Flying car and power distribution system thereof

Abstract

The invention discloses a hovercar and a power distribution system thereof, the hovercar comprises a first flight driving motor set and a second flight driving motor set, the system comprises a first power supply unit used for supplying power to the first flight driving motor set; the second power supply unit is used for supplying power to the second flight driving motor set; the controller is used for controlling the first power supply unit and the second power supply unit based on the operation parameters of the first flight driving motor group, the second flight driving motor group, the first power supply unit and the second power supply unit; when one or more driving motors in the first flight driving motor set and the second flight driving motor set break down or one of the first power supply unit and the second power supply unit breaks down, the flight state of the hovercar is maintained. Therefore, according to the system, power distribution redundancy of the hovercar is achieved, and the hovercar can continue to fly to land at a designated place on the premise that a single power supply unit or a single motor load fails.

Description

Technical Field

[0001] The present application relates to the field of power distribution technology, and in particular to a power distribution system for a flying car and a flying car. Background Art

[0002] In the design of the high-voltage power distribution system of electric vehicles, energy storage batteries are set to power the motors. When the energy storage batteries are low or the power supply system fails, the electric vehicle loses power and can be parked on the spot, safety signs are placed, and personnel are evacuated. However, a flying car cannot hover on the spot after losing power, which is a great danger. Summary of the invention

[0003] The present application aims to solve at least one of the technical problems in the related art to a certain extent. To this end, the first purpose of the present application is to propose a power distribution system for a flying car, which realizes power distribution redundancy for the flying car, and enables the flying car to continue flying and land at a designated location under the premise of failure of a single power supply unit or a single motor load.

[0004] The second purpose of this application is to provide a flying car.

[0005] To achieve the above-mentioned purpose, the first embodiment of the present application proposes a power distribution system for a flying car, the flying car comprising a first flight drive motor group and a second flight drive motor group, the first flight drive motor group and the second flight drive motor group are both symmetrically arranged along the axis direction of the flying car, the power distribution system of the flying car comprises: a first power supply unit, used to supply power to the first flight drive motor group; a second power supply unit, used to supply power to the second flight drive motor group; a controller, used to control the first power supply unit and the second power supply unit based on the operating parameters of the first flight drive motor group, the second flight drive motor group, the first power supply unit and the second power supply unit, so as to maintain the flight state of the flying car when one or more drive motors in the first flight drive motor group and the second flight drive motor group fail or one of the first power supply unit and the second power supply unit fails.

[0006] According to the power distribution system of the flying car of the embodiment of the present application, the first flight drive motor group is powered by the first power supply unit, and the second flight drive motor group is powered by the second power supply unit. The controller controls the first power supply unit and the second power supply unit based on the operating parameters of the first flight drive motor group, the second flight drive motor group, the first power supply unit and the second power supply unit, so as to maintain the flight state of the flying car when one or more drive motors in the first flight drive motor group and the second flight drive motor group fail or one of the first power supply unit and the second power supply unit fails. Thus, the system realizes power distribution redundancy for the flying car, and can enable the flying car to continue to fly and land at a designated location under the premise of failure of a single power supply unit or a single motor load.

[0007] In addition, the power distribution system of the flying car according to the above embodiment of the present application may also have the following additional technical features:

[0008] According to one embodiment of the present application, the circuit structure of the first power supply unit and the second power supply unit is the same, wherein the first power supply unit includes: a first battery pack; a first power distribution unit, the first power distribution unit includes multiple first power supply branches, the input ends of the multiple first power supply branches are connected to the output end of the first battery pack, the output ends of the multiple first power supply branches are respectively connected to the power supply ends of the motors in the first flight drive motor group, and each first power supply branch is respectively connected in series with a controllable switch.

[0009] According to one embodiment of the present application, the flying car includes a third flight drive motor, and the power distribution system also includes a third power supply unit, the third power supply unit includes: a third battery pack and a fourth battery pack; a third power distribution unit, the third power distribution unit includes two third power supply branches, the input ends of the two third power supply branches are respectively connected to the third battery pack and the fourth battery pack, the output ends of the two third power supply branches are connected to the power supply end of the third flight drive motor, and the third power supply branch and the fourth power supply branch are respectively connected in series with controllable switches.

[0010] According to one embodiment of the present application, the second power supply unit includes a second battery pack and a second power distribution unit, the first power distribution unit, the second power distribution unit and the third power distribution unit are arranged in the middle of the cabin of the flying car, and the first battery pack, the second battery, the third battery pack and the fourth battery are arranged on both sides of the first power distribution unit, the second power distribution unit and the third power distribution unit along the axial direction of the cabin.

[0011] According to one embodiment of the present application, the first battery pack and the third battery pack are arranged on one side of the first power distribution unit, the second power distribution unit and the third power distribution unit, and the second battery and the fourth battery are arranged on the other side of the first power distribution unit, the second power distribution unit and the third power distribution unit.

[0012] According to one embodiment of the present application, the first battery pack and the second battery are isolated from each other, the third battery pack and the fourth battery pack are isolated from each other, and the first power distribution unit, the second power distribution unit and the third power distribution unit are isolated from each other.

[0013] According to one embodiment of the present application, the first flight drive motor group and the second flight drive motor group are vertical lift motor groups, and the third flight drive motor is a tail motor.

[0014] According to one embodiment of the present application, the power distribution system includes: a charger, which is respectively connected to a first power supply unit, a second power supply unit and a third power supply unit, and is used to convert electric energy provided by an external charging device to charge multiple power supply units.

[0015] To achieve the above-mentioned purpose, a second embodiment of the present application proposes a flying car, including the above-mentioned power distribution system of the flying car.

[0016] According to the flying car of the embodiment of the present application, based on the above-mentioned power distribution system of the flying car, power distribution redundancy of the flying car is achieved, so that the flying car can continue to fly and land at a designated location under the premise of failure of a single power supply unit or a single motor load.

[0017] In addition, the flying car according to the above embodiment of the present application may also have the following additional technical features:

[0018] According to one embodiment of the present application, the flying car also includes: multiple electronic speed regulators, the power supply units are respectively connected to the power supply ends of the corresponding motors through the corresponding electronic speed regulators; a flight controller is connected to the control ends of the multiple electronic speed regulators, and is used to adjust the power supply voltage and current of the motor based on the electronic speed regulator to control the speed and direction of the motor.

[0019] Additional aspects and advantages of the present application will be given in part in the description below, and in part will become apparent from the description below, or will be learned through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 A connection diagram of a power distribution system of a flying car according to an embodiment of the present application;

[0021] Figure 2 This is a circuit connection diagram of a power distribution system of a flying car according to a specific embodiment of the present application;

[0022] Figure 3 A connection diagram of a power distribution system of a flying car according to an embodiment of the present application;

[0023] Figure 4 A schematic diagram of the distribution of a power distribution system of a flying car according to a specific embodiment of the present application;

[0024] Figure 5 Schematic diagram of a flying car according to an embodiment of the present application. DETAILED DESCRIPTION

[0025] Embodiments of the present application are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present application, and should not be construed as limiting the present application.

[0026] The power distribution system and flying car of the flying car proposed in the embodiments of the present application are described below with reference to the accompanying drawings.

[0027] Figure 1 Schematic diagram of the connection of the power distribution system of the flying car according to an embodiment of the present application.

[0028] like Figure 1 As shown, the flying car includes a first flight drive motor group 200 and a second flight drive motor group 300, and the first flight drive motor group 200 and the second flight drive motor group 300 are both symmetrically arranged along the axis direction of the flying car. The power distribution system 100 of the flying car of the embodiment of the present application may include: a first power supply unit 10, used to supply power to the first flight drive motor group 200; a second power supply unit 20, used to supply power to the second flight drive motor group 300; a controller 30, used to control the first power supply unit 10 and the second power supply unit 20 based on the operating parameters of the first flight drive motor group 200, the second flight drive motor group 300, the first power supply unit 10 and the second power supply unit 20, so as to maintain the flight state of the flying car when one or more drive motors in the first flight drive motor group 200 and the second flight drive motor group 300 fail or one of the first power supply unit 10 and the second power supply unit 20 fails.

[0029] Specifically, the first flight drive motor group 200 and the second flight drive motor group 300 respectively include a plurality of drive motors, which are redundant with each other. For example, the first flight drive motor group 200 and the second flight drive motor group 300 respectively include a plurality of vertical motors for controlling the rotation of the propellers and providing the lift force for the aircraft to be used for the vertical take-off and landing control of the flying car. The plurality of vertical motors are symmetrically distributed at the wing positions along the axis of the flying car, such as Figure 2 and Figure 3 As shown, the first flight drive motor group 200 includes motor 1, motor 2, motor 7 and motor 8, and the second flight drive motor group 300 includes motor 3, motor 4, motor 5 and motor 6.

[0030] The first power supply unit 10 and the second power supply unit 20 are used to output electric energy to the first flight drive motor group 200 and the second flight drive motor group 300. The capacity of the power supply unit can be determined according to the number of motor loads and the design requirements of the flying car.

[0031] During the operation of the flying car, the controller 30 acquires the operating parameters of the first flight drive motor group 200, the second flight drive motor group 300, the first power supply unit 10 and the second power supply unit 20 in real time to monitor the working status of the first flight drive motor group 200, the second flight drive motor group 300, the first power supply unit 10 and the second power supply unit 20, and controls the first power supply unit 10 and the second power supply unit 20 to maintain the flight status of the flying car. For example, in the case of failure of the first power supply unit 10, the function of the first flight drive motor group 200 fails, and the controller 30 can increase the power of the second flight drive motor group 300 by increasing the output of the second power supply unit 20, so that the flying car continues to fly; or when a single motor in the first flight drive motor group 200 and the second flight drive motor group 300 fails, the controller 30 can also increase the power of the adjacent motors to keep the flying car flying.

[0032] Therefore, this embodiment is based on the power supply design of the first power supply unit 10 and the second power supply unit 20 corresponding to the first flight drive motor group 100 and the second flight drive motor group 200, which can achieve power supply redundancy for the power system of the flying car, so that when the motor fails or one of the power supply units fails, the flying state of the flying car can still be maintained, so that the flying car can continue to fly a certain distance to safely land at a designated location, thereby improving operational safety.

[0033] In one embodiment of the present application, the circuit structure of the first power supply unit 10 is the same as that of the second power supply unit 20, wherein the first power supply unit 10 includes: a first battery pack; a first power distribution unit, the first power distribution unit includes a plurality of first power supply branches, the input ends of the plurality of first power supply branches are connected to the output end of the first battery pack, the output ends of the plurality of first power supply branches are respectively connected to the power supply ends of the motors in the first flight drive motor group 200, and each first power supply branch is connected in series with a controllable switch.

[0034] Specifically, the first battery pack is used for storing and outputting electric energy, and the capacity of the first battery pack can be designed according to the number and design requirements of the load devices in the first flight drive motor group 200 .

[0035] The first power distribution unit is used to manage and control the on and off of the output of electrical energy from the first battery pack to the load. A controllable switch, such as a contactor, a relay, an electronic switch tube, etc., is provided for each power supply branch. When a load device on a certain line fails, the controllable switch of the line is urgently cut off to prevent the load device on this line from affecting the power supply of other lines.

[0036] The second power supply unit 20 has the same circuit structure as the first power supply unit 10. Figure 2 and Figure 3 For example, the first flight drive motor group 200 includes motor 1, motor 2, motor 7 and motor 8, the first power supply unit 10 includes a first battery pack (battery pack 1) and a first power distribution unit (PDU1), and the first power distribution unit (PDU1) is provided with four first power supply branches, which are respectively connected to motor 1, motor 2, motor 7 and motor 8, and each first power supply branch is provided with a contactor to control the power supply on and off. The second flight drive motor group 300 includes motor 3, motor 4, motor 5 and motor 6, the second power supply unit 20 includes a second battery pack (battery pack 2) and a second power distribution unit (PDU2), and the second battery pack (battery pack 2) is provided with four second power supply branches, which are respectively connected to motor 3, motor 4, motor 5 and motor 6, and each second power supply branch is provided with a contactor to control the power supply on and off.

[0037] Combination Figure 4 As shown, in one embodiment of the present application, the flying car includes a third flight drive motor 400, and the power distribution system 100 also includes a third power supply unit 40, the third power supply unit 40 includes: a third battery pack and a fourth battery pack; a third power distribution unit, the third power distribution unit includes two third power supply branches, the input ends of the two third power supply branches are respectively connected to the third battery pack and the fourth battery pack, the output ends of the two third power supply branches are connected to the power supply end of the third flight drive motor 400, and the third power supply branch and the fourth power supply branch are respectively connected in series with controllable switches.

[0038] Specifically, the third battery pack and the fourth battery pack are used for storing and outputting electric energy, and the capacity of the battery pack can be designed according to the number and design requirements of the load devices in the third flight drive motor 400 .

[0039] The third power distribution unit is used to manage and control the on and off of the third battery pack and the fourth battery pack outputting electrical energy to the load. A controllable switch is provided for each power supply branch, such as a contactor, a relay, an electronic switch tube, etc. When a battery pack fails in a certain line, the controllable switch of that line is cut off in an emergency to prevent that line from affecting the power supply of other lines.

[0040] Taking the third flight drive motor 400 as a tail thrust motor as an example, Figure 2 and Figure 3 As shown, the third flight drive motor 400 is motor 9, the third battery pack (battery pack 3) and the fourth battery pack (4) are connected in parallel to the busbar, and then the busbar supplies power to the tail thrust motor. At the same time, a contactor is added to the rear end of each battery pack 3 and battery pack 4. When the controller 30 detects that a single battery pack has a problem, the contactor is quickly cut off to prevent the fault from spreading. It can be achieved that a single battery pack in the tail thrust motor power supply unit fails, and the motor can still continue to fly.

[0041] In one embodiment of the present application, the second power supply unit 20 includes a second battery pack and a second power distribution unit, the first power distribution unit, the second power distribution unit and the third power distribution unit are arranged in the middle of the cabin of the flying car, and the first battery pack, the second battery, the third battery pack and the fourth battery are arranged on both sides of the first power distribution unit, the second power distribution unit and the third power distribution unit along the axial direction of the cabin.

[0042] Specifically, continue with Figure 2 and Figure 3 For example, the first battery pack is battery pack 1, the second battery pack is battery pack 2, the third battery pack is battery pack 3, the fourth battery pack is battery pack 4, the first power distribution unit is PDU1, the second power distribution unit is PDU2, and the third power distribution unit is PDU3. In one embodiment, the weight of battery pack 1 and battery pack 2 is set to be the same, and the weight of battery pack 3 and battery pack 4 is the same, so the sum of the weight of battery pack 1 and battery pack 3 is the same as the sum of the weight of battery pack 2 and battery pack 4. PDU1, PDU2 and PDU3 are placed in the middle of the cabin of the flying car, which can be located at the center of mass of the flying car. Battery pack 1, battery pack 2, battery pack 3 and battery pack 4 are distributed on both sides of the designed center of mass, which is beneficial to the weight balance design of the whole vehicle and the stability of the flying car.

[0043] In one embodiment of the present application, the first battery pack and the third battery pack are arranged on one side of the first power distribution unit, the second power distribution unit and the third power distribution unit, and the second battery and the fourth battery are arranged on the other side of the first power distribution unit, the second power distribution unit and the third power distribution unit.

[0044] In other words, the power supply units of the same type of motors are distributed on both sides of the aircraft. When an unknown fault occurs in a battery pack or one side, it will not affect the power supply unit at the other end to continue to supply power, which is conducive to fault isolation and improves safety.

[0045] In one embodiment of the present application, the first battery pack and the second battery are isolated from each other, the third battery pack and the fourth battery pack are isolated from each other, and the first power distribution unit, the second power distribution unit and the third power distribution unit are isolated from each other.

[0046] Continue with Figure 2 and Figure 3 For example, in terms of structure, battery pack 1 is isolated from battery pack 2, and battery pack 3 is isolated from battery pack 4, which is conducive to fault isolation and prevents the spread of faults. PDU1, PDU2 and PDU3 are also designed for distributed isolation, so when a single PDU fails, the fault can also be prevented from spreading.

[0047] Combination Figure 2 and Figure 3 As shown, in one embodiment of the present application, the power distribution system 100 of the flying car also includes: a charger 50, which is respectively connected to the first power supply unit 10, the second power supply unit 20 and the third power supply unit 40, and is used to convert the electric energy provided by the external charging device to charge the multiple power supply units.

[0048] Specifically, Figure 2 For example, the charging gun is connected to the charger 50, and the charger 50 transforms the electric energy transmitted by the charging gun and transmits it to the battery pack 1, the battery pack 2, the battery pack 3, and the battery pack 4 to charge the battery packs.

[0049] As a specific embodiment of the present application, Figure 2 and Figure 3 As shown, the flying car includes 8 vertical lift motors (motors 1-8) and 1 tail motor (motor 9), wherein motor 1, motor 2, motor 7 and motor 8 constitute a first flight drive motor group 200, which is powered by a first power supply unit 10; motor 3, motor 4, motor 5 and motor 6 constitute a second flight drive motor group 300, which is powered by a second power supply unit 20; motor 9 is a third flight drive motor 400, which is powered by a third power supply unit 40.

[0050] In the power supply design for the vertical motor, the battery pack 1 in the first power supply unit 10 supplies power to the two vertical motors (motor 1 and motor 2) away from the left side of the cabin and the two vertical motors (motor 7 and battery 8) away from the right side of the cabin, and the battery pack 2 in the second power supply unit 20 supplies power to the two vertical motors (motor 3 and motor 4) close to the left side of the cabin and the two vertical motors (motor 5 and motor 6) close to the right side of the cabin. At the same time, a contactor is added through the PDU. When the controller 30 detects that a load device on a certain line has a fault, the contactor of the line is urgently cut off to prevent the load device on this line from affecting other lines. In addition, battery pack 1 is structurally isolated from battery pack 2, and battery pack 3 is isolated from battery pack 4 to prevent the fault from spreading;

[0051] For the power supply design of the tail thrust motor, battery pack 3 and battery pack 4 are connected in parallel to the bus, and then power is supplied to the tail thrust motor through the bus. At the same time, a contactor is added to the rear end of battery pack 3 and battery pack 4. When the controller 30 detects a problem with a single battery pack, the contactor is quickly cut off to prevent the fault from spreading.

[0052] In addition, this embodiment uses the charger 50 to charge the battery pack to perform the charging operation.

[0053] The following beneficial effects exist:

[0054] 1. It can realize the power supply redundancy design of the power system of composite wing aircraft;

[0055] 2. If a single battery pack in the vertical take-off motor power supply unit fails, the functions of the four symmetrical motors on one half will fail, but the power of the other four symmetrical motors will be increased, and the flight can still continue;

[0056] 3. Even if a single battery pack in the tail thrust motor power supply unit fails, the motor can still continue to fly;

[0057] 4. When a single vertical take-off motor fails, the adjacent motors can increase power and the aircraft can continue to fly;

[0058] 5. The batteries are distributed, which is conducive to fault isolation;

[0059] 6. The batteries are arranged symmetrically, which is beneficial to the stability of the aircraft.

[0060] In summary, according to the power distribution system of the flying car of the embodiment of the present application, the first power supply unit supplies power to the first flight drive motor group, and the second power supply unit supplies power to the second flight drive motor group. The controller controls the first power supply unit and the second power supply unit based on the operating parameters of the first flight drive motor group, the second flight drive motor group, the first power supply unit, and the second power supply unit, so as to maintain the flight state of the flying car when one or more drive motors in the first flight drive motor group and the second flight drive motor group fail or one of the first power supply unit and the second power supply unit fails. Thus, the system realizes power distribution redundancy for the flying car, and can enable the flying car to continue to fly and land at a designated location under the premise of failure of a single power supply unit or a single motor load.

[0061] Corresponding to the above embodiments, the present application also proposes a flying car.

[0062] like Figure 5 As shown, the flying car 1000 of the embodiment of the present application includes the above-mentioned flying car power distribution system 100.

[0063] According to one embodiment of the present application, the flying car also includes: multiple electronic speed regulators, the power supply units are respectively connected to the power supply ends of the corresponding motors through the corresponding electronic speed regulators; a flight controller is connected to the control ends of the multiple electronic speed regulators, and is used to adjust the power supply voltage and current of the motor based on the electronic speed regulator to control the speed and direction of the motor.

[0064] Specifically, combined Figure 2 As shown, the flight controller is controller 30, the flying car includes 8 vertical lift motors (motors 1-8), 1 tail thrust motor (motors 9) and 9 electronic speed regulators (electronic speed regulators 1-9), 4 battery packs (battery packs 1-4), 3 power distribution units (PDU1-3), controller 30 and charger 50. The vertical lift motors are symmetrically distributed on both sides of the cabin, and a redundant design method is adopted in which two groups of batteries (battery pack 1 and battery pack 2) are used to supply power to the symmetrical motors on both sides of the cabin, respectively. The tail thrust motor adopts a redundant design method in which two groups of battery packs (battery pack 3 and battery pack 4) are used to supply power to one motor. Among them, battery pack 1 supplies power to the electronic speed regulators (electronic speed regulators 1, 2, 7, 8) corresponding to motors 1, 2, 7 and 8, respectively, battery pack 2 supplies power to the electronic speed regulators (electronic speed regulators 3, 4, 5, 6) corresponding to motors 3, 4, 5 and 6, respectively, and battery packs 3 and 4 are connected in parallel to supply power to the electronic speed regulator (electronic speed regulator 9) corresponding to the tail thrust motor.

[0065] The electronic speed regulator is used to control the speed and torque of the motor. Each motor is provided with an electronic speed regulator to prevent a single motor failure from affecting the electric speed regulator and then affecting multiple motors, and to prevent an electric speed regulator failure from affecting multiple motors. At this time, the controller 30 is used to monitor the status of the battery pack, PDU, electric speed regulator, motor, and charger in real time, control the charging and discharging of the battery pack, control the PDU contactor to close, control the output current of the electric speed regulator, etc.

[0066] According to the flying car of the embodiment of the present application, based on the above-mentioned power distribution system of the flying car, power distribution redundancy of the flying car is achieved, so that the flying car can continue to fly and land at a designated location under the premise of failure of a single power supply unit or a single motor load.

[0067] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

[0068] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of this application, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0069] In this application, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0070] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limitations on the present application. Ordinary technicians in the field can change, modify, replace and modify the above embodiments within the scope of the present application.

Claims

1. A power distribution system for a flying car, characterized in that: The flying car comprises a first flight drive motor group and a second flight drive motor group, wherein the first flight drive motor group and the second flight drive motor group are both symmetrically arranged along the axis direction of the flying car, and the power distribution system comprises: A first power supply unit, used to supply power to the first flight drive motor group; a second power supply unit, used to supply power to the second flight drive motor group; A controller is used to control the first power supply unit and the second power supply unit based on the operating parameters of the first flight drive motor group, the second flight drive motor group, the first power supply unit and the second power supply unit, so as to maintain the flight state of the flying car when one or more drive motors in the first flight drive motor group and the second flight drive motor group fail or one of the first power supply unit and the second power supply unit fails.

2. The power distribution system of the flying car according to claim 1, characterized in that: The first power supply unit has the same circuit structure as the second power supply unit, wherein the first power supply unit includes: The first battery pack; A first power distribution unit, wherein the first power distribution unit comprises a plurality of first power supply branches, wherein input ends of the plurality of first power supply branches are connected to output ends of the first battery pack, output ends of the plurality of first power supply branches are respectively connected to power supply ends of motors in the first flight drive motor group, and each first power supply branch is respectively connected in series with a controllable switch.

3. The power distribution system of the flying car according to claim 2, characterized in that: The flying car includes a third flying drive motor, and the power distribution system also includes a third power supply unit, and the third power supply unit includes: a third battery pack and a fourth battery pack; A third power distribution unit, wherein the third power distribution unit comprises two third power supply branches, wherein input ends of the two third power supply branches are respectively connected to the third battery pack and the fourth battery pack, wherein output ends of the two third power supply branches are connected to the power supply end of the third flight drive motor, and the third power supply branch and the fourth power supply branch are respectively connected in series with controllable switches.

4. The power distribution system of the flying car according to claim 3, characterized in that: The second power supply unit includes a second battery pack and a second power distribution unit. The first power distribution unit, the second power distribution unit and the third power distribution unit are arranged in the middle of the cabin of the flying car. The first battery pack, the second battery, the third battery pack and the fourth battery are arranged on both sides of the first power distribution unit, the second power distribution unit and the third power distribution unit along the axial direction of the cabin.

5. The power distribution system of the flying car according to claim 4, characterized in that: The first battery pack and the third battery pack are arranged on one side of the first power distribution unit, the second power distribution unit and the third power distribution unit, and the second battery and the fourth battery are arranged on the other side of the first power distribution unit, the second power distribution unit and the third power distribution unit.

6. The power distribution system of the flying car according to claim 4, characterized in that: The first battery pack and the second battery are isolated from each other, the third battery pack and the fourth battery pack are isolated from each other, and the first power distribution unit, the second power distribution unit and the third power distribution unit are isolated from each other.

7. The power distribution system of the flying car according to claim 3, characterized in that: The first flight drive motor group and the second flight drive motor group are vertical lift motor groups, and the third flight drive motor is a tail motor.

8. The power distribution system of the flying car according to claim 3, characterized in that: The power distribution system comprises: A charger, the charger is connected to the first power supply unit, the second power supply unit and the third power supply unit respectively, and is used to convert electric energy provided by an external charging device to charge the multiple power supply units.

9. A flying car, characterized in that: A power distribution system for a flying car comprising any one of claims 1-8.

10. The power distribution system of the flying car according to claim 9, characterized in that: The flying car also includes: A plurality of electronic speed regulators, the power supply units are connected to the power supply terminals of the corresponding motors through the corresponding electronic speed regulators; The flight controller is connected to the control ends of the multiple electronic speed regulators and is used to adjust the power supply voltage and current of the motor based on the electronic speed regulator to control the speed and direction of the motor.

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