Insulation fault positioning method, device and equipment of flying car and storage medium

Abstract

This application relates to a method, apparatus, device, and storage medium for locating insulation faults in a flying car. The method includes: in response to detecting an insulation fault in the flying car, controlling the power-on / off of the flying body and the ground body of the flying car; and determining the location of the fault source based on the insulation fault detection results obtained during the power-on / off control. The solution provided by this application can quickly locate the fault source by controlling the power-on / off of the flying body and the ground body of the flying car when an insulation fault occurs, which is beneficial to improving the efficiency of fault diagnosis and user experience.

Description

Technical Field

[0001] This application relates to the field of flying car technology, and in particular to a method, apparatus, device and storage medium for locating insulation faults in flying cars. Background Technology

[0002] In related technologies, insulation testing of battery systems involves detecting whether there is a connection between the positive and negative buses of the power battery and the "ground" of the battery system casing, and whether there is a risk of leakage. Insulation testing can prevent electric shock accidents, prevent equipment leakage, and promptly detect and resolve safety risks.

[0003] Flying car power systems contain numerous high-voltage components. Therefore, locating insulation faults in flying cars during malfunctions is crucial for ensuring safe operation. Relying solely on manual inspection of each high-voltage component is not only difficult but also inefficient, potentially leading to a poor user experience. Summary of the Invention

[0004] To address or partially address the problems existing in related technologies, this application provides a method, apparatus, device, and storage medium for locating insulation faults in flying cars. When an insulation fault occurs in a flying car, the location of the fault source can be quickly determined by controlling the power on and off of the flying body and the land-based body of the flying car, which helps to improve the efficiency of fault diagnosis and user experience.

[0005] The first aspect of this application provides a method for locating insulation faults in a flying car, the flying car including a flying body and a land body, the method comprising: in response to detecting an insulation fault in the flying car, performing power-on / off control on the flying body and the land body of the flying car; and determining the location of the fault source based on the insulation fault detection results obtained during the power-on / off control.

[0006] In some implementations, the location of the fault source includes at least one of the following: the fault source is located in the connection section between the aircraft and the land vehicle; the fault source is located in the high-voltage circuit of the aircraft; the fault source is located in the battery system of the aircraft; the fault source is located in the high-voltage circuit of the land vehicle; or the fault source is located in the battery system of the land vehicle.

[0007] In some embodiments, power-on / off control of the flying body and the land vehicle of the flying car includes at least one of the following: when it is determined that the flying body and the land vehicle are connected, disconnecting the connection between the flying body and the land vehicle and powering on the flying body and the land vehicle respectively; when it is determined that there is an insulation fault in the flying body, disconnecting the high-voltage circuit of the flying body and the relay of the flying body's battery system; when it is determined that there is an insulation fault in the land vehicle, disconnecting the high-voltage circuit of the land vehicle and the relay of the land vehicle's battery system.

[0008] In some implementations, the location of the fault source is determined based on the insulation fault detection results obtained during power-on / off control, including at least one of the following: performing insulation fault detection after the aircraft and land vehicle are powered on, obtaining insulation fault detection results for both the aircraft and land vehicle respectively, and determining the fault source as located in the connection section between the aircraft and land vehicle if both insulation fault detection results show no insulation fault; performing insulation fault detection after disconnecting the high-voltage circuit of the aircraft and the relay of the aircraft's battery system, obtaining the insulation fault detection results for the aircraft, and determining the fault source as located in the high-voltage circuit of the aircraft if the insulation fault detection results show no insulation fault; and determining the fault source as located in the high-voltage circuit of the aircraft after disconnecting the high-voltage circuit of the aircraft and the relay of the aircraft's battery system. After disconnecting the relays of the aircraft, insulation fault detection is performed to obtain the insulation fault detection results of the aircraft. If the insulation fault detection results of the aircraft indicate the presence of an insulation fault, the fault source is determined to be located in the battery system of the aircraft. After disconnecting the relays of the high-voltage circuit and the battery system of the land vehicle, insulation fault detection is performed to obtain the insulation fault detection results of the land vehicle. If the insulation fault detection results of the land vehicle indicate the absence of an insulation fault, the fault source is determined to be located in the high-voltage circuit of the land vehicle. After disconnecting the relays of the high-voltage circuit and the battery system of the land vehicle, insulation fault detection is performed to obtain the insulation fault detection results of the land vehicle. If the insulation fault detection results of the land vehicle indicate the presence of an insulation fault, the fault source is determined to be located in the battery system of the land vehicle.

[0009] In some implementations, the method further includes:

[0010] The diagnostic tool is used to initiate insulation fault location and detection for the flying car. The diagnostic tool is equipped with an insulation fault detection mode, and when the insulation fault detection mode is detected to be on, insulation fault detection is performed on the flying car.

[0011] A second aspect of this application provides an insulation fault location device for a flying car. The device includes: a control module for powering on / off control of the flying body and the land body of the flying car in response to detecting an insulation fault in the flying car; and a location module for determining the location of the fault source based on the insulation fault detection results obtained during the power-on / off control.

[0012] A third aspect of this application provides an electronic device, comprising:

[0013] Processor; and

[0014] A memory that stores executable code, which, when executed by the processor, causes the processor to perform the method described above.

[0015] A fourth aspect of this application provides a computer-readable storage medium having executable code stored thereon, which, when executed by a processor of an electronic device, causes the processor to perform the method described above.

[0016] The technical solution provided in this application can include the following beneficial effects: when an insulation failure occurs in a flying car, the location of the fault source can be quickly located by controlling the power on and off of the flying body and the land body of the flying car, which is conducive to improving the efficiency of fault diagnosis and user experience.

[0017] The technical solution of this application can also reduce the difficulty of troubleshooting for after-sales maintenance personnel.

[0018] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and do not limit this application. Attached Figure Description

[0019] The above and other objects, features and advantages of this application will become more apparent from the following description of exemplary embodiments in conjunction with the accompanying drawings, wherein the same reference numerals generally represent the same components in the exemplary embodiments of this application.

[0020] Figure 1 This is a schematic flowchart illustrating the insulation fault location method for a flying car according to an embodiment of this application;

[0021] Figure 2 This is another schematic flowchart illustrating the insulation fault location method for flying cars shown in the embodiments of this application;

[0022] Figure 3 This is a schematic diagram of the structure of the insulation fault location device for a flying car shown in the embodiments of this application;

[0023] Figure 4 This is a schematic diagram of the structure of an electronic device shown in an embodiment of this application. Detailed Implementation

[0024] Embodiments of this application will now be described in more detail with reference to the accompanying drawings. While embodiments of this application are shown in the drawings, it should be understood that this application may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to make this application more thorough and complete, and to fully convey the scope of this application to those skilled in the art.

[0025] The terminology used in this application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. The singular forms “a,” “the,” and “the” used in this application and the appended claims are also 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 includes any or all possible combinations of one or more of the associated listed items.

[0026] 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 one another. For example, without departing from the scope of this application, first information may also be referred to as second information, and similarly, second information may also be referred to as first information. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0027] Insulation fault detection in a battery management system (BMS) involves injecting a pulsed high voltage between the positive and negative terminals or calculating the insulation resistance using a balanced bridge. This method can only report insulation faults when they occur, but it cannot accurately pinpoint the failure point.

[0028] Flying cars can fly in the air or drive on land, and typically consist of a flying body and a land-based body. The high-voltage system architecture involved in flying cars is more complex than that of general equipment or new energy vehicles, and many high-voltage components are coupled together, making it difficult to quickly locate the source of the fault when an insulation failure occurs.

[0029] To address the aforementioned issues, this application provides a method for locating insulation faults in flying cars. When an insulation fault occurs in a flying car, the method can quickly locate the source of the fault by controlling the power on and off of the flying body and the ground body of the flying car, thereby improving the efficiency of fault diagnosis and user experience.

[0030] The technical solutions of the embodiments of this application are described in detail below with reference to the accompanying drawings.

[0031] Figure 1 This is a schematic flowchart illustrating the insulation fault location method for a flying car as shown in the embodiments of this application.

[0032] See Figure 1 An insulation fault location method for a flying car, the flying car comprising a flying body and a land-based body, the method comprising:

[0033] Step 101: In response to the detection of an insulation fault in the flying car, power-on and power-off control is performed on the flying body and the land body of the flying car.

[0034] Step 102: Determine the location of the fault source based on the insulation fault detection results obtained during power-on / off control.

[0035] It's understandable that a flying car generally consists of two parts: the flying body and the land-based body, such as an aircraft and a car. The high-voltage system of an aircraft can include two parts: a battery providing power and a high-voltage load, such as a battery system and a high-voltage circuit. Similarly, the high-voltage system of a car can include two parts: a battery providing power and a high-voltage load, such as a battery system and a high-voltage circuit.

[0036] In the insulation fault location method for flying cars according to the embodiments of this application, the presence of an insulation fault in the flying car can be detected during fault detection. If no insulation fault is detected in the flying car, the user is informed that "no insulation fault is currently detected"; if an insulation fault is detected in the flying car, the insulation fault location of the flying car is further performed.

[0037] It is understood that in the insulation fault location method of the flying car in the embodiments of this application, after an insulation fault is detected in the flying car, it is necessary to perform power-on and power-off control on the flying body and the land body of the flying car. Each power-on and power-off control can obtain insulation fault detection results reflecting different fault source locations. Therefore, it is possible to further quickly and accurately investigate and locate the complex high-voltage components of the flying car, thereby quickly locating the fault source.

[0038] For example, it is possible to control the power supply of the flying vehicle and the land vehicle separately; it is possible to disconnect the high-voltage circuit of the flying vehicle and the relay of the flying vehicle's battery system before powering it on; it is possible to disconnect the high-voltage circuit of the land vehicle and the relay of the land vehicle's battery system before powering it on, and so on.

[0039] The insulation fault location method for flying cars in this application embodiment can quickly locate the fault source by controlling the power on and off of the flying body and the land body of the flying car when an insulation fault occurs. This is beneficial to improving the efficiency of fault diagnosis and user experience. At the same time, it can also reduce the difficulty of fault diagnosis for after-sales maintenance personnel.

[0040] In some embodiments, the source of the fault may be located in the connecting section between the airborne body and the landborne body.

[0041] By disconnecting the connection between the aircraft and the land vehicle, each aircraft and the land vehicle can perform insulation fault detection separately. If no insulation fault is detected in either the aircraft or the land vehicle, the fault source can be located in the connection section between the aircraft and the land vehicle.

[0042] In some embodiments, the source of the fault may be located within the aircraft, such as in the high-voltage circuit of the aircraft or in the battery system of the aircraft.

[0043] For example, the airborne and land-based vehicles can each perform insulation fault detection. If the airborne vehicle detects an insulation fault, it means that the fault source can be located in the airborne vehicle. Then, through further power-on / off control, based on the insulation fault detection results obtained during power-on / off control, the location of the fault source can be located in the high-voltage circuit of the airborne vehicle or in the battery system of the airborne vehicle.

[0044] In some embodiments, the fault source may be located in the landmass, such as in the high-voltage circuit of the landmass or in the battery system of the landmass.

[0045] For example, the aircraft and the land-based vehicle each perform insulation fault detection. If the land-based vehicle detects an insulation fault, it means that the fault source can be located in the land-based vehicle. Then, through further power-on / off control, based on the insulation fault detection results obtained during the power-on / off control, the location of the fault source can be located in the high-voltage circuit of the land-based vehicle or in the battery system of the land-based vehicle.

[0046] The insulation fault location method for flying cars in this application embodiment can accurately determine the location of the fault source, such as the fault source being located in the connection section between the flying body and the land body; the fault source being located in the high-voltage circuit of the flying body; the fault source being located in the battery system of the flying body; the fault source being located in the high-voltage circuit of the land body; the fault source being located in the battery system of the land body, etc. This is beneficial for fault repair personnel to conduct effective fault diagnosis and quickly implement repairs.

[0047] In some embodiments, the location of the fault source is determined based on the insulation fault detection results obtained during power-on / off control, including at least one of the following:

[0048] For example, 1. After the aircraft and the land vehicle are powered on, insulation fault detection is performed, and the insulation fault detection results of the aircraft and the land vehicle are obtained respectively. If the insulation fault detection results of the aircraft and the land vehicle are both negative, the fault source is determined to be located in the connection section between the aircraft and the land vehicle.

[0049] In some embodiments, the source of the fault is determined to be the connecting segment between the airborne and land-based bodies by excluding both the airborne and land-based bodies.

[0050] For example, 2. After disconnecting the high-voltage circuit of the aircraft and the relay of the aircraft's battery system, perform insulation fault detection, obtain the insulation fault detection results of the aircraft, and if the insulation fault detection results of the aircraft indicate that there is no insulation fault, determine that the fault source is located in the high-voltage circuit of the aircraft.

[0051] For example, 3. After disconnecting the high-voltage circuit of the aircraft and the relay of the aircraft's battery system, perform insulation fault detection, obtain the insulation fault detection results of the aircraft, and if the insulation fault detection results of the aircraft indicate the presence of an insulation fault, determine that the fault source is located in the aircraft's battery system.

[0052] In some embodiments, the fault source is first located in the aircraft; then, the high-voltage circuit of the aircraft and the relays of the aircraft's battery system are disconnected; subsequently, the aircraft's overall controller reports a low-voltage power supply to prevent the aircraft's BMS from entering a sleep state and continues insulation detection. Finally, if the insulation fault detection result of the aircraft shows no insulation fault, the fault source is determined to be located in the high-voltage circuit of the aircraft; if the insulation fault detection result shows an insulation fault, the fault source is determined to be located in the aircraft's battery system.

[0053] For example, 4. After disconnecting the high-voltage circuit of the land vehicle and the relay of the battery system of the land vehicle, perform insulation fault detection, obtain the insulation fault detection result of the land vehicle, and if the insulation fault detection result of the land vehicle is that there is no insulation fault, determine that the fault source is located in the high-voltage circuit of the land vehicle.

[0054] For example, 5. After disconnecting the high-voltage circuit of the land vehicle and the relay of the battery system of the land vehicle, perform insulation fault detection, obtain the insulation fault detection result of the land vehicle, and if the insulation fault detection result of the land vehicle indicates the presence of an insulation fault, determine that the fault source is located in the battery system of the land vehicle.

[0055] In some embodiments, the fault source is first located in the land vehicle; then, the high-voltage circuit of the land vehicle and the relays of the land vehicle's battery system are disconnected; subsequently, the land vehicle's overall controller reports a low-voltage power supply to the entire unit, keeping the land vehicle's BMS from entering a sleep state, and continuing insulation detection. Finally, if the insulation fault detection result of the land vehicle indicates that there is no insulation fault, the fault source is determined to be located in the high-voltage circuit of the land vehicle; if the insulation fault detection result indicates that there is an insulation fault, the fault source is determined to be located in the land vehicle's battery system.

[0056] The insulation fault location method for flying cars in this application embodiment can perform targeted power-on and power-off control, such as disconnecting the high-voltage circuit and the relay of the battery system, which is conducive to quickly locating the fault source and improving the efficiency of fault diagnosis and user experience.

[0057] In some embodiments, the insulation fault location method for the flying car further includes: initiating insulation fault location detection of the flying car through a diagnostic instrument; wherein the diagnostic instrument is configured with an insulation fault detection mode, and when the insulation fault detection mode is detected to be on, insulation fault detection is performed on the flying car.

[0058] For example, after configuring the insulation fault detection mode on the diagnostic instrument and turning on the insulation fault detection mode, disconnect the diagnostic instrument from the flying car. The flying car then performs a power-on BMS test. Once the insulation fault detection mode is detected, it determines whether the current fault exists.

[0059] The insulation fault location method for flying cars in this application embodiment can be activated by a diagnostic instrument, which can ensure safety and reduce the difficulty of fault diagnosis for users providing after-sales service when dealing with flying cars with high-voltage coupled architecture, enabling them to quickly locate insulation faults.

[0060] To better understand this application, the following embodiments further illustrate the content of this application, but this application is not limited to the following embodiments.

[0061] Figure 2 This is another schematic flowchart illustrating the insulation fault location method for flying cars in the embodiments of this application.

[0062] See Figure 2 During operation of S210, insulation fault detection is performed.

[0063] For example, in the vehicle's diagnostic mode, an insulation fault diagnostic mode can be added by adding a diagnostic ID. The insulation fault diagnostic mode can be enabled by a diagnostic tool. After the diagnostic tool enables the insulation fault diagnostic mode, it is connected to the vehicle. When the vehicle is powered on, the BMS detects that the insulation fault diagnostic mode is enabled and performs insulation fault detection.

[0064] When operating S220, determine if there is an insulation fault.

[0065] For example, determining whether a current insulation fault exists.

[0066] If the operation is in S231, then determine whether the aircraft and the car are connected.

[0067] For example, if an insulation fault exists, determine whether the aircraft and the car are connected.

[0068] If the operation of S232 fails, a feedback of no insulation fault will be provided, and the insulation fault diagnosis mode will be exited.

[0069] For example, if there is no insulation fault, the vehicle's infotainment system will display a text message indicating that there is currently no insulation fault.

[0070] If the S240 is in operation, the connection is disconnected, and the aircraft and vehicle perform insulation fault detection.

[0071] For example, if the aircraft and the car are currently connected, the connection will be disconnected; after the high-voltage connection is disconnected, the aircraft and the car will each perform insulation fault detection.

[0072] After operating S240, operate S250 to determine whether there are any insulation faults in either the aircraft or the vehicle.

[0073] For example, the results of insulation fault detection from aircraft and automobiles can be used to determine whether there are no insulation faults in either aircraft or automobiles.

[0074] If S261 is not operated, then the aircraft has an insulation fault, while the car does not.

[0075] For example, only the aircraft reported an insulation fault, while the car did not.

[0076] If S262 is not operated, then the vehicle has an insulation fault, but the aircraft does not.

[0077] For example, only the car reported an insulation fault, while the aircraft did not.

[0078] If the operation is S263, then troubleshoot the connection segment.

[0079] For example, if neither the aircraft nor the car reports an insulation fault, the source of the insulation failure is located in the high-voltage connection section between the car and the aircraft, and the connection section is then investigated for faults.

[0080] After operating S261, operating S271 causes the aircraft-side BMS to request the disconnection of the aircraft-side battery high-voltage relay, thus disconnecting the high-voltage circuit; the aircraft as a whole controls the low-voltage power supply, the aircraft-side BMS does not enter sleep mode, and insulation fault detection is performed.

[0081] For example, the aircraft-side BMS requests to disconnect the high-voltage relay of the aircraft-side battery. After disconnecting the high-voltage circuit on the aircraft-side, the aircraft's overall controller reports a low-voltage power supply to the entire aircraft, keeping the aircraft-side BMS from entering a sleep state and continuing to perform insulation fault detection.

[0082] Operate S281 to determine if there is an insulation fault.

[0083] For example, determine whether an insulation fault has been reported at this time.

[0084] If not, troubleshoot the high-voltage circuit by operating S291.

[0085] For example, if the insulation fault no longer reports, then troubleshooting should be performed on the high-voltage circuit at the aircraft end.

[0086] If the operation is as described in S292, then troubleshoot the battery system.

[0087] For example, if an insulation fault is still reported, troubleshoot the aircraft-side battery.

[0088] After operating S262, operating S272 causes the vehicle-side BMS to request the disconnection of the vehicle-side battery high-voltage relay, thus disconnecting the high-voltage circuit; the vehicle controls low-voltage power supply, the vehicle-side BMS does not enter sleep mode, and insulation fault detection is performed.

[0089] For example, the vehicle-side BMS requests to disconnect the high-voltage relay at the vehicle-side battery, thus disconnecting the high-voltage circuit at the vehicle-side. The vehicle controller maintains low-voltage power supply to the entire vehicle, preventing the vehicle-side BMS from entering a sleep state and allowing it to continue performing insulation fault detection.

[0090] Operate S282 to determine if there is an insulation fault.

[0091] For example, determine whether an insulation fault has been reported at this time.

[0092] If the operation is as described in S293, then troubleshoot the battery system.

[0093] For example, if the insulation fault is no longer reported, then the high-voltage circuit at the vehicle end should be investigated for faults.

[0094] If not, troubleshoot the high-voltage circuit by operating S294.

[0095] For example, if an insulation fault is still reported, troubleshoot the battery on the vehicle side.

[0096] The insulation diagnostic mode can be turned off by default after a complete insulation fault detection is performed by the diagnostic instrument (operations S210-S294), or it can be turned off by default after the low-voltage power supply disconnect controller is reset in this mode. If you need to enter the insulation fault detection mode again, you need to manually turn on the diagnostic instrument again.

[0097] Corresponding to the aforementioned application function implementation method embodiments, this application also provides an insulation fault location device for a flying car, an electronic device, and corresponding embodiments.

[0098] Figure 3 This is a schematic diagram of the structure of the insulation fault location device for a flying car shown in the embodiments of this application.

[0099] See Figure 3The insulation fault location device 300 for the flying car in this embodiment includes a control module 310 and a location module 320.

[0100] The control module 310 is used to control the power supply and de-energization of the flying body and the land body of the flying car in response to the detection of an insulation fault in the flying car.

[0101] The positioning module 320 is used to determine the location of the fault source based on the insulation fault detection results obtained during power-on / off control.

[0102] Regarding the apparatus in the above embodiments, the specific manner in which each module performs its operation has been described in detail in the embodiments related to the method, and will not be elaborated further here.

[0103] According to embodiments of this application, any plurality of modules in the control module 310 and the positioning module 320 may be combined into one module, or any one of these modules may be split into multiple modules. Alternatively, at least a portion of the functionality of one or more of these modules may be combined with at least a portion of the functionality of other modules and implemented in one module. According to embodiments of this disclosure, at least one of the control module 310 and the positioning module 320 may be at least partially implemented as hardware circuitry, such as a field-programmable gate array (FPGA), a programmable logic array (PLA), a system-on-a-chip, a system-on-a-substrate, a system-on-package, an application-specific integrated circuit (ASIC), or any other reasonable means of integrating or packaging circuitry, or implemented in software, hardware, or firmware, or in any suitable combination of any of these three implementation methods. Alternatively, at least one of the control module 310 and the positioning module 320 may be at least partially implemented as a computer program module, which, when run, can perform corresponding functions.

[0104] Figure 4 This is a schematic diagram of the structure of an electronic device shown in an embodiment of this application.

[0105] See Figure 4 The electronic device 400 includes a memory 410 and a processor 420.

[0106] The processor 420 can be a Central Processing Unit (CPU), or other general-purpose processors, digital signal processors (DSPs), application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. The general-purpose processor can be a microprocessor or any conventional processor.

[0107] Memory 410 may include various types of storage units, such as system memory, read-only memory (ROM), and permanent storage devices. ROM may store static data or instructions required by processor 420 or other modules of the computer. Permanent storage devices may be read-write storage devices. Permanent storage devices may be non-volatile storage devices that retain stored instructions and data even when the computer is powered off. In some embodiments, permanent storage devices use mass storage devices (e.g., magnetic or optical disks, flash memory) as permanent storage devices. In other embodiments, permanent storage devices may be removable storage devices (e.g., floppy disks, optical drives). System memory may be a read-write storage device or a volatile read-write storage device, such as dynamic random access memory. System memory may store some or all of the instructions and data required by the processor during operation. Furthermore, memory 410 may include any combination of computer-readable storage media, including various types of semiconductor memory chips (e.g., DRAM, SRAM, SDRAM, flash memory, programmable read-only memory), and disks and / or optical disks may also be used. In some embodiments, memory 410 may include a removable storage device that is readable and / or writable, such as a laser disc (CD), a read-only digital multifunction optical disc (e.g., DVD-ROM, dual-layer DVD-ROM), a read-only Blu-ray disc, a high-density optical disc, a flash memory card (e.g., SD card, mini SD card, Micro-SD card, etc.), a magnetic floppy disk, etc. Computer-readable storage media do not contain carrier waves or transient electronic signals transmitted wirelessly or via wired connections.

[0108] The memory 410 stores executable code, which, when processed by the processor 420, can cause the processor 420 to execute part or all of the methods described above.

[0109] Furthermore, the method according to this application can also be implemented as a computer program or computer program product, which includes computer program code instructions for performing some or all of the steps in the method described above.

[0110] Alternatively, this application may be implemented as a computer-readable storage medium (or a non-transitory machine-readable storage medium or a machine-readable storage medium) storing executable code (or computer program or computer instruction code) thereon, which, when executed by a processor of an electronic device (or server, etc.), causes the processor to perform part or all of the steps of the methods described above according to this application.

[0111] The various embodiments of this application have been described above. These descriptions are exemplary and not exhaustive, nor are they 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 chosen to best explain the principles, practical application, or improvement of the technology in the market, or to enable others skilled in the art to understand the embodiments disclosed herein.

Claims

1. A method for locating insulation faults in a flying car, characterized in that, The flying car includes a flying body and a land-based body, and the method includes: In response to the detection of an insulation fault in the flying car, power-on and power-off control is performed on the flying body and the land-based body of the flying car; Based on the insulation fault detection results obtained during the power-on / off control, the location of the fault source is determined; wherein, the location of the fault source includes at least one of the following: the fault source is located in the connection section between the aircraft and the land vehicle; the fault source is located in the high-voltage circuit of the aircraft; the fault source is located in the battery system of the aircraft; the fault source is located in the high-voltage circuit of the land vehicle; the fault source is located in the battery system of the land vehicle; The power-on / off control for the flying body and the land vehicle of the flying car includes: when it is determined that the flying body and the land vehicle are connected, disconnecting the connection between the flying body and the land vehicle and powering on the flying body and the land vehicle respectively; when it is determined that the flying body has an insulation fault, disconnecting the high-voltage circuit of the flying body and the relay of the flying body's battery system; when it is determined that the land vehicle has an insulation fault, disconnecting the high-voltage circuit of the land vehicle and the relay of the land vehicle's battery system. Determining the location of the fault source based on the insulation fault detection results obtained during the power-on / off control includes: After the aircraft and the land vehicle are powered on, insulation fault detection is performed. The insulation fault detection results of the aircraft and the land vehicle are obtained respectively. If the insulation fault detection results of the aircraft and the land vehicle are both negative, the fault source is determined to be located in the connection section between the aircraft and the land vehicle. After disconnecting the high-voltage circuit of the aircraft and the relay of the battery system of the aircraft, insulation fault detection is performed, the insulation fault detection result of the aircraft is obtained, and if the insulation fault detection result of the aircraft is that there is no insulation fault, it is determined that the fault source is located in the high-voltage circuit of the aircraft. After disconnecting the high-voltage circuit of the aircraft and the relay of the battery system of the aircraft, insulation fault detection is performed, the insulation fault detection result of the aircraft is obtained, and if the insulation fault detection result of the aircraft indicates that there is an insulation fault, the fault source is determined to be located in the battery system of the aircraft. After disconnecting the high-voltage circuit of the land vehicle and the relay of the battery system of the land vehicle, insulation fault detection is performed to obtain the insulation fault detection result of the land vehicle. If the insulation fault detection result of the land vehicle is that there is no insulation fault, it is determined that the fault source is located in the high-voltage circuit of the land vehicle. After disconnecting the high-voltage circuit of the land vehicle and the relay of the battery system of the land vehicle, insulation fault detection is performed to obtain the insulation fault detection result of the land vehicle. If the insulation fault detection result of the land vehicle indicates the presence of an insulation fault, the fault source is determined to be located in the battery system of the land vehicle.

2. The method according to claim 1, characterized in that, The method further includes: The insulation fault location and detection of the flying car is initiated by a diagnostic instrument; wherein, the diagnostic instrument is equipped with an insulation fault detection mode, and when the insulation fault detection mode is detected to be turned on, insulation fault detection is performed on the flying car.

3. An insulation fault location device for a flying car, characterized in that, The device includes: The control module is used to control the power supply and de-energization of the flying body and the land-based body of the flying car in response to the detection of an insulation fault in the flying car; The positioning module is used to determine the location of the fault source based on the insulation fault detection results obtained during the power-on / off control; the location of the fault source includes at least one of the following: the fault source is located in the connection section between the aircraft and the land vehicle; the fault source is located in the high-voltage circuit of the aircraft; the fault source is located in the battery system of the aircraft; the fault source is located in the high-voltage circuit of the land vehicle; the fault source is located in the battery system of the land vehicle; The power-on / off control for the flying body and the land vehicle of the flying car includes: when it is determined that the flying body and the land vehicle are connected, disconnecting the connection between the flying body and the land vehicle and powering on the flying body and the land vehicle respectively; when it is determined that the flying body has an insulation fault, disconnecting the high-voltage circuit of the flying body and the relay of the flying body's battery system; when it is determined that the land vehicle has an insulation fault, disconnecting the high-voltage circuit of the land vehicle and the relay of the land vehicle's battery system. Determining the location of the fault source based on the insulation fault detection results obtained during the power-on / off control includes: After the aircraft and the land vehicle are powered on, insulation fault detection is performed. The insulation fault detection results of the aircraft and the land vehicle are obtained respectively. If the insulation fault detection results of the aircraft and the land vehicle are both negative, the fault source is determined to be located in the connection section between the aircraft and the land vehicle. After disconnecting the high-voltage circuit of the aircraft and the relay of the battery system of the aircraft, insulation fault detection is performed, the insulation fault detection result of the aircraft is obtained, and if the insulation fault detection result of the aircraft is that there is no insulation fault, it is determined that the fault source is located in the high-voltage circuit of the aircraft. After disconnecting the high-voltage circuit of the aircraft and the relay of the battery system of the aircraft, insulation fault detection is performed, the insulation fault detection result of the aircraft is obtained, and if the insulation fault detection result of the aircraft indicates that there is an insulation fault, the fault source is determined to be located in the battery system of the aircraft. After disconnecting the high-voltage circuit of the land vehicle and the relay of the battery system of the land vehicle, insulation fault detection is performed to obtain the insulation fault detection result of the land vehicle. If the insulation fault detection result of the land vehicle is that there is no insulation fault, it is determined that the fault source is located in the high-voltage circuit of the land vehicle. After disconnecting the high-voltage circuit of the land vehicle and the relay of the battery system of the land vehicle, insulation fault detection is performed to obtain the insulation fault detection result of the land vehicle. If the insulation fault detection result of the land vehicle indicates the presence of an insulation fault, the fault source is determined to be located in the battery system of the land vehicle.

4. An electronic device, characterized in that, include: processor; as well as A memory having executable code stored thereon, which, when executed by the processor, causes the processor to perform the method as described in claim 1 or 2.

5. A computer-readable storage medium having executable code stored thereon, which, when executed by a processor of an electronic device, causes the processor to perform the method as claimed in claim 1 or 2.

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