Power supply device

Abstract

To provide a power supply apparatus capable of easily performing the control of charging and discharging in a plurality of batteries while inhibiting a control system from being complicated, as compared with the prior art.SOLUTION: A power supply apparatus includes a generator, a drive source, a plurality of electric power supply lines, a plurality of batteries, a diode, a difference calculating unit 11, a difference summing unit 12, and an electric power summing unit 13. The difference calculating unit 11 calculates differences D1, D2, D3, and D4 between the target amounts of charge set in the respective batteries and the estimated amounts of charge in the respective batteries. The difference summing unit 12 sums up the differences in the amount of charge in the respective batteries in the respective electric power supply lines calculated by the difference calculating unit 11. The electric power summing unit 13 sums up the amount of charge calculated by the difference summing unit 12 and electric power required for electric loads. A control unit 9 controls the drive source so that the electric power calculated by the electric power summing unit 13 is generated by the generator.SELECTED DRAWING: Figure 3

Description

[Technical Field]

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

[0002] Conventionally, power supply devices that have a drive source, a generator, multiple batteries, and a motor driven by power from the generator or the batteries have been known, for example, in aircraft power supply devices. For these power supply devices, various technologies have been proposed for improving battery performance by controlling the charging mode of the batteries.

[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 equalize 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 Therefore, an object of the present invention is to provide a power supply device that can easily control the charging and discharging of a plurality of batteries while suppressing the complexity of the control system compared to the prior art. [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 embodiment) includes a generator (for example, generator 3 in the embodiment), a drive source (for example, drive source 2 in the embodiment) that drives the generator, a plurality of power supply lines (for example, power supply line 4 in the embodiment) that supply power generated by the generator to a plurality of electric loads (for example, electric motor 7 in the embodiment), and a plurality of batteries (for example, batteries 1 in the embodiment) that are connected to the respective power supply lines upstream of the electric loads in the power supply direction. a battery 5 connected to the power supply line, a diode (for example, diode 6 in the embodiment) that is provided upstream of the battery on the power supply line and allows power to flow only in one direction from upstream to downstream of the power supply line, and calculates the difference between the target charge amount (for example, first target charge amount T1, second target charge amount T2, third target charge amount T3, and fourth target charge amount T4 in the embodiment) set for each battery and the estimated charge amount (for example, first estimated charge amount SOC1, second estimated charge amount SOC2, third estimated charge amount SOC3, and fourth estimated charge amount SOC4 in the embodiment). and convert it into a power valuea difference calculation unit (for example, the difference calculation unit 11 in the embodiment), and The difference a difference summing unit (for example, the difference summing unit 12 in the embodiment) that sums up the difference sums calculated by the difference summing unit; The power and the power required by the electrical load, and the driving source is controlled so that the generator generates the power calculated by the power totalizing unit.

[0008] Furthermore, the power supply device of the invention described in claim 2 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 that rotates a propeller of the aircraft (e.g., propeller 8 in the embodiment). [Effects of the Invention]

[0009] According to the power supply device of claim 1 of the present invention, in each power supply line, power generated by a generator flows in one direction via diodes and is supplied to each battery. The power supply device has a difference calculation unit, a difference totalization unit, and a power totalization unit, and controls the drive source so that the generator generates the power calculated by the power totalization unit. Since the charge amount of the battery is controlled by the total value of the differences in the battery charge amounts, there is no need for a control device or the like to manage (control) the charge and discharge of each battery, as compared to conventional technology that controls the charge and discharge of each battery, for example. This reduces the cost of the power supply device. Therefore, the charge and discharge of multiple batteries can be easily controlled with a simpler and less expensive configuration than conventional technology. Therefore, it is possible to provide a power supply device that can easily control charging and discharging of a plurality of batteries while suppressing the complexity of the control system compared to conventional techniques. By prioritizing charging of batteries with low charge levels, it is possible to improve the output of the power supply line having the battery with the low charge level. In addition, since the output of each power supply line is averaged, it is possible to suppress the variation in output of each power supply line, thereby enabling stable control. 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.

[0010] According to the power supply device of claim 2 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]

[0011] [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. DETAILED DESCRIPTION OF THE INVENTION

[0012] Hereinafter, an embodiment of the present invention will be described with reference to the drawings.

[0013] (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.

[0014] 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.

[0015] 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.

[0016] 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).

[0017] 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).

[0018] (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.

[0019] (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.

[0020] (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.

[0021] 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.

[0022] 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.

[0023] 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.

[0024] 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.

[0025] (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. The batteries 5 have the same capacity and configuration. However, because the required power and power consumption differ for each power supply line 4, the charge amount and power consumption of each battery 5 are not necessarily constant.

[0026] (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.

[0027] 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.

[0028] (electric motor) One electric motor 7 is provided for each power supply line 4. The electric motors 7 are connected to the respective batteries 5 via inverters 39. Specifically, the first electric motor 41 is provided for the first power supply line 21. The second electric motor 42 is provided for the second power supply line 22. The third electric motor 43 is provided for the third power supply line 23. The fourth electric motor 44 is provided for the fourth power supply line 24. Each electric motor 7 is provided downstream of the battery 5 in the power supply direction. Each electric motor 7 rotates the propeller 8 of the flying body 10 using at least one of the power from the generator 3 and the power from the battery 5. Each electric motor 7 has the same configuration.

[0029] 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.

[0030] (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. 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. 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. The fourth propeller 54 and the fifth propeller 55 are connected to the fourth electric motor 44 and rotate about the rotation axis as the fourth electric motor 44 is driven.

[0031] 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.

[0032] (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 requested power and the charge level of the battery 5 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.

[0033] As shown in FIG. 3, the control unit 9 includes a difference calculation unit 11, a difference totalization unit 12, a required power output unit 14, a power totalization unit 13, and a generator ECU 15.

[0034] The difference calculation unit 11 calculates the difference between the target charge amount set for each battery 5 and the estimated charge amount, and further converts the calculated charge amount difference into a power value and outputs it. The target charge amount is a value that is set in advance based on the flight plan, the ratings of the battery 5, etc., and is set, for example, to "75% of the actual usable capacity of the battery 5." The target charge amount may also be a value having a predetermined range. For example, the target charge amount may be set to "75% to 80% of the usable capacity." The estimated charge amount (hereinafter sometimes referred to as the estimated charge amount) is a value that is uniquely determined (estimated) from the voltage, for example, by measuring the voltage at the battery terminal. The charge amount of the battery 5 may also be estimated using the so-called coulomb counting method (current integration method), which estimates the charge amount of the battery 5 based on the integrated value of the charge / discharge current of the battery 5.

[0035] The difference calculation unit 11 includes a first difference calculation unit 61 , a second difference calculation unit 62 , a third difference calculation unit 63 , and a fourth difference calculation unit 64 . The first difference calculation unit 61 calculates a first difference D1, which is the difference between a first target charge amount T1, which is a target charge amount set for the first battery 31, and a first estimated charge amount SOC1, which is an estimated charge amount of the first battery 31 (D1=T1-SOC1). The first difference D1 is set to a value equal to or greater than zero. For example, if the first estimated charge amount SOC1 is greater than the first target charge amount T1, the first difference D1 may be set to zero. Furthermore, the first difference calculation unit 61 calculates a first FB (feedback) power E1 by converting the charge amount into a power value based on the first difference D1. The first difference calculation unit 61 outputs the first FB power E1 to the difference totalization unit 12, which will be described later.

[0036] The second difference calculation unit 62 calculates a second difference D2, which is the difference between a second target charge amount T2, which is a target charge amount set for the second battery 32, and a second estimated charge amount SOC2, which is an estimated charge amount of the second battery 32 (D2=T2−SOC2). Like the first difference D1, the second difference D2 is set to a value greater than or equal to zero. Furthermore, the second difference calculation unit 62 calculates a second FB power E2 by converting the charge amount into a power value based on the second difference D2. The second difference calculation unit 62 outputs the second FB power E2 to the difference summation unit 12.

[0037] The third difference calculation unit 63 calculates a third difference D3, which is the difference between a third target charge amount T3, which is a target charge amount set for the third battery 33, and a third estimated charge amount SOC3, which is an estimated charge amount of the third battery 33 (D3=T3−SOC3). Like the first difference D1, the third difference D3 is set to a value greater than or equal to zero. Furthermore, the third difference calculation unit 63 calculates a third FB power E3 by converting the charge amount into a power value based on the third difference D3. The third difference calculation unit 63 outputs the third FB power E3 to the difference totalization unit 12.

[0038] The fourth difference calculation unit 64 calculates a fourth difference D4, which is the difference between a fourth target charge amount T4, which is a target charge amount set for the fourth battery 34, and a fourth estimated charge amount SOC4, which is an estimated charge amount of the fourth battery 34 (D4=T4−SOC4). Like the first difference D1, the fourth difference D4 is set to a value greater than or equal to zero. Furthermore, the fourth difference calculation unit 64 calculates a fourth FB power E4 by converting the charge amount into a power value based on the fourth difference D4. The fourth difference calculation unit 64 outputs the fourth FB power E4 to the difference summation unit 12.

[0039] The target charge amounts T1, T2, T3, and T4 are output from a flight control unit (not shown) to each difference calculation unit 11. The target charge amounts T1, T2, T3, and T4 are values ​​that are set for each battery 5. Therefore, the target charge amounts T1, T2, T3, and T4 may be different values ​​from each other or may be the same value.

[0040] The difference summing unit 12 calculates a total power difference E5 by summing up the FB powers based on the differences in the charge amounts of the batteries 5 for each power supply line 4 calculated by the difference calculating unit 11. The difference summing unit 12 calculates the total power difference E5 by adding together the values ​​of the first FB power E1, the second FB power E2, the third FB power E3, and the fourth FB power E4 (E5=E1+E2+E3+E4).

[0041] 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 P1, which is the power required for the first electric motor 41 of the first power supply line 21, a second required power P2, which is the power required for the second electric motor 42 of the second power supply line 22, a third required power P3, which is the power required for the third electric motor 43 of the third power supply line 23, and a fourth required power P4, 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 P1, P2, P3, and P4 to calculate a total required power P5 as the power required by the airframe 19 (P5 = P1 + P2 + P3 + P4).

[0042] The power totalizer 13 sums the difference total power E5 calculated by the difference totalizer 12 and the total required power P5, which is the power required from the electric motor 7 and calculated by the required power output unit 14. The power totalizer 13 sets the sum of the difference total power E5 and the total required power P5 as the target generated power.

[0043] 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.

[0044] 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). At this time, the amount of electric power supplied to a battery 5 whose estimated charge level has already reached the target charge level is set to zero. Therefore, it is possible to restore or maintain the charge level of each battery 5 while satisfying the required output.

[0045] (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, the power generated by the generator 3 in each power supply line 4 flows in one direction due to the diodes 6 and is supplied to each battery 5. The power supply device 1 has a difference calculation unit 11, a difference totalization unit 12, and a power totalization unit 13, and controls the drive source 2 so that the generator 3 generates the power calculated by the power totalization unit 13. Since the charge amount of the batteries 5 is controlled based on the total value of the differences in the charge amounts of the batteries 5, there is no need for a control device or the like to manage (control) the charge and discharge of each battery 5, as compared to, for example, conventional techniques that control the charge and discharge of each battery 5 individually. This reduces the cost of the power supply device 1. Therefore, the charge and discharge of multiple batteries 5 can be easily controlled with a simpler and less expensive configuration than conventional techniques. Therefore, it is possible to provide a power supply device 1 that can easily control charging and discharging of a plurality of batteries 5 while suppressing the complexity of the control system compared to the prior art.

[0046] By prioritizing charging of the battery 5 with the lowest charge level, it is possible to improve the output of the power supply line 4 having the battery 5 with the lowest charge level. Furthermore, since the output of each power supply line 4 is averaged, it is possible to suppress variations in the output of each power supply line 4. This makes it possible to achieve stable control.

[0047] 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.

[0048] 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.

[0049] The power supply device 1 is used as a power source for an electrically propelled aircraft 10. The electrical load is an electric motor 7 that rotates the propellers 8 of the aircraft 10. In an aircraft 10 that flies by rotating multiple propellers 8, the amount of power consumed by each power supply line 4 tends to vary greatly due to factors such as weather and the attitude of the aircraft 10. For this reason, the power supply device 1 described above is particularly suitable for use in aircraft 10 in which the difference in power required for the electrical load (electric motor 7) between the power supply lines 4 is large. 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.

[0050] 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.

[0051] 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.

[0052] The power totalizer 13 may add a predetermined amount to the sum of the difference total power E5 and the total required power P5, taking into account, for example, losses, etc., and set the resulting value as the final target generated power. The power totalizer 13 may output this final target generated power to the generator ECU 15. After calculating a total difference D5 by adding up all the differences D1, D2, D3, and D4, the total difference D5 may be converted to calculate the total differential power E5.

[0053] 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]

[0054] 1 Power supply 2. Drive source 3. Generator 4. Power supply lines 5 Battery 6. Diodes 7 Electric motor (electric load) 8 propellers 10 Flying Objects 11 Difference calculation part 12 Difference summation section 13 Power Totalizer SOC1 First estimated charge (estimated charge) SOC2 Second Estimated Charge (Estimated Charge) SOC3 Third Estimated Charge (Estimated Charge) SOC4 4th Estimated Charge (Estimated Charge) T1 First target charge amount (target charge amount) T2 Second target charge amount (target charge amount) T3 Third target charge amount (target charge amount) T4 Fourth Target Charge Amount (Target Charge Amount)

Claims

1. A generator and a driving 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 diode provided on the power supply line upstream of the battery, the diode allowing power to flow only in one direction from upstream to downstream of the power supply line; a difference calculation unit that calculates a difference between a target charge amount set for each battery and an estimated charge amount and converts the difference into a power value; a difference summing unit that sums up the differences for the power supply lines calculated by the difference calculating unit; a power totalizer that totals the power calculated by the difference totalizer 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. the power supply device is a power source for an electrically propelled aircraft; 2. 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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