Multi-battery-pack power supply system for unmanned aerial vehicle

Abstract

Provided are a multi-battery-pack power supply system for an unmanned aerial vehicle, and an unmanned aerial vehicle. The multi-battery-pack power supply system for an unmanned aerial vehicle comprises: N battery pack units (10) connected in parallel, a pair of busbars (20), and a master control system (30). The N battery pack units (10) connected in parallel are respectively connected to the pair of busbars (20). The pair of busbars (20) are connected by means of a charging port (40). The master control system (30) respectively exchanges data with the N battery pack units (10) connected in parallel, and turns on or off the power supply system by controlling the connection / disconnection of the charging port (40), thus realizing that the N battery pack units (10) connected in parallel respectively supply power to a total load (50) of an unmanned aerial vehicle. By means of using multiple independently operating battery packs connected in parallel, the power supply system increases system redundancy, and extends the range while ensuring flight safety.

Description

UAV multi-pack battery power supply system Technical Field

[0001] The present application relates to the field of power battery technology, and in particular to a multi-pack battery power supply system for unmanned aerial vehicles. Background Art

[0002] In recent years, electricity has become increasingly important as a form of energy for powering aerial vehicles. EVTOL (Electric Vertical Take-Off and Landing) aircraft, in particular, offer significant solutions to traditional commercial aviation challenges, including high space requirements, long distances from urban cores, inability to cover urban transportation, and high driver requirements. While also eliminating the congestion and long detours associated with ground traffic, EVTOLs are poised to become the primary vehicle for future urban air transportation. For EVTOLs, the power supply system must provide sufficient energy during safe flight and landing to ensure the safety of the aircraft and passengers. Therefore, the battery system must have sufficient safety margins.

[0003] Summary of the Invention

[0004] The purpose of this application is to provide a multi-pack battery power supply system for drones. This application utilizes multiple independent working battery packs in parallel to increase system redundancy, ensure flight safety and increase range.

[0005] In order to solve the above technical problems, the present application provides a multi-pack battery power supply system for an unmanned aerial vehicle, comprising: N battery pack units connected in parallel, a pair of buses, and a general control system. The N battery pack units connected in parallel are respectively connected to the pair of buses, and the pair of buses are further connected through a charging port. The general control system exchanges data with the N battery pack units connected in parallel and turns on or off the power supply system by controlling the on and off of the charging port, so that the N battery pack units connected in parallel can respectively power the entire load of the unmanned aerial vehicle.

[0006] The present application also provides an aircraft, comprising the above-mentioned UAV multi-pack battery power supply system.

[0007] Optionally, each of the battery pack units includes a battery pack and a battery pack circuit breaker unit, the battery pack circuit breaker unit is connected to the battery pack, the input end of the battery pack and the output end of the battery pack circuit breaker unit are respectively connected to the pair of buses, and the battery pack circuit breaker unit is used to monitor the corresponding battery pack and cut off its connection with other battery pack units when a fault occurs.

[0008] Optionally, each battery pack disconnecting unit is used to monitor multiple status parameter information of the corresponding battery pack, and when any status parameter of any battery pack exceeds a threshold voltage range, its connection with other battery pack units is cut off, wherein the status parameters of the battery pack include at least voltage, current, SOC (battery state of charge), pressure difference, temperature and insulation status.

[0009] Optionally, a safety unit is further provided between the battery pack and the battery pack circuit breaker unit, and the safety unit is used to provide circuit breaker protection for the corresponding battery pack circuit breaker unit when the current is overloaded.

[0010] Optionally, each of the battery pack units also includes an interconnected power electronic control unit and a battery management system that can exchange data with each other. The input ends of the power electronic control unit and the battery management system are respectively connected to the battery pack and the battery pack circuit breaker unit, and the output ends of the power electronic control unit and the battery management system are connected to the overall control system. The battery management system and the power electronic control unit monitor the battery pack and the battery pack circuit breaker unit respectively, and send the monitoring information to the overall control system.

[0011] Optionally, the master control system includes a master battery management system and an aircraft control system. The master battery management system is connected to each of the battery management systems, and the aircraft control system is connected to each of the power electronic control units. The master battery management system and the aircraft control system exchange data to turn on or off the power supply system by controlling the on and off of the charging port.

[0012] Optionally, a charging circuit breaker unit is also connected between the pair of bus bars, and the charging circuit breaker unit is used to monitor multiple charging status parameters of the charging port. When any charging status parameter exceeds a threshold range, the electrical connection between the pair of bus bars is cut off, wherein the charging status information includes at least voltage and current.

[0013] Optionally, the master battery management system exchanges data with the charging circuit breaker unit to detect the electrical connection between the pair of busbars.

[0014] Optionally, the safety unit is a fuse.

[0015] This application utilizes multiple independent working battery packs in parallel to increase system redundancy, ensuring flight safety while increasing range. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] FIG1 is a schematic diagram showing the unit structure of a multi-pack battery power supply system for a drone according to an embodiment of the present application;

[0017] FIG2 is a schematic diagram showing a specific unit structure of a multi-pack battery power supply system for a drone according to an embodiment of the present application. DETAILED DESCRIPTION

[0018] The following embodiments further illustrate the technical solutions of the present application. It is understood that the specific embodiments described herein are merely for the purpose of explaining the present application. It should also be noted that, for ease of description, only portions relevant to the present application are shown in the accompanying drawings, not all of them.

[0019] In the description of this application, it should be noted that, unless otherwise specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they can refer to fixed or detachable connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in this application in specific contexts.

[0020] In this application, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Moreover, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly below or obliquely below the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0021] The following describes an embodiment of the present application with reference to the accompanying drawings. As shown in Figure 1, the drone multi-pack battery power supply system of the embodiment of the present application includes: N battery pack units 10 connected in parallel, a pair of buses 20, and a total control system 30. The N battery pack units 10 connected in parallel are respectively connected to the pair of buses 20, and the pair of buses 20 are further connected through a charging port 40. The total control system 30 exchanges data with the N battery pack units 10 connected in parallel and turns on or off the power supply system by controlling the on and off of the charging port 40, so that the N battery pack units 10 connected in parallel can respectively power the drone load 50.

[0022] Specifically, as shown in FIG2 , each battery pack unit 10 includes a battery pack 100 and a battery pack disconnecting unit 101. The battery pack disconnecting unit 101 is connected to the battery pack 100. The input end of the battery pack 100 and the output end of the battery pack disconnecting unit 101 are respectively connected to a pair of busbars 20. The battery pack disconnecting unit 101 is used to monitor the corresponding battery pack 100 and disconnect it from other battery pack units 10 when a battery pack 100 fails. Each battery pack disconnecting unit 101 is used to collect multiple status parameters of the battery pack 100 to monitor the health of the corresponding battery pack 100. When any status parameter of any battery pack 100 exceeds a preset threshold range, it disconnects it from other battery pack units 10, thereby shutting down the charging circuit. The status information includes but is not limited to voltage, current, SOC (battery state of charge), differential pressure, temperature, and insulation status. Furthermore, a fuse unit 102 is provided between the battery pack 100 and the battery pack disconnect unit 101. The fuse unit 102 is used to disconnect the corresponding battery pack disconnect unit 101 in the event of a current overload. Each battery pack unit 10 also includes an interconnected power electronic control unit 103 and a battery management system 104. The power electronic control unit 103 and the battery management system 104 can exchange data with each other. The input terminals of the power electronic control unit 103 and the battery management system 104 are connected to the battery pack 100 and the battery pack disconnect unit 101, respectively. The output terminals of the power electronic control unit 103 and the battery management system 104 are connected to the overall control system 30. The battery management system 104 and the power electronic control unit 103 monitor the battery pack 100 and the battery pack disconnect unit 101, respectively, and transmit the monitoring information to the overall control system 30. Furthermore, the master control system 30 includes a master battery management system 301 and an aircraft control system 302. The master battery management system 301 is connected to each battery management system 104, and the aircraft control system 302 is connected to each power electronic control unit 103. The master battery management system 301 collects battery cell monitoring data from each battery management system 104 and sends the collected data to the aircraft control system 302. The aircraft control system 302 executes corresponding instructions based on the received data, such as issuing a warning to the ground station, not performing a power-on operation, and controlling the corresponding faulty battery cell to power off. After the master battery management system 301 and the aircraft control system 302 exchange data, they can also connect the battery system and the ground charging pile by controlling the charging port 40 to charge the battery system. During the charging process, the master battery management system 301 and the ground charging pile interact to control the charging process.Furthermore, a charging circuit breaker unit 60 is connected between a pair of busbars 20. The charging circuit breaker unit 60 is used to collect charging current information to monitor multiple charging status parameters of the charging port 40. When any of its status parameters exceeds a preset threshold range, the electrical connection between the pair of busbars 20 is cut off, wherein the charging status parameters include but are not limited to voltage and current. In addition, the master control battery management system 301 exchanges data with the charging circuit breaker unit 60 to detect the electrical connection between a pair of busbars 20. The insurance unit 102 is a fuse. Preferably, N is greater than 2, that is, 3 or more battery packs are required to be powered in parallel. The present application utilizes N independently working battery packs in parallel to increase system redundancy, ensure flight safety, and increase range.

[0023] The present application also provides an aircraft including the aforementioned multi-pack battery power supply system for unmanned aerial vehicles. The multi-pack battery power supply system for unmanned aerial vehicles utilizes N independently working battery packs in parallel to increase system redundancy, thereby ensuring flight safety and increasing range.

[0024] The above embodiments are merely illustrative of the principles and effects of this application. Anyone skilled in the art may modify or alter the above embodiments without departing from the objectives of this application. Therefore, all equivalent modifications or alterations made by persons skilled in the art without departing from the objectives disclosed herein are intended to be covered by the claims of this application.

Claims

1. A multi-pack battery power supply system for drones, characterized in that: include: N parallel-connected battery pack units (10), a pair of buses (20), and a general control system (30), wherein the N parallel-connected battery pack units (10) are respectively connected to the pair of buses (20), and the pair of buses (20) are further connected via a charging port (40), and the general control system (30) exchanges data with the N parallel-connected battery pack units (10) and opens or closes the power supply system by controlling the on / off of the charging port (40), so that the N parallel-connected battery pack units (10) respectively supply power to the drone load (50).

2. The drone multi-pack battery power supply system according to claim 1, characterized in that: Each of the battery pack units (10) comprises a battery pack (100) and a battery pack disconnecting unit (101); the battery pack disconnecting unit (101) is connected to the battery pack (100); an input end of the battery pack (100) and an output end of the battery pack disconnecting unit (101) are respectively connected to the pair of bus bars (20); the battery pack disconnecting unit (101) is used to monitor the corresponding battery pack (100) and to cut off its connection with other battery pack units (10) when a fault occurs in the battery pack (100).

3. The drone multi-pack battery power supply system according to claim 2, characterized in that: Each battery pack disconnection unit (101) is used to monitor multiple status parameter information of the corresponding battery pack (100), and when any status parameter of any battery pack (100) exceeds a threshold voltage range, the connection between the battery pack and other battery pack units (10) is cut off, wherein the status parameters of the battery pack (100) include at least voltage, current, SOC (battery state of charge), pressure difference, temperature and insulation state.

4. The multi-pack battery power supply system for unmanned aerial vehicles according to claim 2, characterized in that: A safety unit (102) is also provided between the battery pack (100) and the battery pack disconnecting unit (101), and the safety unit (102) is used to provide disconnection protection for the corresponding battery pack disconnecting unit (101) when current is overloaded.

5. The drone multi-pack battery power supply system according to claim 1, characterized in that: Each of the battery pack units (10) further comprises a power electronic control unit (103) and a battery management system (104) which are interconnected and can exchange data with each other. The input ends of the power electronic control unit (103) and the battery management system (104) are respectively connected to the battery pack (100) and the battery pack disconnecting unit (101). The output ends of the power electronic control unit (103) and the battery management system (104) are connected to the overall control system (30). The battery management system (104) and the power electronic control unit (103) monitor the battery pack (100) and the battery pack disconnecting unit (101) respectively, and send the monitoring information to the overall control system (30).

6. The drone multi-pack battery power supply system according to claim 5, characterized in that: The master control system (30) comprises a master battery management system (301) and an aircraft control system (302); the master battery management system (301) is connected to each of the battery management systems (104); the aircraft control system (302) is connected to each of the power electronic control units (103); the master battery management system (301) and the aircraft control system (302) exchange data to open or close the power supply system by controlling the on / off of the charging port (40).

7. The drone multi-pack battery power supply system according to claim 1, characterized in that: A charging disconnect unit (60) is also connected between the pair of bus bars (20), and the charging disconnect unit (60) is used to monitor multiple charging status parameters of the charging port (40), and when any charging status parameter exceeds a threshold range, the electrical connection between the pair of bus bars (20) is cut off, wherein the charging status information includes at least voltage and current.

8. The drone multi-pack battery power supply system according to claim 2, characterized in that: The master battery management system (301) exchanges data with the charging disconnect unit (60) to detect the electrical connection between the pair of bus bars (20).

9. The multi-pack battery power supply system for unmanned aerial vehicles according to claim 4, characterized in that: The safety unit (102) is a fuse.

10. An aircraft, characterized in that: It comprises a multi-pack battery power supply system for a drone as described in any one of claims 1 to 9.

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