busbar is installed inside the power distribution device housing and is connected to the electrical connectors and the circuit elements. The first busbar and the second busbar are flexibly connected via a conductive structure.

[0008] In at least one possible implementation, the circuit breaker has a positioning part, and the cover plate is provided with a plurality of circuit breaker positioning holes, the positioning part corresponding to each of the circuit breaker positioning holes, and the positioning part extending at least partially into the circuit breaker positioning holes to restrict the posture of the circuit breaker.

[0009] In at least one possible implementation, the circuit breaker has an operating section and an electrical connection section. The operating section is located on the outer side of the cover plate for easy operation by personnel. The electrical connection section is located on the inner side of the cover plate and connects to the first busbar and various electrical devices for connecting the electric aircraft.

[0010] In at least one possible implementation, the plurality of circuit breakers in one of the power distribution modules are set at the same angle and in the same direction.

[0011] In at least one possible implementation, the circuit breaker positioning holes on adjacent cover plates are arranged in different positions and / or in different ways.

[0012] In at least one possible implementation, the power distribution structure further includes at least one fuse and at least one contactor, the fuse and the contactor being installed within the housing of the power distribution device and electrically connected to the second busbar.

[0013] In at least one possible implementation, the outer surface of the power distribution device housing is provided with an insulating oxide layer, and the power distribution device housing is provided with a fixed support for connecting an electric aircraft. The surface of the fixed support is not provided with the insulating oxide layer so as to form an electrical connection with the electric aircraft.

[0014] In at least one possible implementation, the power distribution unit housing includes a plurality of cover locks for locking the plurality of covers respectively.

[0015] In at least one possible implementation, the bottom of the power distribution unit housing is formed with one or more bottom cavities for accommodating the circuit breaker and / or a portion of the first busbar.

[0016] This application also provides an electric aircraft that includes the aforementioned low-voltage power distribution device for electric aircraft.

[0017] The low-voltage power distribution device for electric aircraft provided in this application adopts a modular design, connecting the circuit breaker to the housing cover. When the housing cover is opened, the circuit breaker can be directly inspected, maintained, or replaced, giving the low-voltage power distribution device good versatility and ease of maintenance. Furthermore, the maintainability of the power system of the electric aircraft using the aforementioned low-voltage power distribution device can also be improved. Attached Figure Description

[0018] Figure 1 This is a first structural schematic diagram of a power distribution device housing according to one embodiment of this application.

[0019] Figure 2 This is a schematic diagram of the second structure of a power distribution device housing according to one embodiment of this application.

[0020] Figure 3 This is a schematic diagram of the circuit breaker and busbar according to one embodiment of this application.

[0021] Figure 4 This is a schematic diagram of the cooperation between a circuit breaker and a circuit breaker positioning hole according to one embodiment of this application.

[0022] Figure 5 This is another schematic diagram of the circuit breaker and circuit breaker positioning hole according to one embodiment of this application.

[0023] Figure 6 This is a schematic diagram of the first internal structure of a low-voltage power distribution device according to one embodiment of this application.

[0024] Figure 7 This is a schematic diagram of the second internal structure of a low-voltage power distribution device according to one embodiment of this application.

[0025] Explanation of reference numerals in the attached figures

[0026] 100 Power distribution unit housing

[0027] 110 Shell cover plate

[0028] 111 First cover plate

[0029] 112 Second cover plate

[0030] 113 Activity Connection Department

[0031] 120 Body Connection Section

[0032] 121 supports

[0033] 130 electrical connector

[0034] 140 Circuit breaker positioning hole

[0035] 150 Cover Lock

[0036] 160 Bottom convex cavity

[0037] 170 partition

[0038] 200 Power Distribution Structure

[0039] 210 Circuit Breaker

[0040] 211 Operations Department

[0041] 212 Positioning Department

[0042] 213 Electrical connection part

[0043] 220 busbar

[0044] 221 First Convergence Line

[0045] 222 Second Confluence

[0046] 230 Fuse

[0047] 240 contactor

[0048] 250 diode

[0049] 260 Insulating connector Detailed Implementation

[0050] Exemplary embodiments of this application are described below with reference to the accompanying drawings. It should be understood that these specific descriptions are for teaching those skilled in the art how to implement this application only, and are not intended to exhaustively describe all possible methods of this application, nor to limit the scope of this application.

[0051] Embodiments of this application provide a low-voltage power distribution device (hereinafter, sometimes simply referred to as "low-voltage power distribution device") for electric aircraft, such as Figure 1 , Figure 2 and Figure 6 As shown, a low-voltage power distribution device may include a power distribution device housing 100 and a power distribution structure 200 disposed (at least partially) inside the power distribution device housing 100. The power distribution device housing 100 may provide load-bearing and support for the components in the power distribution structure 200.

[0052] The power distribution device housing 100 and power distribution structure 200 of the low-voltage power distribution device can form multiple power distribution modules. For example, in this embodiment, the low-voltage power distribution device can form two power distribution modules: a first power distribution module and a second power distribution module. Each power distribution module can be used for low-voltage power distribution to different equipment / functions / areas / systems on the electric aircraft. It is understood that setting multiple power distribution modules can improve the versatility of the low-voltage power distribution device, that is, it can adapt to the usage needs of various electric aircraft, especially electric vertical take-off and landing aircraft, using the same or similar technical solutions. The specific structure of each power distribution module can be adapted to its actual power distribution needs. For example, the low voltage referred to in this application can be 28V DC.

[0053] like Figure 1 , Figure 2 and Figure 7As shown, the power distribution device housing 100 may include a main body, a housing cover 110, a body connection portion 120, an electrical connector 130, a circuit breaker positioning hole 140, and a cover lock 150. Figure 3 and Figure 6 As shown, the power distribution structure 200 may include a circuit breaker 210, a busbar 220, a fuse 230, a contactor 240, and a diode 250.

[0054] Specifically, such as Figure 1 and Figure 2 As shown, the housing cover 110 may include multiple cover plates for at least partially covering multiple power distribution modules. The number of cover plates may be the same as the number of power distribution modules. For example, in this embodiment, the housing cover 110 may include a first cover plate 111 and a second cover plate 112 for covering the first power distribution module and the second power distribution module, respectively.

[0055] Each cover plate may also be provided with a movable connecting part 113 on one side for movably connecting each cover plate to the main body of the power distribution device housing 100, so that each cover plate can rotate relative to the main body of the power distribution device housing (about the movable connecting part 113 as an axis). For example, the movable connecting part 113 may be a hinge.

[0056] In one possible embodiment, adjacent cover plates can also be connected by a movable connecting part, allowing the adjacent cover plates to rotate relative to each other.

[0057] The thickness of the housing cover 110 can be 1 to 5 mm. Preferably, in this embodiment, the thickness of the housing cover 110 (first cover 111 and second cover 112) can be 2 mm.

[0058] A cover lock 150 can be used to lock the housing cover 110 to restrict rotation of the cover relative to the main body of the power distribution device housing. The power distribution device housing 100 may include a plurality of cover locks 150, the number of which may be the same as the number of covers, allowing each cover to be locked individually. Optionally, the number of cover locks 150 may also be twice the number of covers, allowing one cover to be locked by two cover locks 150 respectively. For example, as... Figure 1 and Figure 2 As shown, each of the first cover plate 111 and the second cover plate 112 is provided with two cover plate locks 150. The cover plate locks 150 and the movable connecting part 113 can be located on opposite sides of the cover plate.

[0059] For example, the cover lock 150 may include a moving part disposed on the housing cover 110 and a limiting part disposed inside the power distribution device housing 100. The working principle of the cover lock 150 is that by rotating the stop plate of the moving part with a key, the limiting part limits the stop plate, thereby locking the cover; by rotating the stop plate of the moving part with a key, the limiting part does not limit the stop plate, thereby releasing the lock of the cover and allowing the cover to rotate around the movable connecting part 113.

[0060] The fuselage connection portion 120 can be disposed on the outer peripheral surface (multiple sides) of the power distribution device housing 100 for connecting the low-voltage power distribution device to the fuselage of the electric aircraft. It is understood that the specific location of the low-voltage power distribution device on the electric aircraft can be determined by the actual layout of the fuselage. Specifically, the fuselage connection portion 120 can include multiple supports 121. For example, in this embodiment, the fuselage connection portion 120 includes four supports 121, which can be respectively disposed on opposite sides of the power distribution device housing 100. Bolt holes can be formed on the supports 121 to facilitate connecting the low-voltage power distribution device to the fuselage of the electric aircraft using bolt connections. The supports 121 can form an electrical connection with the fuselage of the electric aircraft to serve as the grounding structure for the low-voltage power distribution device.

[0061] Electrical connector 130 can be disposed on the outer peripheral surface of the power distribution device housing 100. Electrical connector 130 can be used to connect the power supply of the electric aircraft or various electrical devices of the electric aircraft, that is, the low-voltage power distribution device can form an electrical connection with the outside through electrical connector 130.

[0062] Preferably, the electrical connector 130 can be an aviation connector to meet the power standards of electric aircraft. For example, the electrical connector 130 can be a J599 series or D38999 series connector.

[0063] Preferably, the power distribution unit housing 100 may be provided with multiple electrical connectors 130. Given that the low-voltage power distribution unit has multiple power distribution modules and the electric aircraft has a high electrical load, providing multiple electrical connectors 130 allows the cabling of different systems / functions / areas / equipment to pass through different electrical connectors 130. This improves the safety, maintainability, and reliability of the aviation power distribution system and is more suitable for the modular design of the low-voltage power distribution unit. The internal components of the electrical connectors 130 may include multiple contacts to meet electrical connection requirements. The contacts can be fixed with a sealed structure to ensure good electrical connection and enhance the waterproof and dustproof performance of the electrical connectors 130. The electrical connectors 130 can be circular connectors, which can be connected to the low-voltage power distribution unit using a threaded connection.

[0064] Preferably, the power distribution device housing 100 can be a metal housing. The surface of the power distribution device housing 100 can be formed with a metal oxide film layer through a surface treatment process (e.g., anodizing). For example, the power distribution device housing 100 can be made of aluminum or aluminum alloy, and its surface can be formed with an aluminum oxide film layer through anodizing to enhance the insulation and wear resistance of the power distribution device housing 100. It is understood that the connection structure 120 may not require the above-mentioned surface treatment due to its grounding conductivity requirements.

[0065] The power distribution device housing 100 can also be adapted to form various structures (such as grooves, cavities, channels, etc.) for cables and wire harnesses to accommodate circuit layouts, depending on actual needs.

[0066] The power distribution structure 200 may include multiple circuit breakers 210. The circuit breaker 210 is a circuit protection device that can cut off the circuit when a short circuit or current overload occurs in the circuit, so as to protect the low-voltage power distribution device and electrical equipment and ensure the continuous operation of the low-voltage power grid of the electric aircraft.

[0067] Based on the number of electrical devices in the electric aircraft, the power distribution structure 200 can be equipped with multiple circuit breaker groups, and each circuit breaker group can include multiple circuit breakers 210. For example, Figure 1 and Figure 3 As shown, each power distribution module in this embodiment can be equipped with 4 circuit breaker groups, and each circuit breaker group can include 10 circuit breakers 210, that is, the low-voltage power distribution device can be equipped with a total of 80 circuit breakers. The breaking current of each circuit breaker 210 can be selected according to the current of the load in its corresponding circuit.

[0068] like Figure 4 and Figure 5 As shown, circuit breaker 210 can be connected to housing cover 110. One cover can be connected to at least one circuit breaker assembly, allowing circuit breaker 210 to move with the housing cover 110; that is, the circuit breaker assembly can move with either the first cover 111 or the second cover 112 to which it is connected. For example, housing cover 110 may have a through-hole for circuit breaker 210 to pass through, and circuit breaker 210 can be connected to housing cover 110 via a flange nut.

[0069] Furthermore, the circuit breaker 210 may include an operating section 211, a positioning section 212, and an electrical connection section 213. The operating section 211 can be used for manual operation by the crew; for example, the crew can control the disconnection and connection of the circuit breaker 210 by pressing and pulling. After the circuit breaker 210 is connected to the housing cover 110, its operating section 211 can be located relative to the outer side of the housing cover 110 (the side away from the interior of the low-voltage power distribution unit), that is, the operating section 211 can extend from a through-hole on the housing cover 110. The electrical connection section 213 can be used to connect (directly) the busbar 220 and (via wires) to various electrical devices of the electric aircraft.

[0070] like Figure 4 and Figure 5 As shown, the positioning part 212 of the circuit breaker 210 can mate with the circuit breaker positioning hole 140 of the power distribution device housing 100 to limit the movement of the power distribution device housing 100. Specifically, the circuit breaker positioning hole 140 can be formed in the housing cover plate 110. The circuit breaker positioning hole 140 is naturally adjacent to the through hole on the housing cover plate 110 for extending the operating part 211. The arrangement of the circuit breaker positioning holes 140 can correspond to the arrangement of the circuit breaker 210, that is, the positioning part 212 and the circuit breaker positioning hole 140 can correspond one-to-one.

[0071] For example, each cover plate (first cover plate 111 and second cover plate 112) in this embodiment may be provided with 4 sets of circuit breaker positioning holes 140, and each set may include ten circuit breaker positioning holes 140. The positioning part 212 may be a protrusion extending from the electrical connection part 213 toward the operation part 211, and the positioning part 212 may at least partially extend into one circuit breaker positioning hole 140 on the cover plate 110.

[0072] It is understood that the above structure allows the two structures of a circuit breaker 210 (operating part 211 and positioning part 212) to respectively engage with the housing cover plate 110, preventing the circuit breaker 210 from rotating relative to the housing cover plate 110, thus restricting the posture of each circuit breaker 210. Furthermore, this ensures that all circuit breakers 210 (or all circuit breakers in at least one power distribution module) have the same setting angle and direction, making the operating mode / logic of all circuit breakers 210 consistent. This arrangement of the circuit breakers 210 reduces the possibility of operator error and improves the efficiency of circuit breaker operation, inspection, and maintenance.

[0073] Preferred, such as Figure 1 and Figure 3As shown, the arrangement or form of the circuit breaker positioning holes 140 on all or adjacent cover plates can be different, that is, the arrangement or form of the circuit breakers on all or adjacent cover plates can be different. This technical feature makes it easier to distinguish between different power distribution modules and reduces the risk of human error. For example, in this embodiment, the circuit breakers on the first cover plate 111 and the second cover plate 112 have the same arrangement (both 10 rows and 4 columns), but their arrangement positions on the cover plates are different (in Figure 1 In the middle, the height of the circuit breaker array on the first cover plate 111 is higher than the height of the circuit breakers on the second cover plate 112.

[0074] Furthermore, the busbar 220 of the power distribution structure 200 may include a first busbar 221 and a second busbar 222. For example... Figure 3 and Figure 4 As shown, the first busbar 221 can connect all the circuit breakers 210 in a circuit breaker group to supply power to that group of circuit breakers 210; that is, one first busbar 221 can be installed in one circuit breaker group. The second busbar 222 can connect to one or more first busbars 221 via conductive structures such as wires, forming a flexible connection between the second busbar 222 and the first busbar 221 (understandably, electrical connection elements such as wires can have good deformation capabilities). The conductive structures such as wires connecting the first busbar 221 and the second busbar 222 should have appropriate redundant lengths to ensure that the first busbar 211 remains connected to the second busbar 222 when the cover plate moves. Furthermore, the second busbar 222 can connect to an electrical connector 130 (connected to a power source) to supply power to multiple groups of circuit breakers 210.

[0075] The second busbar 222 can be installed inside the power distribution unit housing 100. The second busbar 222 can connect to the electrical connector 130 and multiple circuit components (including but not limited to fuses, contactors, diodes, etc.). It is understood that when personnel open the cover, the circuit breaker 210 and its connected first busbar 221 can move with the cover, allowing inspection of the connection status between the electrical connection portions 213 of each circuit breaker 210 and the first busbar 221. However, the second busbar 222, the electrical connector 130, and at least some circuit components are connected to the inside of the power distribution unit housing 100 and do not move with the cover. Based on the flexible connection between the first busbar 221 and the second busbar 222, unit or maintenance personnel can inspect the circuit breaker 210 and the first busbar 221 on the inner side of the cover, as well as the various circuit components inside the power distribution unit housing 100, with minimal obstruction when the cover is opened.

[0076] The structure described in this application can effectively reduce mutual obstruction between the internal structures of the low-voltage power distribution device, and provide a clearer and more intuitive circuit display when the cover of the power distribution device is opened, thereby reducing the difficulty of operation, maintenance and repair of the low-voltage power distribution device.

[0077] Preferably, the power distribution housing 100 may also form one or more bottom cavities 160 at its bottom, which may protrude outward relative to the power distribution housing 100 to form a larger receiving space in a portion of the interior of the power distribution housing 100. This receiving space may be used to accommodate a portion of the circuit breaker and / or its connected busbar 220 (first busbar 221). It is understood that, due to the compact interior space of the electric aircraft, this structure can save as much interior space as possible.

[0078] like Figure 7 As shown, the power distribution device housing 100 may also be provided with a partition 170 to divide the internal space of the power distribution device housing 100, so as to form multiple power distribution modules. It is understood that the multiple power distribution modules may not be completely isolated from each other, and the multiple power distribution modules may be electrically connected through busbars or the like.

[0079] Optionally, depending on the specific circuit layout requirements of the low-voltage power distribution device, the power distribution structure 200 can also be equipped with more busbars.

[0080] Preferably, each busbar in the power distribution structure 200 can be a copper busbar.

[0081] Preferably, the busbar 220 may also be provided with an insulating sleeve to prevent the busbar 220 from contacting other non-target conductive devices.

[0082] Furthermore, fuse 230 is also a circuit protection device. Fuse 230 can melt its internal fuse wire to cut off the circuit and protect downstream electrical equipment when a short circuit or excessive load current occurs. The fusing current of fuse 230 can be determined based on the load current of the busbar. For example, the low-voltage power distribution device in this embodiment can be equipped with four fuses 230.

[0083] Contactor 240 can be used to control the rapid disconnection of a circuit, and the on / off state of the circuit can be controlled by controlling contactor 240. Preferably, contactor 240 may further include auxiliary contacts for detecting the closed and open states of the contactor and a discharge diode for discharging the coil inductance after power is cut off.

[0084] Diode 250 is a device with unidirectional current conduction function, which can be used to limit the direction of current flow in a circuit. The base of diode 250 can be connected to the power distribution housing 100, and the unidirectional conductor of diode 250 can be connected to busbar 220.

[0085] The aforementioned fuse 230, contactor 240 and diode 250 are connected via busbar 220. The specific connection method and the resulting circuit structure can be determined by the actual needs of the low-voltage power distribution device.

[0086] In an exemplary circuit configuration, the power source (battery) of the electric aircraft can be connected to the load (various electrical devices of the electric aircraft) via another electrical connector 130 through an electrical connector 130, a fuse 230, a contactor 240, a second busbar 222, a diode 250, a first busbar 221, and a circuit breaker 210.

[0087] The aforementioned busbar 220 and other components can be connected to the interior of the power distribution device housing 100 by an insulating connector 260. This connector isolates the busbar 220 and other components from the power distribution device housing 100 to prevent electrical accidents such as short circuits. The insulating connector 260 is made of a highly insulating material, such as ceramic or special engineering plastic.

[0088] The low-voltage power distribution device provided in the embodiments of this application omits the illustrations of the specific wiring forms of cables, wires, etc. inside it. It can be understood that multiple electrical connection structures such as cables and wires can be arranged and connected in the power distribution structure 200 according to actual needs.

[0089] Embodiments of this application also provide an electric aircraft that may include the low-voltage power distribution device for an electric aircraft described above.

[0090] The following is a brief description of some of the beneficial effects of the above-described embodiments of this application.

[0091] The low-voltage power distribution device and electric aircraft provided in this application adopt a modular design, connecting the circuit breaker to the housing cover. Opening the housing cover allows for direct inspection, maintenance, or replacement of the circuit breaker, reducing obstruction between components within the low-voltage power distribution device and giving it better versatility and maintainability. Furthermore, the maintainability of the power system of the electric aircraft using the aforementioned low-voltage power distribution device is also improved.

[0092] It is understood that, in this application, when the number of parts or components is not specifically limited, the number can be one or more, where multiple refers to two or more. For cases where the number of parts or components shown in the drawings and / or described in the specification is, for example, two, three, four, etc., this specific number is generally exemplary and not restrictive, and can be understood as multiple, i.e., two or more; however, this does not mean that this application excludes the case of one.

[0093] It should be understood that the above embodiments are merely exemplary and are not intended to limit this application. Those skilled in the art can make various modifications and changes to the above embodiments under the teachings of this application without departing from the scope of this application.

Claims

1. A low-voltage power distribution device for an electric aircraft, characterized in that, It includes a power distribution device housing and a power distribution structure, which together form multiple power distribution modules. The power distribution device housing includes a main body, multiple cover plates, and multiple electrical connectors. The multiple cover plates are used to at least partially cover the multiple power distribution modules. Each cover plate is movably connected to the main body of the power distribution device housing via a movable connecting part. The electrical connectors are used to connect to the power supply or electrical equipment of the electric aircraft. The power distribution structure includes multiple circuit breaker groups, busbars, and circuit elements. Each circuit breaker group includes multiple circuit breakers, and each cover plate is connected to at least one circuit breaker group, enabling the circuit breaker group to move with the cover plate to which it is connected. The busbar includes a first busbar and a second busbar. Multiple circuit breakers in a circuit breaker group are each connected to one of the first busbars. The second busbar is installed inside the housing of the power distribution device and is connected to the electrical connector and the circuit components. The first busbar and the second busbar are flexibly connected via a conductive structure.

2. The low-voltage power distribution device for electric aircraft according to claim 1, characterized in that, The circuit breaker has a positioning part, and the cover plate is provided with multiple circuit breaker positioning holes. The positioning part corresponds one-to-one with the positioning hole of the circuit breaker, and the positioning part extends at least partially into the positioning hole of the circuit breaker to restrict the posture of the circuit breaker.

3. The low-voltage power distribution device for electric aircraft according to claim 1, characterized in that, The circuit breaker has an operating section and an electrical connection section. The operating part is located on the outer side of the cover plate to facilitate operation by personnel; The electrical connection is located on the inner side of the cover plate, and the electrical connection connects the first busbar and various electrical devices used to connect the electric aircraft.

4. The low-voltage power distribution device for electric aircraft according to claim 1, characterized in that, The multiple circuit breakers in one of the power distribution modules are set at the same angle and in the same direction.

5. The low-voltage power distribution device for an electric aircraft according to claim 2, characterized in that, The circuit breaker positioning holes on adjacent cover plates are arranged in different positions and / or in different ways.

6. The low-voltage power distribution device for an electric aircraft according to claim 1, characterized in that, The power distribution structure also includes at least one fuse and at least one contactor, the fuse and the contactor being installed inside the power distribution device housing and electrically connected to the second busbar.

7. The low-voltage power distribution device for electric aircraft according to claim 1, characterized in that, An insulating oxide layer is provided on the outer surface of the power distribution device housing. The power distribution device housing is provided with a fixed support for connecting the electric aircraft. The surface of the fixed support is not provided with the insulating oxide layer so as to form an electrical connection with the electric aircraft.

8. The low-voltage power distribution device for an electric aircraft according to claim 1, characterized in that, The power distribution device housing includes multiple cover locks for locking the multiple cover plates respectively.

9. The low-voltage power distribution device for an electric aircraft according to claim 1, characterized in that, The bottom of the power distribution device housing has one or more bottom cavities for accommodating the circuit breaker and / or a portion of the first busbar.

10. An electric aircraft, characterized in that, Includes the low-voltage power distribution device for electric aircraft as described in any one of claims 1 to 9.

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