Flight power system, flight power reconfiguration method, and computer-readable storage medium

Abstract

The application discloses a kind of flight power system, flight power reconfiguration method and computer readable storage medium, the method comprises: if detecting that there is current short circuit in the flight power system, the flight electric drive group that current short circuit occurs is determined, and the flight electric drive group that current short circuit occurs is isolated;Control the rest of the flight electric drive group continues to run.The application guarantees the stability of power supply of flight power system, improves the safety of flight vehicle.

Description

Technical Field

[0001] This invention relates to the field of computer technology, and in particular to a flight propulsion system, a flight propulsion reconfiguration method, and a computer-readable storage medium. Background Technology

[0002] Flight propulsion systems typically employ a multi-system redundancy high-voltage architecture. This architecture includes multiple power supply units and multiple flight electric drives. Since multiple power supply units operate in parallel, a single point of failure, such as a short circuit in a power supply circuit, can cause the entire flight propulsion system to lose power, resulting in a safety accident. Summary of the Invention

[0003] The main objective of this invention is to provide a flight propulsion system, a flight propulsion reconfiguration method, and a computer-readable storage medium, aiming to solve the problem of how to improve the stability of the power supply of a flight propulsion system.

[0004] To achieve the above objectives, the present invention provides a flight propulsion system, the flight propulsion system comprising:

[0005] Power supply unit;

[0006] The flight electric drive unit, and multiple sets of the flight electric drive units are connected in parallel and then connected to the power supply unit;

[0007] An isolation device is provided on the line between each pair of adjacent flight electric drive groups to disconnect the connection between the pairs of adjacent flight electric drive groups.

[0008] Optionally, the isolation device includes a first isolation device and a second isolation device, wherein the first isolation device is disposed on the line between two adjacent sets of the flight electric drive groups located in the middle, and the second isolation device is disposed on the line between the remaining two adjacent sets of the flight electric drive groups.

[0009] Optionally, when the flight electric drive group includes at least two flight electric drives, each flight electric drive group is connected to one of the power supply units.

[0010] Optionally, when the number of power supply units is less than the number of flight electric drive groups, at least two groups of flight electric drive groups are connected to the same power supply unit; when the number of power supply units is equal to the number of flight electric drive groups, each group of flight electric drive groups is connected to a different power supply unit.

[0011] Optionally, the number of power supply units is at least two, and the flight electric drive group located at the edge is directly connected to the power supply unit.

[0012] To achieve the above objectives, the present invention provides a flight dynamics reconfiguration method, applied to a flight dynamics system, the flight dynamics reconfiguration method comprising:

[0013] If a current short circuit is detected in the flight propulsion system, the flight electric drive group that has experienced the current short circuit is identified and isolated.

[0014] Control the remaining flight electric drive units to continue operating.

[0015] Optionally, the step of identifying the flight electric drive unit experiencing a current short circuit and isolating the flight electric drive unit experiencing a current short circuit includes:

[0016] The control isolation device is opened or closed to identify and isolate the flight electric drive unit that has experienced a current short circuit.

[0017] Optionally, the steps of opening or closing the control isolation device include:

[0018] When the initial state of the first isolation device is closed, control the first isolation device to open;

[0019] Identify at least two groups of the described flight electric drive units to be screened;

[0020] The second isolation device between at least two groups of the flight electric drive units to be screened is disconnected, so as to disconnect the circuit of one group of the flight electric drive units.

[0021] If there is no current short circuit in the circuit containing the flight electric drive unit that is not disconnected, then the flight electric drive unit that has experienced a current short circuit is determined to be the disconnected flight electric drive unit.

[0022] Optionally, the steps of opening or closing the control isolation device include:

[0023] When the initial state of the first isolation device is the disconnected state, at least two groups of the flight electric drive groups to be screened are determined.

[0024] The second isolation device between at least two groups of the flight electric drive units to be screened is disconnected, so as to disconnect the circuit of one group of the flight electric drive units.

[0025] If there is no current short circuit in the circuit containing the flight electric drive unit that is not disconnected, then the flight electric drive unit that has experienced a current short circuit is determined to be the flight electric drive unit that has been disconnected.

[0026] Optionally, after the step of disconnecting the second isolation device between at least two groups of flight electric drive units to be screened, the method further includes:

[0027] If the circuit containing the flight electric drive unit that has not been disconnected still has a current short circuit, then the flight electric drive unit that has experienced a current short circuit is determined to be the flight electric drive unit that has not been disconnected.

[0028] Control the first isolation device to close again.

[0029] Optionally, after the step of disconnecting the second isolation device between at least two groups of flight electric drive units to be screened, the method further includes:

[0030] If there is no current short circuit in the circuit where the flight electric drive unit that has not been disconnected is located, then the flight electric drive unit that has experienced a current short circuit is determined to be the flight electric drive unit that has been disconnected.

[0031] If the disconnected flight electric drive unit is connected to a power supply unit, then control the power supply unit connected to the disconnected flight electric drive unit to stop supplying power.

[0032] Optionally, after the step of disconnecting the second isolation device between at least two groups of flight electric drive units to be screened, the method further includes:

[0033] If the circuit containing the flight electric drive unit that has not been disconnected still has a current short circuit, then the flight electric drive unit that has experienced a current short circuit is determined to be the flight electric drive unit that has not been disconnected.

[0034] Control the first isolation device to close again;

[0035] If the flight electric drive unit that is not disconnected is connected to a power supply unit, then control the power supply unit connected to the flight electric drive unit that is not disconnected to stop supplying power.

[0036] To achieve the above objectives, the present invention also provides a flight propulsion system, the flight propulsion system including a memory, a processor, and a power reconfiguration program stored in the memory and executable on the processor, wherein when the power reconfiguration program is executed by the processor, it implements the various steps of the power reconfiguration method as described above.

[0037] To achieve the above objectives, the present invention also provides a computer-readable storage medium storing a power reconfiguration program, which, when executed by a processor, implements the various steps of the power reconfiguration method as described above.

[0038] This invention provides a flight propulsion system, a flight propulsion reconfiguration method, and a computer-readable storage medium. By identifying and isolating the flight electric drive group experiencing a current short circuit, the normal operation of the flight propulsion system of the flying vehicle is ensured, while the remaining flight electric drive groups continue to operate. This ensures that the flight propulsion system provides sufficient power to support the flight of the flying vehicle, avoids the failure of the entire flight propulsion system due to a short circuit in one flight electric drive group, guarantees the stability of the power supply of the flight propulsion system, and improves the safety of the flying vehicle. Attached Figure Description

[0039] Figure 1 This is a schematic diagram of the power system of the present invention;

[0040] Figure 2 This is a schematic diagram of the power system of the present invention;

[0041] Figure 3 This is a schematic diagram of the power system of the present invention;

[0042] Figure 4 This is a schematic diagram of the control module of the power system of the present invention;

[0043] Figure 5 This is a schematic diagram of the control module of the power system of the present invention;

[0044] Figure 6 This is a schematic diagram of the control module of the power system of the present invention;

[0045] Figure 7 This is a schematic diagram of the hardware structure of the flight propulsion system according to an embodiment of the present invention;

[0046] Figure 8 This is a flowchart illustrating the first embodiment of the power reconfiguration method of the present invention;

[0047] Figure 9 This is a detailed flowchart of step S10 in the second embodiment of the dynamic reconfiguration method of the present invention;

[0048] Figure 10 This is a detailed flowchart of step S11 in the third embodiment of the dynamic reconfiguration method of the present invention.

[0049] Figure 11 This is a detailed flowchart of step S11 of the fourth embodiment of the dynamic reconfiguration method of the present invention.

[0050] Explanation of icon numbers:

[0051]

[0052] The realization of the objective, functional features and advantages of the present invention will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0053] It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

[0054] The main solution of this invention is: by identifying and isolating the flight electric drive group that experiences a current short circuit, the normal operation of the flight power system of the flying vehicle is ensured, and the remaining flight electric drive groups are controlled to continue operating, ensuring that the flight power system of the flying vehicle provides sufficient power to support the flight of the flying vehicle. This avoids the entire flight power system from malfunctioning when a short circuit occurs in one flight electric drive group, ensuring the stability of the power supply of the flight power system and improving the safety of the flying vehicle.

[0055] Reference Figures 1 to 3 , Figures 1 to 3 A flight propulsion system is provided, the flight propulsion system comprising: a power supply unit 101; multiple flight electric drive groups connected in parallel and connected to the power supply unit 101; and an isolation device disposed on the line between each pair of adjacent flight electric drive groups for disconnecting the connection between adjacent pairs of flight electric drive groups.

[0056] Optionally, the flight propulsion system is the propulsion system of an aircraft, flying vehicle, etc.

[0057] Optionally, the power supply unit 101 is used to supply power to the flight electric drive assembly, for example, the power supply unit 101 is a battery.

[0058] Optionally, the flight electric drive assembly includes at least one flight electric drive, which provides power to the flight device, which may be a flying car or the like.

[0059] like Figure 1 As shown, the flight electric drive group includes a flight electric drive, wherein flight electric drive group 1 includes flight electric drive 102a, flight electric drive group 2 includes flight electric drive 102b, flight electric drive group 3 includes flight electric drive 102c, and flight electric drive group 4 includes flight electric drive 102d.

[0060] like Figure 2 As shown, the flight electric drive group includes two flight electric drives. Flight electric drive group 1 includes flight electric drive 102a and flight electric drive 102b, flight electric drive group 2 includes flight electric drive 102c and flight electric drive 102d, flight electric drive group 3 includes flight electric drive 102e and flight electric drive 102f, and flight electric drive group 4 includes flight electric drive 102g and flight electric drive 102h.

[0061] Optionally, the isolation device is installed on the wiring between every two adjacent sets of flight electric drive groups, such as... Figure 1 As shown, an isolation device is provided between flight electric drives 102a and 102b, between flight electric drives 102b and 102c, and between flight electric drives 102c and 102d. Figure 2 As shown, an isolation device is provided between flight electric drive group 1 and flight electric drive group 2, an isolation device is provided between flight electric drive group 2 and flight electric drive group 3, and an isolation device is provided between flight electric drive group 3 and flight electric drive group 4.

[0062] Optionally, the isolation device includes a first isolation device 103 and a second isolation device 104. Optionally, the first isolation device 103 can be a fast isolation device, such as an SSPC (Solid-State Power Controller). Optionally, the second isolation device 104 can be a current fuse, etc. Optionally, the first isolation device 103 and the second isolation device 104 can be switching devices.

[0063] Optionally, the first isolation device 103 is disposed on the line between two adjacent sets of flight electric drive groups located in the middle.

[0064] like Figure 1 As shown, the two adjacent flight electric drive groups in the middle are flight electric drive 102b and flight electric drive 102c. The first isolation device 103 is installed on the line between flight electric drive 102b and flight electric drive 102c. The second isolation device 104 is installed on the line between the remaining two adjacent flight electric drive groups, that is, the second isolation device 104 is installed on the line between flight electric drive 102a and flight electric drive 102b, and the second isolation device 104 is installed on the line between flight electric drive 102c and flight electric drive 102d.

[0065] like Figure 2 As shown, the two adjacent groups of flight electric drive groups in the middle are flight electric drive group 2 and flight electric drive group 3. The first isolation device 103 is installed on the line between flight electric drive group 2 and flight electric drive group 3, and the second isolation device 104 is installed on the line between the remaining two adjacent groups of flight electric drive groups, that is, the second isolation device 104 is installed on the line between flight electric drive group 1 and flight electric drive group 2, and the second isolation device 104 is installed on the line between flight electric drive group 3 and flight electric drive group 4.

[0066] Optionally, when the flight electric drive group includes at least two flight electric drives, each flight electric drive group is connected to a power supply unit 101, such as... Figure 2As shown, flight electric drive group 1 is connected to power supply unit 101a, flight electric drive group 2 is connected to power supply unit 101b, flight electric drive group 3 is connected to power supply unit 101c, and flight electric drive group 4 is connected to power supply unit 101d to ensure the power supply of the flight electric drive group and ensure the normal operation of the flight electric drive in the flight electric drive group.

[0067] Optionally, when the number of power supply units is less than the number of flight electric drive groups, at least two flight electric drive groups are connected to the same power supply unit 101. For example... Figure 1 As shown, after the first isolation device 103 is disconnected, the flight electric drive 102a is connected to the power supply unit 101a, the flight electric drive 102b is connected to the power supply unit 101a, the flight electric drive 102c is connected to the power supply unit 101b, and the flight electric drive 102d is connected to the power supply unit 101b.

[0068] like Figure 3 As shown, after the second isolation device 104 and the first isolation device 103 between flight electric drives 102a and 102b are disconnected, flight electric drive 102a is connected to power supply unit 101a, flight electric drive 102b is connected to power supply unit 101b, and flight electric drives 102c and 102d are connected to power supply unit 101c.

[0069] Optionally, when the number of power supply units equals the number of flight electric drive groups, each flight electric drive group is connected to a different power supply unit 101. For example... Figure 2 As shown, when all isolation devices are disconnected, flight electric drive group 1 is connected to power supply unit 101a, flight electric drive group 2 is connected to power supply unit 101b, flight electric drive group 3 is connected to power supply unit 101c, and flight electric drive group 4 is connected to power supply unit 101d.

[0070] Optionally, when there is only one power supply unit 101 and multiple flight electric drive groups, the isolation device that caused the current short circuit can be identified by sequentially disconnecting the isolation devices between each flight electric drive group. For example, if four flight electric drive groups are connected in parallel to the power supply unit 101, in order to determine the specific line where the current short circuit occurred, the isolation devices between each flight electric drive group are disconnected. For example, when the isolation device between flight electric drive group 3 and flight electric drive group 4 is disconnected, there is no current short circuit in the flight power system. Therefore, the flight electric drive group that caused the current short circuit is identified as flight electric drive group 4, and the remaining flight electric drive groups can continue to operate to ensure flight power.

[0071] Optionally, when there are at least two power supply units 101, the flight electric drive units located at the edge are connected to the power supply units 101 respectively, such as... Figure 1As shown, the flight electric drive units located at the edge are flight electric drive 102a and flight electric drive 102d. Flight electric drive 102a and flight electric drive 102d are directly connected to the corresponding power supply unit. Even if the isolation device is disconnected, the flight electric drive units located at the edge will be continuously powered.

[0072] In one embodiment, such as Figure 4 As shown, taking two power supply units and four flight electric drives as an example, the flight power system also includes a control module. The first isolation device control module 501 is connected to the flight electric drive control module 301, specifically to flight electric drive control modules 301a, 301b, 301c, and 301d. The first isolation device control module 501 is also connected to the power supply unit control module, specifically to power supply unit control module 202a and 202b. After the flight electric drive control modules are connected in parallel, they are connected to the flight control module 401, and the power supply unit control modules are also connected to the flight control module 401.

[0073] In one embodiment, such as Figure 5 As shown, taking four power supply units and eight flight electric drives as an example, the flight power system also includes a control module. The first isolation device control module 501 is connected to the flight electric drive control modules respectively, that is, the first isolation device control module 501 is connected to the flight electric drive control modules 301a to 301h respectively; the first isolation device control module 501 is connected to the power supply unit control modules respectively, that is, the first isolation device control module 501 is connected to the power supply unit control modules 202a to 202d respectively; after the flight electric drive control modules are connected in parallel, they are connected to the flight control module 401, and the power supply unit control modules are connected to the flight control module 401 respectively.

[0074] In one embodiment, such as Figure 6As shown, taking three power supply units and four flight electric drives as an example, the flight power system also includes a control module. The first isolation device control module 501 is connected to the flight electric drive control modules respectively, that is, the first isolation device control module 501 is connected to the flight electric drive control modules 301a to 301d respectively; the first isolation device control module 501 is connected to the power supply unit control modules respectively, that is, the first isolation device control module 501 is connected to the power supply unit control modules 202a to 202c respectively; after the flight electric drive control modules are connected in parallel, they are connected to the flight control module 401, and the power supply unit control modules are connected to the flight control module 401 respectively.

[0075] In the technical solution of this embodiment, by setting an isolation device between each adjacent flight electric drive group, the failure of the entire flight power system is prevented when a short circuit occurs in a certain flight electric drive group, thereby ensuring the stability of the power supply of the flight power system and improving the safety of the flying vehicle.

[0076] As one implementation method, the flight propulsion system can be as follows: Figure 7 As shown.

[0077] The embodiments of the present invention relate to a flight propulsion system, which includes: a processor 101, such as a CPU, a memory 102, and a communication bus 103. The communication bus 103 is used to enable communication between these components.

[0078] Memory 102 can be high-speed RAM or stable memory (non-volatile memory), such as disk storage. Figure 7 As shown, the memory 102, which is a computer-readable storage medium, may include a power reconfiguration program; and the processor 101 may be used to call the power reconfiguration program stored in the memory 102 and perform the following operations:

[0079] If a current short circuit is detected in the flight propulsion system, the flight electric drive group that has experienced the current short circuit is identified and isolated.

[0080] Control the remaining flight electric drive units to continue operating.

[0081] Optionally, the processor 101 can be used to call the power reconfiguration program stored in the memory 102 and perform the following operations:

[0082] The control isolation device is opened or closed to identify and isolate the flight electric drive unit that has experienced a current short circuit.

[0083] Optionally, the processor 101 can be used to call the power reconfiguration program stored in the memory 102 and perform the following operations:

[0084] When the initial state of the first isolation device is closed, control the first isolation device to open;

[0085] Identify at least two groups of the described flight electric drive units to be screened;

[0086] The second isolation device between at least two groups of the flight electric drive units to be screened is disconnected, so as to disconnect the circuit of one group of the flight electric drive units.

[0087] If there is no current short circuit in the circuit containing the flight electric drive unit that is not disconnected, then the flight electric drive unit that has experienced a current short circuit is determined to be the disconnected flight electric drive unit.

[0088] Optionally, the processor 101 can be used to call the power reconfiguration program stored in the memory 102 and perform the following operations:

[0089] When the initial state of the first isolation device is the disconnected state, at least two groups of the flight electric drive groups to be screened are determined.

[0090] The second isolation device between at least two groups of the flight electric drive units to be screened is disconnected, so as to disconnect the circuit of one group of the flight electric drive units.

[0091] If there is no current short circuit in the circuit containing the flight electric drive unit that is not disconnected, then the flight electric drive unit that has experienced a current short circuit is determined to be the flight electric drive unit that has been disconnected.

[0092] Optionally, the processor 101 can be used to call the power reconfiguration program stored in the memory 102 and perform the following operations:

[0093] If the circuit containing the flight electric drive unit that has not been disconnected still has a current short circuit, then the flight electric drive unit that has experienced a current short circuit is determined to be the flight electric drive unit that has not been disconnected.

[0094] Control the first isolation device to close again.

[0095] Optionally, the processor 101 can be used to call the power reconfiguration program stored in the memory 102 and perform the following operations:

[0096] If there is no current short circuit in the circuit where the flight electric drive unit that has not been disconnected is located, then the flight electric drive unit that has experienced a current short circuit is determined to be the flight electric drive unit that has been disconnected.

[0097] If the disconnected flight electric drive unit is connected to a power supply unit, then control the power supply unit connected to the disconnected flight electric drive unit to stop supplying power.

[0098] Optionally, the processor 101 can be used to call the power reconfiguration program stored in the memory 102 and perform the following operations:

[0099] If the circuit containing the flight electric drive unit that has not been disconnected still has a current short circuit, then the flight electric drive unit that has experienced a current short circuit is determined to be the flight electric drive unit that has not been disconnected.

[0100] Control the first isolation device to close again;

[0101] If the flight electric drive unit that is not disconnected is connected to a power supply unit, then control the power supply unit connected to the flight electric drive unit that is not disconnected to stop supplying power.

[0102] Based on the hardware architecture and structure of the aforementioned flight propulsion system, an embodiment of the propulsion reconfiguration method of the present invention is proposed.

[0103] Reference Figure 8 , Figure 8 This is a first embodiment of the power reconfiguration method of the present invention, the power reconfiguration method comprising the following steps:

[0104] Step S10: If a current short circuit is detected in the flight power system, the flight electric drive group that has experienced the current short circuit is identified and the flight electric drive group that has experienced the current short circuit is isolated.

[0105] Optionally, the magnitude and direction of the current in the flight propulsion system are detected in real time. Optionally, the first isolation device control module detects the magnitude and direction of the current in the flight propulsion system in real time.

[0106] Optionally, when a short circuit fault occurs in the high-voltage circuit of the flight propulsion system, a short circuit current will be generated. Therefore, if the current exceeds a preset current threshold, it is determined that there is a current short circuit in the flight propulsion system.

[0107] However, if a short circuit occurs in the flight propulsion system, and all the flight electric drive units simultaneously stop working, the aircraft will lose power and crash. If half of the flight electric drive units stop working, the aircraft will descend with a certain acceleration and eventually crash as well. To provide sufficient lift to ensure stable flight and landing, at least a predetermined number of flight electric drive units must operate simultaneously, where the predetermined number is a predetermined proportion of the total number, for example, three-quarters of the total number.

[0108] Therefore, it is necessary to identify the flight electric drive unit experiencing a current short circuit and isolate it, while connecting the remaining flight electric drive units to the power supply unit. Optionally, current detection can be performed on the circuit of each flight electric drive unit individually to identify the flight electric drive unit experiencing a current short circuit.

[0109] Step S20: Control the remaining flight electric drive units to continue operating.

[0110] Optionally, after isolating the flight electric drive unit that experienced a current short circuit, the remaining flight electric drive units are controlled to continue operating in order to provide sufficient lift to ensure the stable flight and landing of the flying vehicle.

[0111] In the technical solution of this embodiment, by identifying and isolating the flight electric drive group that has experienced a current short circuit, the normal operation of the flight power system of the flying vehicle is ensured, and the remaining flight electric drive groups are controlled to continue operating, ensuring that the flight power system of the flying vehicle provides sufficient power to support the flight of the flying vehicle. This avoids the entire flight power system from malfunctioning when a short circuit occurs in one flight electric drive group, ensuring the stability of the power supply of the flight power system and improving the safety of the flying vehicle.

[0112] Reference Figure 9 , Figure 9 In a second embodiment of the power reconfiguration method of the present invention, based on the first embodiment, step S10, which involves identifying the flight electric drive unit experiencing a current short circuit and isolating the flight electric drive unit experiencing the current short circuit, includes:

[0113] Step S11: Control the opening or closing of the isolation device to identify the flight electric drive group that has experienced a current short circuit and isolate the flight electric drive group that has experienced a current short circuit.

[0114] Optionally, when there is one power supply unit and multiple flight electric drive groups, the isolation device where the current short circuit occurred can be identified by sequentially disconnecting the isolation devices between each flight electric drive group. For example, if four flight electric drive groups are connected in parallel to the power supply unit, in order to determine the specific line where the current short circuit occurred, the isolation devices between each flight electric drive group are disconnected. For example, when the isolation device between flight electric drive group 3 and flight electric drive group 4 is disconnected, there is no current short circuit in the flight power system. Therefore, the flight electric drive group where the current short circuit occurred is identified as flight electric drive group 4, and the remaining flight electric drive groups can continue to operate to ensure flight power.

[0115] In the technical solution of this embodiment, by controlling the opening and closing of the isolation device, the flight electric drive group that has experienced a current short circuit is identified and isolated. By identifying and isolating the flight electric drive group that has experienced a current short circuit, the normal operation of the flight power system of the flying vehicle is ensured. The remaining flight electric drive groups are controlled to continue operating, ensuring that the flight power system of the flying vehicle provides sufficient power to support the flight of the flying vehicle. This avoids the failure of the entire flight power system when a short circuit occurs in a certain flight electric drive group, ensuring the stability of the power supply of the flight power system and improving the safety of the flying vehicle.

[0116] Reference Figure 10 , Figure 10 In a third embodiment of the power reconfiguration method of the present invention, based on the first or second embodiment, step S11 includes:

[0117] Step S111: When the initial state of the first isolation device is closed, control the first isolation device to open.

[0118] Step S112: Determine at least two groups of the flight electric drive units to be screened;

[0119] Step S113: Control the second isolation device between at least two groups of flight electric drive groups to be screened to disconnect, so that the circuit of one group of flight electric drive groups is disconnected.

[0120] Step S114: If there is no current short circuit in the circuit where the flight electric drive group that has not been disconnected is located, then the flight electric drive group that has experienced a current short circuit is determined to be the flight electric drive group that has been disconnected.

[0121] Optionally, since the first isolation device 103 is located on the line between two adjacent sets of flight electric drive groups in the middle, the first isolation device 103 is disconnected, the flight electric drive group is divided into two parts, the current of the lines where the two parts of the flight electric drive group are located is re-detected, and the flight electric drive group that still has a current short circuit is determined to be at least two sets of flight electric drive groups to be screened.

[0122] Optionally, the second isolation device 104 between at least two groups of flight electric drive units to be screened is disconnected, thereby disconnecting the circuit of one group of flight electric drive units.

[0123] Optionally, if there is no current short circuit in the circuit where the flight electric drive unit that has not been disconnected is located, then the flight electric drive unit that has experienced a current short circuit is determined to be the disconnected flight electric drive unit.

[0124] Optionally, if a short circuit still exists in the circuit where the flight electric drive unit is located, the flight electric drive unit that has experienced a short circuit is identified as the flight electric drive unit that is not disconnected; the first isolation device 103 is controlled to close again to reconnect the disconnected flight electric drive unit to the power supply unit.

[0125] Optionally, if there is no current short circuit in the circuit where the flight electric drive unit that is not disconnected is located, then the flight electric drive unit that has experienced a current short circuit is determined to be the disconnected flight electric drive unit; if the disconnected flight electric drive unit is connected to a power supply unit, then the power supply unit connected to the disconnected flight electric drive unit is controlled to stop supplying power.

[0126] Optionally, if a current short circuit still exists in the circuit where the flight electric drive unit is located, the flight electric drive unit that has experienced a current short circuit is identified as the flight electric drive unit that is not disconnected; the first isolation device 103 is controlled to close again; if the flight electric drive unit that is not disconnected is connected to a power supply unit, the power supply unit connected to the flight electric drive unit that is not disconnected is controlled to stop supplying power.

[0127] Optionally, such as Figure 1 As shown, taking two power supply units and four flight electric drives as an example, but not limited to this structure, if a current short circuit is detected in the flight power system and the initial state of the first isolation device 103 is closed, then the first isolation device 103 is controlled to open, dividing the flight electric drive group into two parts. Among them, flight electric drives 102a and 102b are connected to power supply unit 101a, and flight electric drives 102c and 102d are connected to power supply unit 101b. The current in the circuit where the two parts of the flight electric drive are located is detected respectively.

[0128] Optionally, if a current short circuit occurs in the circuit containing flight electric drive 102a and flight electric drive 102b, then flight electric drive 102a and flight electric drive 102b are determined to be at least two flight electric drive groups to be screened. The second isolation device 104 between flight electric drive 102a and flight electric drive 102b is disconnected. At this time, the circuit containing flight electric drive 102b is disconnected. If there is no current short circuit in the flight electric drive group that is not disconnected, that is, there is no current short circuit in the circuit containing flight electric drive 102a, then flight electric drive 102b is determined to be the flight electric drive group that has experienced a current short circuit. If a short circuit occurs in an undisconnected flight electric drive unit, the flight electric drive unit where the short circuit occurs is identified as the flight electric drive unit where flight electric drive 102a is located. The first isolation device 103 is closed so that flight electric drive 102b is reconnected to the power supply unit, that is, flight electric drive 102b is connected to power supply unit 101b. Before closing the first isolation device 103, it is also necessary to control the power supply unit 101a connected to flight electric drive 102a to stop supplying power to ensure that the power supply unit is not burned out by the short circuit current.

[0129] Optionally, if a current short circuit occurs in the circuit containing flight electric drives 102c and 102d, then flight electric drives 102c and 102d are determined to be at least two flight electric drive groups to be screened. The second isolation device 104 between flight electric drives 102c and 102d is then disconnected. At this time, the circuit containing flight electric drive 102c is disconnected. If there is no current short circuit in the flight electric drive group that is not disconnected, that is, there is no current short circuit in the circuit containing flight electric drive 102d, then flight electric drive 102c is determined to be the flight electric drive group that has experienced a current short circuit. If a short circuit occurs in an undisconnected flight electric drive unit, the flight electric drive unit where the short circuit occurs is identified as the flight electric drive unit where flight electric drive 102d is located. The first isolation device 103 is then closed so that flight electric drive 102c is reconnected to the power supply unit, that is, flight electric drive 102c is connected to power supply unit 101a. Before closing the first isolation device 103, it is also necessary to control the power supply unit 101b connected to flight electric drive 102d to stop supplying power to ensure that the power supply unit is not burned out by the short circuit current.

[0130] In one embodiment, such as Figure 4 As shown, in the power reconfiguration control strategy, the first isolation device control module 501 monitors the magnitude and direction of the current passing through it in real time. When a short-circuit fault occurs in the flight power system circuit, a short-circuit current is generated. After the first isolation device control module 501 detects that the current is greater than or equal to a preset current threshold, it controls the first isolation device 103 to disconnect within a preset time T1, and then sends the disconnected status of the first isolation device 103 to the power supply unit control module 202a and the power supply unit control module 202b. When the first isolation device 103 is disconnected, the short-circuit fault point is isolated on the side of power supply unit 101a or power supply unit 101b. At this time, two flight electric drive control modules enter a fault state and send a fault status to the flight control module 401, while two flight electric drive control modules remain in the working state and send a working status to the flight control module 401. When the flight control module 401 detects that the flight electric drive control module has entered a fault state, it sends a restart command to the flight electric drive working mode. The flight electric drive control module does not respond to the restart command sent by the flight control module 401 when in a fault state.

[0131] When the first isolation device control module 501 is disconnected, the current flow direction before disconnection is used to determine whether the current flows from the power supply unit 101a side to the power supply unit 101b side. If the current flows from the power supply unit 101b side to the power supply unit 101a side, the second isolation device 1042 is disconnected. If the current flows from the power supply unit 101b side to the power supply unit 101a side, the second isolation device 1041 is disconnected. Specifically, the second isolation device 104 between flight electric drives 102a and 102b is the second isolation device 1041, and the second isolation device 104 between flight electric drives 102c and 102d is the second isolation device 1042.

[0132] The power supply unit control module 202a and power supply unit control module 202b will perform auxiliary judgment. If the power supply unit 101a detects an abnormal current, it will send a second isolation device 1041 cut-off request command to the first isolation device control module 501 to cut off. If the power supply unit 101b detects an abnormal current, it will send a second isolation device 1042 cut-off request command to the first isolation device control module 501 to cut off.

[0133] If the second isolation device 1041 disconnects, the power supply unit control module 202a makes a judgment. If the current returns to normal, it proves that the short circuit point is between isolation device 1 and the first isolation device 103. In this case, power reconfiguration is not required. Power supply unit 101a supplies power to flight electric drive 102a, and power supply unit 101b supplies power to flight electric drives 102c and 102d. If the current does not return to normal, it proves that the short circuit point is between power supply unit 101a and isolation device 1. In this case, power reconfiguration is required. The power supply unit control module 202a sends a power reconfiguration request to the first isolation device control module 501.

[0134] If the second isolation device 1042 disconnects, the power supply unit control module 202b will determine whether the short circuit is between the isolation device 2 and the first isolation device 103. In this case, power reconfiguration is not required. Power supply unit 101b supplies power to flight electric drive 102d, and power supply unit 101a supplies power to flight electric drives 102a and 102b. If the current does not return to normal, it indicates that the short circuit is between power supply unit 101b and isolation device 2. In this case, power reconfiguration is required, and the power supply unit control module 202b sends a power reconfiguration request to the first isolation device control module 501.

[0135] If the first isolation device control module 501 receives a request that all power reconfiguration requests are none, it will remain in the disconnected state. If any power reconfiguration request is yes, it will begin power reconfiguration.

[0136] The first isolation device control module 501 controls the first isolation device 103 to close again, controls the output voltage to rise gradually without damaging components such as capacitors, reaches the battery voltage within time T2, and then sends a message that the power reconfiguration result is complete to the flight electric drive control module.

[0137] After receiving a message indicating that the power reconfiguration is complete and detecting that the flight electric drive input voltage has returned to normal, the flight electric drive control module transitions from a fault state to a standby state. At this point, it responds to a restart command sent by the flight module and then transitions from standby to restart state. Upon detecting that the flight electric drive control module has entered restart state, the flight control module 401 sends the target speed N for the flight electric drive to the flight electric drive control module. The flight electric drive control module responds to the target speed, controlling the flight electric drive to operate at the target speed value and sending the "actual speed of the flight electric drive" to the flight control module 401. Once the flight control module 401 detects that the actual speed of the flight electric drive has reached the target speed, it sends a message indicating that the flight electric drive is in operation to the flight electric drive. Upon receiving this message, the flight electric drive transitions from restart state to operating state, and the power reconfiguration is complete.

[0138] Optionally, such as Figure 2 As shown, taking four power supply units and eight flight electric drives as an example, but not limited to this structure, if a current short circuit is detected in the flight power system, and the initial state of the first isolation device 103 is closed, the first isolation device 103 is opened, dividing the flight electric drive group into two parts. Flight electric drive group 1 and flight electric drive group 2 are connected to power supply units 101a and 101b, while flight electric drive group 3 and flight electric drive group 4 are connected to power supply units 101c and 101d. The current in both circuits is then detected.

[0139] Optionally, if a short circuit occurs in the circuit containing flight electric drive group 1 and flight electric drive group 2, then flight electric drive group 1 and flight electric drive group 2 are identified as at least two flight electric drive groups to be screened. The second isolation device 104 between flight electric drive group 1 and flight electric drive group 2 is disconnected. At this time, the circuit containing flight electric drive group 2 is disconnected. If there is no short circuit in the flight electric drive group that is not disconnected, that is, there is no short circuit in the circuit containing flight electric drive group 1, then flight electric drive group 2 is identified as the flight electric drive group that has experienced a short circuit. The power supply unit 101b connected to flight electric drive group 2 is stopped from supplying power to ensure that the power supply unit is not burned out by the short circuit current. If there is a short circuit in the flight electric drive group that is not disconnected, then flight electric drive group 1 is identified as the flight electric drive group that has experienced a short circuit. The first isolation device 103 is closed so that flight electric drive group 2 is reconnected to the power supply unit, that is, flight electric drives 102c and 102d are connected to power supply units 101b, 101c, and 101d. Before closing the first isolation device 103, it is also necessary to control the power supply unit 101a connected to the flight electric drive group 1 to stop supplying power to ensure that the power supply unit is not burned by the short circuit.

[0140] Optionally, if a short circuit occurs in the circuits containing flight electric drive group 3 and flight electric drive group 4, then flight electric drive group 3 and flight electric drive group 4 are identified as at least two flight electric drive groups to be screened. The second isolation device 104 between flight electric drive group 3 and flight electric drive group 4 is disconnected. At this time, the circuit containing flight electric drive group 3 is disconnected. If there is no short circuit in the flight electric drive group that is not disconnected, that is, there is no short circuit in the circuit containing flight electric drive group 4, then flight electric drive group 4 is identified as the flight electric drive group that has experienced a short circuit. The power supply unit 101d connected to flight electric drive group 4 is controlled to stop supplying power to ensure that the power supply unit is not burned out by the short circuit current. If a short circuit occurs in the flight electric drive unit that has not been disconnected, the flight electric drive unit that has experienced the short circuit is identified as flight electric drive unit 4. The first isolation device 103 is then closed to reconnect flight electric drive unit 3 to the power supply unit. That is, flight electric drive unit 3 is connected to power supply units 101a, 101b, and 101c. Before closing the first isolation device 103, it is also necessary to control the power supply unit 101d connected to flight electric drive unit 4 to stop supplying power to ensure that the power supply unit is not burned out by the short circuit current.

[0141] In one embodiment, such as Figure 5 As shown, the power reconfiguration control strategy is the same as the control strategy for the two battery packs and four flight electric drives. It only requires that the power supply unit on the reconfiguration side be powered down before closing the first isolation device 103.

[0142] Optionally, such as Figure 3As shown, taking three power supply units and four flight electric drives as an example, but not limited to this structure, if a current short circuit is detected in the flight power system and the initial state of the first isolation device 103 is closed, then the first isolation device 103 is opened, dividing the flight electric drive group into two parts. Flight electric drive group 1 and flight electric drive group 2 are connected to power supply units 101a and 101b, and flight electric drive group 3 and flight electric drive group 4 are connected to power supply unit 101c. The current in the circuits of the two flight electric drive groups is detected respectively.

[0143] Optionally, if a short circuit occurs in the circuits containing flight electric drive group 1 and flight electric drive group 2, then flight electric drive group 1 and flight electric drive group 2 are identified as at least two flight electric drive groups to be screened. The second isolation device 104 between flight electric drive group 1 and flight electric drive group 2 is disconnected. At this time, the circuit containing flight electric drive group 2 is disconnected. If there is no short circuit in the flight electric drive group that is not disconnected, that is, there is no short circuit in the circuit containing flight electric drive group 1, then flight electric drive group 2 is identified as the flight electric drive group that has experienced a short circuit. Since flight electric drive group 2 is connected to a power supply unit, the power supply unit 101b connected to flight electric drive group 2 is controlled to stop supplying power to ensure that the power supply unit is not burned out by the short circuit current. If there is a short circuit in the flight electric drive group that is not disconnected, then flight electric drive group 1 is identified as the flight electric drive group that has experienced a short circuit. The first isolation device 103 is closed so that flight electric drive group 2 is reconnected to the power supply unit, that is, flight electric drive 102b is connected to power supply unit 101b and power supply unit 101c. Before closing the first isolation device 103, it is also necessary to control the power supply unit 101a connected to the flight electric drive group 1 to stop supplying power to ensure that the power supply unit is not burned by the short circuit.

[0144] Optionally, if a current short circuit occurs in the circuits containing flight electric drive group 3 and flight electric drive group 4, then flight electric drive group 102c and flight electric drive group 4 are identified as at least two flight electric drive groups to be screened. The second isolation device 104 between flight electric drive group 3 and flight electric drive group 4 is disconnected. At this time, the circuit containing flight electric drive group 3 is disconnected. If there is no current short circuit in the flight electric drive group that is not disconnected, that is, there is no current short circuit in the circuit containing flight electric drive group 4, then flight electric drive 102c is identified as the flight electric drive group that has experienced a current short circuit. If a short circuit occurs in an undisconnected flight electric drive unit, the flight electric drive unit where the short circuit occurs is identified as the flight electric drive unit where flight electric drive 102d is located. The first isolation device 103 is closed so that flight electric drive 102c is reconnected to the power supply unit, that is, flight electric drive 102c is connected to power supply unit 101a. Before closing the first isolation device 103, it is also necessary to control the power supply unit 101b connected to flight electric drive 102c to stop supplying power to ensure that the power supply unit is not burned out by the short circuit current.

[0145] In one embodiment, such as Figure 6As shown, the power reconfiguration control strategy is the same as the control strategy for the two battery packs and four flight electric drives. It only requires that the power supply unit on the reconfiguration side be powered down before closing the first isolation device 103.

[0146] In the technical solution of this embodiment, by controlling the opening or closing of the first isolation device 103 and the second isolation device 104, the flight electric drive group that has experienced a current short circuit is identified and isolated. By identifying and isolating the flight electric drive group that has experienced a current short circuit, the normal operation of the flight power system of the flying vehicle is ensured. The remaining flight electric drive groups are controlled to continue operating, ensuring that the flight power system of the flying vehicle provides sufficient power to support the flight of the flying vehicle. This avoids the entire flight power system from malfunctioning when a short circuit occurs in a certain flight electric drive group, ensuring the stability of the power supply of the flight power system and improving the safety of the flying vehicle.

[0147] Reference Figure 11 , Figure 11 In the fourth embodiment of the dynamic reconfiguration method of the present invention, based on any one of the first to third embodiments, step S11 includes:

[0148] Step S115: When the initial state of the first isolation device is the disconnected state, determine at least two groups of the flight electric drive groups to be screened;

[0149] Step S116: Control the second isolation device between at least two groups of flight electric drive groups to be screened to disconnect, so that the circuit of one group of flight electric drive groups is disconnected.

[0150] Step S117: If there is no current short circuit in the circuit where the flight electric drive group that has not been disconnected is located, then the flight electric drive group that has experienced a current short circuit is determined to be the flight electric drive group that has been disconnected.

[0151] Optionally, when the initial state of the first isolation device 103 is the open state, when a current short circuit occurs in the flight power system, the magnitude and direction of the current of the two flight electric drive groups are directly detected to determine whether at least two flight electric drive groups to be screened have experienced a current short circuit.

[0152] Optionally, the second isolation device 104 between at least two groups of flight electric drive units to be screened is disconnected, thereby disconnecting the circuit of one group of flight electric drive units.

[0153] Optionally, if there is no current short circuit in the circuit where the flight electric drive unit that has not been disconnected is located, then the flight electric drive unit that has experienced a current short circuit is determined to be the disconnected flight electric drive unit.

[0154] Optionally, if a short circuit still exists in the circuit where the flight electric drive unit is located, the flight electric drive unit that has experienced a short circuit is identified as the flight electric drive unit that is not disconnected; the first isolation device 103 is controlled to close again to reconnect the disconnected flight electric drive unit to the power supply unit.

[0155] Optionally, if there is no current short circuit in the circuit where the flight electric drive unit that is not disconnected is located, then the flight electric drive unit that has experienced a current short circuit is determined to be the disconnected flight electric drive unit; if the disconnected flight electric drive unit is connected to a power supply unit, then the power supply unit connected to the disconnected flight electric drive unit is controlled to stop supplying power.

[0156] Optionally, if a current short circuit still exists in the circuit where the flight electric drive unit is located, the flight electric drive unit that has experienced a current short circuit is identified as the flight electric drive unit that is not disconnected; the first isolation device 103 is controlled to close again; if the flight electric drive unit that is not disconnected is connected to a power supply unit, the power supply unit connected to the flight electric drive unit that is not disconnected is controlled to stop supplying power.

[0157] Optionally, such as Figure 1 As shown, taking two power supply units and four flight electric drives as an example, but not limited to this structure, if a current short circuit is detected in the flight power system and the initial state of the first isolation device 103 is closed, then the first isolation device 103 is controlled to open, dividing the flight electric drive group into two parts. Among them, flight electric drives 102a and 102b are connected to power supply unit 101a, and flight electric drives 102c and 102d are connected to power supply unit 101b. The current in the circuit where the two parts of the flight electric drive are located is detected respectively.

[0158] Optionally, if a current short circuit occurs in the circuit containing flight electric drive 102a and flight electric drive 102b, then flight electric drive 102a and flight electric drive 102b are determined to be at least two flight electric drive groups to be screened. The second isolation device 104 between flight electric drive 102a and flight electric drive 102b is disconnected. At this time, the circuit containing flight electric drive 102b is disconnected. If there is no current short circuit in the flight electric drive group that is not disconnected, that is, there is no current short circuit in the circuit containing flight electric drive 102a, then flight electric drive 102b is determined to be the flight electric drive group that has experienced a current short circuit. If a short circuit occurs in an undisconnected flight electric drive unit, the flight electric drive unit where the short circuit occurs is identified as the flight electric drive unit where flight electric drive 102a is located. The first isolation device 103 is closed so that flight electric drive 102b is reconnected to the power supply unit, that is, flight electric drive 102b is connected to power supply unit 101b. Before closing the first isolation device 103, it is also necessary to control the power supply unit 101a connected to flight electric drive 102a to stop supplying power to ensure that the power supply unit is not burned out by the short circuit current.

[0159] Optionally, if a current short circuit occurs in the circuit containing flight electric drives 102c and 102d, then flight electric drives 102c and 102d are determined to be at least two flight electric drive groups to be screened. The second isolation device 104 between flight electric drives 102c and 102d is then disconnected. At this time, the circuit containing flight electric drive 102c is disconnected. If there is no current short circuit in the flight electric drive group that is not disconnected, that is, there is no current short circuit in the circuit containing flight electric drive 102d, then flight electric drive 102c is determined to be the flight electric drive group that has experienced a current short circuit. If a short circuit occurs in an undisconnected flight electric drive unit, the flight electric drive unit where the short circuit occurs is identified as the flight electric drive unit where flight electric drive 102d is located. The first isolation device 103 is then closed so that flight electric drive 102c is reconnected to the power supply unit, that is, flight electric drive 102c is connected to power supply unit 101a. Before closing the first isolation device 103, it is also necessary to control the power supply unit 101b connected to flight electric drive 102d to stop supplying power to ensure that the power supply unit is not burned out by the short circuit current.

[0160] In one embodiment, such as Figure 4 As shown, in the power reconfiguration control strategy, the first isolation device control module 501 monitors the magnitude and direction of the current passing through it in real time. When a short-circuit fault occurs in the flight power system circuit, a short-circuit current is generated. After the first isolation device control module 501 detects that the current is greater than or equal to a preset current threshold, it controls the first isolation device 103 to disconnect within a preset time T1, and then sends the disconnected status of the first isolation device 103 to the power supply unit control module 202a and the power supply unit control module 202b. When the first isolation device 103 is disconnected, the short-circuit fault point is isolated on the side of power supply unit 101a or power supply unit 101b. At this time, two flight electric drive control modules enter a fault state and send a fault status to the flight control module 401, while two flight electric drive control modules remain in the working state and send a working status to the flight control module 401. When the flight control module 401 detects that the flight electric drive control module has entered a fault state, it sends a restart command to the flight electric drive working mode. The flight electric drive control module does not respond to the restart command sent by the flight control module 401 when in a fault state.

[0161] When the first isolation device control module 501 is disconnected, the current flow direction before disconnection is used to determine whether the current flows from the power supply unit 101a side to the power supply unit 101b side. If the current flows from the power supply unit 101b side to the power supply unit 101a side, the second isolation device 1042 is disconnected. If the current flows from the power supply unit 101b side to the power supply unit 101a side, the second isolation device 1041 is disconnected. Specifically, the second isolation device 104 between flight electric drives 102a and 102b is the second isolation device 1041, and the second isolation device 104 between flight electric drives 102c and 102d is the second isolation device 1042.

[0162] The power supply unit control module 202a and power supply unit control module 202b will perform auxiliary judgment. If the power supply unit 101a detects an abnormal current, it will send a second isolation device 1041 cut-off request command to the first isolation device control module 501 to cut off. If the power supply unit 101b detects an abnormal current, it will send a second isolation device 1042 cut-off request command to the first isolation device control module 501 to cut off.

[0163] If the second isolation device 1041 disconnects, the power supply unit control module 202a makes a judgment. If the current returns to normal, it proves that the short circuit point is between isolation device 1 and the first isolation device 103. In this case, power reconfiguration is not required. Power supply unit 101a supplies power to flight electric drive 102a, and power supply unit 101b supplies power to flight electric drives 102c and 102d. If the current does not return to normal, it proves that the short circuit point is between power supply unit 101a and isolation device 1. In this case, power reconfiguration is required. The power supply unit control module 202a sends a power reconfiguration request to the first isolation device control module 501.

[0164] If the second isolation device 1042 disconnects, the power supply unit control module 202b will determine whether the short circuit is between the isolation device 2 and the first isolation device 103. In this case, power reconfiguration is not required. Power supply unit 101b supplies power to flight electric drive 102d, and power supply unit 101a supplies power to flight electric drives 102a and 102b. If the current does not return to normal, it indicates that the short circuit is between power supply unit 101b and isolation device 2. In this case, power reconfiguration is required, and the power supply unit control module 202b sends a power reconfiguration request to the first isolation device control module 501.

[0165] If the first isolation device control module 501 receives a request that all power reconfiguration requests are none, it will remain in the disconnected state. If any power reconfiguration request is yes, it will begin power reconfiguration.

[0166] The first isolation device control module 501 controls the first isolation device 103 to close again, controls the output voltage to rise gradually without damaging components such as capacitors, reaches the battery voltage within time T2, and then sends a message that the power reconfiguration result is complete to the flight electric drive control module.

[0167] After receiving a message indicating that the power reconfiguration is complete and detecting that the flight electric drive input voltage has returned to normal, the flight electric drive control module transitions from a fault state to a standby state. At this point, it responds to a restart command sent by the flight module and then transitions from standby to restart state. Upon detecting that the flight electric drive control module has entered restart state, the flight control module 401 sends the target speed N for the flight electric drive to the flight electric drive control module. The flight electric drive control module responds to the target speed, controlling the flight electric drive to operate at the target speed value and sending the "actual speed of the flight electric drive" to the flight control module 401. Once the flight control module 401 detects that the actual speed of the flight electric drive has reached the target speed, it sends a message indicating that the flight electric drive is in operation to the flight electric drive. Upon receiving this message, the flight electric drive transitions from restart state to operating state, and the power reconfiguration is complete.

[0168] Optionally, such as Figure 2 As shown, taking four power supply units and eight flight electric drives as an example, but not limited to this structure, if a current short circuit is detected in the flight power system, and the initial state of the first isolation device 103 is closed, the first isolation device 103 is opened, dividing the flight electric drive group into two parts. Flight electric drive group 1 and flight electric drive group 2 are connected to power supply units 101a and 101b, while flight electric drive group 3 and flight electric drive group 4 are connected to power supply units 101c and 101d. The current in both circuits is then detected.

[0169] Optionally, if a short circuit occurs in the circuit containing flight electric drive group 1 and flight electric drive group 2, then flight electric drive group 1 and flight electric drive group 2 are identified as at least two flight electric drive groups to be screened. The second isolation device 104 between flight electric drive group 1 and flight electric drive group 2 is disconnected. At this time, the circuit containing flight electric drive group 2 is disconnected. If there is no short circuit in the flight electric drive group that is not disconnected, that is, there is no short circuit in the circuit containing flight electric drive group 1, then flight electric drive group 2 is identified as the flight electric drive group that has experienced a short circuit. The power supply unit 101b connected to flight electric drive group 2 is stopped from supplying power to ensure that the power supply unit is not burned out by the short circuit current. If there is a short circuit in the flight electric drive group that is not disconnected, then flight electric drive group 1 is identified as the flight electric drive group that has experienced a short circuit. The first isolation device 103 is closed so that flight electric drive group 2 is reconnected to the power supply unit, that is, flight electric drives 102c and 102d are connected to power supply units 101b, 101c, and 101d. Before closing the first isolation device 103, it is also necessary to control the power supply unit 101a connected to the flight electric drive group 1 to stop supplying power to ensure that the power supply unit is not burned by the short circuit.

[0170] Optionally, if a short circuit occurs in the circuits containing flight electric drive group 3 and flight electric drive group 4, then flight electric drive group 3 and flight electric drive group 4 are identified as at least two flight electric drive groups to be screened. The second isolation device 104 between flight electric drive group 3 and flight electric drive group 4 is disconnected. At this time, the circuit containing flight electric drive group 3 is disconnected. If there is no short circuit in the flight electric drive group that is not disconnected, that is, there is no short circuit in the circuit containing flight electric drive group 4, then flight electric drive group 4 is identified as the flight electric drive group that has experienced a short circuit. The power supply unit 101d connected to flight electric drive group 4 is controlled to stop supplying power to ensure that the power supply unit is not burned out by the short circuit current. If a short circuit occurs in the flight electric drive unit that has not been disconnected, the flight electric drive unit that has experienced the short circuit is identified as flight electric drive unit 4. The first isolation device 103 is then closed to reconnect flight electric drive unit 3 to the power supply unit. That is, flight electric drive unit 3 is connected to power supply units 101a, 101b, and 101c. Before closing the first isolation device 103, it is also necessary to control the power supply unit 101d connected to flight electric drive unit 4 to stop supplying power to ensure that the power supply unit is not burned out by the short circuit current.

[0171] In one embodiment, such as Figure 5 As shown, the power reconfiguration control strategy is the same as the control strategy for the two battery packs and four flight electric drives. It only requires that the power supply unit on the reconfiguration side be powered down before closing the first isolation device 103.

[0172] Optionally, such as Figure 3As shown, taking three power supply units and four flight electric drives as an example, but not limited to this structure, if a current short circuit is detected in the flight power system and the initial state of the first isolation device 103 is closed, then the first isolation device 103 is opened, dividing the flight electric drive group into two parts. Flight electric drive group 1 and flight electric drive group 2 are connected to power supply units 101a and 101b, and flight electric drive group 3 and flight electric drive group 4 are connected to power supply unit 101c. The current in the circuits of the two flight electric drive groups is detected respectively.

[0173] Optionally, if a short circuit occurs in the circuits containing flight electric drive group 1 and flight electric drive group 2, then flight electric drive group 1 and flight electric drive group 2 are identified as at least two flight electric drive groups to be screened. The second isolation device 104 between flight electric drive group 1 and flight electric drive group 2 is disconnected. At this time, the circuit containing flight electric drive group 2 is disconnected. If there is no short circuit in the flight electric drive group that is not disconnected, that is, there is no short circuit in the circuit containing flight electric drive group 1, then flight electric drive group 2 is identified as the flight electric drive group that has experienced a short circuit. Since flight electric drive group 2 is connected to a power supply unit, the power supply unit 101b connected to flight electric drive group 2 is controlled to stop supplying power to ensure that the power supply unit is not burned out by the short circuit current. If there is a short circuit in the flight electric drive group that is not disconnected, then flight electric drive group 1 is identified as the flight electric drive group that has experienced a short circuit. The first isolation device 103 is closed so that flight electric drive group 2 is reconnected to the power supply unit, that is, flight electric drive 102b is connected to power supply unit 101b and power supply unit 101c. Before closing the first isolation device 103, it is also necessary to control the power supply unit 101a connected to the flight electric drive group 1 to stop supplying power to ensure that the power supply unit is not burned by the short circuit.

[0174] Optionally, if a current short circuit occurs in the circuits containing flight electric drive group 3 and flight electric drive group 4, then flight electric drive group 102c and flight electric drive group 4 are identified as at least two flight electric drive groups to be screened. The second isolation device 104 between flight electric drive group 3 and flight electric drive group 4 is disconnected. At this time, the circuit containing flight electric drive group 3 is disconnected. If there is no current short circuit in the flight electric drive group that is not disconnected, that is, there is no current short circuit in the circuit containing flight electric drive group 4, then flight electric drive 102c is identified as the flight electric drive group that has experienced a current short circuit. If a short circuit occurs in an undisconnected flight electric drive unit, the flight electric drive unit where the short circuit occurs is identified as the flight electric drive unit where flight electric drive 102d is located. The first isolation device 103 is closed so that flight electric drive 102c is reconnected to the power supply unit, that is, flight electric drive 102c is connected to power supply unit 101a. Before closing the first isolation device 103, it is also necessary to control the power supply unit 101b connected to flight electric drive 102c to stop supplying power to ensure that the power supply unit is not burned out by the short circuit current.

[0175] In one embodiment, such as Figure 6As shown, the power reconfiguration control strategy is the same as the control strategy for the two battery packs and four flight electric drives. It only requires that the power supply unit on the reconfiguration side be powered down before closing the first isolation device 103.

[0176] In the technical solution of this embodiment, by controlling the opening or closing of the first isolation device 103 and the second isolation device 104, the flight electric drive group that has experienced a current short circuit is identified and isolated. By identifying and isolating the flight electric drive group that has experienced a current short circuit, the normal operation of the flight power system of the flying vehicle is ensured. The remaining flight electric drive groups are controlled to continue operating, ensuring that the flight power system of the flying vehicle provides sufficient power to support the flight of the flying vehicle. This avoids the entire flight power system from malfunctioning when a short circuit occurs in a certain flight electric drive group, ensuring the stability of the power supply of the flight power system and improving the safety of the flying vehicle.

[0177] The present invention also provides a flight propulsion system, the flight propulsion system including a memory, a processor, and a power reconfiguration program stored in the memory and executable on the processor, the power reconfiguration program implementing the various steps of the power reconfiguration method as described in the above embodiments when executed by the processor.

[0178] The present invention also provides a computer-readable storage medium storing a power reconfiguration program, which, when executed by a processor, implements the various steps of the power reconfiguration method described in the above embodiments.

[0179] The sequence numbers of the above embodiments of the present invention are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments.

[0180] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, system, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, system, article, or apparatus. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, system, article, or apparatus that includes that element.

[0181] Through the above description of the embodiments, those skilled in the art can clearly understand that the systems described in the embodiments can be implemented by means of software plus necessary general-purpose hardware platforms. Of course, they can also be implemented by hardware, but in many cases the former is a better implementation method. Based on this understanding, the technical solution of the present invention, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product is stored in a computer-readable storage medium (such as ROM / RAM, magnetic disk, optical disk) as described above, and includes several instructions to cause a terminal device (which may be a mobile phone, computer, parking management device, air conditioner, or network device, etc.) to execute the systems described in the various embodiments of the present invention.

[0182] The above are merely preferred embodiments of the present invention and do not limit the scope of the patent. Any equivalent structural or procedural transformations made based on the description and drawings of the present invention, or direct or indirect applications in other related technical fields, are similarly included within the scope of patent protection of the present invention.

Claims

1. A flight propulsion system, characterized in that, The flight propulsion system includes: Power supply unit; The flight electric drive unit, and multiple sets of the flight electric drive units are connected in parallel and then connected to the power supply unit; An isolation device is provided on the line between each two adjacent sets of the flight electric drive groups, for disconnecting the connection between the two adjacent sets of the flight electric drive groups; The flight propulsion system performs a power reconfiguration method, the power reconfiguration method comprising: If a current short circuit is detected in the flight propulsion system, the isolation device is opened or closed to identify the flight electric drive unit that has experienced the current short circuit and isolate the flight electric drive unit that has experienced the current short circuit. Control the remaining flight electric drive units to continue operating; The steps for opening or closing the control isolation device include: When the initial state of the first isolation device is closed, control the first isolation device to open; Identify at least two groups of the described flight electric drive units to be screened; The second isolation device between at least two groups of the flight electric drive units to be screened is disconnected, so as to disconnect the circuit of one group of the flight electric drive units. If there is no current short circuit in the circuit containing the flight electric drive unit that is not disconnected, then the flight electric drive unit that has experienced a current short circuit is determined to be the flight electric drive unit that has been disconnected.

2. The flight propulsion system as described in claim 1, characterized in that, The isolation device includes a first isolation device and a second isolation device. The first isolation device is disposed on the line between two adjacent sets of the flight electric drive groups located in the middle, and the second isolation device is disposed on the line between the remaining two adjacent sets of the flight electric drive groups.

3. The flight propulsion system as described in claim 1, characterized in that, When the flight electric drive group includes at least two flight electric drives, each flight electric drive group is connected to one of the power supply units.

4. The flight propulsion system as described in claim 1, characterized in that, When the number of power supply units is less than the number of flight electric drive groups, at least two flight electric drive groups are connected to the same power supply unit; when the number of power supply units is equal to the number of flight electric drive groups, each flight electric drive group is connected to a different power supply unit.

5. The flight propulsion system as described in claim 1, characterized in that, The number of power supply units is at least two, and the flight electric drive group located at the edge is directly connected to the power supply unit.

6. A method for reconfiguring flight dynamics, characterized in that, The flight power reconfiguration method, applied to the flight propulsion system according to any one of claims 1-5, comprises: If a current short circuit is detected in the flight propulsion system, the isolation device is opened or closed to identify the flight electric drive unit that has experienced the current short circuit and isolate the flight electric drive unit that has experienced the current short circuit. Control the remaining flight electric drive units to continue operating; The steps for opening or closing the control isolation device include: When the initial state of the first isolation device is closed, control the first isolation device to open; Identify at least two groups of the described flight electric drive units to be screened; The second isolation device between at least two groups of the flight electric drive units to be screened is disconnected, so as to disconnect the circuit of one group of the flight electric drive units. If there is no current short circuit in the circuit containing the flight electric drive unit that is not disconnected, then the flight electric drive unit that has experienced a current short circuit is determined to be the flight electric drive unit that has been disconnected.

7. The power reconfiguration method as described in claim 6, characterized in that, The steps for disconnecting or closing the control isolation device include: When the initial state of the first isolation device is the disconnected state, at least two groups of the flight electric drive groups to be screened are determined. The second isolation device between at least two groups of the flight electric drive units to be screened is disconnected, so as to disconnect the circuit of one group of the flight electric drive units. If there is no current short circuit in the circuit containing the flight electric drive unit that is not disconnected, then the flight electric drive unit that has experienced a current short circuit is determined to be the flight electric drive unit that has been disconnected.

8. The dynamic reconfiguration method as described in claim 6 or 7, characterized in that, After the step of disconnecting the second isolation device between at least two groups of flight electric drive units to be screened, the method further includes: If the circuit containing the flight electric drive unit that has not been disconnected still has a current short circuit, then the flight electric drive unit that has experienced a current short circuit is determined to be the flight electric drive unit that has not been disconnected. Control the first isolation device to close again.

9. The dynamic reconfiguration method as described in claim 6 or 7, characterized in that, After the step of disconnecting the second isolation device between at least two groups of flight electric drive units to be screened, the method further includes: If there is no current short circuit in the circuit where the flight electric drive unit that has not been disconnected is located, then the flight electric drive unit that has experienced a current short circuit is determined to be the flight electric drive unit that has been disconnected. If the disconnected flight electric drive unit is connected to a power supply unit, then control the power supply unit connected to the disconnected flight electric drive unit to stop supplying power.

10. The dynamic reconfiguration method as described in claim 6 or 7, characterized in that, After the step of disconnecting the second isolation device between at least two groups of flight electric drive units to be screened, the method further includes: If the circuit containing the flight electric drive unit that has not been disconnected still has a current short circuit, then the flight electric drive unit that has experienced a current short circuit is determined to be the flight electric drive unit that has not been disconnected. Control the first isolation device to close again; If the flight electric drive unit that is not disconnected is connected to a power supply unit, then control the power supply unit connected to the flight electric drive unit that is not disconnected to stop supplying power.

11. A flight propulsion system, characterized in that, The flight propulsion system includes a memory, a processor, and a power reconfiguration program stored in the memory and executable on the processor, wherein the power reconfiguration program, when executed by the processor, implements the various steps of the power reconfiguration method as described in any one of claims 6-10.

12. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a power reconfiguration program, which, when executed by a processor, implements the steps of the power reconfiguration method as described in any one of claims 6-10.

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