Multi-pack battery power supply system of unmanned aerial vehicle

Abstract

The invention relates to the technical field of power batteries, and discloses an unmanned aerial vehicle multi-pack battery power supply system. The unmanned aerial vehicle multi-pack battery power supply system comprises N battery pack units connected in parallel, a pair of busbars and a master control system, the N battery pack units connected in parallel are connected with the pair of busbars respectively, and the pair of busbars are connected through a charging port. The master control system exchanges data with the N battery pack units connected in parallel and turns on or turns off the power supply system by controlling the on-off of the charging ports, so that the N battery pack units connected in parallel supply power to the whole load of the unmanned aerial vehicle. A plurality of independent working battery packs are used in parallel, so that the system redundancy is increased, and the flight range is increased while the flight safety is ensured.

Description

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 driving aerial vehicles, especially EVTOL (Electric Vertical Take-Off and Landing) aircraft, which are called "electric vertical take-off and landing aircraft". They can effectively solve the problems of high space requirements for traditional commercial aviation, long distance from the core area of ​​the city, inability to cover urban traffic, and high requirements for drivers. At the same time, they can get rid of the congestion and long-distance detour problems of ground traffic, and will be the main carrier of urban air traffic in the future. For EVTOL, the power supply system must provide enough energy during safe flight and landing to ensure the safety of the aircraft and passengers, so the battery system should have enough safety margin. Summary of the invention

[0003] The purpose of this application is to provide a multi-pack battery power supply system for an unmanned aerial vehicle. This application utilizes multiple independently working battery packs in parallel to increase system redundancy, thereby ensuring flight safety and increasing the range.

[0004] 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, wherein 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, and 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.

[0005] The present application also provides an aircraft, comprising the above-mentioned UAV multi-pack battery power supply system.

[0006] 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.

[0007] 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, cut off its connection with other battery pack units, wherein the status parameters of the battery pack include at least voltage, current, SOC (battery state of charge), pressure difference, temperature and insulation status.

[0008] 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.

[0009] 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.

[0010] 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, the aircraft control system is connected to each of the power electronic control units, and 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.

[0011] 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.

[0012] Optionally, the master battery management system exchanges data with the charging circuit breaker unit to detect the electrical connection between the pair of bus bars.

[0013] Optionally, the insurance unit is a fuse.

[0014] This application utilizes multiple independently working battery packs in parallel to increase system redundancy, thereby ensuring flight safety and increasing the range. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 Shown is a schematic diagram of the unit structure of a multi-pack battery power supply system for a drone according to an embodiment of the present application;

[0016] Figure 2 Shown is a schematic diagram of the specific unit structure of the multi-pack battery power supply system for the drone according to an embodiment of the present application. DETAILED DESCRIPTION

[0017] The following embodiments further illustrate the technical solution of the present application. It is to be understood that the specific embodiments described herein are only used to explain the present application. It should also be noted that, for ease of description, only the parts related to the present application are shown in the drawings, not all.

[0018] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection or a detachable 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, and it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0019] In the present application, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0020] The following describes the embodiments of the present application with reference to the accompanying drawings. Figure 1 As shown, 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 general 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 general 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.

[0021] Specifically, Figure 2As shown, 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 bus bars 20. The battery pack disconnecting unit 101 is used to monitor the corresponding battery pack 100, and cut off its connection with other battery pack units 10 when a battery pack 100 fails. Each battery pack disconnecting unit 101 is used to collect multiple state parameters of the battery pack 100 to monitor the health of the corresponding battery pack 100. When any state parameter of any battery pack 100 exceeds a preset threshold range, it cuts off its connection with other battery pack units 10 to shut down the charging circuit, wherein the state information includes but is not limited to voltage, current, SOC (battery state of charge), pressure difference, temperature and insulation state. Furthermore, a safety unit 102 is provided between the battery pack 100 and the battery pack circuit breaker unit 101, and the safety unit 102 is used to provide circuit breaker protection for the corresponding battery pack circuit breaker unit 101 when the current is overloaded. Each battery pack unit 10 also includes a power electronic control unit 103 and a battery management system 104 that are connected to each other. The power electronic control unit 103 and the battery management system 104 can exchange data with each other. The input ends of the power electronic control unit 103 and the battery management system 104 are connected to the battery pack 100 and the battery pack circuit breaker unit 101 respectively, and 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 circuit breaker unit 101 respectively, and send the monitoring information to the overall control system 30. Furthermore, the master control system 30 includes a master control battery management system 301 and an aircraft control system 302. The master control 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 control battery management system 301 collects the battery unit monitoring data of each battery management system 104, and sends the collected data to the aircraft control system 302. The aircraft control system 302 executes corresponding instructions according to the received data, such as issuing a warning to the ground station, not performing the power-on operation, and controlling the corresponding faulty battery unit to be powered off. After the master control battery management system 301 and the aircraft control system 302 exchange data, the battery system and the ground charging pile can also be connected by controlling the charging port 40 to charge the battery system. During the charging process, the master control battery management system 301 interacts with the ground charging pile to control the charging process. Furthermore, a charging circuit breaker unit 60 is connected between a pair of bus bars 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 bus bars 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 for parallel power supply. The present application uses N independent working battery packs in parallel to increase system redundancy, ensure flight safety and increase range.

[0022] The present application also provides an aircraft, including the above-mentioned drone multi-pack battery power supply system. The drone multi-pack battery power supply system of the present application uses N independent working battery packs in parallel to increase system redundancy, ensure flight safety and increase range.

[0023] The above embodiments are merely illustrative of the principles and effects of the present application. Anyone familiar with the technology may modify or change the above embodiments without violating the purpose of the present application. Therefore, all equivalent modifications or changes made by a person with ordinary knowledge in the relevant technical field without departing from the purpose disclosed in the present application shall still be covered by the claims of the present 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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