Electric aircraft, power distribution system, power supply control method and computer storage medium

Abstract

The invention discloses an electric aircraft, a power distribution system, a power supply control method and a computer storage medium, and the power distribution system of the electric aircraft comprises a first battery pack, a second battery pack, a first isolation device and a second isolation device. Wherein the first battery pack and the second battery pack supply power to the first part of rotor wing motors through the first isolation device, supply power to the second part of rotor wing motors through the second isolation device, and the first isolation device and the second isolation device perform isolation and power reconstruction of a fault line when the power distribution system has a power supply fault. The embodiment of the invention is simple in structure and low in cost.

Description

Technical Field

[0001] The present invention relates to the field of vehicle technology, and in particular to an electric aircraft and a power distribution system, a power supply control method, and a computer storage medium. Background Art

[0002] Electric aircraft refers to machines that fly by driving objects with electricity, such as drones, flying cars, etc. At present, all electric aircraft are multi-rotor structures, such as quad-rotors, hexacopters, octo-rotors, and twelve-rotors, that is, multiple arms are symmetrically arranged on the fuselage, and each arm is provided with a propeller. By adjusting the speed and pulling force distribution of each propeller, the six degrees of freedom of the whole machine, namely pitch, roll, yaw, forward and backward flight, side flight, and lifting and lowering, can be controlled.

[0003] During the flight of an electric aircraft, if a single propeller fails, the remaining propellers will not be able to properly control the yaw motion freedom of the entire aircraft, resulting in an uncontrollable flight attitude of the aircraft, which may cause a catastrophic accident. Therefore, for electric aircraft with high safety requirements, it is usually necessary to consider adding other means to ensure that the six motion degrees of freedom of the aircraft can still be controlled simultaneously after a single propeller fails. For example, arbitrarily select two symmetrical arms from the aircraft's arms, install two small ducts or thrust propellers on these two arms respectively, and directly apply a yaw torque to the aircraft through the small ducts or thrust propellers after a single propeller fails. This is an effective means to achieve simultaneous control of the six motion degrees of freedom after a single propeller fails.

[0004] However, the power supply structure for providing power to various flight control components of electric aircraft in the existing technology is very complex and costly. Summary of the invention

[0005] The main purpose of the present invention is to provide an electric aircraft and its power distribution system, power supply control method, and computer storage medium to solve the problem that the power distribution system of the existing electric aircraft is complex in structure and high in cost.

[0006] To achieve the above-mentioned object, the present invention provides a power distribution system for an electric aircraft, wherein the electric aircraft comprises a fuselage, a plurality of rotors arranged on the fuselage, and a rotor motor corresponding to driving the rotors to work, and the rotor motor is divided into two parts; the power distribution system comprises: a first battery pack, a second battery pack, a first isolation device, and a second isolation device;

[0007] The first battery pack and the second battery pack are electrically connected to the first part of the rotor motor through the first isolation device, so as to provide power to the first part of the rotor motor;

[0008] The first battery pack and the second battery pack are electrically connected to the second part of the rotor motor through the second isolation device, so as to provide power to the second part of the rotor motor;

[0009] When a power supply failure occurs in the power distribution system, the first isolation device and the second isolation device isolate the faulty line and reconstruct the power supply line.

[0010] Optionally, the first part of the rotor motors includes two groups of rotor motors, each group of rotor motors includes two symmetrically arranged rotor motors; the first isolation device includes: a bidirectional isolation component, a first intelligent protection component, and a second intelligent protection component;

[0011] One end of the first intelligent protection component is electrically connected to the first battery pack via a first bus bar, and the other end of the first intelligent protection component is electrically connected to a group of rotor motors in the first part of the rotor motors;

[0012] One end of the second intelligent protection component is electrically connected to the second battery pack via a second bus bar, and the other end of the second intelligent protection component is electrically connected to another group of rotor motors in the first part of the rotor motors;

[0013] One end of the bidirectional isolation component is electrically connected to the first intelligent protection component, and the other end of the bidirectional isolation component is electrically connected to the second intelligent protection component, and is used for being disconnected when triggered by a short-circuit current.

[0014] Optionally, the second isolation device comprises a one-way isolation component group arranged corresponding to the second part of the rotor motor, and each one-way isolation component group comprises two one-way isolation components;

[0015] One end of one unidirectional isolation component in the unidirectional isolation component group is electrically connected to the first battery pack through a first busbar, and one end of the other unidirectional isolation component is electrically connected to the second battery pack through a second busbar; the other ends of the two unidirectional isolation components in the unidirectional isolation group are both electrically connected to the same rotor motor.

[0016] Optionally, the second part of the rotor motor includes two symmetrically arranged rotor motors, a first ducted motor, and a second ducted motor; the one-way isolation component group includes 3 groups, and the first ducted motor and the second ducted motor are both electrically connected to the same group of the one-way isolation component group.

[0017] Optionally, the second part of the rotor motor includes at least two groups of rotor motors, each group of rotor motors includes two symmetrically arranged rotor motors; the one-way isolation component group includes at least 4 groups, and the one-way isolation component group is electrically connected to the second part of the rotor motors accordingly.

[0018] Optionally, the first intelligent protection component is provided with a first controller, and the second intelligent protection component is provided with a second controller; the first controller is used to control whether the first intelligent protection component is disconnected according to the working status of the bidirectional isolation component and the working status of the second isolation device; the second controller is used to control whether the second intelligent protection component is disconnected according to the working status of the bidirectional isolation component and the working status of the second isolation device.

[0019] Optionally, the power distribution system further comprises a control device, which controls the working states of the first isolation device and the second isolation device to isolate the faulty line and reconstruct the power supply line when a power supply failure occurs in the power distribution system.

[0020] Optionally, the bidirectional isolation component includes a bidirectional switch unit; and / or the unidirectional isolation component includes a unidirectional switch unit; and / or the first intelligent protection component and the second intelligent protection component both include a fuse unit.

[0021] An embodiment of the present invention also provides an electric aircraft, comprising a fuselage, a plurality of rotors arranged on the fuselage, and a rotor motor corresponding to driving the rotors, and the rotor motor is divided into two parts; the electric aircraft also includes a power distribution system for providing power to the rotor motor, and the power distribution system is the power distribution system described in any of the above embodiments.

[0022] The embodiment of the present invention further provides a power supply control method for an electric aircraft, comprising:

[0023] During the power supply process, when a short-circuit current caused by a line fault in the power distribution system is detected, the working states of the first isolation device and the second isolation device are controlled to isolate the faulty line from the power distribution system and reconstruct the remaining power supply lines.

[0024] Optionally, the power distribution system is the power distribution system described in the above embodiment; when a short-circuit current caused by a line fault in the power distribution system is detected, the step of controlling the working states of the first isolation device and the second isolation device to isolate the faulty line from the power distribution system includes:

[0025] When a short-circuit current caused by a down-circuit fault in the power distribution system is detected, the bidirectional isolation component is controlled to be disconnected;

[0026] Determine whether it is necessary to control the first intelligent protection component and the second intelligent protection component to be disconnected according to the short-circuit current direction detected by the bidirectional isolation component and the working state of the unidirectional isolation component;

[0027] According to the determination result, the working states of the first smart protection component and the second smart protection component are controlled.

[0028] Optionally, the power distribution system is the power distribution system described in the above embodiment; when a short-circuit current caused by a line fault in the power distribution system is detected, the step of controlling the working states of the first isolation device and the second isolation device to isolate the faulty line from the power distribution system includes:

[0029] The bidirectional isolation component disconnects the electrical connection between the first intelligent protection component and the second intelligent protection component when a short-circuit current is detected;

[0030] The bidirectional isolation component determines the target intelligent protection component to be controlled according to the direction of the short-circuit current, and sends a control instruction to a controller corresponding to the target intelligent protection component;

[0031] The controller corresponding to the target intelligent protection component determines whether to control the target intelligent protection component to be disconnected according to the working status of all unidirectional isolation components;

[0032] According to the determination result, the target intelligent protection component is controlled to be disconnected.

[0033] Optionally, the step of the bidirectional isolation component determining a target intelligent protection component to be controlled according to the direction of the short-circuit current includes:

[0034] When the short-circuit current flows from the first intelligent protection component to the second intelligent protection component, the second intelligent protection component is determined as the target intelligent protection component;

[0035] When the short-circuit current flows from the second intelligent protection component to the first intelligent protection component, the first intelligent protection component is determined as the target intelligent protection component.

[0036] Optionally, the controller corresponding to the target intelligent protection component determines whether to control the target intelligent protection component to disconnect according to the working status of all the one-way isolation components, including:

[0037] When all the one-way isolation components are in a closed state, determining to control the target intelligent protection component to be disconnected;

[0038] When at least one one-way isolation component is in a disconnected state, it is determined that the target intelligent protection component is not disconnected.

[0039] Optionally, the step of controlling the working states of the first isolation device and the second isolation device to reconstruct the remaining power supply lines includes:

[0040] Controls the closing of the bidirectional isolation component.

[0041] An embodiment of the present invention further provides a computer storage medium, characterized in that the computer storage medium stores a power supply control program, and when the power supply control program is executed by the processor, each step of the power supply control method described in any of the above embodiments is implemented.

[0042] The embodiment of the present invention proposes a power distribution system with a simple structure and low cost, which uses a first isolation device to isolate a part of the load and its power supply short-circuit fault, and uses a second isolation device to isolate another part of the load and its power supply short-circuit fault. The two methods are combined to meet the system safety requirements (independence of power supply and load power distribution) while reducing the number of battery packs and the amount of isolation components used, thereby achieving lightweight of the entire machine and reducing system costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] Figure 1 It is a schematic diagram of the structure of the power distribution system of the electric aircraft in the prior art;

[0044] Figure 2 is a schematic structural diagram of a power distribution system of an electric aircraft according to an embodiment of the present invention;

[0045] Figure 3 is a schematic diagram of the structure of a six-rotor electric aircraft in an embodiment of the present invention;

[0046] Figure 4 The embodiment of the present invention is directed to Figure 3 A schematic diagram of a power distribution system of an electric aircraft;

[0047] Figure 5 is a schematic structural diagram of an octorotor electric aircraft in an embodiment of the present invention;

[0048] Figure 6 In the embodiment of the present invention, Figure 5 A schematic diagram of a power distribution system of an electric aircraft;

[0049] Figure 7 It is a flow chart of an embodiment of a power supply control method for an electric aircraft of the present invention;

[0050] Figure 8 It is a flow chart of another embodiment of the power supply control method of the electric aircraft of the present invention.

[0051] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0052] It should be understood that the specific embodiments described herein are only used to explain the present invention, and are not used to limit the present invention.

[0053] In order to ensure the safety of the aircraft, the power supply structure of the aircraft needs to ensure that the rotor that maintains the normal flight of the aircraft and the two small ducts or thrust propellers used to control yaw after a single propeller fails do not fail at the same time (or the probability of simultaneous failure is low enough). For the aircraft's power distribution system, if any load or power supply connected to the power distribution network has a short circuit fault, if the short circuit fault is not isolated from the distribution network in time, the entire distribution network will be paralyzed. Figure 1 , Figure 1 This is a schematic diagram of the power distribution system structure of a six-rotor electric aircraft in the prior art. In order to achieve the goal of not having the rotor and the small duct or thrust propeller of the above-mentioned electric aircraft fail at the same time, someone designed the power distribution system as follows: Figure 1 The structure is that each rotor and small duct or thrust propeller of the aircraft is powered by a battery pack respectively, and the seven battery packs are independent of each other, forming seven independent power distribution networks. In this way, when a short circuit fault occurs in each power distribution network, it will only affect the power supply and load in the distribution network where it is located, and other power supplies and loads on the distribution network will still be able to work normally, thereby avoiding the simultaneous failure of the rotor and small duct or thrust propeller (or reducing the probability of simultaneous failure to a sufficiently low level).

[0054] but, Figure 1 The power supply scheme shown requires the battery pack of the electric aircraft to be split into seven battery packs. More housings, mounting structures, control components and cooling structures are required for the same power, which significantly increases the weight and cost of the battery system, and is not conducive to the lightweight design and cost control of the whole machine. At the same time, each battery pack is completely independent and cannot achieve real-time balancing, resulting in low battery power utilization (the available power is determined by the battery pack with the lowest power) and poor charging convenience (the seven battery packs cannot be charged at the same time), thus failing to ensure a good user experience.

[0055] The embodiment of the present invention proposes a power distribution system with simple structure and low cost, which utilizes bidirectional isolation components in combination with intelligent protection components to isolate a part of the load and its power short-circuit fault, and utilizes unidirectional isolation components to isolate another part of the load and its power short-circuit fault. The two methods are combined to meet the system safety requirements (independence of power supply and load power distribution) while reducing the number of battery packs and the amount of isolation components used, thereby achieving lightweight of the entire machine and reducing system costs.

[0056] Reference Figure 2 , Figure 2It is a structural block diagram of the power distribution system of the electric aircraft in an embodiment of the present invention. The electric aircraft includes a fuselage and a plurality of rotors arranged on the fuselage, and each rotor is provided with a rotor motor corresponding to the rotor, and the rotor motor is used to drive the rotor to work, such as the speed and rotation direction of the rotor. The power distribution system of the electric aircraft is used to provide power to the rotor motor of the electric aircraft, including: a first battery pack 1, a second battery pack 2, a first isolation device 3, and a second isolation device 4. The embodiment of the present invention divides the rotor motor of the electric aircraft into two parts, namely the first part rotor motor and the second part rotor motor.

[0057] The first battery pack 1 and the second battery pack 2 are electrically connected to the first part of the rotor motor through the first isolation device 3, so as to provide power to the first part of the rotor motor. The first battery pack 1 and the second battery pack 2 are electrically connected to the second part of the rotor motor through the second isolation device 4, so as to provide power to the second part of the rotor motor.

[0058] When a power supply fault occurs in the power distribution system, the first isolation device 3 and the second isolation device 4 isolate the faulty line and reconstruct the power supply line.

[0059] The embodiment of the present invention uses the first isolation device and the second isolation device to isolate the faulty line and reconstruct the remaining power supply lines, so that the two battery packs in the power distribution system can achieve grid-connected output, and the short-circuit fault in the power distribution system is quickly isolated without affecting the normal operation of other power supply lines. Therefore, the power distribution system of the electric aircraft in the embodiment of the present invention can achieve the lightweight of the entire aircraft and reduce costs while achieving the safety goal of the aircraft.

[0060] In one embodiment, the first isolation device 1 includes a bidirectional isolation component 10, a first intelligent protection component 12, and a second intelligent protection component 14. One end of the first intelligent protection component 12 is electrically connected to the first battery pack 1 through a first bus bar BUS1, and the other end of the first intelligent protection component 12 is electrically connected to a group of rotor motors in the first part of the rotor motors.

[0061] One end of the second intelligent protection component 14 is electrically connected to the second battery pack 2 via the second bus bar BUS2 , and the other end of the second intelligent protection component 14 is electrically connected to another group of rotor motors in the first part of the rotor motors.

[0062] One end of the bidirectional isolation component 10 is electrically connected to the first intelligent protection component 12 , and the other end of the bidirectional isolation component 10 is electrically connected to the second intelligent protection component 14 . The bidirectional isolation component is disconnected when triggered by a short-circuit current.

[0063] The current direction in the bidirectional isolation component 10 includes flowing from the first intelligent protection component 12 to the second intelligent protection component 14, and flowing from the second intelligent protection component 14 to the first intelligent protection component 12. The bidirectional isolation component is, for example, a bidirectional isolation switch, which is in a closed state under normal working conditions, and is quickly switched to an open state when a short-circuit current flows through the switch. At the same time, the bidirectional isolation component can also detect the direction of the current, for example, whether the current flows from the first intelligent protection component 12 to the second intelligent protection component 14, or from the second intelligent protection component 14 to the first intelligent protection component 12.

[0064] The first intelligent protection component 12 and the second intelligent protection component 14 include, for example, a fuse unit, which is used to receive a control signal and actively blow a fuse based on the control signal, and cannot be restored after blowing a fuse.

[0065] Furthermore, the first intelligent protection component 12 is electrically connected to the bidirectional isolation component 10 and a group of rotor motors through the third bus BUS3. The second intelligent protection component 14 is electrically connected to the bidirectional isolation component 10 and another group of rotor motors through the fourth bus BUS4.

[0066] In the above embodiment, the bidirectional isolation component 10 is quickly disconnected when a short circuit current occurs, and at the same time, a control instruction is sent to the corresponding intelligent protection component according to the current direction, so that the intelligent protection component actively blows and isolates the faulty line.

[0067] In one embodiment, the second isolation device 2 includes a unidirectional isolation component group 20 arranged corresponding to the second partial rotor motor, and each unidirectional isolation component group 20 includes two unidirectional isolation components 21.

[0068] One end of a unidirectional isolation component 21a in the unidirectional isolation component group 20 is electrically connected to the first battery pack 1 through the first bus BUS1, and one end of the other unidirectional isolation component 21b is electrically connected to the second battery pack 2 through the second bus BUS2; the other ends of the two unidirectional isolation components in the unidirectional isolation group 20 are both electrically connected to the same rotor motor.

[0069] The unidirectional isolation component 21 includes, for example, a unidirectional isolation switch, which is disconnected when triggered by a short-circuit current. The structure of the unidirectional isolation component 21 is similar to that of the bidirectional isolation component 10, except that the current flowing through the unidirectional isolation component 21 can only be in one direction.

[0070] In one embodiment, when a short-circuit current occurs, the bidirectional isolation component 10 in the first isolation device 3 detects the short-circuit current and disconnects quickly, and sends a control signal to the corresponding intelligent protection component according to the current direction of the short-circuit current. Specifically, when the short-circuit current direction detected by the bidirectional isolation component 10 is from the first intelligent protection component 12 to the second intelligent protection component 14, the control signal is sent to the second intelligent protection component 14; when the short-circuit current direction detected by the bidirectional isolation component 10 is from the second intelligent protection component 14 to the first intelligent protection component 12, the control signal is sent to the first intelligent protection component 12. The intelligent protection component that receives the control signal determines whether to control the intelligent protection component to disconnect according to the state of the unidirectional isolation component in the second isolation device 4.

[0071] Furthermore, a first controller 13 is correspondingly provided in the above-mentioned first intelligent protection component 12, and a second controller 15 is correspondingly provided in the above-mentioned second intelligent protection component 14; the first controller 13 is used to control whether the first intelligent protection component 12 is disconnected according to the working state of the two-way isolation component 10 and the working state of the second isolation device 4; the second controller 15 is used to control whether the second intelligent protection component 14 is disconnected according to the working state of the two-way isolation component 10 and the working state of the second isolation device 4.

[0072] Specifically, since a power supply failure occurs at any line position of the power distribution system, a short-circuit current will be caused. Therefore, when the bidirectional isolation component 10 detects a short-circuit current, it is necessary to determine whether the fault is caused by the power supply line of the second part of the rotor motor or the power supply line of the first part of the rotor motor. Therefore, based on the working state of the bidirectional isolation component 10 and the working state of the second isolation device 4, it is determined whether to control the second intelligent protection component 14 to disconnect. For example, when the bidirectional isolation component 10 is disconnected and any one of the unidirectional isolation components in the second isolation device 4 is disconnected, it is determined that the short-circuit current is caused by the power supply line fault of the second part of the rotor motor, so the first intelligent protection component 12 and the second intelligent protection component 14 are not disconnected; when the bidirectional isolation component 10 is disconnected and all the unidirectional isolation components in the second isolation device 4 are closed, it is determined that the power supply line of the first part of the rotor motor is faulty, so according to the direction of the short-circuit current, the corresponding intelligent protection component is controlled to disconnect.

[0073] In this embodiment, by setting a corresponding first controller for the first intelligent protection component and a corresponding second controller for the second intelligent protection component, the controllers can independently control the disconnection of each intelligent protection component, thereby avoiding the inability to disconnect the intelligent protection component when the controller fails, which affects the safety of the electric aircraft.

[0074] In one embodiment, the above-mentioned power distribution system also includes a control device, which controls the working state of the first isolation device and the second isolation device in the event of a power supply failure in the power distribution system, isolates the faulty line, and reconstructs the power supply line. It is understandable that the control device can be set independently from the controller of the previous embodiment, and the control device can also replace the previous embodiment to realize the functions of the controller of the previous embodiment. For example, when a short-circuit current caused by a down-circuit fault in the power distribution system is detected, the bidirectional isolation component 10 is controlled to be disconnected; according to the direction of the short-circuit current detected by the bidirectional isolation component 10 and the working state of each unidirectional isolation component 21, it is determined whether it is necessary to control the first intelligent protection component 12 and the second intelligent protection component 14 to be disconnected; according to the determination result, the working state of the first intelligent protection component 12 and the second intelligent protection component 14 is controlled.

[0075] Furthermore, after isolating the faulty power supply line, it is also necessary to control the working state of the first isolation device, that is, to close the bidirectional isolation component and restore the remaining power supply lines to the power distribution network.

[0076] Combined with reference Figure 3 and Figure 4 , Figure 3 is a schematic diagram of the structure of a six-rotor electric aircraft according to an embodiment of the present invention, Figure 4 It is a schematic diagram of the structure of the power distribution system of the six-rotor aircraft according to an embodiment of the present invention.

[0077] The six-rotor aircraft includes a fuselage and six arms, namely arm No. 1, arm No. 2, arm No. 3, arm No. 4, arm No. 5, and arm No. 6. Each arm is provided with a propeller, and arm No. 3 and arm No. 6 are provided with duct structures, namely, the first duct and the second duct. Each propeller is provided with a corresponding drive motor, namely, the propeller on arm No. 1 is provided with rotor motor No. 1, the propeller on arm No. 2 is provided with rotor motor No. 2, the propeller on arm No. 3 is provided with rotor motor No. 3, the propeller on arm No. 4 is provided with rotor motor No. 4, the propeller on arm No. 5 is provided with rotor motor No. 5, the propeller on arm No. 6 is provided with rotor motor No. 6, the first duct is provided with duct motor No. 1, and the second duct is provided with duct motor No. 2. In an embodiment of the present invention, the first part of rotor motors includes rotor motor No. 1, rotor motor No. 4, rotor motor No. 3, and rotor motor No. 6; the second part of rotor motors includes rotor motor No. 3, rotor motor No. 5, ducted motor No. 1, and ducted motor No. 2.

[0078] The power distribution system of the hexacopter includes two battery packs, a bidirectional isolation component, two intelligent protection components, six unidirectional isolation components and a number of busbars.

[0079] Specifically, the first battery pack 1 is connected to the first bus BUS1, and the second battery pack 2 is connected to the second bus BUS2. The No. 1 rotor motor and the No. 4 rotor motor are connected to the third bus BUS3, and the third bus BUS3 is connected to the first bus BUS1 through the first intelligent protection component 12, and is used to receive the power input of the first battery pack 1, and supply power to the No. 1 rotor motor and the No. 4 rotor motor. The No. 3 rotor motor and the No. 4 rotor motor are connected to the fourth bus BUS4, and the fourth bus BUS4 is connected to the second bus BUS2 through the second intelligent protection component 14, and is used to receive the power input of the second battery pack 2, and supply power to the No. 3 rotor motor and the No. 6 rotor motor.

[0080] The third busbar BUS3 and the fourth busbar BUS4 are connected via a bidirectional isolation component 10. The bidirectional isolation component 10 is in a normally closed state when the power distribution system is powered on to achieve real-time balancing of the power between the first battery pack 1 and the second battery pack 2. The bidirectional isolation component 10 can sense the current and current direction flowing through itself. If a short-circuit current is sensed, it will trigger a switch to an open state.

[0081] The first busbar BUS1 and the second busbar BUS2 independently supply power to the No. 2 rotor motor, the No. 5 rotor motor, the No. 1 ducted motor and the No. 2 ducted motor respectively through six unidirectional isolation components 21a-21f and the fifth busbar BUS5, the sixth busbar BUS6 and the seventh busbar BUS7.

[0082] (1) A short circuit occurs on the first busbar BUS1 or the first battery pack 1

[0083] When a short circuit fault occurs in the first bus BUS1 or the first battery pack 1 connected to the first bus BUS1, the bidirectional isolation component senses the short circuit current and is triggered to disconnect quickly. At this time, the components in the power distribution system where the short circuit fault occurs can be isolated, that is, the impact of the short circuit fault is controlled within the first bus BUS1 and the first battery pack 1 connected to the first bus BUS1, the third bus BUS3, and the No. 1 rotor motor and the No. 4 rotor motor connected to the third bus BUS3.

[0084] In order to ensure the power output of the whole machine, the third bus BUS3 and the No. 1 and No. 4 rotor motors connected to the third bus BUS3 need to be connected back to the power distribution network. Therefore, when the bidirectional isolation component is triggered to disconnect by the short-circuit current, it will feed back the short-circuit current direction (flowing from the fourth bus BUS3 to the third bus BUS2) to the controller. The controller controls the first intelligent protection component 12 to blow off according to the short-circuit current direction and the state of each unidirectional isolation component (the unidirectional isolation components 21a~21f are all in the closed state), and the impact of the short-circuit fault is controlled within the first bus BUS1 and the first battery pack 1 connected to the first bus BUS1.

[0085] At this time, the third bus BUS3 and the No. 1 and No. 4 rotor motors connected to the third bus BUS3 are in an open circuit state, and the controller sends a command to the bidirectional isolation component, which closes the bidirectional isolation component, thereby connecting the third bus BUS3 and the No. 1 and No. 4 rotor motors connected to the third bus BUS3 back to the power distribution network to achieve power reconstruction. That is, when the first bus BUS1 or the first battery pack 1 connected to the first bus BUS1 has a short circuit fault, the entire power distribution network only loses the power supply of the first battery pack 1.

[0086] (2) The second busbar BUS2 or the second battery pack has a short circuit fault

[0087] Similarly, when a short circuit fault occurs in the second bus BUS2 or the second battery pack 2 connected to the second bus BUS2, the bidirectional isolation component senses the short circuit current and is triggered to disconnect quickly. At this time, the components in the power distribution system where the short circuit fault occurs can be isolated, that is, the impact of the short circuit fault is controlled within the second bus BUS2 and the second battery pack 2 connected to the second bus BUS2, the fourth bus BUS4, and the No. 3 rotor motor and the No. 6 rotor motor connected to the fourth bus BUS4.

[0088] In order to ensure the power output of the whole machine, the fourth bus BUS4 and the No. 3 and No. 6 rotor motors connected to the fourth bus BUS4 need to be connected back to the power distribution network. Therefore, when the bidirectional isolation component is triggered to disconnect by the short-circuit current, it will feed back the short-circuit current direction (flowing from the third bus BUS3 to the fourth bus BUS4) to the controller. The controller controls the second intelligent protection component 14 to blow off according to the short-circuit current direction and the state of each unidirectional isolation component (the unidirectional isolation components 21a~21f are all in the closed state), and the impact of the short-circuit fault is controlled within the second bus BUS2 and the second battery pack 2 connected to the second bus BUS2.

[0089] At this time, the fourth bus BUS4 and the No. 3 rotor motor and the No. 6 rotor motor connected to the fourth bus BUS4 are in an open circuit state, and the controller sends a command to the bidirectional isolation component, and the bidirectional isolation component is closed, thereby connecting the fourth bus BUS4 and the No. 3 rotor motor and the No. 6 rotor motor connected to the fourth bus BUS4 back to the power distribution network to achieve power reconstruction. That is, when the second bus BUS2 or the second battery pack 2 connected to the second bus BUS2 has a short circuit fault, the entire power distribution network only loses the power supply of the second battery pack 2.

[0090] (3) A short circuit occurs on the third busbar or rotor motor No. 1 or rotor motor No. 4

[0091] When a short circuit fault occurs in the third bus BUS3 or the No. 1 rotor motor or the No. 4 rotor motor connected to the third bus BUS3, the bidirectional isolation component senses the short circuit current and is triggered to disconnect quickly by the short circuit current. At this time, the components in the power distribution system where the short circuit fault occurs can be isolated, that is, the impact of the short circuit fault is controlled within the first bus BUS1 and the first battery pack 1 connected to the first bus BUS1, the third bus BUS3 and the No. 1 rotor motor and the No. 4 rotor motor connected to the third bus BUS3.

[0092] In order to ensure the power output of the whole machine, the first busbar BUS1 and the first battery pack 1 connected to the first busbar BUS1 need to be connected back to the power supply network. Therefore, when the bidirectional isolation component is triggered to disconnect by the short-circuit current, it will feed back the short-circuit current direction (flowing from the fourth busbar BUS4 to the third busbar BUS3) to the controller. The controller controls the first intelligent protection component to blow off according to the short-circuit current direction and the state of each unidirectional isolation component (unidirectional isolation components 21a~21f are all in a closed state), thereby controlling the impact of the short-circuit fault to the third busbar BUS3 and the No. 1 and No. 4 rotor motors connected to the third busbar BUS3, and the first busbar BUS1 and the first battery pack 1 connected to the first busbar BUS1 resume power supply to the distribution network.

[0093] Therefore, when a short circuit occurs in the third bus BUS3 or rotor motor No. 1 or rotor motor No. 4 connected to the third bus BUS3, the entire power distribution network only loses the output of rotor motor No. 1 and rotor motor No. 4. Since rotor No. 1 and rotor No. 4 are arranged symmetrically on the aircraft, it is acceptable for them to lose power at the same time.

[0094] (4) A short circuit occurs on the fourth busbar BUS4 or the No. 3 rotor motor or the No. 6 rotor motor.

[0095] Similarly, when a short circuit occurs in the fourth bus BUS4 or the No. 3 rotor motor or the No. 6 rotor motor connected to the fourth bus BUS4, the bidirectional isolation component senses the short circuit current and is triggered to disconnect quickly by the short circuit current. At this time, the components in the power distribution system where the short circuit occurs can be isolated, that is, the impact of the short circuit failure is controlled within the second bus BUS2 and the second battery pack 2 connected to the second bus BUS2, the fourth bus BUS4 and the No. 3 rotor motor and the No. 6 rotor motor connected to the fourth bus BUS4.

[0096] In order to ensure the power output of the whole machine, the second bus BUS2 and the battery pack 2 connected to the second bus BUS2 need to be connected back to the power distribution network. Therefore, when the bidirectional isolation component is triggered to disconnect by the short-circuit current, it will feed back the short-circuit current direction (flowing from the third bus BUS3 to the fourth bus BUS4) to the controller. The controller controls the second intelligent protection component to blow off according to the short-circuit current direction and the state of each unidirectional isolation component (unidirectional isolation components 21a~21f are all in a closed state), thereby controlling the impact of the short-circuit fault to the fourth bus BUS4 and the No. 3 rotor motor and No. 6 rotor motor connected to the fourth bus BUS4, and the second bus BUS2 and the second battery pack 2 connected to the second bus BUS2 resume power supply to the power distribution network.

[0097] Therefore, when a short circuit occurs in the fourth bus BUS4 or the rotor motor No. 3 or rotor motor No. 6 connected to the fourth bus BUS4, the entire power distribution network only loses the output of rotor motor No. 3 and rotor motor No. 6. Since rotor No. 3 and rotor No. 6 are arranged symmetrically on the aircraft, it is acceptable for them to lose power at the same time.

[0098] (5) At least one of the loads in rotor motor No. 2, rotor motor No. 5, ducted motor No. 1, and ducted motor No. 2 is short-circuited.

[0099] When any one or several loads among rotor motor No. 2, rotor motor No. 5, ducted motor No. 1 and ducted motor No. 2 have a short circuit fault, the two unidirectional isolation components connected to the short-circuited loads are triggered by the short-circuit current and quickly disconnected, thereby isolating the short circuit fault.

[0100] At the same time, the bidirectional isolation component may also sense a large short-circuit current, be triggered to disconnect by the short-circuit current, and feed back the direction of the short-circuit current to the controller. Since the unidirectional isolation component connected to the short-circuit load in each unidirectional isolation component is in a disconnected state, the first intelligent protection component and the second intelligent protection component are not blown off.

[0101] Therefore, when any load of rotor motor No. 2 or No. 5 has a short circuit fault, the entire distribution network only loses the output of the motor with the short circuit fault. When any load of ducted motor No. 1 or No. 2 has a short circuit fault, the entire distribution network only loses the output of ducted motor No. 1 and No. 2, and the output of the six rotor motors is not affected, which does not affect the safety of the entire machine.

[0102] Combined with reference Figure 5 and Figure 6 , Figure 5 is a schematic diagram of the structure of an octorotor aircraft according to an embodiment of the present invention, Figure 6 It is a schematic diagram of the structure of the power distribution system of the octorotor aircraft according to an embodiment of the present invention.

[0103] The eight-rotor aircraft includes a fuselage and eight arms, namely arm No. 1, arm No. 2, arm No. 3, arm No. 4, arm No. 5, arm No. 6, arm No. 7, and arm No. 8, each of which is provided with a propeller. Each propeller is provided with a corresponding drive motor, that is, the propeller on arm No. 1 is provided with rotor motor No. 1, the propeller on arm No. 2 is provided with rotor motor No. 2, the propeller on arm No. 3 is provided with rotor motor No. 3, the propeller on arm No. 4 is provided with rotor motor No. 4, the propeller on arm No. 5 is provided with rotor motor No. 5, the propeller on arm No. 6 is provided with rotor motor No. 6, the propeller on arm No. 7 is provided with rotor motor No. 7, and the propeller on arm No. 8 is provided with rotor motor No. 8. In this embodiment, the first part of the rotor motors includes rotor motor No. 1, rotor motor No. 5, rotor motor No. 3, and rotor motor No. 7; the second part of the rotor motors includes rotor motor No. 2, rotor motor No. 4, rotor motor No. 6, and rotor motor No. 8.

[0104] The power distribution system of the octorotor aircraft includes two battery packs, a bidirectional isolation component, two intelligent protection components, eight unidirectional isolation components and several busbars.

[0105] Specifically, the first battery pack 1 is connected to the first bus BUS1, and the second battery pack 2 is connected to the second bus BUS2. The No. 1 rotor motor and the No. 5 rotor motor are connected to the third bus BUS3, and the third bus BUS3 is connected to the first bus BUS1 through the first intelligent protection component, and is used to receive the power input of the first battery pack 1 and supply power to the No. 1 rotor motor and the No. 5 rotor motor. The No. 3 rotor motor and the No. 7 rotor motor are connected to the fourth bus BUS4, and the fourth bus BUS4 is connected to the second bus BUS2 through the second intelligent protection component, and is used to receive the power input of the second battery pack 2 and supply power to the No. 3 rotor motor and the No. 7 rotor motor.

[0106] The third busbar BUS3 and the fourth busbar BUS4 are connected via a bidirectional isolation component. The bidirectional isolation component is in a normally closed state when the power distribution system is powered on to achieve real-time balance of power between the first battery pack 1 and the second battery pack 2. The bidirectional isolation component can sense the current and current direction flowing through itself. If a short-circuit current is sensed, it will trigger a switch to the disconnected state.

[0107] The first busbar BUS1 and the second busbar BUS2 supply power independently to rotor motor No. 2, rotor motor No. 4, rotor motor No. 6 and rotor motor No. 8 respectively through eight unidirectional isolation components 21a-21h and the fifth busbar BUS5, the sixth busbar BUS6, the seventh busbar BUS7 and the eighth busbar BUS8.

[0108] (1) A short circuit occurs on the first busbar BUS1 or the first battery pack 1

[0109] When a short circuit occurs in the first busbar BUS1 or the first battery pack 1 connected to the first busbar BUS1, the bidirectional isolation component senses the short circuit current and is triggered to disconnect quickly by the short circuit current. When the bidirectional isolation component is triggered to disconnect by the short circuit current, it feeds back the direction of the short circuit current (flowing from the fourth busbar BUS4 to the third busbar BUS3) to the controller. The controller controls the first intelligent protection component to blow off according to the direction of the short circuit current and the state of each unidirectional isolation component (the unidirectional isolation components 21a to 21h are all in the closed state), and controls the impact of the short circuit fault to the first busbar BUS1 and the first battery pack 1 connected to the first busbar BUS1.

[0110] Then, the controller sends an instruction to the bidirectional isolation component to switch the bidirectional isolation component to a closed state, thereby connecting the third bus BUS3 and the No. 1 rotor motor and the No. 5 rotor motor connected to the third bus BUS3 back to the power distribution network to achieve power reconstruction.

[0111] Therefore, when a short circuit fault occurs in the first busbar BUS1 or the first battery pack 1 connected to the first busbar BUS1 , the entire power distribution network only loses the power supply of the first battery pack 1 .

[0112] (2) The second busbar BUS2 or the second battery pack has a short circuit fault

[0113] Similarly, when a short circuit fault occurs in the second bus BUS2 or the second battery pack 2 connected to the second bus BUS2, the bidirectional isolation component senses the short circuit current and is triggered to disconnect quickly. At this time, the components in the power distribution system where the short circuit fault occurs can be isolated, that is, the impact of the short circuit fault is controlled within the second bus BUS2 and the second battery pack 2 connected to the second bus BUS2, the fourth bus BUS4, and the No. 3 rotor motor and the No. 7 rotor motor connected to the fourth bus BUS4.

[0114] The controller controls the second intelligent protection component to blow out according to the direction of the short-circuit current and the state of each unidirectional isolation component (the unidirectional isolation components 21a~21h are all in the closed state), thereby controlling the impact of the short-circuit fault to the second bus BUS2 and the second battery pack 2 connected to the second bus BUS2.

[0115] Then, the controller sends a command to the bidirectional isolation component, and the bidirectional isolation component is closed, thereby connecting the fourth bus BUS4 and the No. 3 rotor motor and the No. 7 rotor motor connected to the fourth bus BUS4 back to the power distribution network to achieve power reconstruction.

[0116] Therefore, when a short circuit fault occurs in the second busbar BUS2 or the second battery pack 2 connected to the second busbar BUS2 , only the power supply of the second battery pack 2 is lost in the entire power distribution network.

[0117] (3) A short circuit occurs on the third bus or on the No. 1 rotor motor or on the No. 5 rotor motor.

[0118] When a short circuit fault occurs in the third bus BUS3 or the No. 1 rotor motor or the No. 5 rotor motor connected to the third bus BUS3, the bidirectional isolation component senses the short circuit current and is triggered to disconnect quickly by the short circuit current. At this time, the components in the power distribution system where the short circuit fault occurs can be isolated, that is, the impact of the short circuit fault is controlled within the first bus BUS1 and the first battery pack 1 connected to the first bus BUS1, the third bus BUS3 and the No. 1 rotor motor and the No. 5 rotor motor connected to the third bus BUS3.

[0119] The controller controls the first intelligent protection component to blow out according to the direction of the short-circuit current and the status of each unidirectional isolation component (the unidirectional isolation components 21a~21h are all in a closed state), thereby controlling the impact of the short-circuit fault within the third bus BUS3 and the rotor motor No. 1 and the rotor motor No. 5 connected to the third bus BUS3, and the first bus BUS1 and the first battery pack 1 connected to the first bus BUS1 resume power supply to the distribution network.

[0120] Therefore, when a short circuit occurs in the third bus BUS3 or rotor motor No. 1 or rotor motor No. 5 connected to the third bus BUS3, the entire power distribution network only loses the output of rotor motor No. 1 and rotor motor No. 5. Since rotor No. 1 and rotor No. 5 are arranged symmetrically on the aircraft, it is acceptable for them to lose power at the same time.

[0121] (4) A short circuit occurs on the fourth busbar BUS4 or the No. 3 rotor motor or the No. 7 rotor motor.

[0122] Similarly, when a short circuit occurs in the fourth bus BUS4 or the No. 3 rotor motor or the No. 7 rotor motor connected to the fourth bus BUS4, the bidirectional isolation component senses the short circuit current and is triggered to disconnect quickly by the short circuit current. At this time, the components in the power distribution system where the short circuit occurs can be isolated, that is, the impact of the short circuit failure is controlled within the second bus BUS2 and the second battery pack 2 connected to the second bus BUS2, the fourth bus BUS4 and the No. 3 rotor motor and the No. 7 rotor motor connected to the fourth bus BUS4.

[0123] The controller controls the second intelligent protection component to blow out according to the direction of the short-circuit current and the state of each unidirectional isolation component (the unidirectional isolation components 21a~21h are all in the closed state), thereby controlling the impact of the short-circuit fault within the fourth bus BUS4 and the No. 3 rotor motor and the No. 7 rotor motor connected to the fourth bus BUS4, and the second bus BUS2 and the second battery pack 2 connected to the second bus BUS2 resume power supply to the distribution network.

[0124] Therefore, when a short circuit occurs in the fourth bus BUS4 or the rotor motor No. 3 or rotor motor No. 7 connected to the fourth bus BUS4, the entire power distribution network only loses the output of rotor motor No. 3 and rotor motor No. 7. Since rotor No. 3 and rotor No. 7 are arranged symmetrically on the aircraft, it is acceptable for them to lose power at the same time.

[0125] (5) At least one load of rotor motor No. 2, rotor motor No. 4, rotor motor No. 6, or rotor motor No. 8 is short-circuited.

[0126] When any one or several loads among rotor motor No. 2, rotor motor No. 4, rotor motor No. 6, and rotor motor No. 8 have a short circuit fault, the two unidirectional isolation components connected to the short-circuited loads are triggered by the short-circuit current and quickly disconnected, thereby isolating the short circuit fault.

[0127] At the same time, the bidirectional isolation component may also sense a large short-circuit current, be triggered to disconnect by the short-circuit current, and feed back the direction of the short-circuit current to the controller. Since the unidirectional isolation component connected to the short-circuit load in each unidirectional isolation component is in a disconnected state, the first intelligent protection component and the second intelligent protection component are not blown off.

[0128] Therefore, when any load among rotor motor No. 2, rotor motor No. 4, rotor motor No. 6, and rotor motor No. 8 has a short circuit fault, the entire power distribution network only loses the output of the motor with the short circuit fault.

[0129] It is understandable that if the aircraft is a twelve-rotor aircraft, that is, on the basis of the eight-rotor aircraft, four more arms are added, each arm is provided with a propeller, and each propeller is provided with a corresponding drive motor. The power distribution system of the twelve-rotor aircraft is based on the eight-rotor aircraft, and the ninth bus BUS9, the tenth bus BUS10, the eleventh bus BUS11, and the twelfth bus BUS12 are added. Each bus corresponds to the first bus BUS1 and the fourth bus BUS4 through two unidirectional isolation components. Each bus is also connected to a rotor motor for receiving power input from the first battery pack 1 and / or the second battery pack 2 to power the rotor motor. The working principle of the power distribution system of the twelve-rotor aircraft can be implemented with reference to the working principle of the power distribution system of the eight-rotor aircraft.

[0130] The present invention also provides an electric aircraft, which includes a fuselage, a plurality of rotors arranged on the fuselage, and a rotor motor corresponding to driving the rotors, and the rotor motor is divided into two parts; the electric aircraft also includes a power distribution system for providing power to the rotor motor, and the power distribution system is the power distribution system described in the above embodiment.

[0131] An embodiment of the present invention further provides a power supply control method for an electric aircraft, the power supply control method comprising the following steps:

[0132] During the power supply process, when a short-circuit current caused by a line fault in the power distribution system is detected, the working states of the first isolation device and the second isolation device are controlled to isolate the faulty line from the power distribution system and reconstruct the remaining power supply lines.

[0133] The embodiment of the present invention is based on the power distribution system structure of the above embodiment. When a short-circuit current is detected in the power distribution system, the fault isolation and power reconstruction of the remaining power supply lines can be achieved by controlling the working states of the first isolation device and the second isolation device. The embodiment of the present invention can quickly isolate the short-circuit fault that occurs without affecting the normal operation of other power supply lines.

[0134] In one embodiment, referring to Figure 7 When a short-circuit current generated by a line fault in the power distribution system is detected, the steps of controlling the working states of the first isolation device and the second isolation device to isolate the faulty line from the power distribution system specifically include:

[0135] S11, when a short-circuit current caused by a down-circuit fault in the power distribution system is detected, the bidirectional isolation component is controlled to be disconnected;

[0136] S12, determining whether it is necessary to control the first intelligent protection component and the second intelligent protection component to be disconnected according to the short-circuit current direction detected by the bidirectional isolation component and the working state of the unidirectional isolation component;

[0137] S13, controlling the working states of the first smart protective component and the second smart protective component according to the determination result.

[0138] In this embodiment, a control device is provided to uniformly collect the working status of the bidirectional isolation components and the unidirectional isolation components, and based on the collected information, the faulty power supply line is determined, and the working status of the first intelligent protection component and the second intelligent protection component is controlled, so that the faulty line can be accurately isolated without affecting the normal operation of other power supply lines.

[0139] In another embodiment, referring to Figure 8 When a short-circuit current generated by a line fault in the power distribution system is detected, the steps of controlling the working states of the first isolation device and the second isolation device to isolate the faulty line from the power distribution system specifically include:

[0140] S21, when the bidirectional isolation component detects a short-circuit current, the bidirectional isolation component disconnects the electrical connection between the first intelligent protection component and the second intelligent protection component;

[0141] S22, the bidirectional isolation component determines the target intelligent protection component to be controlled according to the direction of the short-circuit current, and sends a control instruction to a controller corresponding to the target intelligent protection component;

[0142] S23, the controller corresponding to the target intelligent protection component determines whether to control the target intelligent protection component to be disconnected according to the working status of all unidirectional isolation components;

[0143] S24, when it is determined that the target smart protective component is to be disconnected, the target smart protective component actively disconnects.

[0144] In this embodiment, a corresponding controller is provided for the intelligent protection component so that the controller can independently control the disconnection of the intelligent protection component, thereby avoiding failure to disconnect the intelligent protection component when the controller fails, thereby affecting the safety of the electric aircraft.

[0145] Furthermore, the above step S22 specifically includes:

[0146] When the short-circuit current flows from the first intelligent protection component to the second intelligent protection component, the second intelligent protection component is determined as the target intelligent protection component; when the short-circuit current flows from the second intelligent protection component to the first intelligent protection component, the first intelligent protection component is determined as the target intelligent protection component.

[0147] When a short circuit occurs, the voltage at the end of the bidirectional isolation component where the short circuit occurs will decrease due to the short circuit, and the current will even approach zero. Therefore, based on the direction of the current flowing through the bidirectional isolation component, it is possible to determine which end of the bidirectional isolation component has the short circuit.

[0148] Furthermore, the above step S23 specifically includes:

[0149] When all the one-way isolation components are in a closed state, it is determined that the target intelligent protection component is controlled to be disconnected; when at least one one-way isolation component is in a disconnected state, it is determined that the target intelligent protection component is not disconnected.

[0150] Since a power supply failure at any line position in the power distribution system will cause a short-circuit current, when the bidirectional isolation component 10 detects a short-circuit current, it is necessary to determine whether the power supply line of the second rotor motor is faulty or the power supply line of the first rotor motor is faulty. Therefore, when controlling whether the intelligent protection component is disconnected, it is necessary to determine based on the closed / open state of the unidirectional isolation component.

[0151] In one embodiment, when a short-circuit current caused by a line fault in a power distribution system is detected, the step of controlling the working state of the first isolation device and the second isolation device and reconstructing the remaining power supply lines includes: controlling the bidirectional isolation component to close. After isolating the faulty power supply line, it is also necessary to control the working state of the first isolation device, that is, to close the bidirectional isolation component and restore the remaining power supply lines to the power distribution network.

[0152] The present invention also provides a computer-readable storage medium, wherein the computer-readable storage medium stores a power supply control program, and when the power supply control program is executed by the processor, the steps of the power supply control method described in any of the above embodiments are implemented.

[0153] The serial numbers of the above embodiments of the present invention are only for description and do not represent the advantages or disadvantages of the embodiments.

[0154] It should be noted that, in this article, the terms "include", "comprises" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, system, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, system, article or device. In the absence of further restrictions, an element defined by the sentence "comprises a ..." does not exclude the existence of other identical elements in the process, system, article or device including the element.

[0155] Through the description of the above implementation methods, those skilled in the art can clearly understand that the above-mentioned embodiment system can be implemented by means of software plus a necessary general hardware platform, and of course it can also be implemented by hardware, but in many cases the former is a better implementation method. Based on such an understanding, the technical solution of the present invention is essentially or the part that contributes to the prior art can be embodied in the form of a software product, which is stored in a computer-readable storage medium (such as ROM / RAM, magnetic disk, optical disk) as described above, and includes a number of instructions for a terminal device (which can be a mobile phone, a computer, a parking management device, an air conditioner, or a network device, etc.) to execute the system described in each embodiment of the present invention.

[0156] The above are only preferred embodiments of the present invention, and are not intended to limit the patent scope of the present invention. Any equivalent structure or equivalent process transformation made using the contents of the present invention specification and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present invention.

Claims

1. A power distribution system for an electric aircraft, characterized in that: The electric aircraft comprises a fuselage, a plurality of rotors arranged on the fuselage, and a rotor motor corresponding to driving the rotors, and the rotor motor is divided into two parts; the power distribution system comprises: a first battery pack, a second battery pack, a first isolation device, and a second isolation device; The first battery pack and the second battery pack are electrically connected to the first part of the rotor motor through the first isolation device, so as to provide power to the first part of the rotor motor; The first battery pack and the second battery pack are electrically connected to the second part of the rotor motor through the second isolation device, so as to provide power to the second part of the rotor motor; When a power supply failure occurs in the power distribution system, the first isolation device and the second isolation device isolate the faulty line and reconstruct the power supply line.

2. The power distribution system for an electric aircraft as claimed in claim 1, characterized in that: The first part of the rotor motor includes two groups of rotor motors, each group of rotor motors includes two symmetrically arranged rotor motors; the first isolation device includes: a bidirectional isolation component, a first intelligent protection component, and a second intelligent protection component; One end of the first intelligent protection component is electrically connected to the first battery pack via a first bus bar, and the other end of the first intelligent protection component is electrically connected to a group of rotor motors in the first part of the rotor motors; One end of the second intelligent protection component is electrically connected to the second battery pack via a second bus bar, and the other end of the second intelligent protection component is electrically connected to another group of rotor motors in the first part of the rotor motors; One end of the bidirectional isolation component is electrically connected to the first intelligent protection component, and the other end of the bidirectional isolation component is electrically connected to the second intelligent protection component, and is used for being disconnected when triggered by a short-circuit current.

3. The power distribution system for an electric aircraft according to claim 1 or 2, characterized in that: The second isolation device comprises a one-way isolation component group arranged corresponding to the second part of the rotor motor, and each one-way isolation component group comprises two one-way isolation components; One end of one unidirectional isolation component in the unidirectional isolation component group is electrically connected to the first battery pack through a first busbar, and one end of the other unidirectional isolation component is electrically connected to the second battery pack through a second busbar; the other ends of the two unidirectional isolation components in the unidirectional isolation group are both electrically connected to the same rotor motor.

4. The power distribution system for an electric aircraft as claimed in claim 3, characterized in that: The second part of the rotor motor includes two symmetrically arranged rotor motors, a first ducted motor, and a second ducted motor; the one-way isolation component group includes three groups, and the first ducted motor and the second ducted motor are both electrically connected to the same group of the one-way isolation component group.

5. The power distribution system for an electric aircraft as claimed in claim 3, characterized in that: The second part of the rotor motor includes at least two groups of rotor motors, each group of rotor motors includes two symmetrically arranged rotor motors; the one-way isolation component group includes at least 4 groups, and the one-way isolation component group is electrically connected to the second part of the rotor motors accordingly.

6. The power distribution system for an electric aircraft as claimed in claim 2, characterized in that: The first intelligent protection component is correspondingly provided with a first controller, and the second intelligent protection component is correspondingly provided with a second controller; the first controller is used to control whether the first intelligent protection component is disconnected according to the working state of the two-way isolation component and the working state of the second isolation device; the second controller is used to control whether the second intelligent protection component is disconnected according to the working state of the two-way isolation component and the working state of the second isolation device.

7. The power distribution system for an electric aircraft as claimed in claim 2, characterized in that: The power distribution system further comprises a control device, which controls the working states of the first isolation device and the second isolation device to isolate the faulty line and reconstruct the power supply line when a power supply failure occurs in the power distribution system.

8. The power distribution system for an electric aircraft as claimed in claim 3, characterized in that: The bidirectional isolation component includes a bidirectional switch unit; and / or the unidirectional isolation component includes a unidirectional switch unit; and / or the first smart protection component and the second smart protection component both include a fuse unit.

9. An electric aircraft, characterized in that: The electric aircraft includes a fuselage, a plurality of rotors arranged on the fuselage and rotor motors corresponding to driving the rotors, and the rotor motors are divided into two parts; the electric aircraft also includes a power distribution system for providing power to the rotor motors, and the power distribution system is the power distribution system described in any one of claims 1-8.

10. A power supply control method for an electric aircraft, characterized in that: The power supply control method comprises: During the power supply process, when a short-circuit current caused by a line fault in the power distribution system is detected, the working states of the first isolation device and the second isolation device are controlled to isolate the faulty line from the power distribution system and reconstruct the remaining power supply lines.

11. The power supply control method according to claim 10, characterized in that: The power distribution system is the power distribution system according to claim 3; the step of controlling the working states of the first isolation device and the second isolation device to isolate the faulty line from the power distribution system when a short-circuit current caused by a line fault in the power distribution system is detected comprises: When a short-circuit current caused by a down-circuit fault in the power distribution system is detected, the bidirectional isolation component is controlled to be disconnected; Determine whether it is necessary to control the first intelligent protection component and the second intelligent protection component to be disconnected according to the short-circuit current direction detected by the bidirectional isolation component and the working state of the unidirectional isolation component; According to the determination result, the working states of the first smart protection component and the second smart protection component are controlled.

12. The power supply control method according to claim 10, characterized in that: The power distribution system is the power distribution system according to claim 3; the step of controlling the working states of the first isolation device and the second isolation device to isolate the faulty line from the power distribution system when a short-circuit current caused by a line fault in the power distribution system is detected comprises: The bidirectional isolation component disconnects the electrical connection between the first intelligent protection component and the second intelligent protection component when a short-circuit current is detected; The bidirectional isolation component determines the target intelligent protection component to be controlled according to the direction of the short-circuit current, and sends a control instruction to a controller corresponding to the target intelligent protection component; The controller corresponding to the target intelligent protection component determines whether to control the target intelligent protection component to be disconnected according to the working status of all unidirectional isolation components; According to the determination result, the target intelligent protection component is controlled to be disconnected.

13. The power supply control method according to claim 12, characterized in that: The step of the bidirectional isolation component determining the target intelligent protection component to be controlled according to the direction of the short-circuit current comprises: When the short-circuit current flows from the first intelligent protection component to the second intelligent protection component, the second intelligent protection component is determined as the target intelligent protection component; When the short-circuit current flows from the second intelligent protection component to the first intelligent protection component, the first intelligent protection component is determined as the target intelligent protection component.

14. The power supply control method according to claim 12, characterized in that: The controller corresponding to the target intelligent protection component determines whether to control the target intelligent protection component to disconnect according to the working status of all the one-way isolation components, including: When all the one-way isolation components are in a closed state, determining to control the target intelligent protection component to be disconnected; When at least one one-way isolation component is in a disconnected state, it is determined that the target intelligent protection component is not disconnected.

15. The power supply control method according to claim 11 or 12, characterized in that: The step of controlling the working states of the first isolation device and the second isolation device to reconstruct the remaining power supply lines comprises: Controls the closing of the bidirectional isolation component.

16. A computer storage medium, characterized in that: The computer storage medium stores a power supply control program, and when the power supply control program is executed by the processor, each step of the power supply control method according to any one of claims 10 to 15 is implemented.

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