Aircraft power supply bus power distribution architecture

Abstract

The utility model relates to an aircraft power supply bus distribution architecture, comprising a power supply bus type power supply distribution circuit which comprises a power supply bus, a load distribution branch line, a protector, a power supply branch line of a power supply device and a branch line node. The power supply branch line or the load power distribution branch line is electrically connected with the power supply bus through a branch line node, a plurality of power supplies or loads can be arranged on the power supply bus in parallel, and the power supply bus type power distribution circuit can be arranged into two closed-loop parallel line type positive and negative power supply buses. The system has the advantages of redundant circuit power distribution, few circuit nodes, small system loss, high system reliability, capability of replacing a switchboard, remarkably reduced system weight, simple components and low cost.

Description

Technical Field

[0001] This utility model relates to the field of aircraft power supply technology, specifically to an aircraft power supply bus power distribution architecture. Background Technology

[0002] Aviation power supply refers to the system that provides a stable power supply to aircraft. It ensures that the aircraft's power system, communication, navigation, lighting, flight control system and other key functions can operate normally. During flight, the stability and reliability of the power supply are of paramount importance, as they not only affect flight safety but also the performance of equipment and passenger comfort during flight.

[0003] Currently, the power distribution system for electric aircraft and similar devices typically uses a centralized distribution panel architecture. This centralized distribution panel integrates positive and negative buses, multiple fuses, multi-interface connectors, insulators, and other components. This architecture involves numerous circuit nodes, varying connection impedances depending on the environment, high-quality insulation materials, and significant structural weight. These factors result in high material and manufacturing costs, lower electrical performance, and lower circuit reliability and safety. Currently, there is no superior power distribution architecture available. Utility Model Content

[0004] The purpose of this utility model is to provide an aircraft power bus distribution architecture, which has the advantages of fewer circuit nodes, high reliability, lighter weight and simpler components than the power distribution panel system, and solves the problems mentioned in the background art.

[0005] To achieve the above objectives, this utility model provides the following technical solution: an aircraft power supply bus distribution architecture, including a power bus type power distribution circuit. The power bus type power distribution circuit includes a power bus, load distribution branches, protectors, power supply branches of power devices, and branch nodes. The power supply branches or load distribution branches are electrically connected to the power bus through branch nodes. Multiple power supplies or loads can be connected in parallel on the power bus. The power bus type power distribution circuit can be arranged as two closed-loop parallel line positive and negative power buses.

[0006] Preferably, it also includes a bus connector and a protector. The branch node is provided with a bus connector. The power supply branch and the load distribution branch are electrically connected to the power bus through the bus connector. The bus connector includes a positive connector and a negative connector. The protector can be set as a branch fuse. When the power supply device is designed as a self-balancing power supply, the voltage of a self-balancing power supply is equal to the power supply voltage, and the capacity is determined according to the power distribution system definition.

[0007] Preferably, the power bus type power distribution circuit is arranged as a closed-loop parallel line type positive and negative power bus. The power bus includes power bus one and power bus two. The load distribution branch includes load distribution branch one, load distribution branch two and load distribution branch three. The power supply branch includes power supply branch one and power supply branch two. Power bus one is electrically connected to load distribution branch one, power supply branch one and load distribution branch two. Power bus two is electrically connected to load distribution branch three and power supply branch two. One end of load distribution branch one and load distribution branch three are electrically connected to a motor driver. One end of power supply branch one and power supply branch two are electrically connected to a power supply device.

[0008] Preferably, the power bus type power distribution circuit includes a charging interface and a low-voltage power conversion device, and the load, power supply device, charging interface and low-voltage power conversion device are all connected in parallel on the power bus.

[0009] Preferably, the power bus type distribution circuit is configured as two long oval ring closed-loop parallel line positive and negative power buses, or non-closed-loop parallel line positive and negative power buses, or closed-loop or non-closed-loop single-line power buses.

[0010] The technical solution of this application has the following technical effects: This utility model has the advantages of fewer circuit nodes, high reliability, lighter weight when replacing the distribution panel system, and simpler components with lower cost. By reducing network nodes, the complexity of the system is reduced, which not only reduces the system failure rate, but also makes the system maintenance and management easier. After eliminating intermediate links such as the distribution panel, the overall weight of the system is reduced, thereby improving flight efficiency, reducing energy consumption and increasing payload capacity. In actual use, the parallel connection of multiple power supplies can balance the circuit protection against overload of the power supply device. The redundant power supply of the parallel connection of multiple power supply devices eliminates the single-point failure of regional packet loss. In particular, if a ring bus structure is adopted, the redundancy of the power supply circuit is further increased, which improves the safety of the power distribution system.

[0011] It should be understood that all combinations of the foregoing concepts and the additional concepts described in more detail below can be considered as part of the utility model subject matter of this disclosure, provided that such concepts do not contradict each other. Attached Figure Description

[0012] The accompanying drawings are provided to further illustrate the present invention and form part of the specification. They are used together with the embodiments of the present invention to explain the present invention, but do not constitute a limitation thereof. In the drawings:

[0013] Figure 1 This is a circuit diagram of one embodiment of the present invention;

[0014] Figure 2 This is a circuit diagram of an embodiment of the present invention. Figure 1 ;

[0015] Figure 3 This is a circuit diagram of an embodiment of the present invention. Figure 2 .

[0016] The meanings of the reference numerals in the figure are as follows: 1. Power bus 1; 2. Power bus 2; 3. Load distribution branch 1; 4. Power supply branch 1; 5. Load distribution branch 2; 6. Protector; 7. Load distribution branch 3; 8. Power supply branch 2; 9. Motor driver; 10. Power supply unit; 11. Charging interface; 12. Low-voltage power conversion device. Detailed Implementation

[0017] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. To better understand the technical content of the present utility model, specific embodiments are provided and described in conjunction with the accompanying drawings. Various aspects of the present utility model are described in this disclosure with reference to the accompanying drawings, which show many illustrative embodiments. It should be understood that the various concepts and embodiments described above, as well as those described in more detail below, can be implemented in any of many ways. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the scope of protection of the present utility model.

[0018] As attached Figure 1 To be continued Figure 3 As shown: This embodiment provides an aircraft power bus power distribution architecture, including a power bus type power distribution circuit. The power bus type power distribution circuit includes a power bus, a load distribution branch, a protector 6, a power supply branch and branch node of the power device 10. The power supply branch or load distribution branch is electrically connected to the power bus through the branch node. Multiple power supplies or loads can be connected in parallel on the power bus. The power bus type power distribution circuit can be arranged as two closed-loop parallel line positive and negative power buses.

[0019] Specifically, it also includes bus connectors and protectors 6. Branch nodes are equipped with bus connectors. Power supply branches and load distribution branches are electrically connected to the power bus through bus connectors. Bus connectors include positive and negative connectors. Protectors 6 can be configured as branch fuses. When the power supply unit 10 is designed as a self-balancing power supply, the voltage of a self-balancing power supply is equal to the power supply voltage, and the capacity is determined according to the power distribution system definition.

[0020] In this embodiment: With the protection device 6, when a short circuit fault occurs in the circuit, the current will increase rapidly, and the fuse will melt in a very short time, cutting off the circuit and preventing the short circuit current from causing further damage to the equipment and bus.

[0021] In this embodiment, the parallel operation and automatic balancing of multiple power modules are achieved through the setting of the power supply device 10, thereby improving the reliability and stability of the power system.

[0022] Specifically, the power bus type distribution circuit is arranged as a closed-loop parallel line type positive and negative power bus. The power bus includes power bus 1 and power bus 2. The load distribution branch includes load distribution branch 3, load distribution branch 5 and load distribution branch 3 7. The power supply branch includes power supply branch 4 and power supply branch 2 8. Power bus 1 is electrically connected to load distribution branch 3, power supply branch 4 and load distribution branch 2 5. Power bus 2 is electrically connected to load distribution branch 3 7 and power supply branch 2 8. One end of load distribution branch 3 and load distribution branch 3 7 is electrically connected to a motor driver 9. One end of power supply branch 4 and power supply branch 2 8 is electrically connected to a power supply device 10.

[0023] Specifically, the power bus type power distribution circuit includes a charging interface 11 and a low-voltage power conversion device 12. The load, power supply device 10, charging interface 11 and low-voltage power conversion device 12 are all connected in parallel on the power bus.

[0024] Specifically, the power bus type distribution circuit is arranged as two long oval ring closed-loop parallel line positive and negative power buses, or non-closed-loop parallel line positive and negative power buses, or closed-loop or non-closed-loop single-line power buses.

[0025] Working principle and usage process of this utility model:

[0026] The adoption of a ring power bus distribution circuit increases power circuit redundancy on power bus 1 and power bus 2, improving the safety of the power distribution system. The power supply unit 10 or the load is directly connected to power bus 1 and power bus 2, eliminating the need for a centralized distribution panel, reducing circuit nodes, improving system circuit reliability, and reducing system weight.

[0027] Using bus connectors to connect the power bus and the power supply line allows multiple power supply devices 10 to be connected in parallel, simplifying the power distribution connection method and improving reliability. The parallel connection of multiple power supplies can balance the circuit and protect the power supply devices from overload. The redundant power supply of the multiple power supply devices 10 connected in parallel eliminates single-point failure faults caused by regional packet loss.

[0028] A dedicated bus connector is used to connect the power bus to the load distribution line, and a protector 6 is installed near power bus 1 and power bus 2. Each load distribution is protected by the protector 6, which ensures the protection of power bus 1 and power bus 2 or the load circuit, and guarantees power distribution redundancy and system safety.

[0029] All power supply units 10 or loads are connected to power bus 1 and power bus 2 using dedicated bus connectors, ensuring the electrical performance, structural performance, reliability, maintainability, and durability of the connection.

[0030] The key point of this utility model is to eliminate the distribution panel box and use a closed-loop parallel line positive and negative power bus, bus connector and protector to realize power distribution. In another embodiment, a non-closed-loop parallel line positive and negative power bus, or a closed-loop single line power bus, or a non-closed-loop single line power bus, or no bus connector and protector can be used, all of which are within the protection scope of this utility model.

[0031] It should be noted that in this paper, relational terms such as first and second are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations.

[0032] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Those skilled in the art to which this invention pertains can make various modifications and refinements without departing from the spirit and scope of the present invention. Therefore, the scope of protection of this invention shall be determined by the claims.

Claims

1. An aircraft power bus power distribution architecture, characterized by: The power distribution circuit includes a power bus type power distribution circuit, which includes a power bus, a load distribution branch, a protector (6), a power supply branch and a branch node of a power device (10). The power supply branch or load distribution branch is electrically connected to the power bus through the branch node. Multiple power supplies or loads can be connected in parallel on the power bus. The power bus type power distribution circuit can be arranged as two closed-loop parallel line positive and negative power buses.

2. An aircraft power bus electrical power distribution architecture according to claim 1, wherein: It also includes bus connectors and protectors (6). The branch nodes are equipped with bus connectors. The power supply branch and the load distribution branch are electrically connected to the power bus through the bus connectors. The bus connectors include positive connectors and negative connectors. The protector (6) can be set as a branch fuse. When the power supply device (10) is designed as a self-balancing power supply, the voltage of a self-balancing power supply is equal to the power supply voltage, and the capacity is determined according to the power distribution system definition.

3. An aircraft power bus electrical power distribution architecture according to claim 1, wherein: The power bus type power distribution circuit is arranged as a closed-loop parallel line type positive and negative power bus. The power bus includes power bus one (1) and power bus two (2). The load power distribution branch includes load power distribution branch one (3), load power distribution branch two (5) and load power distribution branch three (7). The power supply branch includes power supply branch one (4) and power supply branch two (8). The power bus one (1) is electrically connected to load power distribution branch one (3), power supply branch one (4) and load power distribution branch two (5). The power bus two (2) is electrically connected to load power distribution branch three (7) and power supply branch two (8). One end of the load power distribution branch one (3) and the load power distribution branch three (7) is electrically connected to a motor driver (9). One end of the power supply branch one (4) and the power supply branch two (8) is electrically connected to a power supply device (10).

4. An aircraft power bus electrical power distribution architecture according to claim 1, wherein: The power bus type power distribution circuit includes a charging interface (11) and a low-voltage power conversion device (12). The load, power supply device (10), charging interface (11) and low-voltage power conversion device (12) are all connected in parallel on the power bus.

5. An aircraft power bus electrical power distribution architecture according to any one of claims 1-4, characterized in that: The power bus type distribution circuit is configured as two long oval ring closed-loop parallel line positive and negative power buses, or non-closed-loop parallel line positive and negative power buses, or closed-loop or non-closed-loop single-line power buses.

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