CN113410877A - Unmanned aerial vehicle power management system - Google Patents
Unmanned aerial vehicle power management systemDownload PDFInfo
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- CN113410877A CN113410877ACN202010262648.1ACN202010262648ACN113410877ACN 113410877 ACN113410877 ACN 113410877ACN 202010262648 ACN202010262648 ACN 202010262648ACN 113410877 ACN113410877 ACN 113410877A
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J4/00—Circuit arrangements for mains or distribution networks not specified as AC or DC
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/36—Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC]
- G01R31/382—Arrangements for monitoring battery or accumulator variables, e.g. SoC
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/36—Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC]
- G01R31/382—Arrangements for monitoring battery or accumulator variables, e.g. SoC
- G01R31/3842—Arrangements for monitoring battery or accumulator variables, e.g. SoC combining voltage and current measurements
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/36—Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC]
- G01R31/389—Measuring internal impedance, internal conductance or related variables
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0047—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with monitoring or indicating devices or circuits
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0063—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with circuits adapted for supplying loads from the battery
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
- H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
- H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D2221/00—Electric power distribution systems onboard aircraft
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
Description
Technical Field
The invention relates to an unmanned aerial vehicle power management system, in particular to an unmanned aerial vehicle power management system capable of managing a plurality of electric energy providing devices according to a plurality of electric quantity information.
Background
Present general unmanned aerial vehicle can't manage in order to provide the device to the electric energy according to the condition of difference, and this will make the electric energy provide the device can't reach higher discharge efficiency, and then leads to unmanned aerial vehicle's flight time to reduce. In view of the above, there is a need for an unmanned aerial vehicle power management system capable of managing a plurality of power supply devices according to a plurality of power information.
Disclosure of Invention
In order to solve the above problems, an idea of the present invention is to provide an unmanned aerial vehicle power management system capable of managing a plurality of power supply devices according to a plurality of power information.
Based on the above idea, the present invention provides an unmanned aerial vehicle power management system, including: a first power supply having a first power; a second power supply having a second power; the first electrode device is connected with the first electric energy supply device and the second electric energy supply device; a third power supply having a third power; a fourth power supply having a fourth power; the second electrode device is connected with the third electric energy supply device and the fourth electric energy supply device; wherein the first and/or second electrical energy providing devices provide the first and/or second electrical energy to the first device of the drone through the first electrode device; wherein the third electrical energy providing device and/or the fourth electrical energy providing device provides the third electrical energy and/or the fourth electrical energy to the second device of the drone through the second electrode device.
In a preferred embodiment of the present invention, the power management system of the drone further includes: a third electrode device connected to the first, second, third and fourth power supply devices; wherein the first and/or second power supply means provides the first and/or second power to the first means via the first and third electrode means; wherein the third power supply device and/or the fourth power supply device provides the third power and/or the fourth power to the second device through the second electrode device and the third electrode device.
In a preferred embodiment of the present invention, the first power supply device, the second power supply device, the third power supply device and the fourth power supply device are all batteries.
In a preferred embodiment of the present invention, the first power supply device is a power generation device capable of continuously generating power, and the second power supply device, the third power supply device and the fourth power supply device are batteries.
In a preferred embodiment of the present invention, the first electrode device includes: the uninterruptible power system is provided with a first switch device and a second switch device, wherein the first switch device is connected with the first power supply device, and the second switch device is connected with the second power supply device; and the electric energy providing management system is connected with the uninterruptible power system and controls the first switch device and the second switch device according to the first electric energy information related to the first electric energy providing device and the second electric energy information related to the second electric energy providing device.
In a preferred embodiment of the present invention, the power management system of the drone further includes: the first electric quantity monitoring device is connected with the first electric energy providing device and the electric energy providing management system and provides the first electric quantity information to the electric energy providing management system; and the second electric quantity monitoring device is connected with the second electric energy providing device and the electric energy providing management system and provides the second electric quantity information to the electric energy providing management system.
In a preferred embodiment of the present invention, the first power information is calculated by the first power monitoring device according to first voltage information and first current information associated with the first power providing device; wherein the second power information is calculated by the second power monitoring device according to the second voltage information and the second current information associated with the second power providing device.
In a preferred embodiment of the present invention, the power supply management system provides at least one of the first power information, the first voltage information, the first current information, the second power information, the second voltage information, and the second current information to a flight control device of the drone to generate and record first internal resistance curvature information and/or second internal resistance curvature information, where the first internal resistance curvature information is associated with the first power supply device, and the second internal resistance curvature information is associated with the second power supply device.
In a preferred embodiment of the present invention, the first power supply device has first internal resistance curvature record information, and the second power supply device has second internal resistance curvature record information; and the unmanned aerial vehicle estimates the electric quantity of the first electric energy providing device and/or the second electric energy providing device according to the first internal resistance curvature information and/or the second internal resistance curvature information and/or the first internal resistance curvature recording information and/or the second internal resistance curvature recording information.
In a preferred embodiment of the present invention, the drone power management system calculates first internal resistance information associated with the first power providing device and/or second internal resistance information associated with the second power providing device, and the drone power management system generates prediction information according to the first internal resistance information and/or the second internal resistance information; wherein the prediction information indicates whether the first internal resistance information and/or the second internal resistance information is about to reach an internal resistance threshold.
In a preferred embodiment of the present invention, the drone power management system calculates first internal resistance information associated with the first power providing device and/or second internal resistance information associated with the second power providing device, and the drone power management system generates a warning message when the first internal resistance information or the second internal resistance information reaches an internal resistance threshold.
The foregoing aspects and other aspects of the present invention will become more apparent upon consideration of the following detailed description of non-limiting embodiments thereof, as illustrated in the accompanying drawings.
Drawings
Fig. 1 is a schematic diagram of an embodiment of an unmanned aerial vehicle power management system according to the present invention.
Fig. 2 is a system architecture diagram of an embodiment of the power management system of the unmanned aerial vehicle of the present invention.
Fig. 3A is a circuit equivalent diagram of an electrical energy providing apparatus according to an embodiment.
Fig. 3B is a graph illustrating an electrical quantity of the electrical energy providing apparatus according to an embodiment.
Description of reference numerals:
100 unmanned aerial vehicle power management system
110 first electric energy supply device
120 second power supply device
130 third power supply device
140 fourth Power supply device
150 first electrode arrangement
160 second electrode arrangement
170 third electrode arrangement
200 unmanned aerial vehicle power management system
210 first power supply device
220 second power supply device
230 third power supply device
240 fourth power supply device
250 first electrode arrangement
252 uninterruptible power system
252A first switching device
252B second switching device
254 electric energy supply management system
260 second electrode arrangement
270 third electrode arrangement
280 first electric quantity monitoring device
290 second power monitoring device
310 usable voltage
320 internal resistance
330 maximum voltage curve
340 may use a voltage curve
350 EDV wire
910 first device
920 second device
Detailed Description
Referring to fig. 1, a schematic diagram of an embodiment of a power management system for an unmanned aerial vehicle according to the invention is illustrated. As shown in fig. 1, the unmanned dronepower management system 100 includes afirst power supply 110, asecond power supply 120, athird power supply 130, afourth power supply 140, afirst electrode 150, asecond electrode 160, and athird electrode 170. Thefirst electrode device 150 connects the firstpower supply device 110 and the secondpower supply device 120. Thesecond electrode device 160 connects the thirdpower supply device 130 and the fourthpower supply device 140. Thethird electrode device 170 is connected to the firstpower supply device 110, the secondpower supply device 120, the thirdpower supply device 130 and the fourthpower supply device 140. Thefirst power supply 110 has the first power, thesecond power supply 120 has the second power, thethird power supply 130 has the third power, and thefourth power supply 140 has the fourth power.
In one embodiment, thefirst electrode assembly 150 couples the positive electrode of the firstpower supply assembly 110 to the positive electrode of the secondpower supply assembly 120. Thesecond electrode device 160 connects the anode of the thirdpower supply device 130 with the anode of the fourthpower supply device 140. Thethird electrode device 170 is connected to the negative electrode of the firstpower supply device 110, the negative electrode of the secondpower supply device 120, the negative electrode of the thirdpower supply device 130, and the negative electrode of the fourthpower supply device 140. Thus, even if the positive electrode of one of thefirst power supply 110 or thesecond power supply 120 is dropped or damaged, the positive electrode of the other is still connected to thefirst electrode device 150 and operates normally, which is a fail-safe function. Similarly, even if the positive electrode of one of the thirdpower supply device 130 or the fourthpower supply device 140 falls off or is damaged, the positive electrode of the other is still connected to thesecond electrode device 160 and operates normally, thereby achieving the fail-safe function. The same is true. Even if the negative electrode of one of the first, second, third and fourthpower providing devices third electrode device 170 and operate normally, thereby achieving the fail-safe function.
In the embodiment shown in fig. 1, the first electricalenergy providing device 110 and/or the second electricalenergy providing device 120 provides the first electrical energy and/or the second electrical energy to a first device (not shown) of the drone through thefirst electrode device 150, and the third electricalenergy providing device 130 and/or the fourth electricalenergy providing device 140 provides the third electrical energy and/or the fourth electrical energy to a second device (not shown) of the drone through thesecond electrode device 160. Alternatively, more specifically, the first electricalenergy supply device 110 and/or the second electricalenergy supply device 120 provides the first electrical energy and/or the second electrical energy to the first device through thefirst electrode device 150 and thethird electrode device 170, and the third electricalenergy supply device 130 and/or the fourth electricalenergy supply device 140 provides the third electrical energy and/or the fourth electrical energy to the second device through thesecond electrode device 160 and thethird electrode device 170.
In one embodiment, the first device may be at least one of a flight control system, a servo motor, and a wireless control device of the drone, and the second device may be at least one of a flight control system, a servo motor, and a wireless control device of the drone. In different embodiments, the first device and the second device may be the same device or different devices. In one embodiment, thefirst power supply 110, thesecond power supply 120, thethird power supply 130 and thefourth power supply 140 are all batteries. In another embodiment, the firstpower supply device 110 is a power generation device capable of continuously generating power, and the secondpower supply device 120, the thirdpower supply device 130 and the fourthpower supply device 140 are all batteries. In one embodiment, thefirst electrode assembly 150 and thesecond electrode assembly 160 are circuit board assemblies.
Referring to fig. 2, a system architecture diagram illustrating an embodiment of the drone power management system according to the present invention is shown. As shown in fig. 2, the unmanned dronepower management system 200 includes a firstpower supply device 210, a secondpower supply device 220, a thirdpower supply device 230, a fourthpower supply device 240, afirst electrode device 250, asecond electrode device 260, athird electrode device 270, a firstpower monitoring device 280, and a secondpower monitoring device 290. Thefirst electrode device 250 includes anuninterruptible power system 252 and a powersupply management system 254. Theuninterruptible power system 252 further includes afirst switching device 252A and asecond switching device 252B. The firstpower supply device 210 has the first power, the secondpower supply device 220 has the second power, the thirdpower supply device 230 has the third power, and the fourthpower supply device 140 has the fourth power.
Thesecond electrode device 260 connects the thirdpower supply device 230 and the fourthpower supply device 240. Thethird electrode device 270 is connected to the firstpower supply device 210, the secondpower supply device 220, the thirdpower supply device 230 and the fourthpower supply device 240. Thefirst switching device 252A of theups system 252 is connected to thefirst power supply 210, and thesecond switching device 252B of theups system 252 is connected to thesecond power supply 220. The powersupply management system 254 is connected to theuninterruptible power system 252. The firstpower monitoring device 280 is connected to the firstpower providing device 210 and thepower management system 254, and the secondpower monitoring device 290 is connected to the secondpower providing device 220 and thepower management system 254.
In the embodiment shown in fig. 2, the firstpower supply device 210 and/or the secondpower supply device 220 provides the first power and/or the second power to afirst device 910 of the drone through thefirst electrode device 250, and the thirdpower supply device 230 and/or the fourthpower supply device 240 provides the third power and/or the fourth power to asecond device 920 of the drone through thesecond electrode device 260. Alternatively, more specifically, the firstpower providing device 210 and/or the secondpower providing device 220 provides the first power and/or the second power to thefirst device 910 through thefirst electrode device 250 and thethird electrode device 270, and the thirdpower providing device 230 and/or the fourthpower providing device 240 provides the third power and/or the fourth power to thesecond device 920 through thesecond electrode device 260 and thethird electrode device 270.
In the embodiment shown in fig. 2, the firstpower monitoring device 280 monitors (or detects) the first voltage information and the first current information of the firstpower providing device 210, and calculates the first power information according to the first voltage information and the first current information, and the firstpower monitoring device 280 then provides the calculated first power information to the power providingmanagement system 254. The secondpower monitoring device 290 monitors (or detects) the second voltage information and the second current information of the secondpower providing device 220, and calculates the second power information according to the second voltage information and the second current information, and the secondpower monitoring device 290 then provides the calculated second power information to the power providingmanagement system 254.
In one embodiment, the firstpower monitoring device 280 calculates first power information according to the first voltage information, the first current information and the current temperature, and the secondpower monitoring device 290 calculates second power information according to the second voltage information, the second current information and the current temperature. In one embodiment, the firstpower monitoring device 280 calculates the first power information according to the first voltage information, the first current information, the current temperature and the number of times of using the firstpower providing device 210, and the secondpower monitoring device 290 calculates the second power information according to the second voltage information, the second current information, the current temperature and the number of times of using the secondpower providing device 220.
In the embodiment shown in fig. 2, the powersupply management system 254 may control thefirst switch device 252A and thesecond switch device 252B according to the first power information associated with the firstpower providing device 210 and the second power information associated with the secondpower providing device 220. In one embodiment, thefirst power supply 210 is the primary power source. Therefore, when the firstpower supply device 210 has enough power, thefirst device 910 of the drone uses the power of the firstpower supply device 210, and the powersupply management system 254 controls thefirst switch device 252A and thesecond switch device 252B such that thefirst switch device 252A is turned on and thesecond switch device 252B is turned off and turned off. When the firstpower supply device 210 is low in power, thefirst device 910 of the drone uses the power of the secondpower supply device 220, and at this time, the powersupply management system 254 controls thefirst switch device 252A and thesecond switch device 252B, so that thefirst switch device 252A is turned off and is not turned on, and thesecond switch device 252B is turned on and is turned on.
In an embodiment, the powersupply management system 254 provides at least one of the first power information, the first voltage information, the first current information, the second power information, the second voltage information, and the second current information to a flight control device (not shown) of the drone, so that the flight control device generates the first internal resistance curvature information and/or the second internal resistance curvature information, and the flight control device of the drone records (or stores) the first internal resistance curvature information and/or the second internal resistance curvature information. Wherein the first internal resistance curvature information indicates an internal resistance curvature of the first power providing device, and the second internal resistance curvature information indicates an internal resistance curvature of the second power providing device. In an embodiment, the first internal resistance curvature information and/or the second internal resistance curvature information is generated by the powersupply management system 254 according to at least one of the first power information, the first voltage information, the first current information, the second power information, the second voltage information, and the second current information, and the powersupply management system 254 then provides the first internal resistance curvature information and/or the second internal resistance curvature information to the flight control device of the drone so as to record (or store) the first internal resistance curvature information and/or the second internal resistance curvature information by the flight control device. In one embodiment, the powersupply management system 254 generates the first internal resistance curvature information according to at least the first power information, the first voltage information, and the first current information, and generates the second internal resistance curvature information according to at least the second power information, the second voltage information, and the second current information.
In one embodiment, the powersupply management system 254 generates the first internal resistance curvature information based on at least the first voltage information and the first current information, and generates the second internal resistance curvature information based on at least the second voltage information and the second current information. In an embodiment, the flight control device calculates first internal resistance curvature information according to at least the first electric quantity information, the first voltage information, and the first current information, and calculates second internal resistance curvature information according to at least the second electric quantity information, the second voltage information, and the second current information. In an embodiment, the flight control device calculates first internal resistance curvature information according to at least the first voltage information and the first current information, and calculates second internal resistance curvature information according to at least the second voltage information and the second current information.
In one embodiment, the firstpower supply device 210 stores a first internal resistance curvature record therein, and the secondpower supply device 220 stores a second internal resistance curvature record therein. The unmanned aerial vehicle can estimate the electric quantity of the first electric energy providing device and/or the second electric energy providing device according to the first internal resistance curvature information and/or the second internal resistance curvature information and/or the first internal resistance curvature record information and/or the second internal resistance curvature record information. In one embodiment, the first internal resistance curvature record information indicates the internal resistance curvature of the firstpower supply device 210 when it was last used, and the second internal resistance curvature record information indicates the internal resistance curvature of the secondpower supply device 220 when it was last used.
In an embodiment, the drone using the dronepower management system 200 determines to use the first internal resistance curvature information or the first internal resistance curvature record information for power estimation of the firstpower providing device 210 according to the first internal resistance curvature information, the first internal resistance curvature record information, and the first voltage information and the first current information currently measured by the firstpower monitoring device 280. For example, when the powersupply management system 254 calculates the first voltage information and the first current information and finds that the first internal resistance curvature information is closer to the current actual internal resistance curvature of the firstpower providing device 210, the power estimation of the firstpower providing device 210 will be performed according to the first internal resistance curvature information. If the powersupply management system 254 calculates the first voltage information and the first current information, and finds that the first internal resistance curvature record information is closer to the current actual internal resistance curvature of the firstpower supply device 210, the power estimation of the firstpower supply device 210 is performed according to the first internal resistance curvature record information.
In an embodiment, the drone using the dronepower management system 200 determines to use the second internal resistance curvature information or the second internal resistance curvature record information for the power estimation of the firstpower providing device 210 according to the second internal resistance curvature information, the second internal resistance curvature record information, and the second voltage information and the second current information currently measured by the secondpower monitoring device 290. For example, when the second internal resistance curvature information is found to be closer to the current actual internal resistance curvature of the secondpower providing device 220 after the power providingmanagement system 254 calculates the second voltage information and the second current information, the power estimation of the secondpower providing device 220 will be performed according to the second internal resistance curvature information. If the electric energy providingmanagement system 254 calculates the second voltage information and the second current information, and finds that the second internal resistance curvature record information is closer to the current actual internal resistance curvature of the second electricenergy providing device 220, the electric energy estimation of the second electricenergy providing device 220 will be performed by using the second internal resistance curvature record information.
In one embodiment, the dronepower management system 200 may calculate first internal resistance information associated with the firstpower providing device 210 and may generate prediction information based on the first internal resistance information, the prediction information indicating whether the first internal resistance information is about to reach an internal resistance threshold. In an embodiment, the unmanned aerial vehiclepower management system 200 may calculate second internal resistance information associated with the secondpower providing device 220, and may generate prediction information according to the second internal resistance information, where the prediction information indicates whether the second internal resistance information is about to reach an internal resistance threshold. In one embodiment, the dronepower management system 200 may calculate a first internal resistance information associated with the firstpower providing device 210 and calculate a second internal resistance information associated with the secondpower providing device 220. The unmanned aerial vehiclepower management system 200 may further generate a prediction information according to the first internal resistance information and/or the second internal resistance information. Wherein the prediction information indicates whether the first internal resistance information and/or the second internal resistance information is about to reach an internal resistance threshold.
In an embodiment, the dronepower management system 200 may calculate a first internal resistance information associated with the firstpower providing device 210, and the dronepower management system 200 may generate the alert information when the first internal resistance information reaches an internal resistance threshold. Thereby informing the user that the firstpower supply device 210 should be serviced or replaced. In an embodiment, the dronepower management system 200 may calculate second internal resistance information associated with the secondpower providing device 220, and the dronepower management system 200 may generate the warning information when the second internal resistance information reaches the internal resistance threshold. Thereby informing the user that the secondpower supply device 220 should be maintained or replaced. In one embodiment, the dronepower management system 200 may calculate a first internal resistance information associated with the firstpower providing device 210 and a second internal resistance information associated with the secondpower providing device 220, and the dronepower management system 200 may generate the alert information when the first internal resistance information or the second internal resistance information reaches the internal resistance threshold. Thereby informing the user that the firstpower supply device 210 or the secondpower supply device 220 should be serviced or replaced. In one embodiment, the internal resistance threshold is a value predetermined by a user.
Referring to fig. 3A and fig. 3B, a circuit equivalent diagram of the power supply device and a power curve diagram of the power supply device in an embodiment are respectively illustrated. As shown in fig. 3A, since theinternal resistance 320 of the power supply consumes a part of the voltage, theusable voltage 310 of the power supply is as follows:
OCV＝V–I*RBAT
wherein the ocv (open circuit voltage) is a usable voltage of the electric power supply device, V is a maximum voltage of the electric power supply device, RBATI is the equivalent internal resistance of the power supply device, I is the current flowing through the power supply device. It should be understood thatThe maximum voltage and the usable voltage of the power supply device both gradually decrease with time or the number of times of use. Themaximum voltage curve 330 in fig. 3B shows that the maximum voltage of the power supply device decreases with the increase of the number of uses, and theusable voltage curve 340 shows that the usable voltage of the power supply device decreases with the increase of the number of uses. The difference between themaximum voltage curve 330 and theusable voltage curve 340 is a portion of the voltage consumed by the internal resistance of the power providing device. In the embodiment shown in fig. 3B, when the internal resistance of the power supply device reaches the internal resistance threshold (i.e., at theEDV line 350 in fig. 3B), the maximum voltage and the usable voltage of the power supply device will rapidly drop.
The power management system of the unmanned aerial vehicle of the present invention has been described with reference to the above description and drawings. It is to be understood that the embodiments of the present invention are for illustration purposes only and that various changes may be made without departing from the spirit and scope of the invention as defined by the appended claims. Therefore, it is intended that the present invention not be limited to the particular embodiments disclosed, but that the true scope and spirit of the invention be indicated by the following claims.
Claims (11)
1. An unmanned aerial vehicle power management system, comprising:
a first power supply having a first power;
a second power supply having a second power;
the first electrode device is connected with the first electric energy supply device and the second electric energy supply device;
a third power supply having a third power;
a fourth power supply having a fourth power; and
the second electrode device is connected with the third electric energy supply device and the fourth electric energy supply device;
wherein the first and/or second electrical energy providing devices provide the first and/or second electrical energy to the first device of the drone through the first electrode device;
wherein the third electrical energy providing device and/or the fourth electrical energy providing device provides the third electrical energy and/or the fourth electrical energy to the second device of the drone through the second electrode device.
2. The unmanned aerial vehicle power management system of claim 1, further comprising:
a third electrode device connected to the first, second, third and fourth power supply devices;
wherein the first and/or second power supply means provides the first and/or second power to the first means via the first and third electrode means;
wherein the third power supply device and/or the fourth power supply device provides the third power and/or the fourth power to the second device through the second electrode device and the third electrode device.
3. The unmanned aerial vehicle power management system of claim 1, wherein the first, second, third, and fourth power supplies are batteries.
4. The unmanned aerial vehicle power management system of claim 1, wherein the first power supply device is a power generation device capable of generating power continuously, and the second power supply device, the third power supply device and the fourth power supply device are batteries.
5. The drone power management system of claim 1, wherein the first electrode device includes:
the uninterruptible power system is provided with a first switch device and a second switch device, wherein the first switch device is connected with the first power supply device, and the second switch device is connected with the second power supply device; and
the power supply management system is connected with the uninterruptible power system and controls the first switch device and the second switch device according to first power information related to the first power supply device and second power information related to the second power supply device.
6. The unmanned aerial vehicle power management system of claim 5, further comprising:
the first electric quantity monitoring device is connected with the first electric energy providing device and the electric energy providing management system and provides the first electric quantity information to the electric energy providing management system; and
and the second electric quantity monitoring device is connected with the second electric energy providing device and the electric energy providing management system and provides the second electric quantity information to the electric energy providing management system.
7. The drone power management system of claim 6, wherein the first power information is calculated by the first power monitoring device based on first voltage information and first current information associated with the first power providing device; wherein the second power information is calculated by the second power monitoring device according to the second voltage information and the second current information associated with the second power providing device.
8. The drone power management system of claim 7, wherein the power supply management system provides at least one of the first power information, the first voltage information, the first current information, the second power information, the second voltage information, and the second current information to a flight control device of the drone to generate and record first and/or second internal resistance curvature information, wherein the first internal resistance curvature information is associated with the first power supply device and the second internal resistance curvature information is associated with the second power supply device.
9. The unmanned aerial vehicle power management system of claim 8, wherein the first power supply device has a first internal resistance curvature record information, and the second power supply device has a second internal resistance curvature record information; and the unmanned aerial vehicle estimates the electric quantity of the first electric energy providing device and/or the second electric energy providing device according to the first internal resistance curvature information and/or the second internal resistance curvature information and/or the first internal resistance curvature recording information and/or the second internal resistance curvature recording information.
10. The drone power management system of claim 1, wherein the drone power management system calculates first internal resistance information associated with the first power providing device and/or second internal resistance information associated with the second power providing device, the drone power management system generating prediction information based on the first internal resistance information and/or the second internal resistance information; wherein the prediction information indicates whether the first internal resistance information and/or the second internal resistance information is about to reach an internal resistance threshold.
11. The drone power management system of claim 1, wherein the drone power management system calculates first internal resistance information associated with the first power providing device and/or second internal resistance information associated with the second power providing device, the drone power management system generating alert information when the first internal resistance information or the second internal resistance information reaches an internal resistance threshold.
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| TW109108809ATWI724824B (en) | 2020-03-17 | 2020-03-17 | UAV power management system |
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| TW202137666A (en) | 2021-10-01 |
| TWI724824B (en) | 2021-04-11 |
| CN113410877B (en) | 2025-08-15 |
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