Disclosure of Invention
In order to solve the above-mentioned problems, an idea of the present invention is to provide an unmanned aerial vehicle power management system that can manage a plurality of power supply devices according to a plurality of power information.
The unmanned aerial vehicle power management system comprises a first power supply device, a second power supply device, a first electrode device, a third power supply device, a fourth power supply device and a second electrode device, wherein the first power supply device is provided with first power, the second power supply device is provided with second power, the first electrode device is connected with the first power supply device and the second power supply device, the third power supply device is provided with third power, the fourth power supply device is provided with fourth power, the second electrode device is connected with the third power supply device and the fourth power supply device, the first power supply device and/or the second power supply device is/are used for providing the first power and/or the second power to the first device of the unmanned aerial vehicle through the first electrode device, and the third power supply device and/or the fourth power supply device is/are used for providing the third power and/or the fourth power to the second device of the unmanned aerial vehicle through the second electrode device.
In a preferred embodiment of the present invention, the unmanned aerial vehicle power management system further comprises a third electrode device connecting the first power supply device, the second power supply device, the third power supply device and the fourth power supply device, wherein the first power supply device and/or the second power supply device provide the first power and/or the second power to the first device through the first electrode device and the third electrode device, and wherein the third power supply device and/or the fourth power supply device provide 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 invention, the first electrode device comprises an uninterruptible power system, a power supply management system and a power supply management system, wherein the uninterruptible power system is provided with a first switch device and a second switch device, the first switch device is connected with the first power supply device, 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 electric quantity information related to the first power supply device and second electric quantity information related to the second power supply device.
In a preferred embodiment of the present invention, the unmanned aerial vehicle power management system further comprises a first power monitoring device connected with the first power providing device and the power providing management system and providing the first power information to the power providing management system, and a second power monitoring device connected with the second power providing device and the power providing management system and providing the second power information to the power 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, and the second power information is calculated by the second power monitoring device according to second voltage information and 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 the flight control device of the unmanned aerial vehicle to generate and record first internal resistance curvature information 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.
In a preferred embodiment of the present invention, 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, wherein the unmanned aerial vehicle performs the power estimation of the first power supply device and/or the second power supply 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 a preferred embodiment of the present invention, the unmanned aerial vehicle power management system calculates first internal resistance information associated with the first power supply device and/or second internal resistance information associated with the second power supply device, and 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 unmanned aerial vehicle power management system calculates first internal resistance information associated with the first power supply device and/or second internal resistance information associated with the second power supply device, and generates warning information 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 invention will become more apparent from the following detailed description of non-limiting embodiments of the invention, taken in conjunction with 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 unmanned aerial vehicle power management system of the present invention.
Fig. 3A is a circuit equivalent diagram of the power supply device according to an embodiment.
Fig. 3B is a graph showing an electric power curve of the electric power supply device according to an embodiment.
Reference numerals illustrate:
100. Unmanned aerial vehicle power management system
110. First electric energy supply device
120. Second electric energy supply device
130. Third electric energy supply device
140. Fourth power supply device
150. First electrode device
160. Second electrode device
170. Third electrode device
200. Unmanned aerial vehicle power management system
210. First electric energy supply device
220. Second electric energy supply device
230. Third electric energy supply device
240. Fourth power supply device
250. First electrode device
252. Uninterruptible power supply system
252A first switching device
252B second switching device
254. Electric energy supply management system
260. Second electrode device
270. Third electrode device
280. First electric quantity monitoring device
290. Second electric quantity monitoring device
310. Can use voltage
320. Internal resistance of
330. Maximum voltage curve
340. Voltage curves can be used
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 present invention is illustrated. As shown in the embodiment of fig. 1, the unmanned aerial vehicle power management system 100 applied to an unmanned aerial vehicle includes a first power supply device 110, a second power supply device 120, a third power supply device 130, a fourth power supply device 140, a first electrode device 150, a second electrode device 160, and a third electrode device 170. The first electrode device 150 connects the first power supply device 110 and the second power supply device 120. The second electrode device 160 connects the third power supply device 130 and the fourth power supply device 140. The third electrode device 170 connects the first power supply device 110, the second power supply device 120, the third power supply device 130, and the fourth power supply device 140. Wherein the first power supply device 110 has a first power, the second power supply device 120 has a second power, the third power supply device 130 has a third power, and the fourth power supply device 140 has a fourth power.
In one embodiment, the first electrode device 150 connects the positive electrode of the first power supply device 110 with the positive electrode of the second power supply device 120. The second electrode device 160 connects the positive electrode of the third power supply device 130 with the positive electrode of the fourth power supply device 140. The third electrode device 170 connects the negative electrode of the first power supply device 110, the negative electrode of the second power supply device 120, the negative electrode of the third power supply device 130, and the negative electrode of the fourth power supply device 140. Thus, even if the positive electrode of one of the first power supply device 110 or the second power supply device 120 is broken or damaged, the positive electrode of the other is still connected to the first electrode device 150 and operates normally, which is a fail-safe function. Similarly, even if the positive electrode of one of the third power supply device 130 or the fourth power supply device 140 is broken or damaged, the positive electrode of the other is still connected to the second electrode device 160 and operates normally, so as to achieve the fail-safe function. And the same is true. Even if the negative electrode of one of the first, second, third and fourth power supply devices 110, 120, 130 and 140 is broken or damaged, the negative electrode of the other power supply device is still connected to the third electrode device 170 and operates normally, so as to achieve the fail-safe function.
In the embodiment shown in fig. 1, the first power supply device 110 and/or the second power supply device 120 pass through the first electrode device 150 to supply the first power and/or the second power to a first device (not shown) of the unmanned aerial vehicle, and the third power supply device 130 and/or the fourth power supply device 140 pass through the second electrode device 160 to supply the third power and/or the fourth power to a second device (not shown) of the unmanned aerial vehicle. Or more specifically, the first and/or second power supply devices 110 and 120 pass through the first and third electrode devices 150 and 170 to supply the first and/or second power to the first device, and the third and/or fourth power supply devices 130 and 140 pass through the second and third electrode devices 160 and 170 to supply the third and/or fourth power to the second device.
In an embodiment, the first device may be at least one of a flight control system, a servo motor and a wireless control device of the unmanned aerial vehicle, and the second device may be at least one of a flight control system, a servo motor and a wireless control device of the unmanned aerial vehicle. In different embodiments, the first device and the second device may be the same device or different devices. In one embodiment, the first power providing device 110, the second power providing device 120, the third power providing device 130 and the fourth power providing device 140 are all batteries. In another embodiment, the first power supply device 110 is a power generation device capable of continuously generating power, and the second power supply device 120, the third power supply device 130 and the fourth power supply device 140 are all batteries. In one embodiment, the first electrode device 150 and the second electrode device 160 are both circuit board devices.
Referring to fig. 2, a system architecture diagram of an embodiment of the unmanned aerial vehicle power management system according to the present invention is illustrated. As shown in the embodiment of fig. 2, the unmanned aerial vehicle power management system 200 applied to the unmanned aerial vehicle includes a first power supply device 210, a second power supply device 220, a third power supply device 230, a fourth power supply device 240, a first electrode device 250, a second electrode device 260, a third electrode device 270, a first power monitoring device 280, and a second power monitoring device 290. Wherein the first electrode device 250 includes an uninterruptible power supply system 252 and an electrical energy supply management system 254. Uninterruptible power system 252 and further includes a first switching device 252A and a second switching device 252B. Wherein the first power supply device 210 has a first power, the second power supply device 220 has a second power, the third power supply device 230 has a third power, and the fourth power supply device 140 has a fourth power.
The second electrode device 260 connects the third power supply device 230 with the fourth power supply device 240. The third electrode device 270 connects the first power supply device 210, the second power supply device 220, the third power supply device 230, and the fourth power supply device 240. The first switching device 252A of the uninterruptible power system 252 is connected to the first power supply 210, and the second switching device 252B of the uninterruptible power system 252 is connected to the second power supply 220. The power supply management system 254 is coupled to the uninterruptible power system 252. The first power monitoring device 280 connects the first power providing device 210 with the power providing management system 254, and the second power monitoring device 290 connects the second power providing device 220 with the power providing management system 254.
In the embodiment shown in fig. 2, the first power supply device 210 and/or the second power supply device 220 pass through the first electrode device 250 to supply the first power and/or the second power to a first device 910 of the unmanned aerial vehicle, and the third power supply device 230 and/or the fourth power supply device 240 pass through the second electrode device 260 to supply the third power and/or the fourth power to a second device 920 of the unmanned aerial vehicle. Or more specifically, the first power supply device 210 and/or the second power supply device 220 pass through the first electrode device 250 and the third electrode device 270 to supply the first power and/or the second power to the first device 910, and the third power supply device 230 and/or the fourth power supply device 240 pass through the second electrode device 260 and the third electrode device 270 to supply the third power and/or the fourth power to the second device 920.
In the embodiment shown in fig. 2, the first power monitoring device 280 monitors (or detects) the first voltage information and the first current information of the first power providing device 210, and calculates the first power information according to the first voltage information and the first current information, and the first power monitoring device 280 then provides the calculated first power information to the power providing management system 254. The second power monitoring device 290 monitors (or detects) the second voltage information and the second current information of the second power providing device 220, and calculates the second power information according to the second voltage information and the second current information, and the second power monitoring device 290 then provides the calculated second power information to the power providing management system 254.
In one embodiment, the first power monitoring device 280 calculates the first power information according to the first voltage information, the first current information and the current temperature, and the second power monitoring device 290 calculates the second power information according to the second voltage information, the second current information and the current temperature. In one embodiment, the first power monitor 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 use of the first power supply 210, and the second power monitor 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 use of the second power supply 220.
In the embodiment shown in fig. 2, the power providing management system 254 may control the first switching device 252A and the second switching device 252B according to the first power information associated with the first power providing device 210 and the second power information associated with the second power providing device 220. In one embodiment, the first power supply 210 is a primary power source. Therefore, when the power of the first power supply device 210 is sufficient, the first device 910 of the unmanned aerial vehicle uses the power of the first power supply device 210, and the power supply management system 254 controls the first switch device 252A and the second switch device 252B such that the first switch device 252A is turned on and turned off and the second switch device 252B is turned off. In the case that the power of the first power supply device 210 is insufficient, the first device 910 of the unmanned aerial vehicle uses the power of the second power supply device 220, and the power supply management system 254 controls the first switch device 252A and the second switch device 252B such that the first switch device 252A is turned off and turned on, and the second switch device 252B is turned on.
In one embodiment, the power providing 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 unmanned aerial vehicle, 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 unmanned aerial vehicle 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 supply device, and the second internal resistance curvature information indicates an internal resistance curvature of the second power supply device. In one embodiment, the electric energy providing management system 254 generates the first internal resistance curvature information and/or the second internal resistance curvature information according to at least one of the first electric quantity information, the first voltage information, the first current information, the second electric quantity information, the second voltage information and the second current information, and the electric energy providing 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 unmanned aerial vehicle, so that the flight control device records (or stores) the first internal resistance curvature information and/or the second internal resistance curvature information. In one embodiment, the power providing 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 power providing 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 one 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 one 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 first power providing device 210 stores therein a first internal resistance curvature record information, and the second power providing device 220 stores therein a second internal resistance curvature record information. 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 an internal resistance curvature of the first power supply device 210 when it was last used, and the second internal resistance curvature record information indicates an internal resistance curvature of the second power supply device 220 when it was last used.
In an embodiment, the unmanned aerial vehicle using the unmanned aerial vehicle power management system 200 determines to use the first internal resistance curvature information or the first internal resistance curvature recording information to perform the power estimation of the first power supply device 210 according to the first internal resistance curvature information, the first internal resistance curvature recording information, and the first voltage information and the first current information currently measured by the first power monitoring device 280. For example, when the power providing 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 first power providing device 210, the power estimation of the first power providing device 210 is performed according to the first internal resistance curvature information. If the power providing 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 first power providing device 210, then the power of the first power providing device 210 is estimated according to the first internal resistance curvature record information.
In an embodiment, the unmanned aerial vehicle using the unmanned aerial vehicle power management system 200 determines to use the second internal resistance curvature information or the second internal resistance curvature recording information to perform the power estimation of the first power supply device 210 according to the second internal resistance curvature information, the second internal resistance curvature recording information, and the second voltage information and the second current information currently measured by the second power monitoring device 290. For example, when the power providing management system 254 calculates the second voltage information and the second current information and finds that the second internal resistance curvature information is closer to the current actual internal resistance curvature of the second power providing device 220, the power estimation of the second power providing device 220 is performed according to the second internal resistance curvature information. If the electric power providing management 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 electric power providing device 220, then the electric power estimation of the second electric power providing device 220 is performed according to the second internal resistance curvature record information.
In one embodiment, the unmanned aerial vehicle power management system 200 may calculate the first internal resistance information associated with the first power supply device 210, and may generate the prediction information according to the first internal resistance information, where the prediction information indicates whether the first internal resistance information is about to reach an internal resistance threshold. In one embodiment, the unmanned aerial vehicle power management system 200 may calculate the second internal resistance information associated with the second power supply device 220, and may generate the prediction information indicating whether the second internal resistance information is about to reach an internal resistance threshold according to the second internal resistance information. In one embodiment, the unmanned aerial vehicle power management system 200 may calculate a first internal resistance information associated with the first power supply device 210 and calculate a second internal resistance information associated with the second power supply device 220. The unmanned aerial vehicle power management system 200 may further generate a prediction message based on the first internal resistance message and/or the second internal resistance message. 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 one embodiment, the unmanned aerial vehicle power management system 200 may calculate the first internal resistance information associated with the first power supply device 210, and the unmanned aerial vehicle power management system 200 may generate the alert information when the first internal resistance information reaches the internal resistance threshold. Thereby informing the user that the first power supply device 210 should be serviced or replaced. In one embodiment, the unmanned aerial vehicle power management system 200 may calculate the second internal resistance information associated with the second power supply device 220, and the unmanned aerial vehicle power management system 200 may generate the alert information when the second internal resistance information reaches the internal resistance threshold. Thereby informing the user that the second power supply 220 should be maintained or replaced. In one embodiment, the unmanned aerial vehicle power management system 200 may calculate first internal resistance information associated with the first power supply device 210 and second internal resistance information associated with the second power supply device 220, and the unmanned aerial vehicle power management system 200 may generate the warning information when the first internal resistance information or the second internal resistance information reaches the internal resistance threshold. Thereby informing the user that the first power supply device 210 or the second power supply device 220 should be maintained or replaced. In one embodiment, the internal resistance threshold is a value preset by a user.
Referring to fig. 3A and 3B, a circuit equivalent diagram of the power supply device and a power curve diagram of the power supply device are illustrated in an embodiment. As shown in the embodiment of fig. 3A, since the internal resistance 320 of the power supply device consumes a part of the voltage, the usable voltage 310 of the power supply device will have the following formula:
OCV=V–I*RBAT
Wherein OCV (open circuit voltage) is the usable voltage of the power supply device, V is the maximum voltage of the power supply device, RBAT is the equivalent internal resistance of the power supply device, and I is the current flowing through the power supply device. It should be appreciated that the maximum voltage and the usable voltage of the power supply device may decrease gradually with time or with the number of uses. The maximum 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 the usable 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 the maximum voltage curve 330 and the usable voltage curve 340 is the partial voltage consumed by the internal resistance of the power supply device. In the embodiment shown in fig. 3B, when the internal resistance of the power providing device reaches the internal resistance threshold (i.e., at the EDV line 350 in fig. 3B), the maximum voltage and the usable voltage of the power providing device will rapidly slip.
Thus, the unmanned aerial vehicle power management system of the present invention has been described with reference to the above description and drawings. It should be understood that the various embodiments of the invention are illustrative only and that various changes may be made without departing from the spirit and scope of the invention as defined by the following claims. Therefore, the specific embodiments described in this specification are not intended to limit the invention, the true scope and spirit of which is disclosed in the claims.