power supply

Abstract

To provide a power supply device that can maintain the balance of the amount of charge among a plurality of batteries, while reducing complication of a control system compared to a prior art.SOLUTION: A power supply device comprises power generators, driving sources, a plurality of power supply lines, a plurality of batteries, a current value calculation unit 11, a battery required power calculation unit 12, and a power add-up unit 13. The current value calculation unit 11 calculates the C rates CR1, CR2, CR3, and CR4 of the batteries based on the amount of charge of the batteries. The battery required power calculation unit 12 calculates a power required for the batteries P or Q based on the calculated C rates CR1, CR2, CR3, and CR4 and the capacities of the batteries. The power add-up unit 13 adds up the power required for the batteries P or Q and power required for current consumers. The control unit 9 controls the driving sources to cause the power generators to generate the power calculated by the power add-up unit 13.SELECTED DRAWING: Figure 3

Description

[Technical Field]

[0001] The present invention relates to a power supply device. [Background technology]

[0002] Conventionally, power supply devices for aircraft and the like have been known that include a drive source, a generator, multiple batteries, and a motor driven by the power of the generator or the batteries. For these power supply devices, various techniques have been proposed for controlling the charge amounts of the multiple batteries so as to balance them.

[0003] For example, Patent Document 1 discloses the configuration of a power supply device equipped with a priority battery current command determiner that detects the charge states of multiple batteries and determines the priority of power supply to each battery based on the detected charge states. The priority battery current command determiner prioritizes control of any two command values ​​from among the multiple batteries: the current command value for the high-voltage battery, the current command value for the low-voltage battery, and the torque command value for the torque required to drive the motor, and controls the remaining one subordinately. According to the technology described in Patent Document 1, this makes it possible to balance the charge amounts of each battery and improve battery performance. [Prior art documents] [Patent documents]

[0004] [Patent Document 1] Japanese Patent Application Laid-Open No. 2000-324871 Summary of the Invention [Problem to be solved by the invention]

[0005] However, in the technology described in Patent Document 1, power allocation to each battery is determined based on the charge level of each battery. In other words, it is necessary to calculate the power required for each battery and then determine the priority, which may complicate the control system configuration. In addition, a device is required to transfer power between multiple batteries, which may complicate the control device and increase costs. Furthermore, precise control is required to keep the charge level of each battery within a predetermined value, which further complicates the control. This may result in a complex and expensive control device.

[0006] SUMMARY OF THE INVENTION It is therefore an object of the present invention to provide a power supply device that can balance the charge amounts of a plurality of batteries while suppressing the complexity of the control system compared to conventional techniques. [Means for solving the problem]

[0007] In order to solve the above problem, a power supply device according to the invention of claim 1 (for example, power supply device 1 in the embodiments) includes a generator (for example, generator 3 in the embodiments), a drive source (for example, drive source 2 in the embodiments) that drives the generator, a plurality of power supply lines (for example, power supply line 4 in the embodiments) that supply power generated by the generator to a plurality of electric loads, a plurality of batteries (for example, battery 5 in the embodiments) that are connected to the respective power supply lines upstream of the electric loads in the power supply direction, and a current value (for example, C rates CR1, CR2, CR3 in the embodiments) that can be passed through each of the batteries based on the charge amount of each of the batteries. a battery required power calculation unit (for example, battery required power calculation unit 12 in the embodiments) that calculates the required power of the battery (for example, battery required power P, Q in the embodiments) based on the current value calculated by the current value calculation unit and the capacity of the battery (for example, battery capacity BA in the embodiments); and a power totalizing unit (for example, power totalizing unit 13 in the embodiments) that totals the power calculated by the battery required power calculation unit and the power required by the electric load, and the driving source is controlled so that the generator generates the power calculated by the power totalizing unit.

[0008] The power supply device according to the invention described in claim 2 further includes an operating state detection unit (e.g., operating state detection unit 17 in the embodiment) that detects the operating states of the plurality of power supply lines, and is characterized in that the amount of power generated by the generator is controlled based on the operating states of the power supply lines detected by the operating state detection unit.

[0009] Furthermore, the power supply device of the invention described in claim 3 is characterized in that the power supply device is a power source for an electrically propelled aircraft (e.g., aircraft 10 in the embodiment), and the electrical load is an electric motor (e.g., electric motor 7 in the embodiment) that rotates a propeller (e.g., propeller 8 in the embodiment) of the aircraft. [Effects of the Invention]

[0010] According to a first aspect of the present invention, the power supply device generates power from a generator and supplies it to multiple batteries via power supply lines. The power supply device includes a current value calculation unit that calculates a current value that can be supplied to the batteries, a battery-required power calculation unit that calculates required power based on the current value calculated by the current value calculation unit and the battery capacity, and a power totalization unit that totals the power and the power required by the electrical loads. The drive source is controlled so that the generator generates the power calculated by the power totalization unit. Therefore, the power to be generated by the generator (generated power) can be easily calculated based on the current value that can be supplied to the batteries and the battery capacity. In the power supply device, the power generated by the generator is distributed to each power supply line according to the potential difference between the batteries. Therefore, the multiple batteries can be charged so that their charge levels are equalized regardless of the potential difference between the batteries. Furthermore, even if the outputs (power consumption) of the electrical loads on each power supply line are different, the battery with the lowest charge level can be charged first. This improves the output of the electrical load connected to the same power supply line as the battery with the lowest charge level. As a result, the outputs of the power supply lines can be balanced, and the variations in the outputs of the electrical loads can be corrected. In other words, the charge amounts of the batteries can be balanced regardless of the outputs of the electrical loads. This allows for stable control. Furthermore, compared to conventional technology that controls charging and discharging for each battery, there is no need for a control device to manage (control) the charging and discharging of each battery. This reduces the cost of the power supply device. Therefore, multiple batteries can be charged evenly with a simpler and cheaper configuration than conventional technology. Therefore, it is possible to provide a power supply device that can balance the charge amounts of a plurality of batteries while suppressing the complexity of the control system compared to the prior art. Since batteries with low charge levels are charged first, over-discharge of low-charged batteries can be prevented. Also, power supply to batteries with relatively high charge levels is restricted, so over-charging of high-charged batteries can be prevented. This allows batteries to be used within their optimum operating range and battery degradation can be suppressed. Furthermore, since no power is exchanged between multiple batteries, the complexity of the control system can be reduced compared to conventional technologies in which power is exchanged between batteries. Also, by controlling the charging and discharging of batteries using only power from the generator without exchanging power between batteries, the efficiency of charging and discharging can be improved.

[0011] According to a power supply device of claim 2 of the present invention, the power supply device further includes an operation state detection unit that detects the operation state of the power supply line, and the power generated by the generator is controlled based on the operation state of the power supply line. As a result, if, for example, a malfunction such as a failure occurs in one of the batteries, it is possible to suppress the power supply to the malfunctioning power supply line. Furthermore, by performing control such as subtracting the amount of power corresponding to the power supply stop from the generated power, it is possible to suppress overcharging of the normal power supply line. Therefore, it is possible to provide a highly versatile power supply device that can deal with accidents and malfunctions such as malfunctions.

[0012] According to the power supply device of claim 3 of the present invention, the power supply device is used as a power source for an electrically propelled aircraft. In an aircraft that flies by rotating multiple propellers, the power consumed by each power supply line tends to vary greatly due to factors such as weather and the aircraft's attitude. Therefore, the power supply device described above is particularly suitable for use in aircraft in which the power required by the electrical load (electric motor) varies greatly from one power supply line to another. In other words, it is possible to supply power according to the power consumption of each power supply line, including the battery. Furthermore, since the power from the generator is distributed according to the power demands of each power supply line, the flying object can be easily controlled. [Brief explanation of the drawings]

[0013] [Figure 1] 1 is an external view of an aircraft equipped with a power supply device according to an embodiment. [Figure 2] 1 is a schematic configuration diagram of a power supply device according to an embodiment. [Figure 3] FIG. 2 is a control block diagram of the power supply device according to the embodiment. [Figure 4] 4 is a flowchart showing a control flow in the power supply device. DETAILED DESCRIPTION OF THE INVENTION

[0014] Hereinafter, an embodiment of the present invention will be described with reference to the drawings.

[0015] (Aircraft) FIG. 1 is an external view of an aircraft 10 equipped with a power supply device 1 according to an embodiment. The flying object 10 is, for example, an electrically propelled aircraft that flies by rotating multiple propellers 8. The flying object 10 includes an airframe 19 and a power supply device 1.

[0016] In this embodiment, eight downward-facing propellers (rotors) 51, 52, 53, 54, 55, 56, 57, and 58 and two rearward-facing propulsion propellers 36 and 37 are attached to the airframe 19. Hereinafter, when the multiple propellers 51, 52, 53, 54, 55, 56, 57, and 58 are not to be distinguished from one another, they may be referred to as propellers 8. The propeller 8 is attached to the airframe 19 via an attachment member (not shown). An electric motor 7 (see FIG. 2) is attached to the base (rotation shaft) of the propeller 8. The electric motor 7 drives the propeller 8. The electric motor 7 is, for example, a brushless DC motor. The propeller 8 is a fixed wing with blades that rotate around an axis parallel to the direction of gravity when the aircraft 10 is in a horizontal position.

[0017] The propulsion propellers 36, 37 are attached to the rear of the aircraft 10. The propulsion propellers 36, 37 are attached to the airframe 19 via mounting members (not shown). An electric motor 7 (see FIG. 2) that drives the propulsion propellers 36, 37 is attached to the base (rotation shaft) of the propulsion propellers 36, 37. The propulsion propellers 36, 37 are fixed wings with blades that rotate around an axis that intersects with the direction of gravity (for example, an axis that runs along the fore-and-aft direction of the aircraft 10) when the aircraft 10 is in a horizontal position.

[0018] The propeller 8 and the propulsion propellers 36 and 37 rotate in response to the control signals, causing the aircraft 10 to fly in a desired flight state. The control signals are signals for controlling the aircraft 10 based on an operator's operation or an instruction from automatic piloting. For example, the aircraft 10 flies when the propellers 51, 54, 55, and 58 rotate in a first direction (e.g., clockwise) and the propellers 52, 53, 56, and 57 rotate in a second direction (e.g., counterclockwise).

[0019] FIG. 2 is a schematic diagram of the power supply device 1 according to the embodiment. As shown in Figure 2, the power supply device 1 is mounted on the above-mentioned aircraft 10. The power supply device 1 is used as a power source for the aircraft 10. The power supply device 1 includes a drive source 2, a generator 3, a plurality of power supply lines 4, a plurality of batteries 5, a diode 6, an electric motor 7 (an electric load in the claims), the above-mentioned propeller 8, and a control unit 9 (see Figure 3).

[0020] (Drive source) The driving source 2 is a so-called gas turbine engine. Multiple driving sources 2 (two in this embodiment) are provided. Since the two driving sources 2 have the same configuration, the following description will be given using one driving source 2 as an example. The driving source 2 has a compressor, a turbine, and a rotating shaft connecting the compressor and the turbine (all not shown). The compressor compresses intake air drawn in through a vent hole (not shown) provided on the body of the aircraft 10. The turbine is connected to the compressor and rotates integrally with the compressor. A starter motor is connected to the driving source 2. When the driving source 2 is started, the starter motor is first driven by power from a battery 5 (described later). As a result, the driving source 2 is started by the rotational force transmitted from the starter motor.

[0021] (Generator) The number of generators 3 provided corresponds to the number of driving sources 2 (two in this embodiment). Since the two generators 3 have the same configuration, the following description will be given using one generator 3 as an example. The generator 3 is connected to the driving source 2 via a transmission shaft 28 and a reduction mechanism (not shown). The generator 3 is disposed on the turbine side in the axial direction of the driving source 2. The generator 3 is disposed coaxially with the driving source 2. The generator 3 generates electric power (AC power) when driven by the driving source 2. The AC power generated by the generator 3 is converted to DC power by a converter 29 of a power drive unit (PDU) (not shown) and stored in each battery 5 via a power supply line 4.

[0022] (power supply line) The power supply line 4 is connected to each of the multiple generators 3 via a converter 29. The power supply line 4 supplies the power generated by the generators 3 to each of the multiple electric motors 7 (electrical loads). A plurality of power supply lines 4 (four in this embodiment) are provided. The power generated by each generator 3 is first integrated and then distributed to four power supply lines 21, 22, 23, and 24 at a predetermined ratio in response to a signal from a control unit 9 (see FIG. 3 ). Specifically, the power generated by the generators 3 is supplied preferentially to the battery 5 with the lowest charge level provided on each power supply line 4. For example, by connecting the battery 5 to a diode 6, the battery 5 with the lowest charge level is supplied with more power preferentially. The power supply line 4 includes a first power supply line 21, a second power supply line 22, a third power supply line 23, and a fourth power supply line 24. A diode 6, an electric motor 7, and a predetermined propeller 8 are connected to each power supply line 4.

[0023] The first power supply line 21 is used as the power supply line 4 for driving the first propeller 51, the eighth propeller 58, and the propulsion propeller 36 out of the eight propellers 8. In other words, the first propeller 51, the eighth propeller 58, and the propulsion propeller 36 are driven by the power supplied to the first power supply line 21.

[0024] The second power supply line 22 is used as the power supply line 4 for driving the second propeller 52, the seventh propeller 57, and the propulsion propeller 36 out of the eight propellers 8. In other words, the second propeller 52, the seventh propeller 57, and the propulsion propeller 36 are driven by the power supplied to the second power supply line 22.

[0025] The third power supply line 23 is used as the power supply line 4 for driving the third propeller 53, the sixth propeller 56, and the propulsion propeller 37 out of the eight propellers 8. In other words, the third propeller 53, the sixth propeller 56, and the propulsion propeller 37 are driven by the electric power supplied to the third power supply line 23.

[0026] The fourth power supply line 24 is used as the power supply line 4 for driving the fourth propeller 54, the fifth propeller 55, and the propulsion propeller 37, among the eight propellers 8. In other words, the fourth propeller 54, the fifth propeller 55, and the propulsion propeller 37 are driven by the power supplied to the fourth power supply line 24.

[0027] (battery) One battery 5 is provided for each power supply line 4. A plurality of batteries 5 (four in this embodiment) are provided. Specifically, the batteries 5 include a first battery 31, a second battery 32, a third battery 33, and a fourth battery 34. The first battery 31 is provided on the first power supply line 21. The second battery 32 is provided on the second power supply line 22. The third battery 33 is provided on the third power supply line 23. The fourth battery 34 is provided on the fourth power supply line 24. Each battery 5 is provided upstream of the electric motor 7 in the power supply direction. Each battery 5 stores surplus power generated by the generator 3 that is not supplied to the electric motor 7. On the other hand, when the power generated by the generator 3 is insufficient compared to the output of the electric motor 7, the electric motor 7 is driven by power from the battery 5.

[0028] In this embodiment, the configuration (rating) of each battery 5 is the same. For example, in this embodiment, the capacity and maximum C rate of each of the four batteries are the same. However, because the required power and power consumption differ for each power supply line 4, the charge amount, C rate, power consumption (discharge amount), etc. of each battery 5 at a given moment are not necessarily constant.

[0029] (diode) One diode 6 is provided for each power supply line 4. That is, a plurality of diodes 6 (four in this embodiment) are provided. Each diode 6 is provided on the power supply line 4 upstream of the battery 5 in the power supply direction. The diode 6 uses power from the battery 5 provided on the corresponding power supply line 4. That is, when the voltage of a battery 5 drops, the voltage of the diode 6 provided on the same power supply line 4 as that battery 5 also drops. As a result, power from the generator is supplied preferentially to the power supply line 4 having the diode 6 with the lowest voltage. The diode 6 basically allows power to flow only in one direction, from upstream to downstream of the power supply line 4. In other words, the diode 6 blocks the reverse flow of power from the battery 5. Therefore, while the generator 3 is generating power, power is not exchanged between the plurality of batteries 5.

[0030] On the other hand, when the drive source 2 starts, the diode 6 allows power to flow from downstream to upstream of the power supply line 4 in response to a control signal. This makes it possible to drive a starter motor connected to the drive source 2 using power from the battery 5.

[0031] (electric motor) An electric motor 7 is provided on each power supply line 4. The electric motor 7 is connected to each battery 5 via an inverter 39. Specifically, the first electric motor 41 (more specifically, the first electric motors 41-1 and 41-2) is provided on the first power supply line 21. The second electric motor 42 (more specifically, the second electric motors 42-1 and 42-2) is provided on the second power supply line 22. The third electric motor 43 (more specifically, the third electric motors 43-1 and 43-2) is provided on the third power supply line 23. The fourth electric motor 44 (more specifically, the fourth electric motors 44-1 and 44-2) is provided on the fourth power supply line 24. Thus, in this embodiment, two electric motors 7 are provided on each power supply line 4. Each electric motor 7 is provided downstream of the battery 5 in the power supply direction. Each electric motor 7 rotates a propeller 8 of the flying vehicle 10 using at least one of the electric power from the generator 3 and the electric power from the battery 5. Each electric motor 7 has the same configuration.

[0032] In addition to the above, the electric motor 7 further includes four electric propulsion motors 71, 72, 73, and 74. The electric propulsion motor 71 is provided on the first power supply line 21. The electric propulsion motor 72 is provided on the second power supply line 22. The electric propulsion motor 73 is provided on the third power supply line 23. The electric propulsion motor 74 is provided on the fourth power supply line 24. The electric propulsion motors 71 and 72 rotate the propulsion propeller 36. The electric propulsion motors 73 and 74 rotate the propulsion propeller 37.

[0033] (propeller) The propellers 8 are each connected to a predetermined electric motor 7. The propellers 8 are driven by electric power from a predetermined power supply line 4. As described above, the first propeller 51 and the eighth propeller 58 are connected to the first electric motor 41 and rotate about the rotation axis as the first electric motor 41 is driven. More specifically, the first propeller 51 is connected to the first electric motor 41-1, and the eighth propeller 58 is connected to the first electric motor 41-2. The second propeller 52 and the seventh propeller 57 are connected to the second electric motor 42 and rotate about the rotation axis as the second electric motor 42 is driven. More specifically, the second propeller 52 is connected to the second electric motor 42-1, and the seventh propeller 57 is connected to the second electric motor 42-2. The third propeller 53 and the sixth propeller 56 are connected to the third electric motor 43 and rotate about the rotation axis as the third electric motor 43 is driven. More specifically, the third propeller 53 is connected to the third electric motor 43-1, and the sixth propeller 56 is connected to the third electric motor 43-2. ​​The fourth propeller 54 and the fifth propeller 55 are connected to the fourth electric motor 44, and rotate around the rotation axis as the fourth electric motor 44 is driven. More specifically, the fourth propeller 54 is connected to the fourth electric motor 44-1, and the fifth propeller 55 is connected to the fourth electric motor 44-2.

[0034] The propulsion propeller 36 is connected to the propulsion electric motors 71 and 72. The propulsion propeller 36 rotates in response to the driving of the propulsion electric motors 71 and 72, and generates a horizontal propulsive force. The propulsion propeller 37 is connected to the propulsion electric motors 73 and 74. The propulsion propeller 37 rotates as the propulsion electric motors 73 and 74 are driven, generating a horizontal propulsive force.

[0035] (Control unit) FIG. 3 is a control block diagram of the power supply device 1 according to the embodiment. The control unit 9 controls the output of the gas turbine engine, thereby controlling the power generated by the generator 3. In the following explanation, when an output request is made to each electric motor 7 (propeller 8), the control for determining the power generated by the generator 3 based on the capacity of the battery 5, the C-rate of the battery 5, and the power required by the electric motor 7 will be described. Note that the control unit 9 may also perform various controls, for example, when power generation by the generator 3 is not performed, or when the aircraft 10 is taking off or landing, cruising, etc.

[0036] As shown in FIG. 3, the control unit 9 includes a current value calculation unit 11, a battery required power calculation unit 12, an operating state detection unit 17, a required power output unit 14, a power totalization unit 13, and a generator ECU 15.

[0037] The current value calculation unit 11 calculates the current value that can be applied to each battery 5 based on the charge amount of each battery 5 (hereinafter, the current value that can be applied may be simply referred to as the "C rate"). Specifically, the current value calculation unit 11 first detects the charge amount of each battery 5. The charge amount of a battery 5 is uniquely determined from the voltage, for example, by measuring the voltage at the battery terminal. Note that, as a method for detecting the charge amount of a battery 5, for example, the so-called coulomb counting method (current integration method) may be used, in which the charge amount of a battery 5 is estimated based on the integrated value of the charge / discharge current of the battery 5.

[0038] Next, the current value calculation unit 11 calculates the C rate of the battery 5 based on the detected charge amount of the battery 5. The current value calculation unit 11 has a first current value calculation unit 61, a second current value calculation unit 62, a third current value calculation unit 63, and a fourth current value calculation unit 64. The first current value calculation unit 61 calculates the C rate CR1 of the first battery 31. The C rate CR1 of the first battery 31 is a value that is uniquely determined depending on the charge amount of the first battery 31. The second current value calculation unit 62 calculates the C rate CR2 of the second battery 32. The C rate CR2 of the second battery 32 is a value that is uniquely determined according to the amount of charge of the second battery 32.

[0039] The third current value calculation unit 63 calculates the C rate CR3 of the third battery 33. The C rate CR3 of the third battery 33 is a value that is uniquely determined according to the amount of charge of the third battery 33. The fourth current value calculation unit 64 calculates the C rate CR4 of the fourth battery 34. The C rate CR4 of the fourth battery 34 is a value that is uniquely determined according to the charge amount of the fourth battery 34.

[0040] The battery required power calculation unit 12 calculates the required power P of the battery 5 based on the current value (C rate) calculated by the current value calculation unit 11 and the capacity BA of the battery 5. The battery required power calculation unit 12 calculates the required power P by multiplying the sum of the C rates calculated by the current value calculation unit 11 by the battery capacity BA per battery (P=BA×(CR1+CR2+CR3+CR4)).

[0041] The operating state detection unit 17 is connected to each power supply line 4. The operating state detection unit 17 is also connected to the battery required power calculation unit 12. The operating state detection unit 17 detects the operating state of each of the multiple power supply lines 4 and outputs the detection result to the battery required power calculation unit 12. The operating state detection unit 17 detects the operating state including, for example, whether or not there is a malfunction (fault, breakdown, etc.) of the battery 5 in each power supply line 4.

[0042] The control unit 9 controls the amount of power generated by the generator 3 based on the operating state of the power supply line 4 detected by the operating state detection unit 17. Specifically, in this embodiment, the battery required power calculation unit 12 calculates a second required power Q of the battery 5 based on the detection results from the operating state detection unit 17, in addition to the C rate of the battery 5 and the capacity BA of the battery 5 described above. The second required power Q of the battery 5 is the required power of the battery 5 when a malfunction occurs in at least some of the power supply lines 4 (batteries 5), compared to the required power P of the battery 5 when all of the power supply lines 4 (batteries 5) are normal. In other words, the required power P is the required power of the battery 5 calculated when the system is functioning normally, and the second required power Q is the required power of the battery 5 calculated when the system is not functioning normally.

[0043] For example, if only the first battery 31 of the multiple batteries 5 is malfunctioning, the battery required power calculation unit 12 calculates a second required power Q of the battery 5 instead of the above-mentioned required power P of the battery 5. The battery required power calculation unit 12 calculates the second required power Q by multiplying the sum of the C rates (CR2, CR3, and CR4) of the batteries (here, the second battery 32, the third battery 33, and the fourth battery 34) determined to be normal among the C rates calculated by the current value calculation unit 11 by the battery capacity BA per battery (Q=BA×(CR2+CR3+CR4)).

[0044] The battery required power calculation unit 12 selects either the required power P or the second required power Q as the power required for the battery 5. More specifically, when all of the power supply lines 4 are operating normally, the battery required power calculation unit 12 selects the required power P as the power required for the battery 5. On the other hand, when at least some of the multiple power supply lines 4 are not operating normally, the battery required power calculation unit 12 selects the second required power Q as the power required for the battery 5. The battery required power calculation unit 12 outputs the selected required power (P or Q) for the battery 5 to the power totalization unit 13, which will be described later.

[0045] The required power output unit 14 detects the power required by the airframe 19 and outputs it to the power totalizing unit 13, which will be described later. The required power of the airframe 19 is the sum of the power required for the electric motors 7 of the power supply lines 4. Specifically, the required power output unit 14 detects a first required power E1, which is the power required for the first electric motor 41 of the first power supply line 21; a second required power E2, which is the power required for the second electric motor 42 of the second power supply line 22; a third required power E3, which is the power required for the third electric motor 43 of the third power supply line 23; and a fourth required power E4, which is the power required for the fourth electric motor 44 of the fourth power supply line 24. Furthermore, the required power output unit 14 adds up the detected required powers E1, E2, E3, and E4 to calculate a total required power E5 as the power required by the airframe 19 (E5 = E1 + E2 + E3 + E4).

[0046] The power totalizer 13 sums the battery required power (P or Q) calculated by the battery required power calculator 12 and the total required power E5, which is the required power from the electric motor 7 calculated by the required power output unit 14. The power totalizer 13 sets the sum of the battery required power (P or Q) and the total required power E5 from the electric motor 7 as the target generated power.

[0047] The generator ECU 15 controls the driving of the drive source 2, thereby controlling the power generated by the generator 3. The target power to be generated calculated by the power totalizer 13 is input to the generator ECU 15. The generator ECU 15 controls the drive source 2 so that the generator 3 generates the target power to be generated calculated by the power totalizer 13.

[0048] A portion of the electric power generated by the generator 3 is supplied to each power supply line 4 according to the power required by each electric motor 7. The remaining portion of the electric power generated by the generator 3 is distributed to each power supply line 4 and charged to each battery 5 so that the battery 5 with the lowest charge level is charged preferentially (more). This makes it possible to restore or maintain the charge level of each battery 5 while satisfying the required output.

[0049] 4 is a flowchart showing the flow of control in the power supply device 1. The control executed by the control unit 9 of the power supply device 1 will be described in detail below with reference to FIG. First, the control unit 9 starts up the system (step S01). Next, the control unit 9 determines whether the system is normal (step S02). A normal system refers to a state in which no faults are found in any of the multiple power supply lines 4, more specifically, in any of the batteries 5 on the power supply lines 4, and each battery 5 is functioning normally.

[0050] If the system is normal (YES in step S02), it is determined whether the generator 3 is generating electricity (step S03). If the generator 3 is not generating electricity (NO in step S03), the process returns to step S02 and waits until the system is normal and generating electricity. If it is determined that the generator 3 is generating electricity (YES in step S03), the current value calculation unit 11 calculates the charge amount and C rate of each battery 5. Specifically, the first current value calculation unit 61 detects the charge amount of the first battery 31 (step S04), and calculates the C rate CR1 of the first battery 31 from the detected charge amount (step S05). Furthermore, the second current value calculation unit 62 detects the charge amount of the second battery 32 (step S06), and calculates the C rate CR2 of the second battery 32 from the detected charge amount (step S07). Similarly, although not shown in FIG. 4, the third current value calculation unit 63 detects the charge amount of the third battery 33, and calculates the C rate CR3 of the third battery 33 from the detected charge amount. The fourth current value calculation unit 64 detects the charge amount of the fourth battery 34, and calculates the C rate CR4 of the fourth battery 34 from the detected charge amount. Note that, in the configuration of this embodiment shown in FIG. 4, an example has been described in which the charge amounts and C rates of the batteries 5 are calculated in parallel, but the charge amounts and C rates of the batteries 5 may be calculated in order from the first battery 31 to the fourth battery 34.

[0051] After the C rates of all batteries 5 have been calculated, the battery power requirement calculation unit 12 adds up the calculated C rates (step S08). Furthermore, the battery power requirement calculation unit 12 multiplies the sum of the added C rates by the battery capacity BA per battery to calculate the battery power requirement P (step S10). After the process of step S10 is completed, the process proceeds to step S11.

[0052] Here, if it is determined in step S02 that the system is not normal (NO in step S02), the process proceeds to step S21. In step S21, it is detected which battery 5 has a failure. Specifically, in this embodiment, it is detected which of the first battery 31, the second battery 32, the third battery 33, and the fourth battery 34 has a failure. In step S21, if a failure in a battery 5 is detected, it is determined whether the system can continue to operate with the remaining normal batteries (for example, whether the aircraft 19 can fly). For example, if a failure has occurred in only one of the four batteries 5, the control unit 9 determines that the system can continue to operate with the remaining three batteries 5, and the process proceeds to step S22. On the other hand, if a failure has occurred in two or more of the four batteries 5, the control unit 9 determines that the system cannot continue to operate with only the remaining batteries 5. In this case, the process proceeds to step S14, where the system is stopped and this flow ends.

[0053] After proceeding to step S22, the control unit 9 next detects the charge amount of the remaining battery 5 that has been determined to be normal (step S22). Furthermore, the control unit 9 calculates the C rate of the normal battery 5 based on the detected charge amount of the normal battery 5 (step S23). Next, the control unit 9 calculates a second required power Q of the battery 5 based on the calculated C rate of the battery 5 and the capacity of the battery 5 (step S24), and proceeds to step S11.

[0054] In step S11, the target power generation is calculated by adding the power required P of the battery 5 calculated in step S10 or the second power required Q of the battery 5 calculated in step S24 to the power required E5 of the aircraft 19 (i.e., the power supplied to the electric motor 7) calculated by the power required output unit 14. Here, the control unit 9 can record the result of the determination as to whether or not the system is normal in step S02, for example, and if it is determined in step S02 that the system is normal, it calculates the target power generation in step S11 using the power required P of the battery 5. On the other hand, if it is determined in step S02 that the system is not normal, for example, the control unit 9 calculates the target power generation in step S11 using the second power required Q of the battery 5.

[0055] Next, the generator ECU 15 controls the driving of the drive source 2 to drive the generator 3, thereby causing the generator 3 to generate power (step S12). At this time, the generator ECU 15 drives the generator 3 so that the power generated by the generator 3 matches the target power generation. When power generation by the generator 3 is completed, it is determined whether or not there is a stop request from the system (step S13). If there is a stop request (YES in step S13), the system is stopped (step S14) and this control flow ends. On the other hand, if there is no stop request (NO in step S13), the process returns to step S02 and the above-mentioned control flow is repeated again.

[0056] In the above embodiment, the system is stopped in step S21 when two or more of the four batteries 5 have failed, but the conditions for whether to stop the system (i.e., the conditions for whether to proceed to YES or NO in step S21) are not limited to this. The threshold number of batteries 5 at which the system is stopped may be set to one, three, or the like. Also, the determination in step S21 may be set in advance to change depending on, for example, the combination of batteries 5 that have failed. Alternatively, the determination in step S21 may be made based on conditions other than the number of batteries 5 that have failed.

[0057] (Action, effect) Next, the operation and effects of the above-described power supply device 1 will be described. According to the power supply device 1 of this embodiment, power generated by the generator 3 is supplied to each of the plurality of batteries 5 through each power supply line 4. The power supply device 1 includes a current value calculation unit 11 that calculates a current value that can be applied to the battery 5, a battery required power calculation unit 12 that calculates a required power (P or Q) based on the current value calculated by the current value calculation unit 11 and the battery capacity, and a power totalizer 13 that totals the power calculated by the current value calculation unit 11 and the power required by the electric motor (electric load) 7. The drive source 2 is controlled so that the power calculated by the power totalizer 13 is generated by the generator 3. Therefore, the power to be generated by the generator 3 (target generated power) can be easily calculated based on the current value that can be applied to the battery 5 and the battery capacity. In the power supply device 1, the power generated by the generator 3 is distributed to each power supply line 4 according to the potential difference between the batteries 5. Therefore, the plurality of batteries 5 can be charged so that the charge amounts are equal, regardless of the potential difference between the batteries 5. Furthermore, even if the outputs (power consumption) of the electric motors 7 on the respective power supply lines 4 are different from one another, the battery 5 with the lowest charge level can be charged first. This allows the output of the electric motor 7 connected to the same power supply line 4 as the battery 5 with the lowest charge level to be improved. As a result, the outputs on the respective power supply lines 4 can be balanced, and the variations in the outputs of the electric motors 7 can be corrected. In other words, the charge levels of the batteries 5 can be balanced regardless of the outputs of the electric motors 7. This enables stable control. Furthermore, compared to the prior art in which charging and discharging are controlled for each battery 5, there is no need for a control device or the like for managing (controlling) charging and discharging for each battery 5. This reduces the cost of the power supply device 1. Therefore, with a simpler and cheaper configuration than before, multiple batteries 5 can be charged evenly. Therefore, it is possible to provide a power supply device 1 that can balance the charge amounts of a plurality of batteries 5 while suppressing the complexity of the control system compared to the prior art. Since batteries 5 with lower charge levels are charged first, it is possible to prevent over-discharge of the batteries 5 with lower charge levels. Furthermore, since the power supply to batteries 5 with relatively higher charge levels is restricted, it is possible to prevent over-charging of the batteries 5 with higher charge levels. Therefore, it is possible to use the batteries 5 within the optimum operating range and to prevent deterioration of the batteries 5. Furthermore, since power is not exchanged between the multiple batteries 5, the control system can be made less complex than in conventional technology in which power is exchanged between the batteries 5. Also, by controlling the charging and discharging of the batteries 5 using only the power from the generator 3 without exchanging power between the batteries 5, the efficiency of charging and discharging can be improved.

[0058] The power supply device 1 further includes an operation state detection unit 17 that detects the operation state of the power supply line 4, and the power generated by the generator 3 is controlled based on the operation state of the power supply line 4. As a result, if a malfunction such as a breakdown occurs in one of the batteries 5, it is possible to suppress the power supply to the malfunctioning power supply line 4. Furthermore, by performing control such as subtracting the amount of power for which the power supply has been stopped from the generated power, it is possible to suppress overcharging of the normal power supply line 4. Therefore, the power supply device 1 can be made highly versatile and can also deal with accidents and malfunctions such as breakdowns.

[0059] The power supply device 1 is a power source for the electrically propelled aircraft 10, and the electrical load is an electric motor 7 that rotates the propellers 8 of the aircraft 10. In this way, the power supply device 1 is used as a power source for the electrically propelled aircraft 10. Here, in an aircraft 10 that flies by rotating multiple propellers 8, the variation in power consumed by each power supply line 4 is likely to be large due to factors such as weather and the aircraft's attitude. For this reason, the power supply device 1 described above is more suitable for use in an aircraft 10 in which the power required by the electric motor varies greatly among the power supply lines 4. In other words, power can be supplied according to the power consumption of each power supply line 4, including the battery 5. Furthermore, since the power from the generator 3 is distributed according to the power demands of each power supply line 4, the flying object 10 can be easily controlled.

[0060] The technical scope of the present invention is not limited to the above-described embodiment, and various modifications can be made without departing from the spirit of the present invention. In each of the above-described embodiments, four power supply lines 4 are connected to each of two generators 3, but this is not limiting. For example, two power supply lines 4 may be connected to one generator 3. That is, the first power supply line 21 and the second power supply line 22 may be connected to one of the two generators 3, and the third power supply line 23 and the fourth power supply line 24 may be connected to the other of the two generators 3. In this case, the first power supply line 21 and the second power supply line 22 may be independent of the third power supply line 23 and the fourth power supply line 24.

[0061] The number of generators 3 and drive sources 2 is not limited to two. Similarly, the number of propellers 8 is not limited to eight. Furthermore, the combination of each propeller 8 and power supply line 4 is not limited to the above-described embodiment. Furthermore, diode 6 does not have to be provided. If diode 6 is not provided, the exchange of power between batteries 5 may be restricted, for example, by controlling the power supply.

[0062] The batteries 5 may have different capacities and ratings. In this case, after calculating the C rate of each battery 5, the required power P may be calculated by multiplying the C rate and battery capacity for each battery 5 and adding these values ​​together. In other words, if the battery capacities of the first battery 31, the second battery 32, the third battery 33, and the fourth battery 34 are BA1, BA2, BA3, and BA4, respectively, the required power P may be calculated by the formula P=BA1×CR1+BA2×CR2+BA3×CR3+BA4×CR4. The same applies to the second required power Q.

[0063] The first current value calculation unit 61, the second current value calculation unit 62, the third current value calculation unit 63, and the fourth current value calculation unit 64 may be integrated together. That is, the C rates (CR1, CR2, CR3, and CR4) of each battery 5 may be calculated by a single current value calculation unit 11. The operation state detection unit 17 may be omitted. However, the configuration of this embodiment having the operation state detection unit 17 is advantageous in that overcharging can be suppressed and versatility can be improved by controlling using the detection result of the operation state detection unit 17.

[0064] In the above embodiment, an example has been described in which only the first battery 31 has a malfunction, but this is not limiting. For example, if only the second battery 32 has a malfunction, the second required power Q may be calculated using a C rate other than that of the second battery 32 (in this case, Q = BA × (CR1 + CR3 + CR4)). Similarly, if only the third battery 33 has a malfunction, the second required power Q may be calculated using a C rate other than that of the third battery 33 (in this case, Q = BA × (CR1 + CR2 + CR4)). Similarly, if only the fourth battery 34 has a malfunction, the second required power Q may be calculated using a C rate other than that of the fourth battery 34 (in this case, Q = BA × (CR1 + CR2 + CR3)). Furthermore, for example, if a malfunction occurs in the first battery 31 and the second battery 32, the second required power Q may be calculated using a C rate other than that of the first battery 31 and the second battery 32 (in this case, Q=BA×(CR3+CR4)). The same applies to other combinations.

[0065] In the above-described embodiment, the second required power Q is calculated by excluding the C rate of the battery 5 in which a malfunction has occurred from the calculation, but this is not limiting. For example, the C rate value may be corrected according to the state of the power supply line 4 by multiplying the C rate value by coefficients (K1, K2, K3, and K4) according to the operating state of each power supply line 4. That is, Q may be calculated as Q=BA×(K1·CR1+K2·CR2+K3·CR3+K4·CR4). Here, the coefficients K1 to K4 may be values ​​that change according to the operating state of the power supply line 4. The coefficients K1 to K4 may be preset values, or may be values ​​that change as appropriate using, for example, machine learning.

[0066] In addition, within the scope of the spirit of the present invention, it is possible to replace the components in the above-described embodiments with well-known components as appropriate, and the above-described embodiments may be combined as appropriate. [Explanation of symbols]

[0067] 1 Power supply 2. Drive source 3. Generator 4. Power supply lines 5 Battery 7 Electric motor (electric load) 8 propellers 10 Flying Objects 11 Current value calculation section 12 Battery power requirement calculation section 13 Power Totalizer 17 Operation status detection unit BA,BA1,BA2,BA3,BA4 Battery capacity CR1, CR2, CR3, CR4 C rate (current value that can be applied to the battery) P,Q Battery power requirement

Claims

1. A generator and a drive source that drives the generator; a plurality of power supply lines that supply the power generated by the generator to a plurality of electrical loads, respectively; a plurality of batteries connected to the respective power supply lines upstream of the electrical load in a power supply direction; a current value calculation unit that calculates a current value that can be applied to each of the batteries based on the charge amount of each of the batteries; a battery required power calculation unit that calculates the required power of the battery based on the current value calculated by the current value calculation unit and the capacity of the battery; a power totalizer that totals the power calculated by the battery power requirement calculator and the power required by the electrical load; Equipped with A power supply device characterized in that the drive source is controlled so that the generator generates the electric power calculated by the electric power totaling unit.

2. further comprising an operation state detection unit that detects the operation states of the plurality of power supply lines; 2. The power supply device according to claim 1, wherein the amount of power generated by the generator is controlled based on the operating state of the power supply line detected by the operating state detection unit.

3. the power supply device is a power source for an electrically propelled aircraft; 3. The power supply device according to claim 1, wherein the electric load is an electric motor that rotates a propeller of the flying object.

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