Aging power supply limiting method and unmanned aerial vehicle

Abstract

The embodiment of the application discloses a method for limiting an aging power supply and a UAV. The method is applied to a UAV, and the UAV comprises a power supply device, a flight control system and a motor. The method comprises the following steps: acquiring a power supply device parameter; judging whether the power supply device is an aging power supply device according to the power supply device parameter; if yes, allowing the power supply device to supply power to the flight control system, and sending a flight prohibition signal to the flight control system, so that the flight control system limits the rotation of the motor. Through the above method, when the power supply device is detected to be aging to a certain degree, the rotation of the motor is limited, and the flight of the UAV is limited, so that the use of large current of the aging power supply device is avoided, and safety accidents are avoided to a certain extent. In addition, the method is simple to control, convenient to operate and obvious in effect.

Description

TECHNICAL FIELD

[0001] The embodiment of the present application relates to the field of unmanned aerial vehicle, in particular to a method for limiting aged power supply and unmanned aerial vehicle. BACKGROUND

[0002] At present, the multi-rotor unmanned aerial vehicle needs large power when taking off, so the discharge rate of the battery used for supplying power to the motor is also large. However, with the increase of the use frequency of the battery, the aging degree of the battery is also higher. When the aged battery is still used, if not limited, a serious fire and explosion accident may occur due to the change of the chemical substances in the battery.

[0003] The conventional method for limiting the aged battery generally limits the charging voltage and current, or limits the use power, and these methods need to be matched with the charger or the control is complex. Therefore, it is necessary to provide a method which is simple in control and obvious in effect. SUMMARY

[0004] The embodiment of the present application mainly solves the technical problem of providing a method for limiting aged power supply, which can limit the flight of the unmanned aerial vehicle when the power supply device is aged to a certain degree, and then avoid the continuous use of large current, so that the safety accident can be avoided to a certain extent.

[0005] To solve the above technical problem, one technical scheme adopted by the embodiment of the present application is to provide a method for limiting aged power supply, applied to an unmanned aerial vehicle, the unmanned aerial vehicle comprising a power supply device, a flight control system and a motor, the method comprising: acquiring a power supply device parameter; judging whether the power supply device is an aged power supply device according to the power supply device parameter; if yes, allowing the power supply device to supply power to the flight control system, and sending a flight prohibition signal to the flight control system to make the flight control system limit the rotation of the motor.

[0006] In some embodiments, after judging that the power supply device is not an aged power supply device, the method further comprises: judging whether the power supply device meets other limiting conditions; if yes, allowing the power supply device to supply power to the flight control system and the motor.

[0007] In some embodiments, after sending the flight prohibition signal to the flight control system, the method further comprises: sending a prompt signal to a control device to prompt the user that the power supply device has been aged and needs to be replaced.

[0008] In some embodiments, the power supply device parameter comprises a battery cycle number.

[0009] In some embodiments, the determining whether the power supply device is an aging power supply device according to the power supply device parameter comprises: determining whether the battery cycle number is greater than a preset threshold N; if yes, determining that the power supply device is an aging power supply device; if no, determining that the power supply device is not an aging power supply device.

[0010] In some embodiments, the satisfying other restriction conditions comprises: the temperature of the power supply device is not higher than a preset temperature threshold; and the power supply device is in a safe state.

[0011] In some embodiments, the preset threshold N is 150% of the warranty cycle number of the battery.

[0012] To solve the above technical problems, another technical scheme adopted by the embodiments of the present application is to provide a UAV, comprising: a fuselage, a power supply device and a flight control system, wherein the fuselage is internally provided with a motor for driving the UAV to fly; the power supply device is accommodated in the fuselage, a signal output end of the power supply device is connected to a signal input end of the flight control system, an electric energy output end of the power supply device is connected to an electric energy input end of the motor and an electric energy input end of the flight control system, and the power supply device is used to provide electric power for the motor and the flight control system; and the flight control system is accommodated in the fuselage, and a signal output end of the flight control system is connected to a control end of the motor.

[0013] In some embodiments, the power supply device comprises: a battery pack, a temperature and voltage sampling module, a current sampling module, a battery management chip and a battery microprocessor, wherein the electric energy output end of the power supply device is the electric energy output end of the battery pack; a sampling end of the current sampling module is connected to the electric energy output end of the battery pack, a signal output end of the current sampling module is connected to a first signal input end of the battery management chip, and the current sampling unit is used to acquire the charging current and the discharging current of the battery pack; a sampling end of the temperature and voltage sampling module is connected to the electric energy output end of the battery pack, a signal output end of the temperature and voltage sampling module is connected to a second signal input end of the battery management chip, and the temperature and voltage sampling module is used to collect the output voltage and the temperature of the battery pack; the battery management chip is in communication connection with the battery microprocessor, and the battery management chip is used to calculate the battery cycle number; and the battery microprocessor is in communication connection with the flight control system, and the battery microprocessor is used to execute the restriction method of an aging power supply device as described above.

[0014] In some embodiments, the UAV further comprises a radio frequency module, the radio frequency module is in communication connection with the battery microprocessor and the flight control system, and the radio frequency module is in communication connection with a control device in a radio manner.

[0015] In some embodiments, the control device comprises a remote controller and a mobile phone.

[0016] The beneficial effect of the embodiment of the present application is that, unlike the prior art, the embodiment of the present application can limit the rotation of the motor and thus limit the flight of the unmanned aerial vehicle when detecting that the power supply device is aged to a certain extent, avoid the use of large current of the aged power supply device, and to a certain extent, avoid safety accidents. In addition, the method is simple to control, easy to operate and has obvious effect. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 is a schematic diagram of an application environment of the embodiment of the present application;

[0018] Figure 2 is a structural schematic diagram of an unmanned aerial vehicle provided by the embodiment of the present application;

[0019] Figure 3 is a structural schematic diagram of a power supply device provided by the embodiment of the present application;

[0020] Figure 4 is a structural schematic diagram of a power supply device provided by the embodiment of the present application, wherein the loop switch is a charging switch tube;

[0021] Figure 5 is a structural schematic diagram of a power supply device provided by the embodiment of the present application, wherein the loop switch is a discharging switch tube;

[0022] Figure 6 is a flowchart of a limiting method of an aged power supply provided by the embodiment of the present application;

[0023] Figure 7 is a flowchart of step S200 in the limiting method of the aged power supply provided by the embodiment of the present application;

[0024] Figure 8 is a flowchart of another limiting method of an aged power supply provided by the embodiment of the present application. DETAILED DESCRIPTION

[0025] The present application will be described in detail below with specific embodiments. The following embodiments will help those skilled in the art to further understand the present application, but do not limit the present application in any form. It should be noted that for those skilled in the art, without departing from the concept of the present application, a number of modifications and improvements can be made. These all belong to the protection scope of the present application.

[0026] In order to make the purposes, technical solutions and advantages of the present application clearer, the present application will be further described in detail below with reference to the drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and not intended to limit the present application.

[0027] Figure 1 The schematic diagram of the application environment of the embodiments of the present application. As shown in the figure, the application environment takes the unmanned aerial vehicle system as an example, which includes the unmanned aerial vehicle 10, the remote control device 20 and the wireless network 30. Figure 1

[0028] The unmanned aerial vehicle 10 can be any type of power-driven (such as electric power) unmanned aerial vehicle, including but not limited to quadcopters, fixed-wing aircraft and helicopter models, etc. In this embodiment, the quadcopter is taken as an example for description. The main body of the unmanned aerial vehicle 10 can be mounted with several different functional modules, which can be software modules, hardware modules or software and hardware combined, modular devices for realizing one or more functions.

[0029] In some embodiments, the unmanned aerial vehicle 10 can include a fuselage, an arm, a power device and a flight controller. The fuselage is the main structure of the unmanned aerial vehicle 10, which provides sufficient space to accommodate one or more components. It can have a suitable volume and shape according to actual needs and be made of corresponding materials.

[0030] The arm is the part extending outward from the fuselage, which serves as the mounting or fixing structure of the unmanned aerial vehicle power device such as propeller. The arm can be integrally formed with the fuselage, or can be connected with the fuselage in a detachable manner. Typically, on the quadcopter, the arm can be provided as four, extending along the diagonal line symmetrically, forming the mounting position of four propellers.

[0031] The power device can be driven by any type of energy, mounted and fixed at the mounting position at the end of the arm, which is a structural device for providing flight power for the unmanned aerial vehicle. For example, the propeller driven by the motor. The power provided by the power device or the actual structure used can be determined according to the actual needs.

[0032] The flight controller is the control core of the unmanned aerial vehicle built-in the fuselage. It can be any type of electronic device with suitable logic judgment and computing ability, including but not limited to processor chips based on large-scale integrated circuits, integrated system on chip (SOC) and processors and storage media connected through bus.

[0033] ​The remote control device 20 can be any type of device for establishing a communication connection with the UAV, controlling the UAV, such as a remote controller. The remote controller can be equipped with one or more different user interaction devices based on which user instructions are collected or information is displayed and fed back to the user, realizing the interaction between the user and the UAV.

[0034] The interaction devices include, but are not limited to, buttons, scroll wheels, display screens, touch screens, mice, speakers, and joysticks. For example, the remote control device 20 can be equipped with a display screen through which the user's remote control instructions for the UAV are received and through which aerial images are displayed to the user, or a corresponding simulation driving interface is presented to the user on which one or more flight parameters, such as flight speed, heading, or remaining power, are displayed.

[0035] In other embodiments, the remote control device 20 can also be implemented by a smart terminal. The smart terminal includes, but is not limited to, a smartphone, a tablet computer, a laptop computer, a wearable device, and the like. The smart terminal establishes a communication connection with the UAV by running a specially set APP client or a web page, realizing data transmission between the UAV and the smart terminal.

[0036] The wireless network 30 can be a wireless communication network based on any type of data transmission principle for establishing a data transmission channel between two nodes. For example, a Bluetooth network, a WiFi network, a wireless cellular network, or a combination thereof in different signal frequency bands. The frequency band or network form actually used by the wireless network 30 is related to the communication equipment used by the UAV 10 and the remote control device 20.

[0037] Based on the above application environment, the present embodiment provides a UAV, a structural schematic diagram of which is shown in Figure 2 The UAV includes a body 100, a power supply device 200, a flight control system 300, and a radio frequency module 400, wherein,

[0038] The body 100 is provided with a power system for driving the UAV 10 to fly. In the present embodiment, the power system is an electric motor 110. The electric motor (English: Electric machinery, commonly known as "motor") refers to an electromagnetic device that realizes the conversion or transmission of electric energy according to the electromagnetic induction law.

[0039] Preferably, the type of the electric motor 110 is a brushless electric motor. The number of the electric motor 110 is determined according to the number of the rotors installed on the body 100 of the UAV 10. If the UAV 10 is a four-rotor UAV, the UAV 10 contains four electric motors 110; if the UAV 10 is a six-rotor UAV, the UAV contains six electric motors 110.

[0040] The power supply device 200 is accommodated in the fuselage 100, and it is understood that the power supply device 200 is used to supply power to the entire unmanned aerial vehicle 10, which is specifically manifested as directly supplying power to the motor 110 and the flight control system 300, and indirectly supplying power to the radio frequency module 400. The circuit connection relationship between the power supply device 200 and other components is that the power output end of the power supply device 200 is connected to the power input end of the flight control system 300 and the power input end of the motor 110, and the signal output end of the power supply device 200 is connected to the signal input end of the flight control system 300.

[0041] The flight control system 300 can stabilize the flight attitude of the unmanned aerial vehicle 10 and can control the unmanned aerial vehicle 10 to fly autonomously or semi-autonomously, and is the core system of the unmanned aerial vehicle 10 to complete the entire flight process of taking off, flying in the air, performing tasks, and returning to the field for recovery. The flight control system 300 is also accommodated in the fuselage 100, and the signal output end thereof is connected to the control end of the motor 110 to control the motor 100, and the flight control system 300 and the power supply device 200 are in communication connection.

[0042] The radio frequency module 400 is also accommodated in the fuselage 100 of the unmanned aerial vehicle 10, and the radio frequency module 400 establishes communication connection with the power supply device 200 and the flight control system 300, respectively. In addition, the radio frequency module 400 also establishes communication connection with the control device outside the unmanned aerial vehicle 10 through wireless connection. It can be seen that the role of the radio frequency module 400 is to receive the signal sent by the user through the control device, and transmit the signal to the power supply device 200 or the flight control system 300, so as to realize the control of the unmanned aerial vehicle 10 by the user through the control device; or receive the information sent by the battery device 200, and transmit the information to the control device through wireless connection, so as to realize the information feedback of the power supply device 200 in time.

[0043] In some embodiments, the control device includes a mobile phone and a remote controller.

[0044] It should be noted that the power supply device 200 in the embodiment of the application is not a power supply in the general sense which only includes a battery pack. The power supply device 200 is a smart battery, and a structural schematic diagram thereof is shown in Figure 3 Figure 3 A structural schematic diagram of a power supply device provided by the embodiment of the application, the power supply device 200 includes a battery pack 210, a temperature and voltage sampling module 220, a battery management chip 230, a battery microprocessor 240, and a current sampling module 250, wherein,

[0045] ​The sampling end of the temperature and voltage sampling module 220 is connected to the power output end of the battery pack 210, and the signal output end of the temperature and voltage sampling module 220 is connected to the second signal input end of the battery management chip 230. The temperature and voltage sampling module 220 is used to collect temperature information and voltage information of the battery pack 210, and transmit the temperature information and voltage information to the battery management chip 230.

[0046] The sampling end of the current sampling module 250 is connected to the power output end of the battery pack 210, and the signal output end of the current sampling module 250 is connected to the first signal input end of the battery management chip 230. The current sampling module 250 is used to collect current information of the battery pack 210, and transmit the current information to the battery management chip 230.

[0047] The battery management chip 230 is in communication connection with the battery microprocessor 240. In addition to being used to obtain temperature information, voltage information and current information of the battery pack 210, the battery management chip 230 is also used to count the battery cycle number.

[0048] Preferably, the battery cycle number is calculated by recording the discharge process of the battery pack 210, for example, recording the discharge of a certain proportion of the battery pack 210 as one cycle, and then the battery management chip 230 increases the value of the battery cycle number by one. Essentially, the battery cycle number is a value used to reflect the aging degree of the battery pack 210. Therefore, in addition to the calculation method mentioned above, the battery cycle number can also be a recorded value obtained by other methods.

[0049] The battery microprocessor 240 is in communication connection with the flight control system 300, and the battery microprocessor 240 is used to execute a preset method.

[0050] In other embodiments, another unmanned aerial vehicle is also provided, which uses a charging switch tube as a loop switch, and a structural schematic diagram thereof is shown in Figure 4 The unmanned aerial vehicle 10 includes a battery pack 210, a temperature and voltage sampling module 220, a battery management chip 230, a battery microprocessor 240, a current sampling module 250, a loop switch 260, a power supply and communication output port 270, and a voltage stabilizing power supply 280. Among them,

[0051] The sampling end of the temperature and voltage sampling module 220 is connected to the power output end of the battery pack 210, and the signal output end of the temperature and voltage sampling module 220 is connected to the second signal input end of the battery management chip 230. The temperature and voltage sampling module 220 is used to collect temperature information and voltage information of the battery pack 210, and transmit the temperature information and voltage information to the battery management chip 230.

[0052] The first sampling end of the current sampling module 250 is connected to the negative pole of the battery pack 210, the second sampling end of the current sampling module 250 is connected to the negative input end of the power supply and communication output port 270, and the signal output end of the current sampling module 250 is connected to the first signal input end of the battery management chip 230. The current sampling module 250 is used to collect the current information of the battery pack 210 and transmit the current information to the battery management chip 230.

[0053] Preferably, the loop switch 260 is a charging switch tube, and the circuit connection relationship is that the drain of the loop switch 260 is connected to the positive pole of the battery pack 210, the gate of the loop switch 260 is connected to the signal output end of the battery management chip 230, and the source of the loop switch 260 is connected to the positive input end of the power supply and communication output port 270.

[0054] The battery management chip 230 is in communication connection with the battery microprocessor 240, and the battery management chip 230 is used to count the battery cycle number in addition to being used to obtain the temperature information, voltage information and current information of the battery pack 210.

[0055] Preferably, the calculation method of the battery cycle number is to record the discharging process of the battery pack 210, for example, to record the cumulative discharge of a certain proportion of the battery pack 210 as one cycle, and then the battery management chip 230 increases the value of the battery cycle number by one. Essentially, the battery cycle number is a value used to reflect the aging degree of the battery pack 210. Therefore, in addition to the calculation method mentioned above, the battery cycle number can also be a recorded value obtained by other methods.

[0056] The battery microprocessor 240 is in communication connection with the power supply and communication output port 270, and the battery microprocessor 240 is used to execute a preset method.

[0057] The power supply and communication output port 270 is in communication connection with the flight control system 300.

[0058] Of course, the loop switch 260 can also be connected to the negative pole of the battery pack 210, as shown in Figure 5 Figure 5 It is a structural schematic diagram of a UAV, the loop switch of the UAV is a discharging diode, and the UAV includes a battery pack 210, a temperature and voltage sampling module 220, a battery management chip 230, a battery microprocessor 240, a current sampling module 250, a loop switch 260, a power supply and communication output port 270 and a voltage stabilizing power supply 280. Among them,

[0059] ​The sampling end of the temperature and voltage sampling module 220 is connected to the power output end of the battery pack 210, and the signal output end of the temperature and voltage sampling module 220 is connected to the second signal input end of the battery management chip 230. The temperature and voltage sampling module 220 is used to collect temperature information and voltage information of the battery pack 210, and transmit the temperature information and voltage information to the battery management chip 230.

[0060] The first sampling end of the current sampling module 250 is connected to the positive electrode of the battery pack 210, the second sampling end of the current sampling module 250 is connected to the positive input end of the power and communication output port 270, and the signal output end of the current sampling module 250 is connected to the first signal input end of the battery management chip 230. The current sampling module 250 is used to collect current information of the battery pack 210, and transmit the current information to the battery management chip 230.

[0061] Preferably, the loop switch 260 is a discharge switch tube, and the circuit connection relationship is that the source of the loop switch 260 is connected to the negative electrode of the battery pack 210, the gate of the loop switch 260 is connected to the signal output end of the battery management chip 230, and the drain of the loop switch 260 is connected to the positive and negative input ends of the power and communication output port 270.

[0062] The battery management chip 230 is in communication connection with the battery microprocessor 240, and the battery management chip 230 is used to count the battery cycle number in addition to being used to obtain the temperature information, voltage information and current information of the battery pack 210.

[0063] Preferably, the calculation method of the battery cycle number is to record the discharge process of the battery pack 210, for example, to record the cumulative discharge of a certain proportion of the battery pack 210 as one cycle, and then the battery management chip 230 increases the value of the battery cycle number by one. Essentially, the battery cycle number is a value used to reflect the aging degree of the battery pack 210. Therefore, in addition to the calculation method mentioned above, the battery cycle number can also be a record value obtained by other methods.

[0064] The battery microprocessor 240 is in communication connection with the power and communication output port 270, and the battery microprocessor 240 is used to execute a preset method.

[0065] The power and communication output port 270 is in communication connection with the flight control system 300.

[0066] In the embodiment of the application, based on the above-mentioned application scenario, the application embodiment provides a limiting method for an aging power supply, which is applied to the take-off process of the unmanned aerial vehicle, the method is executed by the battery microprocessor 240, a flowchart of the method is as shown in Figure 6 The method comprises the following steps:

[0067] Step S100: obtaining the power device parameter;

[0068] After starting the power device of the unmanned aerial vehicle, the battery microprocessor sends a reading signal to the battery management chip, so that the battery management chip sends the power device parameter to the battery microprocessor.

[0069] The battery device parameter includes the battery cycle number, which is recorded and stored by the battery management chip.

[0070] Step S200: determining whether the power device is an aged power device according to the power device parameter;

[0071] According to the power device parameter obtained by the battery management chip, it is determined whether the power device is an aged power device, and if so, step S300 is performed.

[0072] In some embodiments, the power device parameter is the battery cycle number, and the step further includes the following steps, as shown in Figure 7

[0073] Step S210: determining whether the battery cycle number is greater than a preset threshold N;

[0074] The obtained power cycle number from the battery management chip is compared with the preset threshold N, and the preset threshold N can be defined and valued according to specific applications.

[0075] In the embodiment of the application, the preset threshold N is a preset cycle number threshold, and its value is 150% of the power device warranty cycle number.

[0076] If the obtained power cycle number is greater than the preset threshold N, step S220 is performed; if the obtained power cycle number is not greater than the preset threshold N, step S230 is performed.

[0077] Step S220: determining that the power device is an aged power device;

[0078] Step S230: determining that the power device is not an aged power device;

[0079] Step S300: allowing the power device to supply power to the flight control system, and sending a flight prohibition signal to the flight control system to make the flight control system limit the rotation of the motor.

[0080] After determining that the power device is an aged power device, the battery microprocessor still does not limit the power device to supply power to the flight control system, but sends a flight prohibition signal to the flight control system. After receiving the flight prohibition signal, the flight control system sends a limiting signal to the motor to limit the rotation of the motor. It should be noted that during the entire process, the unmanned aerial vehicle is always in standby state, i.e. the power device still supplies power normally, but the rotation of the motor is limited.​

[0081] In addition, considering the existence of other limiting conditions, the embodiment of the present application further provides another limiting method for the aged power supply, a flowchart of which is shown in Figure 8 The method comprises the following steps:

[0082] Step S100: obtaining the power supply device parameter;

[0083] After starting the power supply device of the unmanned aerial vehicle, the battery microprocessor sends a reading signal to the battery management chip, so that the battery management chip sends the power supply device parameter to the battery microprocessor.

[0084] Preferably, the battery device parameter is the battery cycle number, which is recorded and stored by the battery management chip.

[0085] Step S200: determining whether the power supply device is an aged power supply device according to the power supply device parameter;

[0086] According to the power supply device parameter obtained by the battery management chip, it is determined whether the power supply device is an aged power supply device. If yes, step S300 is performed; if no, step S500 is performed.

[0087] In some embodiments, the power supply device parameter is the battery cycle number, and the step further comprises the following steps, as shown in Figure 7

[0088] Step S210: determining whether the battery cycle number is greater than a preset threshold N;

[0089] The obtained power supply cycle number from the battery management chip is compared with the preset threshold N, which can be defined and valued according to specific applications.

[0090] In the embodiment of the present application, the preset threshold N is a preset cycle number threshold, and its value is 150% of the warranty cycle number of the power supply device. Of course, the preset cycle number threshold can also take a larger value, and its value range only needs to be greater than the warranty cycle number, which is sufficient to cover the life cycle of the power supply device.

[0091] If the obtained power supply cycle number is greater than the preset threshold N, step S220 is performed; if the obtained power supply cycle number is not greater than the preset threshold N, step S230 is performed.

[0092] Step S220: determining that the power supply device is an aged power supply device;

[0093] Step S230: determining that the power supply device is not an aged power supply device;

[0094] ​Step S300: Allow the power supply equipment to supply power to the flight control system and send a no-fly signal to the flight control system to restrict the rotation of the motors.

[0095] After determining that the power supply unit is aging, the battery microprocessor does not restrict the power supply unit from powering the flight control system, but it will send a no-fly signal to the flight control system. Upon receiving this no-fly signal, the flight control system sends a restriction signal to the motors to limit their rotation. It should be noted that throughout this process, the drone remains in standby mode, meaning the power supply unit continues to provide power normally, but the motor rotation is restricted.

[0096] Step S400: Send a prompt signal to the control device to remind the user that the power supply equipment is aging and needs to be replaced.

[0097] After the battery microprocessor sends a no-fly signal to the flight control system to restrict the motor's rotation, it also sends a warning signal to the control device wirelessly via the radio frequency module. This warning signal is used to inform the user that the drone's power supply has aged to a certain extent, and that using this aged power supply to power the motors could potentially cause an accident; thus, it prompts the user to replace the aged power supply.

[0098] Step S500: Determine whether the power supply device meets other limiting conditions;

[0099] After determining that the power supply device is not an aging power supply device, it is also necessary to determine whether the power supply device meets other limiting conditions. If it does, proceed to step S600.

[0100] In some embodiments, other limiting conditions include: determining whether the temperature of the power supply device is not higher than a preset temperature threshold; and determining whether the power supply device is in a safe state.

[0101] In some embodiments, determining whether the power supply device is in a safe state includes:

[0102] Determine whether the input current of the power supply device exceeds a preset input current threshold; determine whether the output current of the power supply device exceeds a preset output current threshold; determine whether the output voltage of the power supply device exceeds a preset output voltage threshold. If the input current, output current, and output voltage of the power supply device do not exceed the preset input current threshold, then the power supply device is determined to be in a safe state.

[0103] When the power supply device meets the following conditions: the temperature of the power supply device is not higher than the preset temperature threshold and the power supply device is in a safe state, then step S600 is executed.

[0104] Step S600: Allow the power supply device to supply power for the flight control system and the motor.

[0105] At this point, it can be determined that the power supply device is not an aging power supply device and meets other restriction conditions, so the power supply device has no use risk. The UAV can be normally started and taken off.

[0106] Compared with the prior art, the embodiments of the present application can limit the rotation of the motor and the flight of the UAV when the power supply device is detected to be aged to a certain extent, thereby avoiding the use of large current by the aged power supply device and to a certain extent, avoiding safety accidents. In addition, the method is simple to control, convenient to operate and has obvious effect.

[0107] The above description is only an embodiment of the present application, and does not limit the patent scope of the present application, and any equivalent structure or equivalent process transformation using the content of the specification and drawings, or direct or indirect application in other related technical fields, are also included in the patent protection scope of the present application.

Claims

1. A method for limiting an aging power supply applied to a UAV, the UAV comprising a power supply device, a flight control system and a motor, characterized in that, The limiting method comprises: acquiring power supply device parameters; determining whether the power supply device is an aged power supply device according to the power supply device parameters; if yes, allowing the power supply device to supply power to the flight control system, and sending a flight prohibition signal to the flight control system to make the flight control system limit the rotation of the motor; sending a prompt signal to a control device to prompt a user that the power supply device has aged; if the power supply device is determined not to be the aged power supply device, determining whether the power supply device meets other limiting conditions, determining whether the input current of the power supply device exceeds a preset input current threshold, determining whether the output current of the power supply device exceeds a preset output current threshold, and determining whether the output voltage of the power supply device exceeds a preset output voltage threshold, if the input current of the power supply device does not exceed the preset input current threshold, the output current of the power supply device does not exceed the preset output current threshold, and the output voltage of the power supply device does not exceed the preset output voltage threshold, it is determined that the power supply device is in a safe state; if yes, allowing the power supply device to supply power to the flight control system and the motor.

2. The method of claim 1, wherein, After sending the flight prohibition signal to the flight control system, the method further comprises: sending a prompt signal to a control device to prompt a user that the power supply device has aged, prompting the user to replace the power supply device.

3. The method of claim 2, wherein, The power supply device parameters include the number of battery cycles.

4. The method of claim 3, wherein, The determination of whether the power supply device is an aged power supply device according to the power supply device parameters comprises: determining whether the number of battery cycles is greater than a preset threshold N; if yes, determining that the power supply device is an aged power supply device; if no, determining that the power supply device is not an aged power supply device.

5. The method of claim 4, wherein, The preset threshold N is 150% of the warranty cycle number of the power supply device.

6. A drone, characterized in that, Comprise: a fuselage, a power supply device and a flight control system, wherein the fuselage is provided with a motor for driving the flight of the unmanned aerial vehicle; the power supply device is accommodated in the fuselage, the signal output end of the power supply device is connected to the signal input end of the flight control system, the power output end of the power supply device is connected to the power input end of the motor and the power input end of the flight control system, and the power supply device is used to provide power for the motor and the flight control system; the flight control system is accommodated in the fuselage, the signal output end of the flight control system is connected to the control end of the motor, and a prompt signal is sent to a control device to prompt a user that the power supply device has aged; The power supply device comprises: a battery pack, a temperature and voltage sampling module, a current sampling module, a battery management chip and a battery microprocessor, wherein the power output end of the power supply device is the power output end of the battery pack; the sampling end of the current sampling module is connected to the power output end of the battery pack, the signal output end of the current sampling module is connected to the first signal input end of the battery management chip, and the current sampling module is used to acquire the charging current and discharging current of the battery pack; The sampling end of the temperature and voltage sampling module is connected to the electric energy output end of the battery pack, the signal output end of the temperature and voltage sampling module is connected to the second signal input end of the battery management chip, and the temperature and voltage sampling module is used for collecting the output voltage and temperature of the battery pack. The battery management chip is in communication connection with the battery microprocessor, and the battery management chip is used for calculating the battery cycle number. The battery microprocessor is communicatively coupled to the flight control system, the battery microprocessor configured to perform the steps of claim 1 5. The method of claim 1-4, wherein the aging power supply is a battery.

7. The drone of claim 6, wherein, The unmanned aerial vehicle further comprises a radio frequency module, which is in communication connection with the battery microprocessor and the flight control system, and the radio frequency module is in communication connection with the control device in the form of radio.

8. The drone of claim 7, wherein, The control device comprises a remote controller and a mobile phone.

Images