Power supply system, moving body and control method for power supply system

Abstract

To provide a power supply system, a moving body and a control method for the power supply system.SOLUTION: In a power supply system 26 mounted on an electrically-driven vertical takeoff / landing aircraft (eVTOL aircraft), a battery controller 94 provides a flight controller 86 with first information representing the upper limit of electric power that a battery can input / output continuously for a first period and second information representing the upper limit of electric power that the battery can input / output continuously for a second period, and a motor controller 98 controls a plurality of VTOL drive devices each having a VTOL electric motor and a plurality of cruise drive devices each having a cruise electric motor.SELECTED DRAWING: Figure 3

Description

[Technical Field]

[0001] The present disclosure relates to a power supply system, a mobile object, and a method for controlling a power supply system. [Background technology]

[0002] Patent Document 1 listed below discloses an aircraft having a battery and a generator driven by a gas turbine engine as a power source for an electric motor. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Japanese Patent Publication No. 2020-075649 Summary of the Invention [Problem to be solved by the invention]

[0004] There is a need for better power supply systems, better vehicles, and better methods of controlling power supply systems.

[0005] The present invention aims to solve the above-mentioned problems. [Means for solving the problem]

[0006] A first aspect of the present disclosure is a power supply system comprising: a first generator driven by a first gas turbine engine to generate electricity; a first power control unit that converts AC power output from the first generator into DC power; a first power supply circuit that supplies the output power of the first power control unit to a first load device; a first battery connected in parallel to the first power control unit; a load controller that controls the first load device; and a battery controller that manages the first battery, wherein the battery controller provides capacity information to the load controller, the capacity information including first information indicating an upper limit of power that the first battery can continuously input and output over a first period of time, and second information indicating an upper limit of power that the first battery can continuously input and output over a second period of time that is longer than the first period, and the load controller controls the first load device based on the capacity information provided from the battery controller.

[0007] A second aspect of the present disclosure is a mobile object having the power supply system according to the first aspect.

[0008] A third aspect of the present disclosure is a control method for a power supply system including a first generator driven by a first gas turbine engine to generate electricity, a first power control unit that converts AC power output from the first generator into DC power, a first power supply circuit that supplies the output power of the first power control unit to a first load device, a first battery connected in parallel to the first power control unit, a load controller that controls the first load device, and a battery controller that manages the first battery, the control method including an information providing step of providing capacity information from the battery controller to the load controller, the capacity information including first information indicating an upper limit of power that the first battery can continuously input and output over a first period of time, and second information indicating an upper limit of power that the first battery can continuously input and output over a second period of time that is longer than the first period, and a control step of controlling the first load device by the load controller based on the capacity information provided from the battery controller. [Effects of the Invention]

[0009] According to the present disclosure, it is possible to provide a better power supply system, a better mobile body, and a better method for controlling a power supply system. [Brief explanation of the drawings]

[0010] [Figure 1] FIG. 1 is a schematic diagram of a moving object according to an embodiment. [Figure 2] FIG. 2 is a schematic diagram showing the configuration of an electrical system of a power supply system according to an embodiment. [Figure 3] FIG. 3 is a schematic diagram showing the configuration of a control system of the power supply system according to one embodiment. [Figure 4] FIG. 4 is a graph showing the time-dependent changes in the upper limit value and the lower limit value of the output power of each of the first power generating device and the second power generating device. [Figure 5] FIG. 5 is a map showing upper limit values ​​of output power and input power of each battery of the first, second, third and fourth power storage devices. [Figure 6] FIG. 6 is a flowchart of the command value determination control executed in the management controller and the flight controller. [Figure 7] FIG. 7 is a flowchart of the output power arbitration process. [Figure 8] FIG. 8 is a flowchart of the output power arbitration process. DETAILED DESCRIPTION OF THE INVENTION

[0011] Conventionally, power supply systems equipped with two power sources, a power generator and a battery, have been proposed as power supply systems to be installed in electric vertical take-off and landing aircraft (eVTOL aircraft). The electric motors that drive each rotor of the eVTOL aircraft are driven by power supplied from the power generator and power supplied from the battery.

[0012] The power generation system includes a gas turbine engine, a generator driven by the gas turbine engine, and a power control unit that converts three-phase AC power output from the generator into DC power. When the power demands of the electric motors increase or decrease, the output power of the gas turbine engine is increased or decreased to increase or decrease the output power of the power generation system. However, because the time response of the output power of the gas turbine engine is relatively slow, the increase or decrease in the output power of the power generation system may not be able to keep up with the increase or decrease in the power demands of the electric motors.

[0013] Therefore, if the power required by each electric motor increases and the output power of the power generator is insufficient, the output power of the battery is supplied to each electric motor in addition to the output power of the power generator.Also, if the power required by each electric motor decreases and the output power of the power generator is surplus, part of the output power of the power generator is stored in the battery.

[0014] However, because there is a limit to the amount of power that a battery can charge and discharge, if the battery is charged and discharged according to the power required by each electric motor, there is a risk that the battery will be overcharged or overdischarged.The power supply system disclosed herein can prevent overcharging and overdischarging of the battery.

[0015] [One embodiment] [Configuration of moving objects] FIG. 1 is a schematic diagram of a moving body 10 in one embodiment. The moving body 10 in one embodiment is an electric vertical take-off and landing aircraft (eVTOL aircraft). The moving body 10 has an airframe 12. The airframe 12 is provided with a cockpit, a cabin, etc. A pilot sits in the cockpit and operates the moving body 10. Passengers sit in the cabin. The moving body 10 may be operated automatically.

[0016] The moving body 10 has a front wing 14 and a rear wing 16. When the moving body 10 moves forward, lift is generated on each of the front wing 14 and the rear wing 16.

[0017] The vehicle 10 has eight VTOL rotors 18. One VTOL electric motor 20 is provided for each VTOL rotor 18. The vehicle 10 has two cruise rotors 22. Two cruise electric motors 24 are provided for each cruise rotor 22.

[0018] [Power supply system configuration] 2 is a schematic diagram showing the configuration of the electrical system of power supply system 26 in one embodiment. Power supply system 26 has two power supply systems: first power supply system 28a and second power supply system 28b. Power supply system 26 includes a first power generator 30a that is the main power source for first power supply system 28a. Power supply system 26 also includes a second power generator 30b that is the main power source for second power supply system 28b.

[0019] Each of the first power generating unit 30a and the second power generating unit 30b has a gas turbine engine 32, a generator 34, and a power control unit (hereinafter referred to as PCU) 36. The gas turbine engine 32 drives the generator 34, which then generates electricity. The PCU 36 converts AC power generated by the generator 34 into DC power and outputs it. When starting the gas turbine engine 32, the PCU 36 converts DC power input to the PCU 36 into AC power and outputs it to the generator 34. The generator 34 is operated by the AC power, and the generator 34 drives the gas turbine engine 32.

[0020] The gas turbine engine 32 of the first power generating unit 30a corresponds to the first gas turbine engine of the present invention. The generator 34 of the first power generating unit 30a corresponds to the first generator of the present invention. The PCU 36 of the first power generating unit 30a corresponds to the first power control unit of the present invention. The gas turbine engine 32 of the second power generating unit 30b corresponds to the second gas turbine engine of the present invention. The generator 34 of the second power generating unit 30b corresponds to the second generator of the present invention. The PCU 36 of the second power generating unit 30b corresponds to the second power control unit of the present invention.

[0021] Each of the first power generating device 30a and the second power generating device 30b may include various sensors such as voltage sensors and current sensors, and elements such as fuses, relays, breakers, diodes, transistors, resistors, coils, and capacitors.

[0022] The power supply system 26 includes a first power supply circuit 38a, a second power supply circuit 38b, a third power supply circuit 38c, and a fourth power supply circuit 38d.

[0023] The first power supply circuit 38a supplies the DC power output from the first power generation device 30a to the first load module 40a. The second power supply circuit 38b supplies the DC power output from the second power generation device 30b to the second load module 40b. The third power supply circuit 38c supplies the DC power output from the first power generation device 30a to the third load module 40c. The fourth power supply circuit 38d supplies the DC power output from the second power generation device 30b to the fourth load module 40d.

[0024] Each of the first load module 40 a, the second load module 40 b, the third load module 40 c, and the fourth load module 40 d has two VTOL drive units 42 and one cruise drive unit 44.

[0025] Each VTOL drive device 42 has an inverter 46 and a VTOL electric motor 20. The inverter 46 converts DC power input thereto into three-phase AC power and outputs it to the VTOL electric motor 20.

[0026] Each cruise drive device 44 has an inverter 48 and a cruise electric motor 24. The inverter 48 converts DC power input thereto into three-phase AC power and outputs it to the cruise electric motor 24.

[0027] Each of the first load module 40a and the second load module 40b includes a DC-DC converter 50. The DC-DC converter 50 reduces the voltage of the DC power input to the DC-DC converter 50 and outputs the reduced voltage to a device that operates on DC power. The device that operates on DC power is, for example, a cooling device that cools the PCU 36, the inverter 46, the inverter 48, etc.

[0028] Each of the first load module 40a, the second load module 40b, the third load module 40c and the fourth load module 40d may have various sensors such as voltage sensors, current sensors, fuses, relays, breakers, diodes, transistors, resistors, coils, capacitors and other elements.

[0029] The VTOL electric motor 20 and the cruise electric motor 24 of the first load module 40a each correspond to a first load device of the present invention. The VTOL electric motor 20 and the cruise electric motor 24 of the second load module 40b each correspond to a second load device of the present invention.

[0030] A first power storage device 52a is connected to the first power supply circuit 38a. A second power storage device 52b is connected to the second power supply circuit 38b. A third power storage device 52c is connected to the third power supply circuit 38c. A fourth power storage device 52d is connected to the fourth power supply circuit 38d.

[0031] Each of the first power storage device 52a, the second power storage device 52b, the third power storage device 52c, and the fourth power storage device 52d has a battery 54. The battery 54 is, for example, a lithium ion battery. The battery 54 of the first power storage device 52a corresponds to the first battery of the present invention. The battery 54 of the second power storage device 52b corresponds to the second battery of the present invention.

[0032] Each of the first power storage device 52a, the second power storage device 52b, the third power storage device 52c, and the fourth power storage device 52d may have various elements such as various sensors such as voltage sensors and current sensors, fuses, relays, breakers, diodes, transistors, resistors, coils, and capacitors.

[0033] The first power supply circuit 38a and the second power supply circuit 38b are connected by a first connection circuit 56a, and the third power supply circuit 38c and the fourth power supply circuit 38d are connected by a second connection circuit 56b.

[0034] The power supply system 26 includes a main junction box 58 and a battery junction box 60 .

[0035] The main junction box 58 has a first disconnecting device 62a and a second disconnecting device 62b. The first disconnecting device 62a can disconnect the first power generating unit 30a from the first power supply circuit 38a and the third power supply circuit 38c. The second disconnecting device 62b can disconnect the second power generating unit 30b from the second power supply circuit 38b and the fourth power supply circuit 38d.

[0036] The main junction box 58 has a third shutoff device 64a, a fourth shutoff device 64b, a fifth shutoff device 64c, and a sixth shutoff device 64d. The third shutoff device 64a can shut off the first power generating device 30a from the first power supply circuit 38a. The fourth shutoff device 64b can shut off the second power generating device 30b from the second power supply circuit 38b. The fifth shutoff device 64c can shut off the first power generating device 30a from the third power supply circuit 38c. The sixth shutoff device 64d can shut off the second power generating device 30b from the fourth power supply circuit 38d.

[0037] The main junction box 58 has a first connection device 66a and a second connection device 66b. The first connection device 66a can connect the first power supply circuit 38a to the second power supply circuit 38b via the first connection circuit 56a. The second connection device 66b can connect the third power supply circuit 38c to the fourth power supply circuit 38d via the second connection circuit 56b.

[0038] Each of the first breaking device 62a, the second breaking device 62b, the third breaking device 64a, the fourth breaking device 64b, the fifth breaking device 64c, the sixth breaking device 64d, the first connecting device 66a, and the second connecting device 66b has two contactors 68. One contactor 68 is provided on the positive wiring, and the other contactor 68 is provided on the negative wiring.

[0039] The main junction box 58 includes a first reverse current prevention device 70a, a second reverse current prevention device 70b, a third reverse current prevention device 70c, and a fourth reverse current prevention device 70d. Each of the first reverse current prevention device 70a, the second reverse current prevention device 70b, the third reverse current prevention device 70c, and the fourth reverse current prevention device 70d includes a diode 72 and an insulated gate bipolar transistor (hereinafter referred to as an IGBT) 74. When the IGBT 74 is OFF, the diode 72 prevents reverse current flow in each of the first power supply circuit 38a, the second power supply circuit 38b, the third power supply circuit 38c, and the fourth power supply circuit 38d. When the IGBT 74 is ON, the diode 72 is bypassed and reverse current is allowed in each of the first power supply circuit 38a, the second power supply circuit 38b, the third power supply circuit 38c, and the fourth power supply circuit 38d.

[0040] The battery junction box 60 includes a seventh disconnecting device 78a, an eighth disconnecting device 78b, a ninth disconnecting device 78c, and a tenth disconnecting device 78d. Each of the seventh disconnecting device 78a, the eighth disconnecting device 78b, the ninth disconnecting device 78c, and the tenth disconnecting device 78d includes three contactors 80 and one pre-charge resistor 82. Of the three contactors 80, one contactor 80 is provided on the positive electrode wiring. Of the three contactors 80, another contactor 80 is provided on the negative electrode wiring. Of the three contactors 80, yet another contactor 80 is provided in a pre-charge circuit that bypasses the contactor 80 provided on the negative electrode. The pre-charge resistor 82 is provided in series with the contactor 80 in the pre-charge circuit.

[0041] The seventh disconnecting device 78a can disconnect the first power storage device 52a from the first power supply circuit 38a. The eighth disconnecting device 78b can disconnect the second power storage device 52b from the second power supply circuit 38b. The ninth disconnecting device 78c can disconnect the third power storage device 52c from the third power supply circuit 38c. The tenth disconnecting device 78d can disconnect the fourth power storage device 52d from the fourth power supply circuit 38d.

[0042] When the first power generation device 30a and the first load module 40a are precharged with DC power from the first power storage device 52a, the seventh breaking device 78a outputs DC power from the first power storage device 52a to the first power supply circuit 38a via the precharge circuit. When the second power generation device 30b and the second load module 40b are precharged with DC power from the second power storage device 52b, the eighth breaking device 78b outputs DC power from the second power storage device 52b to the second power supply circuit 38b via the precharge circuit. When the first power generation device 30a and the third load module 40c are precharged with DC power from the third power storage device 52c, the ninth breaking device 78c outputs DC power from the third power storage device 52c to the third power supply circuit 38c via the precharge circuit. When the second power generation device 30b and the fourth load module 40d are precharged with DC power from the fourth power storage device 52d, the tenth circuit breaker 78d outputs DC power from the fourth power storage device 52d to the fourth power supply circuit 38d via the precharge circuit.

[0043] [Control system configuration] 3 is a schematic diagram showing the configuration of a control system of the power supply system 26 in one embodiment. The power supply system 26 in one embodiment has a management controller 84, a flight controller 86, an engine controller 88, a power generation controller 90, a junction box controller 92, a battery controller 94, a DC-DC controller 96, and a motor controller 98.

[0044] Each of the management controller 84, flight controller 86, engine controller 88, power generation controller 90, junction box controller 92, battery controller 94, DC-DC controller 96 and motor controller 98 transmits and receives signals via control area network communication.

[0045] Each of the management controller 84, flight controller 86, engine controller 88, power generation controller 90, junction box controller 92, battery controller 94, DC-DC controller 96 and motor controller 98 has a calculation unit and a memory unit (not shown).

[0046] The arithmetic unit is, for example, a processor such as a CPU (Central Processing Unit) or a GPU (Graphics Processing Unit). The arithmetic unit controls each device by executing a program stored in the storage unit. At least a part of the arithmetic unit may be realized by an integrated circuit such as an ASIC (Application Specific Integrated Circuit) or an FPGA (Field-Programmable Gate Array). At least a part of the arithmetic unit may be realized by an electronic circuit including discrete devices.

[0047] The storage unit is composed of a volatile memory (not shown) and a non-volatile memory (not shown), which are computer-readable storage media. The volatile memory is, for example, a random access memory (RAM). The non-volatile memory is, for example, a read-only memory (ROM), a flash memory, etc. Data, etc., are stored in the volatile memory. Programs, tables, maps, etc., are stored in the non-volatile memory. At least a part of the storage unit may be provided in the processor, integrated circuit, etc. described above.

[0048] The management controller 84 manages the power supplied to each of the first load module 40a, the second load module 40b, the third load module 40c, and the fourth load module 40d. The flight controller 86 manages the operation of each of the first load module 40a, the second load module 40b, the third load module 40c, and the fourth load module 40d. The flight controller 86 corresponds to the load controller of the present invention.

[0049] The engine controller 88 controls the rotation speed and torque of the gas turbine engine 32 based on information sent from the management controller 84. The engine controller 88 monitors the status of the gas turbine engine 32, such as the rotation speed and torque, and sends information indicating the status of the gas turbine engine 32 to the management controller 84.

[0050] The power generation controller 90 controls the rotation speed and torque of the generator 34 based on information sent from the management controller 84. The power generation controller 90 monitors the status of the generator 34, such as the rotation speed and torque, and sends information indicating the status of the generator 34 to the management controller 84.

[0051] The junction box controller 92 controls the main junction box 58 based on information sent from the management controller 84. The junction box controller 92 controls the ON / OFF of each contactor 68 in the main junction box 58 and controls the ON / OFF of each IGBT 74. The junction box controller 92 monitors the status of each contactor 68 and each IGBT 74 in the main junction box 58, and sends information indicating the status of the main junction box 58 to the management controller 84.

[0052] The battery controller 94 controls the battery junction box 60 based on information sent from the management controller 84. The battery controller 94 controls the ON / OFF of each contactor 80 in the battery junction box 60. The battery controller 94 monitors the status of the battery 54 and the battery junction box 60, and sends information indicating the status of the battery 54 and the battery junction box 60 to the management controller 84. The battery controller 94 sends information such as the SOC (State of Charge) of the battery 54, the upper limit of the output power of the battery 54, and the upper limit of the input power of the battery 54 to the management controller 84 as the status of the battery junction box 60. The battery controller 94 sends information such as the ON / OFF status of each contactor 80 to the management controller 84 as the status of the battery junction box 60.

[0053] The DC-DC controller 96 controls the DC-DC converter 50 based on information sent from the flight controller 86. The motor controller 98 controls each VTOL drive unit 42 and each cruise drive unit 44 based on information sent from the flight controller 86.

[0054] [Estimation of power output from power generating equipment] In one embodiment of the power supply system 26, the output power of the first power generation device 30a is increased or decreased in accordance with an increase or decrease in the power required by the first load module 40a and the third load module 40c. Similarly, in one embodiment of the power supply system 26, the output power of the second power generation device 30b is increased or decreased in accordance with an increase or decrease in the power required by the second load module 40b and the fourth load module 40d.

[0055] When increasing or decreasing the output power of the first power generating unit 30a and the output power of the second power generating unit 30b, the output power of the gas turbine engine 32 is increased or decreased. However, because the time response of the output power of the gas turbine engine 32 is relatively slow, it takes time to increase or decrease the output power of the first power generating unit 30a and the output power of the second power generating unit 30b.

[0056] By acquiring information in advance about the future trends in the output power of the first power generation device 30a and the output power of the second power generation device 30b, the flight controller 86 can adjust the output power of each of the first load module 40a, the second load module 40b, the third load module 40c, and the fourth load module 40d in accordance with the future trends in the output power of the first power generation device 30a and the output power of the second power generation device 30b.

[0057] Fig. 4 is a graph showing the time changes in the upper limit and lower limit of the output power of each of the first power generator 30a and the second power generator 30b. As shown in Fig. 4, the management controller 84 estimates the time changes in the upper limit and lower limit of the output power of the first power generator 30a and the second power generator 30b from the present time (t0) onwards. The management controller 84 transmits information on the time changes in the upper limit and lower limit of the output power of the first power generator 30a and the second power generator 30b to the flight controller 86 as capacity information of each of the first power generator 30a and the second power generator 30b.

[0058] [Upper limit of input / output power of storage battery] FIG. 5 is a map showing the upper limit values ​​of output power and input power of each battery 54 of the first power storage device 52a, the second power storage device 52b, the third power storage device 52c, and the fourth power storage device 52d. The map in FIG. 5 shows the upper limit value (output upper limit value) that can be continuously output for a first period (T1 [s]) and the upper limit value (input upper limit value) that can be continuously input for the first period (T1 [s]). The map in FIG. 5 also shows the upper limit value (output upper limit value) that can be continuously output for a second period (T2 [s]) and the upper limit value (input upper limit value) that can be continuously input for the second period (T2 [s]). The map in FIG. 5 also shows the upper limit value (output upper limit value) that can be continuously output for a third period (T3 [s]) and the upper limit value (input upper limit value) that can be continuously input for the third period (T3 [s]). The length of the second period is longer than the length of the first period. The length of the third period is longer than the length of the second period. As shown in FIG. 5, the upper limit of the output power and the upper limit of the input power of the battery 54 change depending on the SOC of the battery 54.

[0059] The management controller 84 transmits information on the output upper limit value and input upper limit value for each period of each of the first storage device 52a, the second storage device 52b, the third storage device 52c, and the fourth storage device 52d, which corresponds to the SOC of each battery 54 at the current time, to the flight controller 86 as capacity information of each of the first storage device 52a, the second storage device 52b, the third storage device 52c, and the fourth storage device 52d.

[0060] The information on the upper limit value that can be continuously output for a first period and the upper limit value that can be continuously input for the first period of the battery 54 of the first power storage device 52a corresponds to first information of the present invention. The information on the upper limit value that can be continuously output for a second period and the upper limit value that can be continuously input for the second period of the battery 54 of the first power storage device 52a corresponds to second information of the present invention. The information on the upper limit value that can be continuously output for a first period and the upper limit value that can be continuously input for the first period of the battery 54 of the second power storage device 52b corresponds to third information of the present invention. The information on the upper limit value that can be continuously output for a second period and the upper limit value that can be continuously input for the second period of the battery 54 of the second power storage device 52b corresponds to fourth information of the present invention.

[0061] [Regarding output power arbitration] The flight controller 86 estimates the future output power of each of the first load module 40a, the second load module 40b, the third load module 40c, and the fourth load module 40d, for example, in accordance with the amount of operation of a control (not shown) by the pilot. The flight controller 86 also estimates the future required power of each of the first load module 40a, the second load module 40b, the third load module 40c, and the fourth load module 40d from the future output power of each of the first load module 40a, the second load module 40b, the third load module 40c, and the fourth load module 40d.

[0062] The flight controller 86 determines whether the total future output power of the first power generation device 30a, the first power storage device 52a, and the third power storage device 52c will be insufficient for the total power required by the future first load module 40a and the third load module 40c, based on the capability information of the first power generation device 30a and the capability information of the first power storage device 52a and the third power storage device 52c. Similarly, the flight controller 86 determines whether the total future output power of the second power generation device 30b, the second power storage device 52b, and the fourth power storage device 52d will be insufficient for the total power required by the future second load module 40b and the fourth load module 40d, based on the capability information of the second power generation device 30b and the capability information of the second power storage device 52b and the fourth power storage device 52d.

[0063] If the total output power of the first power generation device 30a, the first power storage device 52a, and the third power storage device 52c is expected to be insufficient, the flight controller 86 limits the output power of each of the first load module 40a and the third load module 40c. Similarly, if the total output power of the second power generation device 30b, the second power storage device 52b, and the fourth power storage device 52d is expected to be insufficient, the flight controller 86 limits the output power of each of the second load module 40b and the fourth load module 40d.

[0064] Furthermore, when the total output power of the first power generation device 30a, the first power storage device 52a, and the third power storage device 52c is expected to be insufficient, and the total output power of the second power generation device 30b, the second power storage device 52b, and the fourth power storage device 52d is expected to be sufficient, the flight controller 86 increases the output power of each of the second load module 40b and the fourth load module 40d. However, the output power of each of the second load module 40b and the fourth load module 40d is adjusted so that the power required by the second load module 40b and the fourth load module 40d is equal to or less than the total output power of the second power generation device 30b, the second power storage device 52b, and the fourth power storage device 52d. This makes it possible to compensate for the limited output power of each of the first load module 40a and the third load module 40c with the increased output power of each of the second load module 40b and the fourth load module 40d.

[0065] Similarly, if the total output power of the second power generation device 30b, the second power storage device 52b, and the fourth power storage device 52d is expected to be insufficient but the total output power of the first power generation device 30a, the first power storage device 52a, and the third power storage device 52c is expected to be sufficient, the flight controller 86 increases the output power of each of the first load module 40a and the third load module 40c. However, the output power of each of the first load module 40a and the third load module 40c is adjusted so that the power required by the first load module 40a and the third load module 40c is equal to or less than the total output power of the first power generation device 30a, the first power storage device 52a, and the third power storage device 52c. This makes it possible to compensate for the limited output power of each of the second load module 40b and the fourth load module 40d with the increased output power of each of the first load module 40a and the third load module 40c.

[0066] [Command value determination control] FIG. 6 is a flowchart of the command value determination control executed by the management controller 84 and the flight controller 86.

[0067] In step S1, the management controller 84 estimates the time changes of the upper and lower limits of the output power of the first power generator 30a and the second power generator 30b, and generates capacity information for each of the first power generator 30a and the second power generator 30b. Then, the process proceeds to step S2.

[0068] In step S2, the management controller 84 generates capacity information that is information on the output upper limit value and input upper limit value for each period of each of the first power storage device 52a, the second power storage device 52b, the third power storage device 52c, and the fourth power storage device 52d, which corresponds to the current SOC of each battery 54. Thereafter, the process proceeds to step S3.

[0069] In step S3, the management controller 84 transmits the capacity information of each of the first power generation device 30a and the second power generation device 30b, and the capacity information of each of the first power storage device 52a, the second power storage device 52b, the third power storage device 52c, and the fourth power storage device 52d to the flight controller 86. Thereafter, the process proceeds to step S4.

[0070] In step S4, the flight controller 86 executes an output power arbitration process. Then, the process proceeds to step S5. The output power arbitration process will be described in detail later.

[0071] In step S5, the flight controller 86 transmits command values ​​for each of the first load module 40a, the second load module 40b, the third load module 40c, and the fourth load module 40d to the motor controller 98. The motor controller 98 controls each of the first load module 40a, the second load module 40b, the third load module 40c, and the fourth load module 40d based on the command values ​​for each of the first load module 40a, the second load module 40b, the third load module 40c, and the fourth load module 40d. Then, the command value determination control ends.

[0072] [Output power arbitration process] 7 and 8 are flowcharts of the output power arbitration process in step S4 described above.

[0073] In step S11, the flight controller 86 determines a command value for the VTOL electric motor 20 and a command value for the cruise electric motor 24 of each of the first load module 40a, the second load module 40b, the third load module 40c, and the fourth load module 40d. The command value for the VTOL electric motor 20 and the command value for the cruise electric motor 24 are determined based on, for example, the amount of operation of an operator (not shown) by the pilot. Then, the process proceeds to step S12.

[0074] In step S12, the flight controller 86 estimates the future output power of each of the first load module 40a, the second load module 40b, the third load module 40c, and the fourth load module 40d, and then proceeds to step S13.

[0075] In step S13, the flight controller 86 estimates the future power requirements of each of the first load module 40a, the second load module 40b, the third load module 40c, and the fourth load module 40d, and then proceeds to step S14.

[0076] In step S14, the flight controller 86 determines whether the sum of the output power of the first power generation device 30a, the output power of the first power storage device 52a, and the output power of the third power storage device 52c is expected to be insufficient relative to the sum of the power required by the first load module 40a and the power required by the third load module 40c. If it is determined that the sum of the output power of the first power generation device 30a, the output power of the first power storage device 52a, and the output power of the third power storage device 52c is expected to be insufficient (step S14: YES), the process proceeds to step S15. If it is determined that the sum of the output power of the first power generation device 30a, the output power of the first power storage device 52a, and the output power of the third power storage device 52c is not expected to be insufficient (step S14: NO), the process proceeds to step S20.

[0077] In step S15, the flight controller 86 determines whether the sum of the output power of the second power generation device 30b, the output power of the second power storage device 52b, and the output power of the fourth power storage device 52d is expected to be insufficient relative to the sum of the power required by the second load module 40b and the power required by the fourth load module 40d. If it is determined that the sum of the output power of the second power generation device 30b, the output power of the second power storage device 52b, and the output power of the fourth power storage device 52d is expected to be insufficient (step S15: YES), the process proceeds to step S16. If it is determined that the sum of the output power of the second power generation device 30b, the output power of the second power storage device 52b, and the output power of the fourth power storage device 52d is not expected to be insufficient (step S15: NO), the process proceeds to step S18.

[0078] In step S16, the flight controller 86 corrects the command values ​​for the VTOL electric motors 20 and the cruise electric motors 24 of the first load module 40a and the third load module 40c so as to limit the output power of the first load module 40a and the output power of the third load module 40c. Then, the process proceeds to step S17.

[0079] In step S17, the flight controller 86 corrects the command values ​​for the VTOL electric motor 20 and the cruise electric motor 24 of the second load module 40b and the fourth load module 40d so as to limit the output power of the second load module 40b and the output power of the fourth load module 40d. Then, the output power arbitration process ends.

[0080] As described above, if it is determined in step S15 that the sum of the output power of the second power generation device 30b, the output power of the second power storage device 52b, and the output power of the fourth power storage device 52d is not expected to be insufficient (step S15: NO), the process proceeds to step S18.

[0081] In step S18, the flight controller 86 corrects the command values ​​for the VTOL electric motors 20 and the cruise electric motors 24 of the first load module 40a and the third load module 40c so as to limit the output power of the first load module 40a and the output power of the third load module 40c. Then, the process proceeds to step S19.

[0082] In step S19, the flight controller 86 corrects the command values ​​for the VTOL electric motor 20 and the cruise electric motor 24 of the second load module 40b and the fourth load module 40d so as to increase the output power of the second load module 40b and the output power of the fourth load module 40d. Then, the output power arbitration process ends.

[0083] As described above, if it is determined in step S14 that the sum of the output power of the first power generation device 30a, the output power of the first power storage device 52a, and the output power of the third power storage device 52c is not expected to be insufficient (step S14: NO), the process proceeds to step S20.

[0084] In step S20, the flight controller 86 determines whether the sum of the output power of the second power generation device 30b, the output power of the second power storage device 52b, and the output power of the fourth power storage device 52d is expected to be insufficient relative to the sum of the power required by the second load module 40b and the power required by the fourth load module 40d. If it is determined that the sum of the output power of the second power generation device 30b, the output power of the second power storage device 52b, and the output power of the fourth power storage device 52d is expected to be insufficient (step S20: YES), the process proceeds to step S21. If it is determined that the sum of the output power of the second power generation device 30b, the output power of the second power storage device 52b, and the output power of the fourth power storage device 52d is not expected to be insufficient (step S20: NO), the output power arbitration process ends.

[0085] In step S21, the flight controller 86 corrects the command values ​​for the VTOL electric motors 20 and the cruise electric motors 24 of the first load module 40a and the third load module 40c so as to increase the output power of the first load module 40a and the output power of the third load module 40c. Then, the process proceeds to step S22.

[0086] In step S22, the flight controller 86 corrects the command values ​​for the VTOL electric motor 20 and the cruise electric motor 24 of the second load module 40b and the fourth load module 40d so as to limit the output power of the second load module 40b and the output power of the fourth load module 40d. Then, the output power arbitration process ends.

[0087] The following additional notes are further disclosed regarding the above embodiment.

[0088] (Appendix 1) The power supply system (26) of the present disclosure includes a first generator (34) driven by a first gas turbine engine (32) to generate electricity, a first power control unit (36) that converts AC power output from the first generator into DC power, a first power supply circuit (38a) that supplies the output power of the first power control unit to a first load device, a first battery (54) connected in parallel to the first power control unit, a load controller (86) that controls the first load device, and a battery controller (94) that manages the first battery, wherein the battery controller provides the load controller with capacity information including first information indicating an upper limit of power that the first battery can continuously input and output over a first period and second information indicating an upper limit of power that the first battery can continuously input and output over a second period longer than the first period, and the load controller controls the first load device based on the capacity information provided by the battery controller.

[0089] (Appendix 2) The power supply system according to Supplementary Note 1 further comprises a second generator (34) driven by a second gas turbine engine (32) to generate power, a second power control unit (36) that converts AC power output from the second generator into DC power, a second power supply circuit (38b) that supplies the output power of the second power control unit to a second load device, and a second battery (54) connected in parallel with the second power control unit, wherein the load controller controls the second load device, the battery controller manages the second battery, and the capacity information includes the capacity information of the second battery. The power control unit may further include third information indicating an upper limit of power that the first battery can continuously input and output over the first period, and fourth information indicating an upper limit of power that the second battery can continuously input and output over the second period, and when it is expected that the sum of the output power of the first power control unit and the output power of the first battery will be insufficient for the power required by the first load device, and when it is expected that the sum of the output power of the second power control unit and the output power of the second battery will not be insufficient for the power required by the second load device, the output power of the first load device may be limited and the output power of the second load device may be increased.

[0090] (Appendix 3) The moving body (10) of the present disclosure has the power supply system described in Supplementary Note 1 or 2.

[0091] (Appendix 4) The control method for a power supply system disclosed herein includes a first generator driven by a first gas turbine engine to generate electricity, a first power control unit that converts AC power output from the first generator into DC power, a first power supply circuit that supplies the output power of the first power control unit to a first load device, a first battery connected in parallel with the first power control unit, a load controller that controls the first load device, and a battery controller that manages the first battery, and includes an information providing step of providing capacity information from the battery controller to the load controller, the capacity information including first information indicating an upper limit of power that can be continuously input and output by the first battery over a first period of time and second information indicating an upper limit of power that can be continuously input and output by the first battery over a second period of time that is longer than the first period, and a control step of controlling the first load device by the load controller based on the capacity information provided from the battery controller.

[0092] Although the present disclosure has been described in detail, the present disclosure is not limited to the individual embodiments described above. Various additions, substitutions, modifications, partial deletions, etc. are possible in these embodiments without departing from the gist of the present disclosure or the spirit of the present disclosure derived from the content of the claims and their equivalents. These embodiments can also be implemented in combination. For example, in the above-described embodiments, the order of each operation and the order of each process are shown as examples and are not limited to these. The same applies when numerical values ​​or mathematical expressions are used in the description of the above-described embodiments. [Explanation of symbols]

[0093] 10...Mobile 20...VTOL electric motor (first load device, second load device) 24... Cruise electric motor (first load device, second load device) 26...Power supply system 32...Gas turbine engine (first gas turbine engine, second gas turbine engine) 34...Generator (1st generator, 2nd generator) 36...Power control unit (first power control unit, second power control unit) 38a...First power supply circuit 38b...Second power supply circuit 54...Battery (1st battery, 2nd battery) 86...Flight controller (load controller) 94...Battery controller

Claims

1. a first generator driven by the first gas turbine engine to generate electricity; a first power control unit that converts AC power output from the first generator into DC power; a first power supply circuit that supplies the output power of the first power control unit to a first load device; a first battery connected in parallel to the first power control unit; a load controller for controlling the first load device; a battery controller that manages the first battery; Equipped with the battery controller provides the load controller with capability information including first information indicating an upper limit of power that can be continuously input / output to / from the first battery for a first period and second information indicating an upper limit of power that can be continuously input / output to / from the first battery for a second period longer than the first period; The load controller controls the first load device based on the capacity information provided by the battery controller.

2. 2. The power supply system according to claim 1, a second generator driven by the second gas turbine engine to generate electricity; a second power control unit that converts AC power output from the second generator into DC power; a second power supply circuit that supplies the output power of the second power control unit to a second load device; a second battery connected in parallel with the second power control unit; and The load controller controls the second load device; the battery controller manages the second battery; the capacity information includes third information indicating an upper limit of power that can be continuously input / output from / to the second battery during the first period, and fourth information indicating an upper limit of power that can be continuously input / output from / to the second battery during the second period, A power supply system that limits the output power of the first load device and increases the output power of the second load device when the sum of the output power of the first power control unit and the output power of the first battery is expected to be insufficient for the power required by the first load device, and when the sum of the output power of the second power control unit and the output power of the second battery is expected to be sufficient for the power required by the second load device.

3. A mobile object comprising the power supply system according to claim 1 or 2.

4. a first generator driven by the first gas turbine engine to generate electricity; a first power control unit that converts AC power output from the first generator into DC power; a first power supply circuit that supplies the output power of the first power control unit to a first load device; a first battery connected in parallel to the first power control unit; a load controller for controlling the first load device; a battery controller that manages the first battery; A control method for a power supply system, comprising: an information providing step of providing, from the battery controller to the load controller, capability information including first information indicating an upper limit of power that can be continuously input / output to / from the first battery for a first period and second information indicating an upper limit of power that can be continuously input / output to / from the first battery for a second period longer than the first period; a control step of controlling the first load device by the load controller based on the capacity information provided by the battery controller; A control method for a power supply system, comprising:

Images