Power consumption control method and system, storage medium and electronic device

Abstract

Embodiments of the present application provide a power consumption control method and system, a storage medium and an electronic device, wherein the method comprises: in the case of determining that the flight equipment is in a landed state, identifying the power supply mode of the power supply in the flight equipment; in the case of the power supply mode being the uninterrupted battery replacement mode, controlling the boost-buck module of the flight equipment to enter the working state, and after the boost-buck module works for a preset time period, determining the first power consumption value of a plurality of components in the flight equipment, wherein the boost-buck module is used to charge the capacitor in the power supply; determining the target component in the plurality of components according to a preset rule, and adjusting the power consumption value of the target component from the first power consumption value to the second power consumption value, wherein the second power consumption value is the minimum power consumption value required by the target component when the flight equipment maintains data continuous transmission. Through the present application, the problem that the power consumption of the flight equipment is large during the battery replacement process and the continuous endurance time of the capacitor is too short is solved.

Description

Technical Field

[0001] Embodiments of the present application relate to the field of aircraft batteries, and more specifically, to a power consumption control method and system, a storage medium, and an electronic device. Background Art

[0002] Currently, consumer and industrial drones powered by lithium batteries generally have short flight times. To ensure long-term, uninterrupted operation, batteries must be frequently replaced. However, this process often involves a power outage and restart. After the system restarts, it must undergo re-binding and data updates, which can be time-consuming and create a poor experience for users with high efficiency requirements. To address this issue, a supercapacitor is often added to the drone as a backup battery. When the drone battery is removed, it seamlessly connects to the supercapacitor for power, maintaining normal operation for a short period of time. Once the battery is replaced, it recharges the supercapacitor, ensuring continuous power for the next battery replacement. However, in practice, this solution often faces the problem of excessive power consumption by the drone system. Furthermore, due to weight and volume limitations, the supercapacitor's capacity is limited, resulting in a short discharge duration.

[0003] Regarding the problems in related technologies where flight equipment consumes large amounts of power during battery replacement and the capacitor's continuous flight time is too short, no effective solution has yet been proposed. Summary of the Invention

[0004] The embodiments of the present application provide a power consumption control method and system, a storage medium, and an electronic device to at least solve the problem that the flight equipment consumes a lot of power during battery replacement and the continuous battery life of the capacitor is too short.

[0005] According to one embodiment of the present application, a power consumption control method is provided, including: when it is determined that the aircraft device is in a landed state, identifying the power supply mode of a power supply in the aircraft device; when the power supply mode is a continuous power replacement battery mode, controlling a buck-boost module of the aircraft device to enter an operating state, and after the buck-boost module has been operating for a preset time period, determining a first power consumption value of multiple components in the aircraft device, wherein the buck-boost module is used to charge a capacitor in the power supply; determining a target component among the multiple components according to a preset rule, and adjusting the power consumption value of the target component from the first power consumption value to a second power consumption value, wherein the second power consumption value is the minimum power consumption value required for the target component when the aircraft device maintains continuous data transmission.

[0006] In an exemplary embodiment, the power consumption control method further includes: when the power supply mode of the power supply is adjusted from the continuous battery replacement mode to the battery power supply mode, detecting the operating status of the flight device; when the flight device is in a flight state, determining the third power consumption value of the flight device in the flight state; when the third power consumption value is greater than or equal to the second power consumption value, controlling the buck-boost module to enter a non-working state.

[0007] In an exemplary embodiment, the power consumption control method further includes: when the power supply mode is a data copy mode, sending standby information to the user of the flight equipment, wherein the standby information includes at least the duration during which the remaining power in the power supply allows the data copy mode to be maintained; and determining the response information of the user after sending the standby information, wherein the response information is used to indicate the flight equipment.

[0008] In an exemplary embodiment, a target component is determined among the multiple components according to a preset rule, including: when it is determined that the preset rule is a power consumption screening rule, a real-time power consumption value corresponding to each component among the multiple components is determined, wherein the power consumption screening rule includes at least a reference value for different components to be allowed to initiate power consumption adjustment; and a component whose real-time power consumption value is greater than or equal to the reference value is determined as a target component to perform power consumption adjustment.

[0009] In an exemplary embodiment, the power consumption control method further includes: obtaining the unplugging time of the first battery in the power supply; when the unplugging time is greater than a preset time, sending a prompt message to the user of the flight equipment, wherein the prompt message is used to instruct the user to install a second battery in the power supply, and the remaining power of the first battery is less than that of the second battery; when the unplugging time is less than or equal to the preset time, obtaining battery information of the installed battery in the power supply.

[0010] In an exemplary embodiment, the power consumption control method further includes: comparing the similarity between the battery information and historical battery information, wherein the historical battery information is used to indicate the battery information stored by the flight device before entering the landing state; when the similarity is greater than or equal to a preset similarity, determining that the battery in the power supply has not been replaced; and when the similarity is less than a preset similarity, determining that the power supply has completed the battery replacement.

[0011] According to another embodiment of the present application, a power consumption control system is also provided, including: an identification unit for identifying a power supply mode of a power supply in the flight equipment when it is determined that the flight equipment is in a landed state; a control unit for controlling the buck-boost module of the flight equipment to enter a working state when the power supply mode is a continuous battery replacement mode, and determining a first power consumption value of multiple components in the flight equipment after the buck-boost module has been working for a preset time period, wherein the buck-boost module is used to charge a capacitor in the power supply; an adjustment unit for determining a target component among the multiple components according to a preset rule, and adjusting the power consumption value of the target component from the first power consumption value to a second power consumption value, wherein the second power consumption value is the minimum power consumption value required for the target component when the flight equipment maintains continuous data transmission.

[0012] According to another embodiment of the present application, a computer-readable storage medium is provided, in which a computer program is stored. The computer program is configured to execute the steps of any one of the above method embodiments when run.

[0013] According to another embodiment of the present application, an electronic device is provided, including a memory and a processor, wherein the memory stores a computer program, and the processor is configured to run the computer program to execute the steps in any one of the above method embodiments.

[0014] According to the present application, when it is determined that the aircraft device is in a landed state, the power supply mode of the power supply within the aircraft device is identified; when the power supply mode is a continuous battery replacement mode, the buck-boost module of the aircraft device is controlled to enter an operating state, and after the buck-boost module has been operating for a preset period of time, a first power consumption value of multiple components in the aircraft device is determined, wherein the buck-boost module is used to charge a capacitor in the power supply; a target component is determined from the multiple components according to a preset rule, and the power consumption value of the target component is adjusted from the first power consumption value to a second power consumption value, wherein the second power consumption value is the minimum power consumption value required by the target component to maintain continuous data transmission of the aircraft device. The above technical solution controls the timing of charging the capacitor and adjusts the power consumption value of the aircraft device in the landed state, thereby maintaining the aircraft device at the lowest power consumption by continuously replacing the battery, increasing the seamless power supply switching time, and extending the life of the charged capacitor by setting a power consumption control strategy while keeping the capacitor size unchanged. This solves the problem of high power consumption during battery replacement and short battery life of the capacitor in the aircraft device. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present application and, together with the description, serve to explain the principles of the present application.

[0016] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, for ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0017] Figure 1 This is a hardware structure block diagram of a terminal device according to the power consumption control method of an embodiment of the present application;

[0018] Figure 2 is a flow chart of a power consumption control method according to an embodiment of the present application;

[0019] Figure 3 is a schematic diagram of power supply for a flight device according to an embodiment of the present application;

[0020] Figure 4 The following is a flow chart of a UAV power consumption control solution based on supercapacitors;

[0021] Figure 5 is a structural block diagram of a power consumption control system according to an embodiment of the present application; DETAILED DESCRIPTION

[0022] In order to enable those skilled in the art to better understand the solutions of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts should fall within the scope of protection of the present invention.

[0023] It should be noted that the terms "first", "second", etc. in the description and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present invention described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions. For example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0024] The method embodiments provided in the embodiments of the present application can be executed in a target terminal, a mobile terminal or a similar computing device. Taking running on the target terminal as an example, Figure 1 FIG. 1 is a block diagram of the hardware structure of a target terminal of a power consumption control method according to an embodiment of the present invention. Figure 1 As shown, the target terminal 10 may include one or more ( Figure 1 Only one is shown in the figure) processor 102 (processor 102 may include but is not limited to a microprocessor MCU or a programmable logic device FPGA and other processing devices) and a memory 104 for storing data. Optionally, the above-mentioned target terminal may also include a transmission device 106 and an input and output device 108 for communication functions. It will be understood by those skilled in the art that Figure 1 The structure shown is only for illustration and does not limit the structure of the target terminal. Figure 1 More or fewer components than shown, or with Figure 1 Equivalent functions or comparisons shown Figure 1 Shown are different configurations with more functionality.

[0025] The memory 104 can be used to store computer programs, for example, software programs and modules of application software, such as the computer program corresponding to the power consumption control method in the embodiment of the present invention. The processor 102 executes various functional applications and data processing by running the computer program stored in the memory 104, that is, to implement the above-mentioned method. The memory 104 may include a high-speed random access memory, and may also include a non-volatile memory, such as one or more magnetic storage devices, flash memory, or other non-volatile solid-state memory. In some instances, the memory 104 may further include a memory remotely located relative to the processor 102, and these remote memories may be connected to the target terminal 10 via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0026] The transmission device 106 is configured to receive or transmit data via a network. A specific example of the aforementioned network may include a wireless network provided by the communications provider of the target terminal 10. In one embodiment, the transmission device 106 includes a network interface controller (NIC), which can be connected to other network devices via a base station to enable communication with the Internet. In another embodiment, the transmission device 106 may be a radio frequency (RF) module, which is configured to communicate with the Internet wirelessly.

[0027] Alternatively, as an optional implementation, Figure 2As shown, the above power consumption control method can be applied in a flight equipment control system, including:

[0028] Step S202: When it is determined that the aircraft has landed, identifying a power supply mode of a power supply within the aircraft;

[0029] As an optional example, the flight device includes a detection component, which can be an altitude detection unit or a flight detection unit, for determining the current operating status of the flight device. Optionally, the judgment of the above-mentioned landing state can be based on the propeller of the flight device stopping rotating.

[0030] Step S204: When the power supply mode is the continuous battery replacement mode, controlling a buck-boost module of the aircraft device to enter an operating state, and determining first power consumption values ​​of multiple components in the aircraft device after the buck-boost module operates for a preset period of time, wherein the buck-boost module is used to charge a capacitor in the power supply;

[0031] It should be noted that the buck-boost module can boost or buck the output voltage of the capacitor in the power supply, meaning that the flight control system can control the output voltage of the capacitor through the buck-boost module. The capacitor can be a supercapacitor or other capacitor that can provide a stable power supply to the flight device within a short replacement period.

[0032] Among them, the above-mentioned non-stop battery replacement mode is that the aircraft equipment can replace the battery with insufficient remaining power in the power supply with a new battery that has been fully charged while ensuring normal data transmission and equipment control, thereby ensuring the power needs of the aircraft equipment while ensuring the uninterrupted workflow of the aircraft equipment.

[0033] Step S206, determining a target component among the multiple components according to a preset rule, and adjusting the power consumption value of the target component from a first power consumption value to a second power consumption value, wherein the second power consumption value is the minimum power consumption value required by the target component when the flight equipment maintains continuous data transmission.

[0034] In an exemplary embodiment, the above-mentioned step S206 is implemented in the following manner: when it is determined that the preset rule is a power consumption screening rule, the real-time power consumption value corresponding to each component of the multiple components is determined, wherein the power consumption screening rule at least includes a reference value for different components to be allowed to initiate power consumption adjustment; and the component whose real-time power consumption value is greater than or equal to the reference value is determined as the target component to perform power consumption adjustment.

[0035] It should be noted that since different types of aircraft equipment may add or change the size of components based on actual usage, when determining which components' power consumption needs to be shut down or adjusted in the aircraft's continuous battery swapping mode, adjustments must be made in conjunction with power consumption screening rules. Optionally, these power consumption screening rules may include, but are not limited to, component information for different components, corresponding power consumption requirements for different components, and corresponding data transmission requirements for different components. This power consumption requirement is then combined with the actual operating power consumption of different components in the aircraft equipment to determine the power consumption range within which each component can be adjusted while ensuring normal functionality. Furthermore, adjustment reference values ​​can be set for each component, thereby improving the efficiency of determining the target components for power consumption adjustment.

[0036] In addition, the difference between the real-time power consumption value and the reference value can also be determined. If the difference is within the preset range, it means that the component is an original component of the flight equipment, and the target component can be determined directly by referring to the historical adjustment record; if the difference is not within the preset range, it means that the component is a non-original component of the flight equipment, and it is necessary to determine the adjustment method suitable for the current non-original component based on the specification type of the non-original component. Using the above technical solution, components can be screened by power consumption value, and components that do not need to run in the uninterrupted power mode of the flight equipment can be determined to increase the duration of the capacitor powering the flight equipment after charging.

[0037] In an exemplary embodiment, after the above-mentioned step S206, the above-mentioned power consumption control method also includes: when the power supply mode of the power supply is adjusted from the continuous battery replacement mode to the battery power supply mode, detecting the operating status of the aircraft device; when the aircraft device is in a flight state, determining the third power consumption value of the aircraft device in the flight state; when the third power consumption value is greater than or equal to the second power consumption value, controlling the buck-boost module in the aircraft device to enter a non-working state.

[0038] As an optional example, when it is determined that the flight device has completed the battery replacement and is in a flight state, the buck-boost module connected to the capacitor will be disconnected from operation. For example, after the battery is replaced, the battery is turned on for communication. After the control system of the drone (equivalent to the flight device in the above embodiment) recognizes the new battery, it restores the normal function of the module that was previously turned off or reduced in power consumption (equivalent to the target component in the above embodiment). The drone is put into a ready-to-fly state. After the drone takes off, the control system turns off the supercapacitor (equivalent to the capacitor in the above embodiment) buck-boost module to reduce the power consumption of the drone battery, thereby saving the power consumption of the power supply during use, so that the power provided by the power supply can maintain the use of the drone for a longer time.

[0039] In an exemplary embodiment, after the above-mentioned step S202, the above-mentioned power consumption control method also includes: when the power supply mode is a data copy mode, sending standby information to the user of the aircraft equipment, wherein the standby information at least includes the duration of the remaining power in the power supply allowing the data copy mode to be maintained; determining the response information of the user after sending the standby information, wherein the response information is used to indicate the aircraft equipment.

[0040] Simply put, since aircraft batteries require replacement, the remaining power of the power supply can only guarantee normal data transmission time of the aircraft in data copy mode. Therefore, it is necessary to remind users to complete data copy within a safe period of time to avoid data transmission failure due to insufficient power or restart of the aircraft control system.

[0041] In an exemplary embodiment, step S206, determining a target component from the plurality of components according to a preset rule, includes the following steps:

[0042] In the case where it is determined that the preset rule is an adjustment rule, a target priority corresponding to each of the multiple components is determined, wherein the adjustment rule is used to indicate the priority of power consumption adjustment of different components; the multiple components are sorted according to the target priority; a first target component whose target priority is greater than or equal to a first preset priority is marked as an adjustment component to obtain a component set; wherein the first preset priority is used to indicate that the power consumption of the component is allowed to be adjusted to zero; and a target component to be subjected to power consumption adjustment is determined based on the component set.

[0043] That is, the target device has multiple different components at the same time, and each component has different functions. In order to ensure the optimal operation of different components, when adjusting power consumption, the adjustment priority corresponding to different components can be determined, and then the components that need to be adjusted first can be quickly adjusted to improve the overall adjustment effect.

[0044] Optionally, after sorting multiple components according to the target priority, the method further includes: marking a second target component whose target priority is less than the first preset priority and greater than or equal to the first preset priority as an adjustment supplementary component, and the second preset priority is used to indicate that the power consumption of the component is allowed to be adjusted to the minimum power consumption value during normal operation.

[0045] Through the above steps, when it is determined that the aircraft device is in a landed state, the power supply mode of the power supply within the aircraft device is identified; when the power supply mode is a continuous battery replacement mode, the buck-boost module of the aircraft device is controlled to enter an operating state, and after the buck-boost module has been operating for a preset period of time, a first power consumption value of multiple components in the aircraft device is determined, wherein the buck-boost module is used to charge a capacitor in the power supply; a target component is determined from the multiple components according to a preset rule, and the power consumption value of the target component is adjusted from the first power consumption value to a second power consumption value, wherein the second power consumption value is the minimum power consumption value required by the target component for the aircraft device to maintain continuous data transmission. The above technical solution controls the timing of charging the capacitor and adjusts the power consumption value of the aircraft device in the landing state, thereby maintaining the aircraft device at the lowest power consumption by continuously replacing the battery, increasing the switching time of seamless power supply, and extending the life of the charged capacitor by setting a power consumption control strategy while keeping the capacitor size unchanged, thereby solving the problem of high power consumption during battery replacement and short continuous battery life of the capacitor in the aircraft device.

[0046] In addition, due to reasons of the buck-boost module itself, it may not be possible to adjust the output voltage of the capacitor to the voltage corresponding to the power supply. In this case, the buck-boost module can be instructed to adjust the output voltage of the capacitor to a target voltage, wherein the difference between the target voltage and the voltage corresponding to the power supply is less than a preset threshold, thereby maintaining normal data transmission of the flight equipment under capacitor power supply.

[0047] As an optional embodiment, after adjusting the power consumption value of the target component from the first power consumption value to the second power consumption value, the above method also includes: obtaining the unplugging time of the first battery in the power supply; when the unplugging time is greater than the preset time, sending a prompt message to the user of the flight equipment, wherein the prompt message is used to instruct the user to install a second battery in the power supply, and the remaining power of the first battery is less than that of the second battery; when the unplugging time is less than or equal to the preset time, obtaining battery information of the installed battery in the power supply.

[0048] It is understandable that in order to avoid the capacitor participating in the power supply of the aircraft equipment and the battery not being replaced for a long time, the battery replacement can be carried out while ensuring the continuous operation of the aircraft equipment by recording the unplugging time, and when there is not much time left, the user of the aircraft equipment is reminded to complete the battery replacement as soon as possible.

[0049] Optionally, when the unplugging time is less than or equal to the preset time, after obtaining the battery information of the installed battery in the power supply, the above method further includes: comparing the similarity between the battery information and historical battery information, wherein the historical battery information is used to indicate the battery information stored by the flight equipment before entering the landing state; when the similarity is greater than or equal to the preset similarity, determining that the battery in the power supply has not been replaced; when the similarity is less than the preset similarity, determining that the power supply has completed the battery replacement.

[0050] Simply put, when it is determined that the battery has been removed and then installed, the accuracy of the battery replacement is determined by comparing the corresponding battery information with the historical battery information of the battery used by the aircraft between landing states.

[0051] In order to better understand the technical solutions of the embodiments and optional embodiments of the present invention, the process of the above-mentioned power consumption control method is explained below with reference to examples, but it is not intended to limit the technical solutions of the embodiments of the present invention.

[0052] In an alternative example, Figure 3 : is a schematic diagram of power supply of a flight device according to an embodiment of the present application; Figure 3 As shown, the supercapacitor passes through the buck-boost module and isolation circuit 2, and the drone battery passes through isolation circuit 1 to the power supply port, where they jointly power the drone system and its modules. Generally, if the supercapacitor's boosted voltage is lower than the drone battery's voltage, the drone control system controls the boost module; otherwise, it steps down. The drone battery charges the supercapacitor via the charging module. The isolation circuit prevents the boosted and boosted voltages of the drone battery and supercapacitor from flowing into each other.

[0053] Alternatively, the aforementioned supercapacitors generally refer to capacitors that store a relatively large amount of electricity. These capacitors generally have the characteristics of capacitance, as well as high and low temperature resistance and high charge and discharge current. The reason lithium batteries are not used as backup batteries is mainly due to their narrow charge and discharge temperature range, as well as the risk of over-discharge and safety hazards associated with long-term storage.

[0054] In addition, considering that the battery is usually replaced after the drone takes off, the optional embodiment of the present application makes full use of this opportunity to make a reasonable control strategy. The general process is as follows: Figure 4 shown. Figure 4 The following is a flow chart of a supercapacitor-based UAV power consumption control solution. It specifically includes the following steps:

[0055] Step S41: After determining that the drone control system detects that the drone has landed, the judgment that the drone has landed may be based on the propeller stopping rotation.

[0056] Step S42: Determine whether the drone control system detects that the user has turned on the non-stop battery replacement mode.

[0057] Step S43: If the drone control system detects that the user has not turned on the non-stop battery replacement mode, the drone control system does not turn on the supercapacitor buck-boost module and waits according to the normal process to allow the user to copy data and perform other operations.

[0058] Step S44: If the user detects that the uninterrupted battery replacement mode has been enabled, the drone control system activates the buck-boost module. Simultaneously, the control system shuts down or reduces the power consumption of non-essential modules such as vision, obstacle avoidance, and radar, ensuring that the entire system maintains the minimum power consumption while maintaining the necessary operating conditions.

[0059] Step S45: After the battery is replaced, the battery is turned on and communication is resumed. After the drone control system recognizes the new battery, it restores the previously disabled or power-reduced modules to normal function, placing the drone in a ready-to-fly state.

[0060] Step S46: After the drone takes off, the control system turns off the supercapacitor buck-boost module to reduce the power consumption of the drone battery.

[0061] It should be noted that the reason the buck-boost circuit is disabled after takeoff is to prevent the user from suddenly unplugging the battery and replacing it before takeoff. Reducing the power consumption of this circuit after takeoff can extend flight time to a certain extent. The above process of reducing power consumption after the drone is grounded generally takes less than a few hundred milliseconds to prevent the user from unplugging the battery before the process is completed.

[0062] Additionally, it should be noted that, in actual use, the supercapacitors described above can be single-cell or multi-cell, multi-string configurations. The decision to take off or land a drone is not limited to the propellers stopping. The isolation circuit can be an ideal diode, Schottky diode, or other device. In some cases, isolation circuit 1 or isolation circuit 2 can be omitted. There are no restrictions on how the drone can reduce system power consumption. The control method for the buck-boost module is not limited to buck-boost; in some cases, only boosting or only bucking can be sufficient. The drone can also detect battery removal or insertion using any method; it can be circuit recognition or communication. The timing for reducing power consumption is not limited to landing. Upon receiving a descent command, in addition to ensuring necessary power consumption, it is also possible to disable or reduce the power consumption of non-essential sensors or modules. However, the most appropriate time is generally when the propellers are stopped. The user can select whether to enable the battery replacement mode without interruption; it can be configured via a remote control or a mobile phone. The duration of the power reduction should be as short as possible. If this cannot be shortened, the timing for determining power reduction should be further advanced.

[0063] In summary, through the above optional implementation scheme, the system power consumption will be reduced through a series of operations at the appropriate time node, so that the burden on the supercapacitor is minimized when the battery is unplugged, thereby extending the life of the supercapacitor and ensuring that the battery is replaced for a long time without power failure or restart. Without affecting the user experience, this series of control strategies can greatly improve the battery life of the supercapacitor, effectively ensuring the time for battery replacement. In addition, the volume and weight requirements of the supercapacitor can be reduced through policy control, which also increases the life of the drone to a certain extent. The above solution adopts user-defined shutdown or startup of the uninterrupted power replacement mode, which can take into account users who normally use the drone, is flexible and convenient, and has a wider range of usage scenarios.

[0064] It should be noted that for the aforementioned method embodiments, for simplicity of description, they are all expressed as a series of action combinations. However, those skilled in the art should be aware that the present invention is not limited by the order of the actions described, because according to the present invention, certain steps can be performed in other orders or simultaneously. Secondly, those skilled in the art should also be aware that the embodiments described in this specification are all preferred embodiments, and the actions and modules involved are not necessarily required by the present invention.

[0065] Through the description of the above embodiments, those skilled in the art can clearly understand that the method according to the above embodiment can be implemented by means of software plus the necessary general hardware platform, and of course it can also be implemented by hardware, but in many cases the former is a better implementation method. Based on this understanding, the technical solution of the present invention is essentially or the part that contributes to the prior art can be embodied in the form of a software product, which is stored in a storage medium (such as ROM / RAM, magnetic disk, optical disk), and includes a number of instructions for enabling a terminal device (which can be a mobile phone, computer, server, or network device, etc.) to execute the methods described in each embodiment of the present invention.

[0066] According to another aspect of the embodiment of the present invention, a power consumption control system is also provided. Figure 5 As shown, the system includes:

[0067] an identification unit 502, configured to identify a power supply mode of a power supply in the aircraft when determining that the aircraft has landed;

[0068] a control unit 504 configured to, when the power supply mode is the continuous battery replacement mode, control a buck-boost module of the aircraft device to enter an operating state, and determine first power consumption values ​​of multiple components in the aircraft device after the buck-boost module operates for a preset period of time, wherein the buck-boost module is configured to charge a capacitor in a power supply;

[0069] The adjustment unit 506 is used to determine the target component among the multiple components according to a preset rule, and adjust the power consumption value of the target component from a first power consumption value to a second power consumption value, wherein the second power consumption value is the minimum power consumption value required by the target component when the flight equipment maintains continuous data transmission.

[0070] The system identifies the power supply mode of the aircraft's power supply when it is determined that the aircraft is in a landed state. If the power supply mode is a continuous battery swap mode, the system controls the aircraft's buck-boost module to enter an operating state. After the buck-boost module operates for a preset period of time, the system determines a first power consumption value for multiple components in the aircraft, wherein the buck-boost module is used to charge a capacitor in the power supply. A target component is identified from the multiple components according to a preset rule, and the power consumption value of the target component is adjusted from the first power consumption value to a second power consumption value, wherein the second power consumption value is the minimum power consumption value required by the target component to maintain continuous data transmission for the aircraft. The system employs the above-mentioned technical solution, which controls the timing of charging the capacitor and adjusts the power consumption value of the aircraft in the landing state, thereby maintaining the aircraft at the lowest power consumption while continuously swapping batteries, increasing the seamless power supply switching time. While maintaining the same capacitor size, the system also extends the life of the charged capacitor by setting a power consumption control strategy, thereby resolving the issues of high power consumption during battery replacement and short battery life for the capacitor.

[0071] In an exemplary embodiment, the above-mentioned system also includes: a detection unit, which is used to detect the operating status of the flight equipment after adjusting the power consumption value of the target component from the first power consumption value to the second power consumption value, when the power supply mode of the power supply is adjusted from the continuous battery replacement mode to the battery power supply mode; when the flight equipment is in a flight state, determine the third power consumption value of the flight equipment in the flight state; when the third power consumption value is greater than or equal to the second power consumption value, control the buck-boost module in the flight equipment to enter a non-working state.

[0072] In an exemplary embodiment, the above-mentioned system also includes: an information unit for, after determining that the aircraft device is in a landed state, identifying the power supply mode of the power supply in the aircraft device, and if the power supply mode is a data copy mode, sending standby information to the user of the aircraft device, wherein the standby information at least includes the length of time that the remaining power in the power supply allows the data copy mode to be maintained; and determining the response information of the user after sending the standby information, wherein the response information is used to indicate the aircraft device.

[0073] In an exemplary embodiment, the above-mentioned adjustment unit is also used to determine the real-time power consumption value corresponding to each of the multiple components when it is determined that the preset rule is a power consumption screening rule, wherein the power consumption screening rule at least includes a reference value for different components to be allowed to initiate power consumption adjustment; and the component whose real-time power consumption value is greater than or equal to the reference value is determined as the target component to perform power consumption adjustment.

[0074] In an exemplary embodiment, the above-mentioned system also includes: a time unit, which is used to obtain the unplugging time of the first battery in the power supply after adjusting the power consumption value of the target component from the first power consumption value to the second power consumption value; when the unplugging time is greater than the preset time, send a prompt message to the user of the flight equipment, wherein the prompt message is used to instruct the user to install a second battery in the power supply, and the remaining power of the first battery is less than that of the second battery; when the unplugging time is less than or equal to the preset time, obtain battery information of the installed battery in the power supply.

[0075] In an exemplary embodiment, the above-mentioned time unit is also used to obtain the battery information of the installed battery in the power supply when the unplugging time is less than or equal to the preset time, and then compare the similarity between the battery information and the historical battery information, wherein the historical battery information is used to indicate the battery information stored by the flight equipment before entering the landing state; when the similarity is greater than or equal to the preset similarity, it is determined that the battery in the power supply has not been replaced; when the similarity is less than the preset similarity, it is determined that the power supply has completed the battery replacement.

[0076] It should be noted that the above-mentioned units can be implemented by software or hardware. For the latter, it can be implemented in the following ways, but not limited to: the above-mentioned units are all located in the same processor; or the above-mentioned units are located in different processors in any combination.

[0077] An embodiment of the present invention further provides a storage medium storing a computer program, wherein the computer program is configured to execute the steps of any of the above method embodiments when running.

[0078] Optionally, in this embodiment, the storage medium may be configured to store a computer program for performing the following steps:

[0079] When it is determined that the aircraft device is in a landed state, identifying a power supply mode of a power supply in the aircraft device;

[0080] When the power supply mode is the continuous battery replacement mode, controlling a buck-boost module of the aircraft device to enter an operating state, and determining first power consumption values ​​of multiple components in the aircraft device after the buck-boost module operates for a preset period of time, wherein the buck-boost module is used to charge a capacitor in a power supply;

[0081] A target component is determined from the multiple components according to a preset rule, and a power consumption value of the target component is adjusted from a first power consumption value to a second power consumption value, wherein the second power consumption value is the minimum power consumption value required by the target component when the flight device maintains continuous data transmission.

[0082] Optionally, in this embodiment, the above-mentioned storage medium may include but is not limited to: a USB flash drive, a read-only memory (ROM), a random access memory (RAM), a mobile hard disk, a magnetic disk or an optical disk, and other media that can store computer programs.

[0083] Optionally, specific examples in this embodiment may refer to the examples described in the above embodiments and optional implementation modes, and this embodiment will not be described in detail here.

[0084] An embodiment of the present invention further provides an electronic device, comprising a memory and a processor, wherein the memory stores a computer program, and the processor is configured to run the computer program to execute the steps in any one of the above method embodiments.

[0085] Optionally, the electronic device may further include a transmission device and an input / output device, wherein the transmission device is connected to the processor, and the input / output device is connected to the processor.

[0086] Optionally, in this embodiment, the processor may be configured to execute the following steps through a computer program:

[0087] When it is determined that the aircraft device is in a landed state, identifying a power supply mode of a power supply in the aircraft device;

[0088] When the power supply mode is the continuous battery replacement mode, controlling a buck-boost module of the aircraft device to enter an operating state, and determining first power consumption values ​​of multiple components in the aircraft device after the buck-boost module operates for a preset period of time, wherein the buck-boost module is used to charge a capacitor in a power supply;

[0089] A target component is determined from the multiple components according to a preset rule, and a power consumption value of the target component is adjusted from a first power consumption value to a second power consumption value, wherein the second power consumption value is the minimum power consumption value required by the target component when the flight device maintains continuous data transmission.

[0090] Optionally, in this embodiment, a person of ordinary skill in the art may understand that all or part of the steps in the various methods of the above embodiments may be completed by instructing the hardware related to the terminal device through a program, and the program may be stored in a computer-readable storage medium, which may include: a flash drive, a read-only memory (ROM), a random access memory (RAM), a magnetic disk or an optical disk, etc.

[0091] The serial numbers of the above embodiments of the present invention are for description only and do not represent the advantages or disadvantages of the embodiments.

[0092] If the integrated units in the above embodiments are implemented in the form of software functional units and sold or used as independent products, they can be stored in the above-mentioned computer-readable storage medium. Based on this understanding, the technical solution of the present invention, or the part that contributes to the existing technology, or all or part of the technical solution can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes a number of instructions for causing one or more computer devices (such as personal computers, servers, or network devices) to execute all or part of the steps of the methods described in various embodiments of the present invention.

[0093] In the above embodiments of the present invention, the description of each embodiment has its own focus. For parts that are not described in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0094] In the several embodiments provided in this application, it should be understood that the disclosed client can be implemented in other ways. Among them, the device embodiments described above are merely illustrative. For example, the division of the units is merely a logical function division. In actual implementation, there may be other division methods, such as multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. In addition, the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of units or modules, and can be electrical or other forms.

[0095] The units described as separate components may or may not be physically separate, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed across multiple network units. Some or all of these units may be selected to achieve the purpose of this embodiment according to actual needs.

[0096] In addition, the functional units in the various embodiments of the present invention may be integrated into a single processing unit, each unit may exist physically separately, or two or more units may be integrated into a single unit. The aforementioned integrated units may be implemented in the form of hardware or software functional units.

[0097] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be regarded as within the scope of protection of the present invention.

Claims

1. A power consumption control method, characterized in that: include: When it is determined that the aircraft device is in a landed state, identifying a power supply mode of a power supply in the aircraft device; When the power supply mode is the continuous battery replacement mode, controlling a buck-boost module of the aircraft device to enter an operating state, and determining first power consumption values ​​of multiple components in the aircraft device after the buck-boost module operates for a preset period of time, wherein the buck-boost module is used to charge a capacitor in a power supply; A target component is determined from the multiple components according to a preset rule, and a power consumption value of the target component is adjusted from a first power consumption value to a second power consumption value, wherein the second power consumption value is the minimum power consumption value required by the target component when the flight device maintains continuous data transmission.

2. The method according to claim 1, characterized in that The method further comprises: detecting the operating status of the flight device when the power supply mode of the power supply is adjusted from the non-stop battery replacement mode to the battery power supply mode; When the aircraft is in a flight state, determining a third power consumption value of the aircraft in the flight state; When the third power consumption value is greater than or equal to the second power consumption value, the buck-boost module is controlled to enter a non-working state.

3. The method according to claim 1, characterized in that The method further comprises: When the power supply mode is the data copy mode, sending standby information to a user of the aircraft device, wherein the standby information at least includes a duration during which the remaining power in the power supply allows the data copy mode to be maintained; Determine response information of the user object after sending the standby information, wherein the response information is used to indicate the flying device.

4. The method according to claim 1, wherein Determining a target component from the plurality of components according to a preset rule includes: In the case where it is determined that the preset rule is an adjustment rule, determining a target priority corresponding to each of the multiple components, wherein the adjustment rule is used to indicate a priority for power consumption adjustment of different components; sorting the plurality of components according to the target priority; Marking a first target component whose target priority is greater than or equal to a first preset priority as an adjustment component to obtain a component set; wherein the first preset priority is used to indicate that the power consumption of the component is allowed to be adjusted to zero; A target component for which power consumption adjustment is to be performed is determined based on the component set.

5. The method according to claim 1, wherein Determining a target component from the plurality of components according to a preset rule includes: In the case where it is determined that the preset rule is a power consumption screening rule, determining a real-time power consumption value corresponding to each of the multiple components, wherein the power consumption screening rule at least includes reference values ​​for different components to be allowed to initiate power consumption adjustment; The components whose real-time power consumption values ​​are greater than or equal to the reference value are determined as target components to be subjected to power consumption adjustment.

6. The method according to claim 1, characterized in that The method further comprises: Obtaining a duration in which a first battery in the power supply has been removed; When the unplugging time is longer than a preset time, a prompt message is sent to a user of the aircraft device, wherein the prompt message is used to instruct the user to install a second battery in the power supply, and the remaining power of the first battery is less than that of the second battery; When the unplugging time is less than or equal to the preset time, battery information of the battery installed in the power supply is obtained.

7. The method according to claim 6, characterized in that The method further comprises: comparing the battery information with historical battery information for similarity, wherein the historical battery information is used to indicate battery information stored before the aircraft enters a landing state; When the similarity is greater than or equal to a preset similarity, determining that the battery in the power supply has not been replaced; When the similarity is less than a preset similarity, it is determined that the battery replacement of the power supply has been completed.

8. A power consumption control system, characterized in that: include: an identification unit, configured to identify a power supply mode of a power supply in the aircraft when it is determined that the aircraft is in a landed state; a control unit, configured to, when the power supply mode is the continuous battery replacement mode, control a buck-boost module of the aircraft device to enter an operating state, and determine first power consumption values ​​of multiple components in the aircraft device after the buck-boost module has been operating for a preset period of time, wherein the buck-boost module is configured to charge a capacitor in a power supply; An adjustment unit is used to determine a target component among the multiple components according to a preset rule, and adjust the power consumption value of the target component from a first power consumption value to a second power consumption value, wherein the second power consumption value is the minimum power consumption value required by the target component when the flight equipment maintains continuous data transmission.

9. A computer-readable storage medium, characterized in that The computer-readable storage medium stores a computer program, wherein when the computer program is executed by a processor, the steps of the method described in any one of claims 1 to 7 are implemented.

10. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the computer program, the steps of the method according to any one of claims 1 to 7 are implemented.

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