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

Abstract

Disclosed in the present application are an electric aircraft, a power distribution system, a power supply control method and a computer storage medium. 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; the first battery pack and the second battery pack supply power to first rotor motors by means of the first isolation device, and supply power to second rotor motors by means of the second isolation device; when a power supply fault occurs in the power distribution system, the first isolation device and the second isolation device isolate a faulty line and perform power reconfiguration. The embodiments of the present application have simple structures and low costs.

Description

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

[0001] This application claims priority to the Chinese patent application filed with the State Intellectual Property Office on October 23, 2023, with application number 2023113791255 and application name “Electric Aircraft and Power Distribution System, Power Supply Control Method, Computer Storage Medium”, the entire contents of which are incorporated by reference into this application. Technical Field

[0002] The present application relates to the field of vehicle technology, and in particular to electric aircraft and power distribution systems, power supply control methods, and computer storage media. Background Art

[0003] Electric aircraft are machines that fly using electricity, such as drones and flying cars. Current electric aircraft all feature multi-rotor structures, such as quadrotors, hexacopters, octorotors, and dodecapopters. These aircraft have multiple arms symmetrically arranged on a fuselage, each equipped with a propeller. By adjusting the speed and force distribution of each propeller, the aircraft can control six degrees of freedom: pitch, roll, yaw, forward and backward flight, sideways flight, and lift.

[0004] If a single propeller fails during flight, the remaining propellers will not be able to effectively control the yaw motion 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 degrees of freedom of the aircraft can still be controlled simultaneously after a single propeller fails. For example, two symmetrical arms of the aircraft are randomly selected, and two small ducted or thrust propellers are installed on these two arms respectively. After a single propeller fails, the yaw torque is directly applied to the aircraft through the small ducted or thrust propellers. This is an effective means to achieve simultaneous control of the six degrees of freedom of the aircraft after a single propeller fails.

[0005] However, the current power supply structure for providing power to various flight control components of electric aircraft is very complex and costly.

[0006] Summary of the Invention

[0007] The main purpose of this application is to provide an electric aircraft and its power distribution system, power supply control method, and computer storage medium to solve the problems of complex structure and high cost of the power distribution system of electric aircraft in related technologies.

[0008] To achieve the above objectives, the present application provides a power distribution system for an electric aircraft, the electric aircraft comprising a fuselage, a plurality of rotors disposed on the fuselage, and rotor motors for driving the rotors, wherein the rotor motors are 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;

[0009] The first battery pack and the second battery pack are electrically connected to the first part of the rotor motor through a first isolation device, so as to provide power to the first part of the rotor motor;

[0010] The first battery pack and the second battery pack are electrically connected to the second rotor motor via a second isolation device, for providing power to the second rotor motor;

[0011] When a power supply fault 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.

[0012] In one embodiment, 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;

[0013] One end of the first intelligent protection component is electrically connected to the first battery pack via a first busbar, 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;

[0014] One end of the second intelligent protection component is electrically connected to the second battery pack via a second busbar, and the other end of the second intelligent protection component is electrically connected to another set of rotor motors in the first part of the rotor motors;

[0015] 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 configured to be disconnected when triggered by a short-circuit current.

[0016] In one embodiment, the second isolation device includes a one-way isolation component group corresponding to the second rotor motor, and each one-way isolation component group includes two one-way isolation components;

[0017] 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.

[0018] In one embodiment, 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.

[0019] In one embodiment, 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.

[0020] In one embodiment, 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 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.

[0021] In one embodiment, the power distribution system further includes 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 fault occurs in the power distribution system.

[0022] In one embodiment, 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.

[0023] An embodiment of the present application also provides an electric aircraft, comprising 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 of the above embodiments.

[0024] The present application also provides a method for controlling power supply of an electric aircraft, including:

[0025] 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.

[0026] In one embodiment, the power distribution system is the power distribution system described in the above embodiment; the step of controlling the operating 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 generated by a line fault in the power distribution system is detected includes:

[0027] When a short-circuit current is detected due to a down-circuit fault in the power distribution system, the bidirectional isolation component is controlled to disconnect;

[0028] 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;

[0029] According to the determination result, the working states of the first smart protection component and the second smart protection component are controlled.

[0030] In one embodiment, the power distribution system is the power distribution system described in the above embodiment; the step of controlling the operating 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 generated by a line fault in the power distribution system is detected includes:

[0031] 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;

[0032] 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 the controller corresponding to the target intelligent protection component;

[0033] 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 one-way isolation components;

[0034] According to the determination result, the target intelligent protection component is controlled to be disconnected.

[0035] In one embodiment, the step of determining, by the bidirectional isolation component, a target intelligent protection component to be controlled according to the direction of the short-circuit current includes:

[0036] 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 to be the target intelligent protection component;

[0037] 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.

[0038] In one embodiment, the controller corresponding to the target smart protective component determines whether to control the target smart protective component to disconnect according to the working status of all unidirectional isolation components, including:

[0039] When all the one-way isolation components are in a closed state, determining to control the target intelligent protection component to be disconnected;

[0040] When at least one one-way isolation component is in an open state, it is determined that the target intelligent protection component is not open.

[0041] In one embodiment, 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:

[0042] Controls the closing of bidirectional isolation components.

[0043] An embodiment of the present application 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, the various steps of the power supply control method described in any of the above embodiments are implemented.

[0044] The embodiment of the present application 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 lightweighting of the entire machine and reducing system costs.

[0045] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] The above and other objects, features and advantages of the present application will become more apparent through a more detailed description of exemplary embodiments of the present application in conjunction with the accompanying drawings, wherein the same reference numerals generally represent the same components in the exemplary embodiments of the present application.

[0047] FIG1 is a schematic structural diagram of a power distribution system of an electric aircraft in the related art;

[0048] FIG2 is a schematic structural diagram of a power distribution system of an electric aircraft according to an embodiment of the present application;

[0049] FIG3 is a schematic structural diagram of a six-rotor electric aircraft according to an embodiment of the present application;

[0050] FIG4 is a schematic structural diagram of a power distribution system for the electric aircraft of FIG3 according to an embodiment of the present application;

[0051] FIG5 is a schematic structural diagram of an octorotor electric aircraft according to an embodiment of the present application;

[0052] FIG6 is a schematic structural diagram of a power distribution system for the electric aircraft of FIG5 in an embodiment of the present application;

[0053] FIG7 is a flow chart of an embodiment of a power supply control method for an electric aircraft according to the present invention;

[0054] FIG8 is a flow chart of another embodiment of a power supply control method for an electric aircraft according to the present application. DETAILED DESCRIPTION

[0055] The following describes embodiments of the present application in more detail with reference to the accompanying drawings. Although the accompanying drawings illustrate embodiments of the present application, it should be understood that the present application can be implemented in various forms and should not be limited by the embodiments described herein. Rather, these embodiments are provided to make the present application more thorough and complete, and to fully convey the scope of the present application to those skilled in the art.

[0056] The terms used in this application are for the purpose of describing specific embodiments only and are not intended to limit this application. As used in this application and the appended claims, the singular forms "a," "an," "the," and "the" are intended to include the plural forms, unless the context clearly indicates otherwise. It should also be understood that the term "and / or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.

[0057] It should be understood that although the terms "first", "second", "third", etc. may be used in this application to describe various information, this information should not be limited to these terms. These terms are only used to distinguish information of the same type from each other. For example, without departing from the scope of this application, the first information may also be referred to as the second information, and similarly, the second information may also be referred to as the first information. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0058] To ensure the safety of the aircraft, the aircraft's power supply structure must ensure that the rotors that maintain normal flight and the two small ducts or thrust propellers used to control yaw after a single propeller fails do not fail simultaneously (or the probability of simultaneous failure is sufficiently low). For the aircraft's power distribution system, if any load or power supply connected to the power distribution network experiences a short circuit fault, the entire distribution network will be paralyzed if the short circuit fault is not promptly isolated from the distribution network. Referring to Figure 1, Figure 1 is a schematic diagram of the power distribution system structure for a six-rotor electric aircraft in the related art. In order to achieve the goal of preventing the rotor and small duct or thrust propeller of the above-mentioned electric aircraft from failing at the same time, the relevant technology designs the power distribution system into the structure of Figure 1, that is, 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 distribution network, it will only affect the power supply and load in the distribution network where it is located, and the 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).

[0059] However, the power supply scheme shown in Figure 1 requires the electric aircraft's battery pack to be split into seven. This requires more housings, mounting structures, control components, and cooling structures for the same power level, significantly increasing the weight and cost of the battery system and hindering the lightweight design and cost control of the entire aircraft. Furthermore, the battery packs are completely independent of each other, making real-time balancing impossible. This results in low battery utilization (the available power is determined by the battery pack with the lowest power) and poor charging convenience (all seven packs cannot be charged simultaneously), making it impossible to guarantee a good user experience.

[0060] The embodiment of the present application proposes a power distribution system with a simple structure and low cost, which uses bidirectional isolation components combined with intelligent protection components to isolate one part of the load and its power supply short-circuit fault, and uses unidirectional isolation components to isolate another part of the load and its power supply short-circuit fault. The combination of the two methods can 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 lightweighting of the entire machine and reducing system costs.

[0061] Refer to Figure 2, which is a structural block diagram of the power distribution system of the electric aircraft in an embodiment of the present application. The electric aircraft includes a fuselage and a plurality of rotors arranged on the fuselage. Each rotor is provided with a corresponding rotor motor, which 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, and includes: 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 application divides the rotor motor of the electric aircraft into two parts, namely the first part rotor motor and the second part rotor motor.

[0062] The first battery pack 1 and the second battery pack 2 are electrically connected to the first rotor motor via a first isolation device 3 to provide power to the first rotor motor. The first battery pack 1 and the second battery pack 2 are electrically connected to the second rotor motor via a second isolation device 4 to provide power to the second rotor motor.

[0063] 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.

[0064] The embodiment of the present application utilizes a first isolation device and a second isolation device to isolate the faulty circuit and reconfigure the remaining power supply circuits, enabling grid-connected output through two battery packs in the power distribution system. This also allows for rapid isolation of short-circuit faults in the power distribution system without affecting the normal operation of other power supply circuits. Therefore, the power distribution system of the electric aircraft of the embodiment of the present application achieves overall aircraft lightweighting and cost reduction while achieving aircraft safety goals.

[0065] 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 via a first busbar BUS1, and the other end of the first intelligent protection component 12 is electrically connected to a group of rotor motors in the first section.

[0066] 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.

[0067] 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.

[0068] The direction of current flowing through the bidirectional isolation component 10 includes either flowing from the first intelligent protective component 12 to the second intelligent protective component 14 or from the second intelligent protective component 14 to the first intelligent protective component 12. This bidirectional isolation component, for example, is a bidirectional isolating switch. Under normal operating conditions, the switch is closed. When a short-circuit current flows through the switch, it quickly switches to an open state. Furthermore, the bidirectional isolation component can detect the direction of current flow, for example, whether it is flowing from the first intelligent protective component 12 to the second intelligent protective component 14, or from the second intelligent protective component 14 to the first intelligent protective component 12.

[0069] 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.

[0070] Furthermore, the first intelligent protection component 12 is electrically connected to the bidirectional isolation component 10 and one set of rotor motors via a third busbar BUS3. The second intelligent protection component 14 is electrically connected to the bidirectional isolation component 10 and another set of rotor motors via a fourth busbar BUS4.

[0071] 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.

[0072] In one embodiment, the second isolation device 2 includes a one-way isolation component group 20 corresponding to the second rotor motor, and each one-way isolation component group 20 includes two one-way isolation components 21.

[0073] 4 , one end of a one-way isolation component 21a in the one-way isolation component group 20 is electrically connected to the first battery pack 1 via the first bus BUS1, and one end of the other one-way isolation component 21b is electrically connected to the second battery pack 2 via the second bus BUS2; the other ends of the two one-way isolation components in the one-way isolation group 20 are both electrically connected to the same rotor motor.

[0074] The unidirectional isolation component 21 comprises, for example, a unidirectional isolating switch, which is opened 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 flow in one direction.

[0075] 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 quickly disconnects. Based on the direction of the short-circuit current, a control signal is sent to the corresponding intelligent protection component. For example, if the bidirectional isolation component 10 detects the short-circuit current flowing 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. If the bidirectional isolation component 10 detects the short-circuit current flowing 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. Upon receiving the control signal, the intelligent protection component determines whether to disconnect the intelligent protection component based on the status of the unidirectional isolation component in the second isolation device 4.

[0076] Furthermore, a first controller is correspondingly provided in the above-mentioned first intelligent protection component 12, and a second controller is correspondingly provided in the above-mentioned second intelligent protection component 14; the first controller is used to control whether the first intelligent protection component 12 is disconnected according to the working status of the bidirectional isolation component 10 and the working status of the second isolation device 4; the second controller is used to control whether the second intelligent protection component 14 is disconnected according to the working status of the bidirectional isolation component 10 and the working status of the second isolation device 4.

[0077] For example, since a power supply failure at any line location 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 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 be disconnected. 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 fault in the power supply line 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 fault is caused by the power supply line of the first part of the rotor motor, so according to the direction of the short-circuit current, the corresponding intelligent protection component is controlled to be disconnected.

[0078] 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 their respective intelligent protection components, thereby avoiding the inability to disconnect the intelligent protection components when the controller fails, which affects the safety of the electric aircraft.

[0079] In one embodiment, the above-mentioned power distribution system further includes a control device, which controls the working states 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 generated by a downlink fault in the power distribution system is detected, the bidirectional isolation component 10 is controlled to disconnect; based on the direction of the short-circuit current detected by the bidirectional isolation component 10 and the working states 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 disconnect; based on the determination result, the working states of the first intelligent protection component 12 and the second intelligent protection component 14 are controlled.

[0080] Furthermore, after isolating the faulty power supply line, it is necessary to control the working state of the first isolation device, ie, close the bidirectional isolation component and restore the remaining power supply lines to the power distribution network.

[0081] 3 and 4 , FIG3 is a schematic structural diagram of the six-rotor electric aircraft according to an embodiment of the present application, and FIG4 is a schematic structural diagram of the power distribution system of the six-rotor aircraft according to an embodiment of the present application.

[0082] The six-rotor aircraft includes a fuselage and six arms, namely arm 1, arm 2, arm 3, arm 4, arm 5, and arm 6. Each arm is equipped with a propeller, and arm 3 and arm 6 are each equipped with a duct structure, namely the first duct (duct 1) and the second duct (duct 2). Each propeller is correspondingly provided with a drive motor, that is, the propeller on arm 1 is correspondingly provided with rotor motor 1, the propeller on arm 2 is correspondingly provided with rotor motor 2, the propeller on arm 3 is correspondingly provided with rotor motor 3, the propeller on arm 4 is correspondingly provided with rotor motor 4, the propeller on arm 5 is correspondingly provided with rotor motor 5, and the propeller on arm 6 is correspondingly provided with rotor motor 6. The first duct is correspondingly provided with ducted motor 1, and the second duct is correspondingly provided with ducted motor 2. In an embodiment of the present application, the first part of the rotor motors includes rotor motor No. 1, rotor motor No. 4, rotor motor No. 3, and rotor motor No. 6; the second part of the rotor motors includes rotor motor No. 3, rotor motor No. 5, ducted motor No. 1, and ducted motor No. 2.

[0083] The power distribution system of the hexacopter includes two battery packs, a bidirectional isolation component, two intelligent protection components, six unidirectional isolation components and several busbars.

[0084] For example, battery pack 1 is connected to bus bar BUS1, and battery pack 2 is connected to bus bar BUS2. Rotor motors 1 and 4 are connected to bus bar BUS3, which is connected to bus bar BUS1 via smart protection component 12. This bus bar receives power from battery pack 1 and supplies power to motors 1 and 4. Rotor motors 3 and 4 are connected to bus bar BUS4, which is connected to bus bar BUS2 via smart protection component 14. This bus bar receives power from battery pack 2 and supplies power to motors 3 and 6.

[0085] The third busbar BUS3 and the fourth busbar BUS4 are connected via a bidirectional isolation component 10. This component is normally closed when the power distribution system is powered on, enabling real-time charge balancing between the first battery pack 1 and the second battery pack 2. The bidirectional isolation component 10 can sense the current and direction flowing through it. If it detects a short-circuit current, it triggers a switch to the open state.

[0086] The first busbar BUS1 and the second busbar BUS2 independently supply power to rotor motor No. 2, rotor motor No. 5, ducted motor No. 1 and ducted motor No. 2 respectively through six unidirectional isolation components 21a~21f and the fifth busbar BUS5, the sixth busbar BUS6 and the seventh busbar BUS7.

[0087] (1) A short circuit occurs on the first busbar BUS1 or the first battery pack 1

[0088] When a short circuit fault 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. 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 busbar BUS1 and the first battery pack 1 connected to the first busbar BUS1, the third busbar BUS3, and the No. 1 rotor motor and the No. 4 rotor motor connected to the third busbar BUS3.

[0089] To ensure the complete machine's power output, the third busbar BUS3 and the No. 1 and No. 4 rotor motors connected to it need to be connected back to the power distribution network. Therefore, when the bidirectional isolation component is triggered to open by the short-circuit current, it simultaneously feeds back the short-circuit current direction (from the fourth busbar BUS3 to the third busbar BUS2) to the controller. Based on the short-circuit current direction and the status of the unidirectional isolation components (unidirectional isolation components 21a-21f are all closed), the controller controls the first intelligent protection component 12 to blow open, limiting the impact of the short-circuit fault to the first busbar BUS1 and the first battery pack 1 connected to it.

[0090] At this point, the third busbar BUS3 and the No. 1 and No. 4 rotor motors connected to it are both open-circuited. The controller sends a command to the bidirectional isolation component, which closes, thereby connecting the third busbar BUS3 and the No. 1 and No. 4 rotor motors connected to it back to the power distribution network, achieving power reconfiguration. In other words, if a short circuit occurs on the first busbar BUS1 or the first battery pack 1 connected to it, the entire power distribution network loses only the power supplied by the first battery pack 1.

[0091] (2) A short circuit occurs on the second busbar BUS2 or the second battery pack

[0092] Similarly, when a short circuit fault occurs in the second busbar BUS2 or the second battery pack 2 connected to the second busbar BUS2, 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 that have a short circuit fault can be isolated, that is, the impact of the short circuit fault is controlled within the second busbar BUS2 and the second battery pack 2 connected to the second busbar BUS2, the fourth busbar BUS4 and the No. 3 rotor motor and the No. 6 rotor motor connected to the fourth busbar BUS4.

[0093] To ensure the overall power output of the entire machine, the fourth busbar BUS4 and the No. 3 and No. 6 rotor motors connected to it need to be connected back to the power distribution network. Therefore, when the bidirectional isolation component is triggered to open by the short-circuit current, it simultaneously feeds back the short-circuit current direction (flow from the third busbar BUS3 to the fourth busbar BUS4) to the controller. Based on the short-circuit current direction and the status of the unidirectional isolation components (unidirectional isolation components 21a-21f are all closed), the controller controls the second intelligent protection component 14 to blow open, limiting the impact of the short-circuit fault to the second busbar BUS2 and the second battery pack 2 connected to it.

[0094] At this point, the fourth busbar BUS4 and the No. 3 and No. 6 rotor motors connected to it are both open-circuited. The controller sends a command to the bidirectional isolation component, which closes, thereby connecting the fourth busbar BUS4 and the No. 3 and No. 6 rotor motors connected to it back to the power distribution network, achieving power reconfiguration. In other words, if a short circuit occurs on the second busbar BUS2 or the second battery pack 2 connected to it, the entire power distribution network only loses power from the second battery pack 2.

[0095] (3) A short circuit occurs on the third busbar or rotor motor No. 1 or rotor motor No. 4

[0096] 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 of the power distribution system that have a short circuit fault 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.

[0097] To ensure the complete machine's power output, the first busbar BUS1 and the first battery pack 1 connected to it need to be connected back to the power supply network. Therefore, when the short-circuit current triggers the bidirectional isolation component to disconnect, it simultaneously feeds back the short-circuit current direction (from the fourth busbar BUS4 to the third busbar BUS3) to the controller. Based on the short-circuit current direction and the status of the unidirectional isolation components (unidirectional isolation components 21a-21f are all closed), the controller controls the first intelligent protection component to trip, thereby limiting the impact of the short-circuit fault to the third busbar BUS3 and rotor motors 1 and 4 connected to it. The first busbar BUS1 and the first battery pack 1 connected to it resume powering the distribution network.

[0098] Therefore, when a short circuit occurs in the third bus BUS3 or the 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.

[0099] (4) A short circuit occurs on the fourth busbar BUS4 or the rotor motor No. 3 or the rotor motor No. 6

[0100] Similarly, when a short circuit fault 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 that have a short circuit fault 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.

[0101] To ensure the complete machine's power output, the second busbar BUS2 and the battery pack 2 connected to it 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 simultaneously feeds back the short-circuit current direction (from the third busbar BUS3 to the fourth busbar BUS4) to the controller. Based on the short-circuit current direction and the status of each unidirectional isolation component (unidirectional isolation components 21a-21f are all closed), the controller controls the second intelligent protection component to blow open, thereby limiting the impact of the short-circuit fault to the fourth busbar BUS4 and the No. 3 and No. 6 rotor motors connected to it. The second busbar BUS2 and the second battery pack 2 connected to it resume powering the power distribution network.

[0102] 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.

[0103] (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.

[0104] 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, isolating the short circuit fault.

[0105] 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.

[0106] Therefore, if a short-circuit occurs in either rotor motor 2 or rotor motor 5, the entire power distribution network loses only the output of the motor that suffered the short-circuit. Conversely, if a short-circuit occurs in either ducted motor 1 or ducted motor 2, the entire power distribution network loses only the output of ducted motors 1 and 2, leaving the output of all six rotor motors unaffected, thus maintaining the safety of the entire aircraft.

[0107] 5 and 6 , FIG5 is a schematic structural diagram of an octorotor aircraft according to an embodiment of the present application, and FIG6 is a schematic structural diagram of a power distribution system of an octorotor aircraft according to an embodiment of the present application.

[0108] The octocopter includes a fuselage and eight arms, namely arm 1, arm 2, arm 3, arm 4, arm 5, arm 6, arm 7, and arm 8, each of which is provided with a propeller. Each propeller is provided with a corresponding drive motor, that is, the propeller on arm 1 is provided with rotor motor 1, the propeller on arm 2 is provided with rotor motor 2, the propeller on arm 3 is provided with rotor motor 3, the propeller on arm 4 is provided with rotor motor 4, the propeller on arm 5 is provided with rotor motor 5, the propeller on arm 6 is provided with rotor motor 6, the propeller on arm 7 is provided with rotor motor 7, and the propeller on arm 8 is provided with rotor motor 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.

[0109] 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.

[0110] For example, battery pack 1 is connected to bus bar BUS1, and battery pack 2 is connected to bus bar BUS2. Rotor motors 1 and 5 are connected to bus bar BUS3, which is connected to bus bar BUS1 via a first intelligent protection component. This receives power from battery pack 1 and supplies power to motors 1 and 5. Rotor motors 3 and 7 are connected to bus bar BUS4, which is connected to bus bar BUS2 via a second intelligent protection component. This receives power from battery pack 2 and supplies power to motors 3 and 7.

[0111] The third busbar BUS3 and the fourth busbar BUS4 are connected via a bidirectional isolation component. This component is normally closed when the power distribution system is powered on, enabling real-time charge balancing between the first battery pack 1 and the second battery pack 2. The bidirectional isolation component can sense the current and direction flowing through it. If it detects a short-circuit current, it triggers a switch to the open state.

[0112] The first busbar BUS1 and the second busbar BUS2 independently supply power 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.

[0113] (1) A short circuit occurs on the first busbar BUS1 or the first battery pack 1

[0114] When a short circuit occurs on the first busbar BUS1 or the first battery pack 1 connected to it, the bidirectional isolation component senses the short-circuit current and, triggered by the short-circuit current, rapidly disconnects. While disconnecting, the bidirectional isolation component simultaneously transmits the short-circuit current direction (from the fourth busbar BUS4 to the third busbar BUS3) to the controller. Based on the short-circuit current direction and the status of each unidirectional isolation component (unidirectional isolation components 21a-21h are all closed), the controller controls the first intelligent protection component to trip, limiting the impact of the short circuit to the first busbar BUS1 and the first battery pack 1 connected to it.

[0115] Then, the controller sends an instruction to the bidirectional isolation component, switching 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.

[0116] 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 .

[0117] (2) A short circuit occurs on the second busbar BUS2 or the second battery pack

[0118] Similarly, when a short circuit fault occurs in the second busbar BUS2 or the second battery pack 2 connected to the second busbar BUS2, 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 that have a short circuit fault can be isolated, that is, the impact of the short circuit fault is controlled within the second busbar BUS2 and the second battery pack 2 connected to the second busbar BUS2, the fourth busbar BUS4 and the No. 3 rotor motor and the No. 7 rotor motor connected to the fourth busbar BUS4.

[0119] The controller controls the second 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 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.

[0120] Then, the controller sends an instruction to the bidirectional isolation component, and the bidirectional isolation component closes, 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.

[0121] Therefore, when a short circuit fault occurs in the second busbar BUS2 or the second battery pack 2 connected to the second busbar BUS2 , the entire power distribution network only loses the power supply of the second battery pack 2 .

[0122] (3) A short circuit occurs on the third busbar or rotor motor No. 1 or rotor motor No. 5

[0123] 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 of the power distribution system that have a short circuit fault 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.

[0124] 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 the closed state), thereby controlling the impact of the short-circuit fault to the third bus BUS3 and the rotor motor No. 1 and 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.

[0125] Therefore, when a short circuit occurs in the third bus BUS3 or the 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.

[0126] (4) A short circuit occurs on the fourth busbar BUS4 or the No. 3 rotor motor or the No. 7 rotor motor.

[0127] Similarly, when a short circuit fault 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 of the power distribution system that have a short circuit fault 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.

[0128] The controller controls the second 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 the closed state), thereby controlling the impact of the short-circuit fault to the fourth bus BUS4 and the rotor motor No. 3 and rotor motor No. 7 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.

[0129] 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.

[0130] (5) At least one load in rotor motor No. 2, rotor motor No. 4, rotor motor No. 6, or rotor motor No. 8 has a short circuit fault.

[0131] 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-circuit load are triggered by the short-circuit current and quickly disconnected, isolating the short circuit fault.

[0132] 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.

[0133] 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.

[0134] It is understandable that if the aircraft is a twelve-rotor aircraft, that is, on the basis of an 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 busbar BUS9, the tenth busbar BUS10, the eleventh busbar BUS11, and the twelfth busbar BUS12 are added. Each busbar is connected to the first busbar BUS1 and the fourth busbar BUS4 through two one-way isolation components. Each busbar 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.

[0135] The present application 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.

[0136] The present invention also provides a method for controlling power supply of an electric aircraft, the method comprising the following steps:

[0137] 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.

[0138] Based on the power distribution system structure of the above-described embodiment, the present embodiment of the present invention detects a short-circuit current in the power distribution system and, by controlling the operating states of the first and second isolation devices, achieves fault isolation and power reconfiguration of the remaining power supply lines. This embodiment of the present invention can quickly isolate a short-circuit fault without affecting the normal operation of other power supply lines.

[0139] In one embodiment, referring to FIG7 , 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 include:

[0140] S11, when a short-circuit current caused by a downlink fault in the power distribution system is detected, the bidirectional isolation component is controlled to be disconnected.

[0141] 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.

[0142] S13: Control the working states of the first smart protective component and the second smart protective component according to the determination result.

[0143] 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.

[0144] In another embodiment, referring to FIG8 , when a short-circuit current generated by a line fault in the power distribution system is detected, 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:

[0145] S21 , when the bidirectional isolation component detects a short-circuit current, the bidirectional isolation component disconnects the electrical connection between the first smart protection component and the second smart protection component.

[0146] 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.

[0147] 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 the one-way isolation components.

[0148] S24 , when it is determined that the target smart protective component is to be disconnected, the target smart protective component actively disconnects.

[0149] In this embodiment, by providing a corresponding controller for the intelligent protection component, 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.

[0150] In one embodiment, the above step S22 may include:

[0151] When the short-circuit current flows from the first smart protection component to the second smart protection component, the second smart protection component is determined as the target smart protection component; when the short-circuit current flows from the second smart protection component to the first smart protection component, the first smart protection component is determined as the target smart protection component.

[0152] 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 failure.

[0153] In one embodiment, the above step S23 may include:

[0154] 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 an open state, it is determined that the target intelligent protection component is not disconnected.

[0155] Because a power supply failure at any point 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 fault is in the power supply line for the second rotor motor or the first rotor motor. Therefore, when controlling whether the intelligent protection element should be disconnected, it is necessary to determine whether the unidirectional isolation component is closed or open.

[0156] In one embodiment, when a short-circuit current generated by a line fault in the power distribution system is detected, controlling the operating states of the first and second isolation devices to reconfigure the remaining power supply lines includes controlling the bidirectional isolation component to close. After isolating the faulty power supply line, it is necessary to further control the operating state of the first isolation device, i.e., to close the bidirectional isolation component, to restore the remaining power supply lines to the power distribution network.

[0157] The present application also provides a computer-readable storage medium, which stores a power supply control program. When the power supply control program is executed by the processor, the power supply control program implements the various steps of the power supply control method described in any of the above embodiments.

[0158] The serial numbers of the above embodiments of the present application are for description only and do not represent the advantages or disadvantages of the embodiments.

[0159] It should be noted that, in this document, the terms "comprises," "includes," or any other variations thereof are intended to encompass non-exclusive inclusion, such that a process, system, article, or device comprising a series of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, system, article, or device. In the absence of further limitations, an element defined by the phrase "comprising a ..." does not exclude the presence of other identical elements in the process, system, article, or device comprising the element.

[0160] Through the description of the above embodiments, those skilled in the art can clearly understand that the above embodiment system can be implemented by means of software plus the necessary general hardware platform, or of course by hardware, but in many cases the former is a better embodiment. Based on this understanding, the technical solution of the present application, or the part that contributes to the relevant technology, 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 enabling a terminal device (which can be a mobile phone, computer, parking management equipment, air conditioner, or network equipment, etc.) to execute the system described in each embodiment of the present application.

[0161] The embodiments of the present application have been described above. The above description is illustrative and not exhaustive, and is not limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is selected to best explain the principles of the embodiments, their practical applications, or improvements to the technology in the market, or to enable other persons skilled in the art to understand the embodiments disclosed herein.

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 generated 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 generated 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 one-way 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 determining the target intelligent protection component to be controlled according to the direction of the short-circuit current by the bidirectional isolation component includes: 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 unidirectional 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 includes: 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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