Power state control method and flight equipment

Abstract

The present application discloses a power state control method and an aircraft device, which are applied to an aircraft device, wherein the aircraft device includes at least two power supply systems; the power supply system includes a high-voltage system and a corresponding power management system; the high-voltage system includes a high-voltage battery; and the high-voltage batteries are arranged in parallel. The method includes: upon detecting that the high-voltage system is in a preset state, determining the state of the aircraft device's emergency power-off switch; if the emergency power-off switch is in a closed state, switching all high-voltage systems to a high-voltage emergency power-off state; if the emergency power-off switch is in an open state and an emergency power-off request is received, the aircraft device's air-to-ground state is in the air, and at least one powered-on high-voltage system is in a normal state; then, by adjusting the overall power of the aircraft device, switching the high-voltage system corresponding to the emergency power-off request to a high-voltage emergency power-off state. Thus, when the high-voltage system is in the preset state, the state of the high-voltage system is adjusted in a timely manner, reducing the impact on the aircraft device caused by abnormal power-off.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft equipment, and more specifically, to a power state control method and aircraft equipment. Background Art

[0002] Aircraft typically use high-voltage batteries as their power source. To improve the safety of aircraft, high-voltage batteries are often designed with redundancy. However, if an abnormal power outage occurs during aircraft operation, the battery's heavy load can cause a shock to the aircraft, affecting its safe use. Summary of the Invention

[0003] In view of the above problems, this application proposes a power status control method and flight equipment, which can timely adjust the status of the high-voltage system when the flight equipment experiences abnormal power failure, reduce the impact of battery power failure under high load on the flight equipment, and improve the safety of the flight equipment.

[0004] In a first aspect, an embodiment of the present application provides a power state control method, which is applied to an aircraft device, wherein the aircraft device includes at least two power systems; each power system includes a high-voltage system and a corresponding power management system; the high-voltage system includes a high-voltage battery; the high-voltage batteries of at least two power systems are arranged in parallel, and the method includes: when it is detected that the high-voltage system is in a preset state, determining the state of the emergency power-off switch of the aircraft device; wherein the preset state includes: at least one of a high-voltage initialization state, a high-voltage power-on state, a high-voltage charging waiting state, a high-voltage charging configuration confirmation state, a high-voltage charging state, and a high-voltage preparation state; if the state of the emergency power-off switch is closed, all high-voltage systems are switched to a high-voltage emergency power-off state; if the state of the emergency power-off switch is open, and an emergency power-off request sent by any power management system is received, the air-to-ground state of the aircraft device is an airborne state, and there is at least one powered-on high-voltage system in a normal state; then, by adjusting the overall power of the aircraft device, the high-voltage system corresponding to the emergency power-off request is switched to a high-voltage emergency power-off state.

[0005] In a second aspect, an embodiment of the present application further provides a flight device comprising a processor, a memory, and one or more applications; the one or more applications are stored in the memory and configured to be executed by the processor to implement the above-mentioned power state control method.

[0006] The technical solution provided in the present application is applied to an aircraft, wherein the aircraft includes at least two power systems; each power system includes a high-voltage system and a corresponding power management system; the high-voltage system includes a high-voltage battery; the high-voltage batteries of at least two power systems are arranged in parallel, and the method includes: when detecting that the high-voltage system is in a preset state, determining the state of an emergency power-off switch of the aircraft; wherein the preset state includes at least one of a high-voltage initialization state, a high-voltage power-on state, a high-voltage charging waiting state, a high-voltage charging configuration confirmation state, a high-voltage charging state, and a high-voltage preparation state; if the state of the emergency power-off switch is closed, switching all high-voltage systems to a high-voltage emergency power-off state; if the state of the emergency power-off switch is open, and an emergency power-off request sent by any power management system is received, the air-to-ground state of the aircraft is in the air, and at least one powered-on high-voltage system is in a normal state; switching the high-voltage system corresponding to the emergency power-off request to a high-voltage emergency power-off state by adjusting the total power of the aircraft. Therefore, when the high-voltage system is in a preset state, the corresponding high-voltage system is controlled to enter a high-voltage emergency power-off state according to the state of the emergency power-off switch and the actual conditions of the power management system, the air-ground state and the high-voltage system, so as to timely adjust the state of the high-voltage system and reduce the impact on the flight equipment caused by abnormal power-off, thereby improving the safety of the flight equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] In order to more clearly illustrate the technical solutions in the embodiments of this application, the following is a brief introduction to the drawings required for describing the embodiments. Obviously, the drawings described below are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments and drawings obtained by ordinary technicians in this field without creative work are within the scope of protection of this invention.

[0008] Figure 1 This is a flow chart of a power state control method provided in an embodiment of the present application.

[0009] Figure 2 It is a structural schematic diagram of a flying device provided in an embodiment of the present application.

[0010] Figure 3 It is a structural schematic diagram of another flying device provided in an embodiment of the present application.

[0011] Figure 4 It is a structural diagram of a power state control device provided in an embodiment of the present application.

[0012] Figure 5 It is a structural diagram of a computer-readable storage medium provided in an embodiment of the present application. DETAILED DESCRIPTION

[0013] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application.

[0014] Aircraft typically use high-voltage batteries as their power source. To improve the safety of aircraft, high-voltage batteries are often designed with redundancy. However, if an abnormal power outage occurs during aircraft operation, the battery's heavy load can cause a shock to the aircraft, impacting its safety.

[0015] To improve the above-mentioned problems, the present application provides a power state control method and an aircraft device, which are applied to an aircraft device, wherein the aircraft device includes at least two power systems; each power system includes a high-voltage system and a corresponding power management system; the high-voltage system includes a high-voltage battery; the high-voltage batteries of at least two power systems are arranged in parallel, and the method includes: when detecting that the high-voltage system is in a preset state, determining the state of an emergency power-off switch of the aircraft device; wherein the preset state includes: at least one of a high-voltage initialization state, a high-voltage power-on state, a high-voltage charging waiting state, a high-voltage charging configuration confirmation state, a high-voltage charging state, and a high-voltage preparation state; if the state of the emergency power-off switch is closed, switching all high-voltage systems to a high-voltage emergency power-off state; if the state of the emergency power-off switch is open, and an emergency power-off request sent by any power management system is received, the air-to-ground state of the aircraft device is an airborne state, and at least one powered-on high-voltage system is in a normal state; then, by adjusting the total power of the aircraft device, switching the high-voltage system corresponding to the emergency power-off request to a high-voltage emergency power-off state.

[0016] Therefore, when the high-voltage system is in a preset state, the corresponding high-voltage system is controlled to enter a high-voltage emergency power-off state according to the state of the emergency power-off switch and the actual conditions of the power management system, the air-ground state and the high-voltage system, so as to timely adjust the state of the high-voltage system and reduce the impact on the flight equipment caused by abnormal power-off, thereby improving the safety of the flight equipment.

[0017] The power state control method provided by the embodiment of the present invention is described in detail below.

[0018] See also Figure 1 , Figure 1 FIG1 is a flow chart of a power state control method provided by an embodiment of the present application. The power state control method includes steps 110 to 130.

[0019] The power state control method provided in the embodiment of the present application is applied to aircraft equipment. Figure 2As shown, the flying device 200 includes at least two power supply systems 210 ; each power supply system 210 includes a high voltage system 211 and a corresponding power management system 212 (Battery Management System, BMS).

[0020] The high-voltage system 211 includes a high-voltage battery 2111 ; the high-voltage batteries 2111 of at least two power supply systems 210 are arranged in parallel.

[0021] In step 110 , when it is detected that the high voltage system is in a preset state, the state of the emergency power-off switch of the flight equipment is determined.

[0022] In an embodiment of the present application, the preset state includes at least one of a high voltage initialization state, a high voltage power-on state, a high voltage charging waiting state, a high voltage charging configuration confirmation state, a high voltage charging state, and a high voltage ready state.

[0023] In some embodiments, as Figure 2 As shown, the flight device 200 may also include a central control module 220, a low-voltage wake-up button (not shown), a high-voltage power-on button (not shown), etc. The pilot can control the status of each button as needed, such as whether the button is pressed. The central control module 220 can detect the status of each button and perform corresponding operations based on the status of the entire button.

[0024] In some embodiments, the central control module 220 may adopt a controller such as an MCU (Microcontroller Unit), a CPU (Central Processing Unit), etc., and the specific controller may be selected according to actual use needs.

[0025] In some embodiments, when the low-voltage wake-up button of the flight device is pressed, the central control module of the flight device performs initialization verification, and the default state of the process of all high-voltage systems is set to the high-voltage initialization state, so that all high-voltage systems enter the high-voltage initialization state.

[0026] In some embodiments, when the high voltage system is in the high voltage initialization state and the high voltage power on button of the flight device is pressed, the process of the high voltage system switches from the high voltage initialization state to the high voltage initialization state.

[0027] In some embodiments, the aircraft device can be charged via a charging gun. When the aircraft device is connected to the charging gun, the power management system is in a power waiting state for charging, and the central control module of the aircraft device detects that the air-to-ground state of the aircraft device is a ground state, the high-voltage system process switches from a high-voltage initialization state to a high-voltage charging waiting state.

[0028] In some embodiments, when the flight device is connected to the charging gun and the power management system determines that the high-voltage system process is in a high-voltage charging waiting state, the high-voltage system process switches from the high-voltage charging waiting state to the high-voltage charging configuration confirmation state.

[0029] In some embodiments, when the high-voltage system process is in the high-voltage charging configuration confirmation state, the power management system, under the action of the central control module of the flight equipment, changes from the power waiting for charging state to the power charging state, and the high-voltage system process switches from the high-voltage charging configuration confirmation state to the high-voltage charging state.

[0030] In some embodiments, after the power management system is fully charged or after the power management system sends a charging fault signal, the process of the high-voltage system switches from the high-voltage charging state to the high-voltage ready state.

[0031] In some embodiments, the flight device further includes an emergency power-off switch (not shown). In an emergency, the user can control the state of the emergency power-off switch to control the operating state of the power supply system.

[0032] In some embodiments, the state of the emergency power-off switch of the aircraft device includes a closed state and an open state. When the user presses the emergency power-off switch, the aircraft device generates an emergency power-off closed signal to the central control module of the aircraft device, or when the user releases the emergency power-off switch, the aircraft device generates an emergency power-off disconnect signal to the central control module of the aircraft device. The central control module executes corresponding measures to adjust the power system according to the state of the emergency power-off switch.

[0033] When the high-voltage system is detected to be in the high-voltage initialization state, high-voltage power-on state, high-voltage charging waiting state, high-voltage charging configuration confirmation state, high-voltage charging state, or high-voltage preparation state, the state of the emergency power-off switch is promptly determined so that corresponding measures can be taken according to the state of the emergency power-off switch in subsequent steps to reduce the impact on the aircraft equipment when an abnormal power-off occurs, thereby improving the reliability and safety of the aircraft equipment.

[0034] In step 120 , if the state of the emergency power-off switch is closed, all high-voltage systems are switched to a high-voltage emergency power-off state.

[0035] In an embodiment of the present application, the emergency power-off switch is the highest priority for users to arbitrate emergency conditions of the entire machine. When the emergency power-off switch is in a closed state, the processes controlling all high-voltage systems are switched to a high-voltage emergency power-off state.

[0036] In some embodiments, when all processes of the high-voltage system are in a high-voltage emergency power-off state, the central control unit of the flight equipment sends a switch disconnection request to all power management systems so that the power management systems control the corresponding switch modules to disconnect, thereby completing the synchronous power-off of all high-voltage systems.

[0037] By using the emergency power-off switch status as the highest priority for arbitrating emergency conditions of the entire aircraft, the system promptly responds to user requests to control the aircraft through the emergency power-off switch. This allows users to make corresponding judgments based on their driving experience and actual conditions and promptly control the aircraft through the emergency power-off switch, thereby reducing the impact of power system anomalies on the aircraft.

[0038] In step 130, if the state of the emergency power-off switch is disconnected, and an emergency power-off request is received from any power management system, and the ground state of the aircraft equipment is in the air, and there is at least one powered-on high-voltage system in a normal state; then by adjusting the overall power of the aircraft equipment, the high-voltage system corresponding to the emergency power-off request is switched to a high-voltage emergency power-off state.

[0039] In some embodiments, when the emergency power-off switch is in the off state, it indicates that the user is unable to make a corresponding judgment based on driving experience and actual conditions, or the user is not aware of any abnormality in the power system of the aircraft.

[0040] In an embodiment of the present application, if the state of the emergency power-off switch is disconnected, and an emergency power-off request is received from any power management system, and the central control module of the flight equipment detects that the ground state of the flight equipment is in the air, and there is at least one powered-on high-voltage system in a normal state, the central control module of the flight equipment sends a whole-machine power adjustment request, and the flight equipment responds to the whole-machine power adjustment request to adjust the whole-machine power of the flight equipment, thereby causing the high-voltage system corresponding to the power management system that issued the emergency power-off request to enter a high-voltage emergency power-off state.

[0041] More specifically, in some embodiments, the step of switching the high-voltage system corresponding to the emergency power-off request to a high-voltage emergency power-off state by adjusting the power of the flight equipment may include the following steps.

[0042] (1) Perform a power downgrade operation to adjust the overall power of the flight equipment to below a preset downgrade threshold.

[0043] In an embodiment of the present application, each power supply system further includes a switch module, and the switch module is used to control the on / off of the path where the corresponding high-voltage system is located.

[0044] In some embodiments, the switch module can be a main relay, which is arranged in the circuit where the high-voltage battery is located. When the main relay is in a closed state, the circuit where the high-voltage battery is located is in a conductive state; and when the main relay is in an open state, the circuit where the high-voltage battery is located is in a disconnected state.

[0045] In some embodiments, as Figure 2 As shown, the flight device 200 may further include a power distribution module 230, a flight control module 240, and a flight management module 250. In some embodiments, the power distribution module may be a power distribution unit (PDU). In some embodiments, the flight control module may be a flight control computer (FCC), such as a flight controller. The flight management module may be a flight management computer (FMC). The flight management module may convert control commands from the flight control module and the central control module to control the power system.

[0046] In actual use, the flight control module can adjust the power of the entire aircraft. Specifically, in some embodiments, the step of performing a power reduction operation to adjust the power of the entire aircraft to below a preset reduction threshold may include the step of: sending a power reduction request to the flight control module, so that the flight control module adjusts the power of the entire aircraft to below the preset reduction threshold.

[0047] In some embodiments, the preset degradation threshold is related to the power management system and the power distribution module. The value of the preset degradation threshold may be a current threshold for on-load power-off allowed by the power management system and the power distribution module.

[0048] In an embodiment of the present application, upon determining that the state of the emergency power-off switch is in the disconnected state, receiving an emergency power-off request sent by any power management system, and the central control module of the flight equipment detecting that the ground state of the flight equipment is in the air state, and that there is at least one powered-on high-voltage system in a normal state, the central control module of the flight equipment sends a power degradation request to the flight control module, the flight control module receives and responds to the power degradation request, adjusts the flight envelope power of the flight equipment, and adjusts the overall power of the flight equipment to below the preset degradation threshold.

[0049] (2) If the overall power of the flight equipment is below a preset degradation threshold, the high-voltage system corresponding to the emergency power-off request is switched to a high-voltage emergency power-off state.

[0050] In an embodiment of the present application, the central control module monitors that the overall power of the flight equipment is below a preset degradation threshold, and controls the high-voltage system corresponding to the power management system that issues an emergency power-off request to enter a high-voltage emergency power-off state.

[0051] In some embodiments, the step of performing a power degradation operation to adjust the overall power of the flight equipment to below a preset degradation threshold may include the steps of: if the overall power of the flight equipment is below the preset degradation threshold, switching the high-voltage system corresponding to the emergency power-off request to a high-voltage emergency power-off state, and sending a switch disconnection request to the power management system corresponding to the high-voltage system in the high-voltage emergency power-off state to control the corresponding switch module to disconnect.

[0052] In an embodiment of the present application, the central control module monitors that the overall power of the flight equipment is below a preset degradation threshold, and the corresponding high-voltage system enters a high-voltage emergency power-off state. When it is determined that the corresponding high-voltage system is in a high-voltage emergency power-off state, the central control module sends a switch disconnection request to the power management system that issued the emergency power-off request. The corresponding power management system receives and responds to the switch disconnection request, disconnects the corresponding switch module, and disconnects the path of the circuit where the corresponding high-voltage battery is located.

[0053] (3) After the high-voltage system corresponding to the emergency power-off request switches to the high-voltage emergency power-off state, a power recovery operation is performed to adjust the overall power of the flight equipment to a normal power threshold.

[0054] In an embodiment of the present application, after the central control unit detects that the path of the circuit where the corresponding high-voltage battery is located is disconnected, that is, the high-voltage system corresponding to the emergency power-off request switches to a high-voltage emergency power-off state, the central control module controls the flight equipment to perform a power recovery operation to adjust the overall power of the flight equipment to a normal power threshold.

[0055] More specifically, in some embodiments, the step of performing a power recovery operation to adjust the overall power of the flight equipment to a normal power threshold includes the following steps: sending a power recovery request to the flight control module; so that the flight control module adjusts the overall power of the flight equipment to a normal power threshold.

[0056] In an embodiment of the present application, after the central control module detects that the path of the circuit where the corresponding high-voltage battery is located is disconnected, the central control module sends a power reset request to the flight control module. The flight control module receives and responds to the power reset request. The flight control module adjusts the flight envelope power of the flight equipment to adjust the overall power of the flight equipment to the normal power threshold.

[0057] Based on the aircraft's ground-to-air status and the aircraft's power arbitration abnormal power-off conditions, the impact of heavy battery load loss on the aircraft during an abnormal power-off is reduced, thereby improving the reliability and safety of the aircraft. Furthermore, when the aircraft's ground-to-air status is in the air, abnormal power-off of a single battery pack is a prerequisite for implementing redundancy design.

[0058] In addition, when the ground state of the flying device is in the air, how to realize the power reduction operation of multiple battery packs is also a prerequisite for realizing the redundancy design. Specifically, in some embodiments, realizing the power reduction operation of multiple battery packs may include the following steps.

[0059] (1) If any high-voltage system is in the high-voltage standby state and its corresponding power management system is in the power reduction state, the high-voltage system in the high-voltage standby state is switched to the high-voltage reduction state.

[0060] In some embodiments, if the power management system is detected to be in an over-temperature state or a fault, the power management system is controlled to enter a power reduction state. When the power management system is detected to exceed a normal threshold, it can be determined that the power management system is in an over-temperature state.

[0061] (2) When it is detected that any high-voltage system is in a power reduction state, the discharge parameters of all power management systems are obtained.

[0062] In some embodiments, the discharge parameter may be power information such as instantaneous maximum discharge power, constant maximum discharge power, and average discharge power of the power management system. In the embodiment of the present application, the discharge parameter is instantaneous maximum discharge power.

[0063] (3) Determine the total degradation threshold based on the discharge parameters and determine the corresponding degraded flight power.

[0064] In the embodiment of the present application, the value of the total degradation threshold is the sum of the instantaneous maximum discharge powers of all high-voltage systems. It is understandable that the value of the total degradation threshold can be flexibly adjusted according to actual conditions.

[0065] (4) Adjust the overall power of the flight equipment to below the degraded flight power according to the degraded flight power.

[0066] In some embodiments, if the temperature of the power management system returns to a normal threshold, or the fault of the power management system is eliminated, the power management system switches from the power reduction state to the battery standby state to restore the power of the entire machine, which may specifically include the following steps.

[0067] (1) If it is detected that a power management system switches from a power reduction state to a power standby state, the high voltage system corresponding to the power management system switched to the power standby state is controlled to switch from the high voltage reduction state to the high voltage standby state.

[0068] (2) When it is detected that all high-voltage systems are in the high-voltage standby state, the overall power of the flight equipment is adjusted to the normal power threshold.

[0069] When any high-voltage system is in high-voltage standby state and the corresponding power management system is in battery power reduction, the power of the entire machine is adjusted to achieve power reduction operation of multiple battery packs.

[0070] It is worth noting that since the flight equipment includes multiple power supply systems and the high-voltage batteries of the multiple power supply systems are arranged in parallel, if the high-voltage batteries of the multiple power supply systems are powered on asynchronously, a current surge will be generated when the switch module is closed, which will affect the stability of the flight equipment. In order to synchronize the power-on of the high-voltage batteries of the multiple power supply systems, in some embodiments, when the charging gun of the flight equipment is in an unconnected state, if it is determined that the flight equipment meets the preset power-on conditions, the power supply system is controlled to perform the power-on operation.

[0071] In an embodiment of the present application, if the power management system does not detect that a charging plug is connected to the aircraft, it determines whether the aircraft meets a preset power-on condition. Specifically, in some embodiments, the step of determining whether the aircraft meets the preset power-on condition may include the step of: if the high-voltage system is in a high-voltage initial state and the high-voltage power-on switch of the aircraft is in a closed state, determining that the aircraft meets the preset power-on condition.

[0072] Further, in some embodiments, the step of controlling the power supply system to perform a power-on operation when the charging gun of the aircraft device is in an unconnected state and determining that the aircraft device meets a preset power-on condition may include the step of controlling the power supply system to perform a power-on operation when the charging gun of the aircraft device is in an unconnected state and determining that the aircraft device meets a preset power-on condition and determining that no high-voltage suppression fault exists in all high-voltage systems.

[0073] In some embodiments, high voltage suppression faults include communication abnormalities, low voltage faults, high voltage interlocks, wiring harness abnormalities (e.g., insulation harness abnormalities), power management system faults, motor faults, high voltage battery overtemperature, high voltage battery thermal runaway, or high voltage battery voltage deviation.

[0074] If the power management system does not detect that a charging plug is connected to the aircraft device, the high-voltage system is in the high-voltage initial state, the high-voltage power-on switch is in the closed state, and the high-voltage suppression fault described above does not exist, then the power management system is controlled to perform a power-on operation. Specifically, in some embodiments, the step of controlling the power management system to perform a power-on operation may include the following steps.

[0075] (1) Switch the high voltage system to the power-on request state.

[0076] In an embodiment of the present application, the high voltage system switches from a high voltage initial state to a power-on request state.

[0077] (2) Sending a switch closing request to the power management system to control the power management system to perform pre-charging processing.

[0078] In an embodiment of the present application, when the high-voltage system enters a power-on request state, the central control module sends a switch closing request to the power management system. When the power management system receives the switch closing request, the power management system performs pre-charging processing.

[0079] (3) After determining that the power management system has completed the pre-charging process, the power management system controls the corresponding switch module to close.

[0080] In an embodiment of the present application, after the power management system completes the pre-charging process, the power management system automatically controls the corresponding switch module to close.

[0081] (4) Switching the high voltage system to a high voltage standby state; and switching the power management system to a power standby state.

[0082] In an embodiment of the present application, after the power management system automatically controls the corresponding switch module to close, the process of the high-voltage system switches from the power-on request state to the high-voltage ready state, and the power management system switches to the power ready state.

[0083] By setting the conditions for powering on the flight equipment, the pilot only needs to operate the high-voltage power-on switch to achieve synchronous power-on of the high-voltage system, solving the problem of battery surge, reducing the layout of additional operating switches, reducing the cost of the flight equipment, and simplifying operation.

[0084] In some embodiments, if it is determined that the aircraft device meets the preset charging conditions, the power supply system is controlled to perform a charging operation.

[0085] Furthermore, in some embodiments, if it is determined that the charging gun of the aircraft is in a connected state, the aircraft is determined to be on the ground, and the high-voltage system is determined to be in an initial state, then it is determined that the aircraft meets the preset charging conditions.

[0086] In an embodiment of the present application, the power management system detects that the aircraft is connected to the charging gun, the central control module detects that the aircraft is in the ground state, and the high-voltage system process is in the initial state, and controls the power system to perform a charging operation. Specifically, in some embodiments, the step of controlling the power system to perform a charging operation may include the following steps.

[0087] (1) When the power management system determines that the charging gun of the flight equipment is in the connected state, the power management system switches to the power waiting for charging state.

[0088] (2) When it is determined that the flight equipment is on the ground, the high voltage system is switched to the high voltage charging waiting state.

[0089] In an embodiment of the present application, after the power management system enters the power waiting state, the central control module determines the air-ground state of the flight equipment. When the central control module determines that the air-ground state of the flight equipment is the ground state, the process of the high-voltage system switches from the high-voltage initial state to the high-voltage charging waiting state.

[0090] (3) When the high-voltage system is in a high-voltage charging waiting state, a switch closing request is sent to the power management system to control the power management system to perform pre-charging processing.

[0091] In an embodiment of the present application, when the high-voltage system process enters the high-voltage charging waiting state, the central control module sends a switch closing request to the power management system, the power management system receives and responds to the switch closing request, and the power management system automatically performs pre-charging processing.

[0092] (4) After determining that the power management system has completed the pre-charging process, the power management system controls the corresponding switch module to close.

[0093] In an embodiment of the present application, after completing the pre-charging process, the power management system controls the corresponding switch module to close.

[0094] (5) After the power management system confirms that the charging configuration status of the flight equipment is waiting for charging, the high-voltage system is switched to the high-voltage charging configuration confirmation state.

[0095] In an embodiment of the present application, the process of the high-voltage system switches from a high-voltage charging waiting state to a high-voltage charging configuration confirmation state. After the process of the high-voltage system enters the high-voltage charging configuration confirmation state, the central control module sends a charging request to the power management system.

[0096] (6) Sending a charging request to the power management system; and switching the power management system to the power charging state and switching the high-voltage system to the high-voltage charging state.

[0097] In an embodiment of the present application, after the power management system receives and responds to the charging request, the power management system switches the process of the high-voltage system to a high-voltage charging state.

[0098] (7) After receiving the charging completion signal sent by the power management system, the high-voltage system is switched to the high-voltage charging completion state to send a switch disconnection request and a charging disconnection request to the power management system.

[0099] In an embodiment of the present application, the charging completion signal includes a fully charged signal or a charging fault signal. After the high-voltage system process is in the high-voltage charging completion state, the central control module sends a charging disconnection request and a switch disconnection request to the power management system to stop the charging operation.

[0100] In some embodiments, the aerial device further includes a motor control module and a flight control module. In some embodiments, the motor control module may be a motor controller. In some embodiments, the flight control module may be a flight controller. It is worth noting that the aerial device can be charged in more than one manner; the charging type can be determined based on the communication status between the motor control module and the flight control module.

[0101] Specifically, in some embodiments, if it is determined that the aircraft device meets the preset charging conditions, then controlling the power supply system to perform the charging operation may include the following steps.

[0102] (1) If it is determined that the flight device meets the preset charging conditions, the charging type is determined according to the first communication state of the motor control module and the second communication state of the flight control module.

[0103] (2) Determine the charging protection method of the flight equipment based on the charging type.

[0104] (3) Execute charging protection mode.

[0105] (4) Control the power supply system to perform charging operations.

[0106] In some embodiments, the step of determining the charging type based on the first communication status of the motor control module and the second communication status of the flight control module may include the steps of: if it is determined according to the first communication status and the second communication status that there is no communication failure in the motor control module and the flight control module, then determining the charging type as the whole-machine charging type; if it is determined according to the first communication status and the second communication status that there is a communication failure in the motor control module and / or the flight control module, then determining the charging type as the battery pack disassembly charging type.

[0107] In an embodiment of the present application, if it is detected that the first communication state of each motor control module is no communication fault and the second communication state of the flight control module is no communication fault, the charging type is determined to be the whole-machine charging type.

[0108] In an embodiment of the present application, if the charging type is determined to be the whole-machine charging type, the central management unit sends a shutdown request to the flight control module to put the flight device into a propeller-stopped state.

[0109] In an embodiment of the present application, if it is detected that the first communication state of each motor control module is a communication failure, and the second communication state of the flight control module is a communication failure, the charging type is determined to be a battery pack removal charging type.

[0110] In an embodiment of the present application, if the charging type is determined to be a battery pack removal charging type, only the emergency power-off state of a single power management system is responded to as a battery protection condition for the charging process to cancel the voltage deviation monitoring of different high-voltage systems, thereby avoiding the situation where the high-voltage battery pack data is inconsistent with the high-voltage system configured in the entire machine, resulting in the flight equipment being unable to charge normally.

[0111] After the flight equipment completes a normal flight, when the flight equipment meets the corresponding conditions, the flight equipment can perform a normal power-off operation. Specifically, in some embodiments, when it is detected that the high-voltage system is in a high-voltage standby state and no emergency power-off signal sent by the power management system is received, if the flight equipment meets the preset power-off conditions, the high-voltage system will be switched to a high-voltage normal power-off state.

[0112] In some embodiments, the preset power-off condition includes the aircraft being on the ground and the high-voltage power-off switch being closed. The pilot can press the high-voltage power-off switch to cause the aircraft to generate a power-off request. The central control module detects that the aircraft is on the ground and has not received an emergency power-off signal from the power management system. The aircraft responds to the power-off request, switching the high-voltage system from a high-voltage standby state to a high-voltage normal power-off state, completing the normal power-off operation.

[0113] In some embodiments, when the process of the high-voltage system is in the high-voltage initial state and the power management system does not detect that the flight equipment is connected to the charging gun, if an abnormality is detected in the CAN communication diagnosis, the flight control module and the power management system, the process of the high-voltage system is controlled to switch from the high-voltage initial state to the high-voltage failure protection state.

[0114] In some embodiments, when the high-voltage system process is in any process other than the charging process and the flight controller detects that the air-to-ground state of the flight equipment is the ground state, if a high-voltage suppression fault occurs (high-voltage suppression faults include communication abnormalities, low-voltage faults, high-voltage interlocks, wiring harness abnormalities (such as insulation harness abnormalities), power management system faults, motor faults, high-voltage battery over-temperature, high-voltage battery thermal runaway, or high-voltage battery voltage deviation is too large, etc.), the high-voltage system process enters a high-voltage failure protection state.

[0115] In some embodiments, when a process of the high-voltage system is in a high-voltage power-on request state, a failure or failure to respond occurs when the power management system performs pre-charge processing, and the process of the high-voltage system enters a high-voltage failure protection state.

[0116] In some embodiments, when the high voltage system process enters a high voltage failure protection state, the flight controller sends a switch disconnect request to the power management system and generates a fault prompt message.

[0117] A control method provided in an embodiment of the present application is applied to an aircraft, wherein the aircraft includes at least two power systems; each power system includes a high-voltage system and a corresponding power management system; the high-voltage system includes a high-voltage battery; the high-voltage batteries of at least two power systems are arranged in parallel, and the control method includes: when detecting that the high-voltage system is in a preset state, determining the state of an emergency power-off switch of the aircraft; wherein the preset state includes at least one of a high-voltage initialization state, a high-voltage power-on state, a high-voltage charging waiting state, a high-voltage charging configuration confirmation state, a high-voltage charging state, and a high-voltage preparation state; if the emergency power-off switch is in a closed state, switching all high-voltage systems to a high-voltage emergency power-off state; if the emergency power-off switch is in an open state, and an emergency power-off request is received from any power management system, the air-to-ground state of the aircraft is an airborne state, and at least one powered-on high-voltage system is in a normal state; switching the high-voltage system corresponding to the emergency power-off request to a high-voltage emergency power-off state by adjusting the total power of the aircraft. Therefore, when the high-voltage system is in a preset state, the corresponding high-voltage system is controlled to enter a high-voltage emergency power-off state according to the state of the emergency power-off switch and the actual conditions of the power management system, the air-ground state and the high-voltage system, so as to timely adjust the state of the high-voltage system and reduce the impact on the flight equipment caused by abnormal power-off, thereby improving the safety of the flight equipment.

[0118] See also Figure 3 , Figure 3A structural diagram of a flying device 300 provided in an embodiment of the present application. The flying device 300 in the present application can be a flying vehicle and an electric aircraft. The flying device 300 in the present application can include one or more of the following components: a processor 310, a memory 320, and one or more applications, wherein the one or more applications can be stored in the memory 320 and configured to be executed by one or more processors 310, and the one or more programs are configured to execute the power state control method described in the aforementioned method embodiment.

[0119] The processor 310 may include one or more processing cores. The processor 310 utilizes various interfaces and circuits to connect various components within the aircraft device 300. It executes instructions, programs, code sets, or instruction sets stored in the memory 320, as well as accesses data stored in the memory 320, to perform various functions and process data within the aircraft device 300. Optionally, the processor 310 may be implemented using at least one of the following hardware forms: a digital signal processing (DSP), a field-programmable gate array (FPGA), or a programmable logic array (PLA). The processor 310 may integrate one or a combination of a central processing unit (CPU), a graphics processing unit (GPU), and a modem. The CPU primarily handles the operating system, user interface, and application programs; the GPU is responsible for rendering and drawing display content; and the modem handles wireless communications. It is understood that the modem may not be integrated into the processor 310 and may instead be implemented via a separate communications chip.

[0120] Memory 320 may include random access memory (RAM) or read-only memory (ROM). Memory 320 may be used to store instructions, programs, codes, code sets, or instruction sets. Memory 320 may include a program storage area and a data storage area. The program storage area may store instructions for implementing an operating system, instructions for implementing at least one function, and instructions for implementing the various method embodiments described below. The data storage area may also store data generated by the flight device 300 during use.

[0121] See also Figure 4, an embodiment of the present application also provides a power state control device 400, which is applied to aircraft equipment, the aircraft equipment including at least two power systems; each power system includes a high-voltage system and a corresponding power management system; the high-voltage system includes a high-voltage battery; the high-voltage batteries of at least two power systems are arranged in parallel, and the power state control device 400 includes: a state detection module 410, a first switching module 420 and a second switching module 430.

[0122] Among them, the status detection module 410 is used to determine the status of the emergency power-off switch of the flight equipment when it is detected that the high-voltage system is in a preset state; wherein the preset state includes: high-voltage initialization state, high-voltage power-on state, high-voltage charging waiting state, high-voltage charging configuration confirmation state, high-voltage charging state and high-voltage ready state. At least one of the state.

[0123] The first switching module 420 is used to switch all high-voltage systems to a high-voltage emergency power-off state if the emergency power-off switch is in a closed state;

[0124] The second switching module 430 is used to switch the high-voltage system corresponding to the emergency power-off request to a high-voltage emergency power-off state by adjusting the overall power of the aircraft equipment if the emergency power-off switch is in the disconnected state and an emergency power-off request is received from any power management system, the ground-to-air state of the aircraft equipment is in the air, and there is at least one powered-on high-voltage system in a normal state.

[0125] It should be noted that, for the apparatus embodiments, since they are basically similar to the method embodiments, the description is relatively simple, and the relevant parts can be referred to the partial description of the method embodiments. Any processing method described in the method embodiments can be implemented by the corresponding processing module in the apparatus embodiments, and will not be described in detail in the apparatus embodiments.

[0126] In addition, the functional modules in the various embodiments of the present application may be integrated into a processing module, or each module may exist physically separately, or two or more modules may be integrated into a single module. The above-mentioned integrated modules may be implemented in the form of hardware or software functional modules.

[0127] Please refer to Figure 5 , which shows a block diagram of a computer-readable storage medium 500 provided in an embodiment of the present application. The computer-readable storage medium 500 stores program code 510, which can be called by a processor to execute the power state control method described in the above method embodiment.

[0128] The computer-readable storage medium 500 can be an electronic memory such as a flash memory, an EEPROM (Electrically Erasable Programmable Read-Only Memory), an EPROM, a hard disk, or a ROM. Alternatively, the computer-readable storage medium includes a non-transitory computer-readable storage medium. The computer-readable storage medium 500 has storage space for program code that executes any method step in the power state control method described above. These program codes 510 can be read from or written to one or more computer program products. The program code can be compressed, for example, in a suitable form.

[0129] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. A power state control method, characterized in that: Applied to an aircraft, the aircraft comprising at least two power systems; each of the power systems comprising a high-voltage system and a corresponding power management system; the high-voltage system comprising a high-voltage battery; the high-voltage batteries of the at least two power systems being arranged in parallel; the method comprising: determining a state of an emergency power-off switch of the flight device upon detecting that the high-voltage system is in a preset state; wherein the preset state includes at least one of a high-voltage initialization state, a high-voltage power-on state, a high-voltage charging waiting state, a high-voltage charging configuration confirmation state, a high-voltage charging state, and a high-voltage ready state; If the state of the emergency power-off switch is closed, all high-voltage systems are switched to a high-voltage emergency power-off state; If the state of the emergency power-off switch is disconnected and an emergency power-off request sent by any of the power management systems is received, the air-to-ground state of the aircraft device is in the air, and there is at least one powered-on high-voltage system in a normal state; then by adjusting the overall power of the aircraft device, the high-voltage system corresponding to the emergency power-off request is switched to the high-voltage emergency power-off state.

2. The power state control method according to claim 1, wherein: The step of switching the high-voltage system corresponding to the emergency power-off request to a high-voltage emergency power-off state by adjusting the power of the flight equipment includes: Performing a power reduction operation to adjust the entire power of the flight equipment to below a preset reduction threshold; If the total power of the flight equipment is below a preset degradation threshold, switching the high-voltage system corresponding to the emergency power-off request to a high-voltage emergency power-off state; After the high-voltage system corresponding to the emergency power-off request is switched to a high-voltage emergency power-off state, a power recovery operation is performed to adjust the entire power of the flight equipment to a normal power threshold.

3. The power state control method according to claim 2, wherein: Each of the power supply systems further includes a switch module, the switch module being used to control the on / off of the corresponding path of the high-voltage system; the flight equipment further includes: a power distribution module and a flight control module; The performing of the power degradation operation to adjust the entire power of the flight equipment to below a preset degradation threshold includes: Sending a power degradation request to the flight control module; so that the flight control module adjusts the entire power of the flight equipment to below the preset degradation threshold; If the entire power of the flight equipment is below a preset degradation threshold, switching the high-voltage system corresponding to the emergency power-off request to a high-voltage emergency power-off state includes: If the total power of the flight equipment is below a preset degradation threshold, switching the high-voltage system corresponding to the emergency power-off request to a high-voltage emergency power-off state; Sending a switch disconnect request to the power management system corresponding to the high-voltage system in the high-voltage emergency power-off state to control the corresponding switch module to disconnect; The performing of the power recovery operation to adjust the entire power of the flight equipment to a normal power threshold includes: Sending a power recovery request to the flight control module; so that the flight control module adjusts the entire power of the flight equipment to a normal power threshold.

4. The power state control method according to claim 1, wherein: The method further comprises: If any of the high-voltage systems is in a high-voltage standby state and its corresponding power management system is in a power reduction state, the high-voltage system in the high-voltage standby state is switched to a high-voltage power reduction state; When it is detected that any of the high-voltage systems is in the power reduction state, obtaining discharge parameters of all power management systems; Determine a total degradation threshold according to the discharge parameters, and determine a corresponding degraded flight power; According to the degraded flight power, the entire power of the flight equipment is adjusted to be below the degraded flight power.

5. The power state control method according to claim 4, characterized in that: The method further comprises: If it is detected that the power management system switches from the power reduction state to the power standby state, the high-voltage system corresponding to the power management system switched to the power standby state is controlled to switch from the high-voltage power reduction state to the high-voltage standby state; When it is detected that all high-voltage systems are in the high-voltage ready state, the entire power of the flight equipment is adjusted to a normal power threshold.

6. The power state control method according to claim 1, wherein: The method further comprises: When the charging gun of the aircraft device is in an unconnected state, if it is determined that the aircraft device meets a preset power-on condition, the power supply system is controlled to perform a power-on operation.

7. The power state control method according to claim 6, characterized in that: When the charging gun of the aircraft device is in an unconnected state, if it is determined that the aircraft device meets a preset power-on condition, controlling the power supply system to perform a power-on operation includes: When the charging gun of the aircraft device is in an unconnected state, if it is determined that the aircraft device meets the preset power-on conditions and it is determined that all high-voltage systems have no high-voltage suppression faults, the power supply system is controlled to perform a power-on operation.

8. The power state control method according to claim 6, wherein: Determining that the flight device meets a preset power-on condition includes: If the high-voltage system is in a high-voltage initial state and the high-voltage power-on switch of the aircraft device is in a closed state, it is determined that the aircraft device meets a preset power-on condition.

9. The power state control method according to claim 8, wherein: The power supply system further includes a switch module, which is used to control the on / off of the corresponding path where the high-voltage system is located; The controlling the power supply system to perform a power-on operation includes: Switching the high voltage system to a power-on request state; sending a switch closing request to the power management system to control the power management system to perform a pre-charge process; After determining that the power management system completes the pre-charging process, the power management system controls the corresponding switch module to close; Switching the high-voltage system to a high-voltage standby state; and Switch the power management system to a power ready state.

10. The power state control method according to claim 1, wherein: The method further comprises: If it is determined that the aircraft device meets the preset charging condition, the power supply system is controlled to perform a charging operation.

11. The power state control method according to claim 10, wherein: The flying device further includes a motor control module and a flight control module; if it is determined that the flying device meets a preset charging condition, controlling the power supply system to perform a charging operation includes: If it is determined that the flight device meets the preset charging condition, determining the charging type according to the first communication state of the motor control module and the second communication state of the flight control module; determining a charging protection mode for the aircraft device according to the charging type; Executing the charging protection mode; The power supply system is controlled to perform a charging operation.

12. The power state control method according to claim 11, wherein: The determining the charging type according to the first communication state of the motor control module and the second communication state of the flight control module includes: If it is determined according to the first communication state and the second communication state that neither the motor control module nor the flight control module has a communication fault, then determining that the charging type is a whole-machine charging type; If it is determined that a communication failure exists in the motor control module and / or the flight control module according to the first communication status and the second communication status, the charging type is determined to be a battery pack removal charging type.

13. The power state control method according to claim 10, wherein: The method further comprises: If it is determined that the charging gun of the aerial device is in a connected state, the aerial device is in a ground state, and the high-voltage system is in an initial state, it is determined that the aerial device meets the preset charging conditions.

14. The power state control method according to claim 13, wherein: The power supply system further includes a switch module, which is used to control the on / off of the corresponding path where the high-voltage system is located; The controlling the power supply system to perform a charging operation includes: When the power management system determines that the charging gun of the aircraft device is in the connected state, the power management system switches to the power waiting for charging state; When it is determined that the flight equipment is in a ground state, switching the high-voltage system to a high-voltage charging waiting state; When the high-voltage system is in the high-voltage charging waiting state, sending a switch closing request to the power management system to control the power management system to perform a pre-charging process; After determining that the power management system completes the pre-charging process, the power management system controls the corresponding switch module to close; After the power management system confirms that the charging configuration state of the aircraft device is waiting for charging, switching the high-voltage system to the high-voltage charging configuration confirmation state; Sending a charging request to the power management system; switching the power management system to a power charging state; and switching the high-voltage system to a high-voltage charging state; After receiving the charging completion signal sent by the power management system, the high-voltage system is switched to a high-voltage charging completion state to send a switch disconnection request and a charging disconnection request to the power management system; wherein the charging completion signal includes: a full charge signal or a charging fault signal.

15. The power state control method according to claim 1, wherein: The method further comprises: When it is detected that the high-voltage system is in the high-voltage standby state and no emergency power-off signal is received from the power management system, if the flight equipment meets the preset power-off conditions, the high-voltage system is switched to the high-voltage normal power-off state.

16. The power state control method according to claim 15, characterized in that: The preset power-off condition includes that the flight equipment is on the ground and the high-voltage power-off switch is in a closed state.

17. A flying device, characterized in that: include: one or more processors; Memory; One or more applications, wherein the one or more applications are stored in the memory and are configured to be executed by the one or more processors according to the power state control method according to any one of claims 1 to 16.

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