Power Supply System

Abstract

To provide a power supply system which can determine whether or not each of current devices has a failure.SOLUTION: In a power supply system 22, a power supply circuit 24 includes two main power source devices 26, two auxiliary power source devices 28, two load modules 30, two main power source circuits 32, two auxiliary power source circuits 34, and two load circuits 36. In the power supply circuit 24, power is supplied from both the two main power source devices 26 to each of the two load modules 30. The auxiliary power source devices 28 supply power to the load modules 30. The power supply system has a current sensor 62 and a current sensor 63 for detecting current flowing through the main power source circuits, the auxiliary power source circuits have current sensors 65 for detecting current flowing through the auxiliary power source circuits, and the load circuits have load current sensors 64 for detecting current flowing through the load circuits.SELECTED DRAWING: Figure 4

Description

[Technical Field]

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

[0002] Patent Document 1 below discloses a current sensor abnormality detection device that determines whether each of multiple stack current sensors is abnormal. Each stack current sensor detects the current flowing through each stack in a battery system having multiple stacks connected in parallel. The determination is made based on the current flowing through the entire battery system detected by an upstream current sensor, the current flowing through each stack detected by each stack current sensor, and a shunt ratio, which is the ratio of the current flowing through the entire battery system to the current flowing through each stack. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Japanese Patent Application Laid-Open No. 2013-235689 Summary of the Invention [Problem to be solved by the invention]

[0004] The technology disclosed in Patent Document 1 above has a problem in that the current division ratio of the current flowing through each stack is fixed, and in a circuit where the current division ratio is not fixed, it is not possible to determine whether each current sensor has failed.

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

[0006] A power supply system according to an embodiment of the present invention includes one or more main power supply units that supply power to one or more load devices, auxiliary power supply units provided for each of the load devices and that supply power to each of the load devices, a main power supply circuit connected to one or more of the main power supply units, an auxiliary power supply circuit provided for each of the auxiliary power supply units and connected to each of the auxiliary power supply units, load circuits provided for each of the load devices, connected to the main power supply circuit and the auxiliary power supply circuit at a junction where the current flowing through the main power supply circuit and the current flowing through the auxiliary power supply circuit join, and connected to each of the load devices, a main power supply current sensor that detects the current flowing in the main power supply circuit, an auxiliary power supply current sensor that detects the current flowing in the auxiliary power supply circuit, and a load current sensor that detects the current flowing in the load circuit. [Effects of the Invention]

[0007] According to the present invention, each current Sensor Whether or not the of It can be determined. [Brief explanation of the drawings]

[0008] [Figure 1] Figure 1 is a schematic diagram of an aircraft. [Figure 2] FIG. 2 is a schematic diagram showing the configuration of the power supply system. [Figure 3] FIG. 3 is a block diagram showing the configuration of the control system. [Figure 4] FIG. 4 is a schematic diagram of a power supply system. [Figure 5] FIG. 5 is a schematic diagram of a power supply system. [Figure 6] FIG. 6 is a schematic diagram of a power supply system. [Figure 7] FIG. 7 is a schematic diagram of a power supply system. [Figure 8] FIG. 8 is a schematic diagram of a power supply system. DETAILED DESCRIPTION OF THE INVENTION

[0009] [First embodiment] [Aircraft configuration] FIG. 1 is a schematic diagram of an aircraft 10. The aircraft 10 of this embodiment is an electric vertical take-off and landing aircraft (eVTOL aircraft). In the aircraft 10, a rotor is driven by an electric motor. In the aircraft 10, the rotor generates vertical thrust and horizontal thrust. The aircraft 10 is also a hybrid aircraft. The aircraft 10 has a generator and a battery as power sources for the electric motor. In the aircraft 10, power generated by the generator is supplied to the electric motor. When the power generated by the generator is insufficient to meet the required power, power stored in the battery is supplied to the electric motor.

[0010] The aircraft 10 has a fuselage 12. The fuselage 12 is provided with a cockpit, a cabin, etc. A pilot sits in the cockpit and pilots the aircraft 10. The cabin houses passengers, etc. The aircraft 10 may be piloted automatically.

[0011] The aircraft 10 has a front wing 14 and a rear wing 16. When the aircraft 10 moves forward, lift is generated on each of the front wing 14 and the rear wing 16.

[0012] The aircraft 10 has eight VTOL rotors 18. The eight VTOL rotors 18 are rotor 18La, rotor 18Lb, rotor 18Lc, rotor 18Ld, rotor 18Ra, rotor 18Rb, rotor 18Rc, and rotor 18Rd.

[0013] The rotating shaft of each VTOL rotor 18 extends in the vertical direction of the airframe 12. The thrust of each VTOL rotor 18 is controlled by adjusting the rotor rotation speed and the blade pitch angle. Each VTOL rotor 18 is used during vertical takeoff, transition from vertical takeoff to cruising, transition from cruising to vertical landing, vertical landing, hovering in the air, etc. Each VTOL rotor 18 is also used during attitude control.

[0014] Lift thrust is generated by controlling the thrust of each VTOL rotor 18. Lift thrust refers to thrust in the vertical direction. Controlling the thrust of each VTOL rotor 18 causes a roll moment, a pitch moment, and a yaw moment to act on the airframe 12.

[0015] The aircraft 10 has two cruise rotors 20. The two cruise rotors 20 are rotor 20L and rotor 20R. Rotor 20L and rotor 20R are attached to the rear of the fuselage 12.

[0016] The rotating shaft of each cruise rotor 20 extends in the fore-and-aft direction of the airframe 12. The thrust of each cruise rotor 20 is controlled by adjusting the rotor rotation speed and blade pitch angle. Each cruise rotor 20 is used during transition from vertical takeoff to cruise, during cruise, and during transition from cruise to vertical landing, etc.

[0017] Cruise thrust is generated by controlling the thrust of each cruise rotor 20. Cruise thrust refers to thrust in the horizontal direction.

[0018] [Power supply system configuration] 2 is a schematic diagram showing the configuration of the power supply system 22. The power supply system 22 has a power supply circuit 24, two main power supply devices 26, and six auxiliary power supply devices 28.

[0019] The power supply circuit 24 supplies power from both of the two main power supplies 26 to each of the six load modules 30. An auxiliary power supply 28 is provided for each load module 30. If the power supplied from the main power supplies 26 to the load module 30 is insufficient, power is supplied from the auxiliary power supply 28 to the load module 30. The load modules 30 correspond to the load devices of the present invention.

[0020] The power supply circuit 24 has two main power supply circuits 32, six auxiliary power supply circuits 34, and six load circuits 36. Each main power supply circuit 32 is connected to both of the two main power supply units 26. An auxiliary power supply circuit 34 is provided for each auxiliary power supply unit 28, and each auxiliary power supply circuit 34 is connected to each auxiliary power supply unit 28. Each auxiliary power supply circuit 34 is connected to both of the two main power supply circuits 32. A load circuit 36 ​​is provided for each load module 30, and the load circuit 36 ​​is connected to the load module 30. Each load circuit 36 ​​is connected to the main power supply circuit 32 and the auxiliary power supply circuit 34 at the junction where the current flowing through the two main power supply circuits 32 and the current flowing through the auxiliary power supply circuit 34 join.

[0021] The main power supply device 26 has a gas turbine 38, a generator 40, and a power control unit (hereinafter referred to as PCU) 42. The gas turbine 38 drives the generator 40, which then generates electricity. The PCU 42 converts AC power generated by the generator 40 into DC power and outputs it to the power supply circuit 24.

[0022] When starting the gas turbine 38, the PCU 42 converts the DC power supplied from the power supply circuit 24 into AC power and outputs it to the generator 40. The generator 40 operates using the power input from the PCU 42, and the generator 40 drives the gas turbine 38.

[0023] Of the six load modules 30, four load modules 30 each have two drive units 44. The other two load modules 30 each have one drive unit 44 and one converter 46. The drive units 44 drive each of the VTOL rotors 18 or each of the cruise rotors 20.

[0024] Each drive unit 44 has an electric motor 48 and an inverter 50. The electric motor 48 is a three-phase motor. Each VTOL rotor 18 is connected to the output shaft of the corresponding electric motor 48. Each cruise rotor 20 is connected to the output shaft of the corresponding electric motor 48. The inverter 50 converts the DC power supplied from the power supply circuit 24 into three-phase AC power and outputs it to the electric motor 48.

[0025] The converter 46 reduces the voltage of the DC power supplied from the power supply circuit 24 and outputs it to devices that operate on DC power. Examples of devices that operate on DC power include cooling devices that cool the power supply circuit 24, the PCU 42, the inverter 50, etc. Examples of devices that operate on DC power include an ECU (Electronic Control Unit) that controls the power supply circuit 24, the gas turbine 38, the PCU 42, the inverter 50, etc.

[0026] Each auxiliary power supply 28 has a battery 52. ​​The battery 52 is charged by power supplied from the main power supply 26. The power charged in the battery 52 is supplied to the load module 30.

[0027] Each main power supply circuit 32 has a shared bus 54, two breaker devices 56, six breaker devices 58, two current sensors 62, and six current sensors 63. The current sensors 62 and 63 correspond to the main power supply current sensors of the present invention. The current sensor 62 corresponds to the first main power supply current sensor of the present invention. The current sensor 63 corresponds to the second main power supply current sensor of the present invention.

[0028] The two main power supplies 26 are connected in parallel to each other by a shared bus 54. The six load modules 30 are connected in parallel to each other by the shared bus 54. The main power circuit 32 supplies power from the two main power supplies 26 to each load module 30.

[0029] Each interruption device 56 is provided between each main power supply device 26 and the shared bus 54. The interruption device 56 includes a contactor 57a and a contactor 57b. The contactor 57a is provided on the positive wiring of the main power supply circuit 32. The contactor 57b is provided on the negative wiring of the main power supply circuit 32.

[0030] Each of the disconnection devices 56 switches between a conductive state and a disconnection state between each of the main power supply devices 26 and the shared bus 54 .

[0031] Each interrupting device 58 is provided between each load module 30 and the shared bus 54. The interrupting device 58 includes a contactor 59a and a contactor 59b. The contactor 59a is provided on the positive wiring of the main power supply circuit 32. The contactors 59b are provided on the negative wiring of the main power supply circuit 32.

[0032] Each interruption device 58 switches between a conductive state and a disconnection state between each load module 30 and the shared bus 54 .

[0033] Each current sensor 62 is provided between each interrupting device 56 and the shared bus 54. The current sensor 62 is provided on the positive wiring of the main power supply circuit 32. Each current sensor 63 is provided between each interrupting device 58 and the shared bus 54. The current sensor 63 is provided on the positive wiring of the main power supply circuit 32.

[0034] Each auxiliary power supply circuit 34 has a breaker device 60 and a current sensor 65. The current sensor 65 corresponds to the auxiliary power supply current sensor of the present invention.

[0035] The interrupter 60 has a contactor 61a, a contactor 61b, and a pre-charge circuit 61c. The contactor 61a is provided on the positive wiring of the auxiliary power supply circuit 34. The contactor 61b is provided on the negative wiring of the auxiliary power supply circuit 34. The pre-charge circuit 61c is provided in parallel with the contactor 61b. The pre-charge circuit 61c has a contactor 61d and a resistor 61e. The current sensor 65 is provided on the negative wiring of the auxiliary power supply circuit 34.

[0036] Each breaker device 60 may include only the contactor 61b and the precharge circuit 61c. The precharge circuit 61c may be provided in parallel with the contactor 61a. In this case, each breaker device 60 may include only the contactor 61a and the precharge circuit 61c.

[0037] The load circuit 36 ​​has a current sensor 64. The current sensor 64 is provided on the positive electrode wiring of the load circuit 36. The current sensor 64 corresponds to the load current sensor of the present invention.

[0038] Diodes 66 are provided between the two main power supply circuits 32 and each auxiliary power supply circuit 34. The anode of each diode 66 is connected to the two main power supply circuits 32, and the cathode is connected to the auxiliary power supply circuit 34. Each diode 66 allows power to be supplied from the two main power supply circuits 32 to each auxiliary power supply circuit 34. Each diode 66 prevents power from being supplied from each auxiliary power supply circuit 34 to the two main power supply circuits 32.

[0039] As a result, power is supplied from the main power supply 26 to each auxiliary power supply 28 via each diode 66. As a result, the battery 52 of each auxiliary power supply 28 is charged. Furthermore, if the main power supply circuit 32 is short-circuited, power from each auxiliary power supply 28 is prevented from flowing to the main power supply circuit 32. As a result, even if the main power supply circuit 32 is short-circuited, power can be supplied from each auxiliary power supply 28 to the drive unit 44 and converter 46 in each load module 30.

[0040] A transistor 67 is provided in parallel with each diode 66. When the transistor 67 is on, power is supplied from each auxiliary power supply 28 to the main power circuit 32, bypassing the diode 66.

[0041] A current sensor 68 is provided between one of the two main power supply devices 26 and the two main power supply circuits 32. The current sensor 68 is provided on the positive wiring connecting the one of the main power supply devices 26 and the two main power supply circuits 32.

[0042] [Control system configuration] 3 is a block diagram showing the configuration of the control system of the aircraft 10. The control system includes a power supply controller 70 and a flight controller 72.

[0043] The power supply controller 70 includes a calculation unit 74 and a storage unit 76. The calculation unit 74 is a processor such as a CPU (Central Processing Unit) or a GPU (Graphics Processing Unit). The calculation unit 74 includes a battery monitoring unit 78 and a fault determination unit 80. The battery monitoring unit 78 and the fault determination unit 80 are realized by the calculation unit 74 executing a program stored in the storage unit 76. At least a portion of the battery monitoring unit 78 and the fault determination unit 80 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 portion of the battery monitoring unit 78 and the fault determination unit 80 may be realized by an electronic circuit including discrete devices.

[0044] The storage unit 76 is configured by a volatile memory (not shown) and a nonvolatile memory (not shown), which are computer-readable storage media. The volatile memory is, for example, a random access memory (RAM). The nonvolatile 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 nonvolatile memory. At least a part of the storage unit 76 may be provided in the processor, integrated circuit, etc. described above.

[0045] The flight controller 72 has a calculation unit 82 and a memory unit 84. The calculation unit 82 is a processor such as a CPU (Central Processing Unit) or a GPU (Graphics Processing Unit). The calculation unit 82 has a load control unit 86. The load control unit 86 is realized by the calculation unit 82 executing a program stored in the memory unit 84. The load control unit 86 may be realized by an integrated circuit such as an ASIC (Application Specific Integrated Circuit) or an FPGA (Field-Programmable Gate Array). The load control unit 86 may be realized by an electronic circuit including discrete devices.

[0046] The storage unit 84 is configured by 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 84 may be provided in the above-mentioned processor, integrated circuit, etc.

[0047] The battery monitoring unit 78 monitors the SOC (State Of Charge) of the battery 52 of each auxiliary power supply 28. The battery monitoring unit 78 outputs the SOC of the battery 52 of each auxiliary power supply 28 to the failure determination unit 80.

[0048] The failure determination unit 80 determines whether or not each current sensor of the power supply circuit 24 has failed, based on the current detected by each current sensor. When determining whether or not each current sensor has failed, the failure determination unit 80 controls each inverter 50 via the load control unit 86 of the flight controller 72. The failure determination of each current sensor will be described in detail below.

[0049] [Current sensor failure determination] FIG. 4 is a schematic diagram of the power supply system 22. The schematic diagram of FIG. 4 shows the circuit configuration of the power supply circuit 24 between two main power supply devices 26 and two load modules 30. Below, the fault determination of each current sensor will be explained using FIG. 4. 3 If the number of load modules 30 is more than one, 3 Even if there are two or more current sensors, the failure determination for each current sensor is performed in the same manner as described below.

[0050] The arrows in Fig. 4 indicate the direction in which the current value detected by each current sensor is positive. For the purpose of explaining the failure determination of each current sensor below, unique reference symbols are assigned to each main power supply unit 26, each auxiliary power supply unit 28, each load module 30, each main power supply circuit 32, each auxiliary power supply circuit 34, each load circuit 36, each interrupting device 56, each interrupting device 58, each interrupting device 60, each current sensor 62, each current sensor 63, each current sensor 64, and each current sensor 65 in Fig. 4.

[0051] The fault determination unit 80 performs fault determination for each current sensor when power is supplied from the main power supply 26 to the load module 30. When power is supplied from the main power supply 26 to the load module 30, one of the two main power supply circuits 32 is used. For example, as shown in FIG. 4, the circuit breaker 56a, the circuit breaker 56b, the circuit breaker 58a, and the circuit breaker 58b are each in a conductive state. Also, the circuit breaker 56c, the circuit breaker 56d, the circuit breaker 58c, and the circuit breaker 58d are each in a cut-off state. In this case, the values ​​of the current I2c of the current sensor 62c, the current I2d of the current sensor 62d, the current I3c of the current sensor 63c, and the current I3d of the current sensor 63d are all zero.

[0052] (When all current sensors are normal) When all the current sensors in Figure 4 are normal, the currents detected by each current sensor have the following relationship:

[0053] I2a+I2b=I3a+I3b I3a=I5a-I4a I3b=I5b-I4b I1=I2a

[0054] If the currents detected by the current sensors satisfy the above relationship, the failure determination unit 80 determines that none of the current sensors are at fault.

[0055] (When the current sensor between the main power supply and the main power circuit fails) Current sensor 68 is provided between main power supply device 26a and main power supply circuit 32a. Current sensor 68 is also provided between main power supply device 26a and main power supply circuit 32b. If current sensor 68 in Figure 4 fails, the currents detected by each current sensor will have the following relationship:

[0056] I2a+I2b=I3a+I3b I3a=I5a-I4a I3b=I5b-I4b I1 ≠ I2a

[0057] If the currents detected by the current sensors satisfy the above relationship, the failure determination unit 80 determines that the current sensor 68 has failed.

[0058] (When the current sensor in the main power circuit fails) The current sensor 62 and the current sensor 63 are provided in the main power supply circuit 32. When the current sensor 62a in Fig. 4 fails, the currents detected by the current sensors have the following relationship.

[0059] I2a+I2b≠I3a+I3b I3a=I5a-I4a I3b=I5b-I4b I1 ≠ I2a

[0060] If the currents detected by the current sensors satisfy the above relationship, the failure determination unit 80 determines that the current sensor 62a has failed.

[0061] When the current sensor 62b in FIG. 4 fails, the currents detected by the current sensors have the following relationship.

[0062] I2a+I2b≠I3a+I3b I3a=I5a-I4a I3b=I5b-I4b I1=I2a

[0063] If the currents detected by the current sensors satisfy the above relationship, the failure determination unit 80 determines that the current sensor 62b has failed.

[0064] When the current sensor 63a in FIG. 4 fails, the currents detected by the current sensors have the following relationship.

[0065] I2a+I2b≠I3a+I3b I3a ≠ I5a-I4a I3b=I5b-I4b I1=I2a

[0066] If the currents detected by the current sensors satisfy the above relationship, the failure determination unit 80 determines that the current sensor 63a has failed.

[0067] When the current sensor 63b in FIG. 4 fails, the currents detected by the current sensors have the following relationship.

[0068] I2a+I2b≠I3a+I3b I3a=I5a-I4a I3b ≠ I5b-I4b I1=I2a

[0069] If the currents detected by the current sensors satisfy the above relationship, the failure determination unit 80 determines that the current sensor 63b has failed.

[0070] (When the current sensor in the auxiliary power circuit or the current sensor in the load circuit fails) The current sensor 65 is provided in the auxiliary power supply circuit 34. The current sensor 64 is provided in the load circuit 36. When the current sensor 65a in FIG. 4 fails or when the current sensor 64a fails, the currents detected by the current sensors have the following relationship:

[0071] I2a+I2b=I3a+I3b I3a ≠ I5a-I4a I3b=I5b-I4b I1=I2a

[0072] In other words, whether current sensor 65a or current sensor 64a fails, the relationship between the currents detected by each current sensor is the same, so it is not possible to distinguish between a failure of current sensor 65a and a failure of current sensor 64a.

[0073] In this case, the failure determination unit 80 stops the supply of power to the load module 30a. Specifically, the failure determination unit 80 turns off all switching elements of the inverter 50 of the drive unit 44 in the load module 30a via the load control unit 86.

[0074] When the supply of power to the load module 30a is stopped, if the current I3a detected by the current sensor 63a and the current I4a detected by the current sensor 65a have the following relationship, the fault determination unit 80 determines that the current sensor 65a has failed.

[0075] I3a ≠ -I4a

[0076] When the supply of power to the load module 30a is stopped, if the current I3a detected by the current sensor 63a and the current I4a detected by the current sensor 65a have the following relationship, the fault determination unit 80 determines that the current sensor 64a has failed.

[0077] I3a=-I4a

[0078] When the current sensor 65b or the current sensor 64b in FIG. 4 fails, the currents detected by the current sensors have the following relationship.

[0079] I2a+I2b=I3a+I3b I3a=I5a-I4a I3b ≠ I5b-I4b I1=I2a

[0080] In other words, whether current sensor 65b or current sensor 64b fails, the relationship between the currents detected by each current sensor is the same, so it is not possible to distinguish between a failure of current sensor 65b and a failure of current sensor 64b.

[0081] In this case, the failure determination unit 80 stops the supply of power to the load module 30b. Specifically, the failure determination unit 80 turns off all switching elements of the inverter 50 of the drive unit 44 in the load module 30b via the load control unit 86.

[0082] When the supply of power to the load module 30b is stopped, if the current I3b detected by the current sensor 63b and the current I4b detected by the current sensor 65b have the following relationship, the fault determination unit 80 determines that the current sensor 65b has failed.

[0083] I3b ≠ -I4b

[0084] When the supply of power to the load module 30b is stopped, if the current I3b detected by the current sensor 63b and the current I4b detected by the current sensor 65b have the following relationship, the fault determination unit 80 determines that the current sensor 64b has failed.

[0085] I3b=-I4b

[0086] If the SOC of the battery 52 in the auxiliary power supply 28a is less than a predetermined value, the failure determination unit 80 stops the supply of power to the load module 30a. This is because if the supply of power to the load module 30a is stopped while the SOC of the battery 52 in the auxiliary power supply 28a is equal to or greater than the predetermined value, the battery 52 in the auxiliary power supply 28a will be charged with surplus power, causing the battery 52 to become overcharged. Similarly, if the SOC of the battery 52 in the auxiliary power supply 28b is less than the predetermined value, the failure determination unit 80 stops the supply of power to the load module 30b.

[0087] When the supply of power to the load module 30a is stopped, the load control unit 86 increases the output power of the electric motor 48 of the drive unit 44 in the load module 30b compared to when power is being supplied to the load module 30a. When the supply of power to the load module 30a is stopped, thrust is not generated by the VTOL rotor 18 driven by the electric motor 48 of the drive unit 44 in the load module 30a. In this case, the output power of the electric motor 48 of the drive unit 44 in the load module 30b is increased to compensate for the thrust from another VTOL rotor 18. Similarly, when the supply of power to the load module 30b is stopped, the load control unit 86 increases the output power of the electric motor 48 of the drive unit 44 in the load module 30a compared to when power is being supplied to the load module 30b.

[0088] As described above, if the supply of power to some of the load modules 30 is stopped and thrust from some of the cruise rotors 20 cannot be obtained, the output of the electric motor 48 driving another cruise rotor 20 may be increased.

[0089] [Action and effect] 5 is a schematic diagram of a comparative example of a power supply system 22. In the power supply system 22, current sensors 62 and 63 must be provided in the main power supply circuit 32 to detect abnormalities such as a break or short circuit in the main power supply circuit 32. Also, a current sensor 65 must be provided in the auxiliary power supply circuit 34 to detect abnormalities such as a break or short circuit in the auxiliary power supply circuit 34.

[0090] In order to determine whether or not each of current sensor 62, current sensor 63, and current sensor 65 has failed, it is possible to duplicate each of current sensor 62, current sensor 63, and current sensor 65, as shown in Figure 5.

[0091] However, if current sensor 62, current sensor 63, and current sensor 65 are all duplicated, there is a problem that the weight of power supply system 22 increases, and there is also a problem that the manufacturing cost of power supply system 22 increases.

[0092] In the power supply system 22 of this embodiment, a current sensor 64 is provided in the load circuit 36. The load circuit 36 ​​is connected to the main power supply circuit 32 and the auxiliary power supply circuit 34 at a junction where the current flowing through the main power supply circuit 32 and the current flowing through the auxiliary power supply circuit 34 join together. This allows the failure determination unit 80 to determine whether or not each of the current sensors 62, 63, and 65 has failed, without having to duplicate all of the current sensors 62, 63, and 65. This prevents an increase in the weight of the power supply system 22. It also prevents an increase in the manufacturing cost of the power supply system 22.

[0093] In the power supply system 22 of this embodiment, when power is being supplied from the main power supply device 26 to all of the load modules 30, the failure determination unit 80 determines whether or not a failure has occurred in the current sensor 62 or the current sensor 63 of the main power supply circuit 32. This allows the failure determination unit 80 to accurately determine whether or not a failure has occurred in the current sensor 62 or the current sensor 63.

[0094] In the power supply system 22 of this embodiment, in a state in which the supply of power from the main power supply device 26 to only one load module 30 is stopped, the failure determination unit 80 determines whether a failure has occurred in the current sensor 65 of the auxiliary power supply circuit 34 or the current sensor 64 of the load circuit 36. This allows the failure determination unit 80 to accurately determine whether a failure has occurred in the current sensor 65 or the current sensor 64.

[0095] In the power supply system 22 of this embodiment, when the SOC of the battery 52 in the auxiliary power supply device 28 is less than a predetermined value, the failure determination unit 80 stops the supply of power to the load module 30 corresponding to the auxiliary power supply device 28. This makes it possible to prevent the battery 52 from being overcharged.

[0096] In the power supply system 22 of this embodiment, when the supply of power to some of the load modules 30 is stopped, the failure determination unit 80 increases the output power of the electric motors 48 of the drive units 44 in the other load modules 30 via the load control unit 86 compared to when power is being supplied to some of the load modules 30. As a result, even when some of the VTOL rotors 18 stop, the thrust can be compensated for by the remaining VTOL rotors 18. Similarly, even when some of the cruise rotors 20 stop, the thrust can be compensated for by the remaining cruise rotors 20.

[0097] The present invention is not limited to the above-described embodiment, and various configurations can be adopted without departing from the gist of the present invention.

[0098] Regardless of the structure of the power supply circuit 24 of the first embodiment, in various power supply circuits 24, the failure determination unit 80 can determine whether or not each current sensor has failed using a method similar to that of the first embodiment.

[0099] 6 is a schematic diagram of the power supply system 22. In the power supply system 22 of the first embodiment (FIG. 4), the power supply circuit 24 has two main power supply circuits 32. In contrast, as shown in FIG. 6, the power supply circuit 24 may have one main power supply circuit 32. In this case, the current sensor 68 may be provided in the main power supply circuit 32.

[0100] Fig. 7 is a schematic diagram of the power supply system 22. In the power supply system 22 of the first embodiment (Fig. 4), the power supply circuit 24 supplies power to each load module 30 from two main power supply devices 26. Alternatively, as shown in Fig. 7, the power supply circuit 24 may supply power to each load module 30 from one main power supply device 26. In this case, the current sensor 68 can be omitted.

[0101] Fig. 8 is a schematic diagram of the power supply system 22. In the power supply system 22 of the first embodiment (Fig. 4), the power supply circuit 24 supplies power to each load module 30 from two main power supply devices 26. Alternatively, as shown in Fig. 8, the power supply circuit 24 may supply power to each load module 30 from three main power supply devices 26. In this case, two current sensors 68 need to be provided.

[0102] In the power supply system 22 of the first embodiment, the main power supply device 26 includes a gas turbine 38, a generator 40, and a PCU 42. Alternatively, the main power supply device 26 may include a battery or a capacitor.

[0103] The main power supply 26 may include a gas turbine 38, a generator 40, and a PCU 42, as well as elements such as sensors, fuses, relays, breakers, diodes, transistors, resistors, coils, and capacitors.

[0104] In the power supply system 22 of the first embodiment, the auxiliary power supply 28 includes a battery 52. ​​Alternatively, the auxiliary power supply 28 may include a gas turbine, a generator, and a PCU. Alternatively, the auxiliary power supply 28 may include a capacitor.

[0105] In addition to the battery 52, the auxiliary power supply 28 may include elements such as sensors, fuses, relays, breakers, diodes, transistors, resistors, coils, and capacitors.

[0106] The load module 30 may include an electric motor 48, a drive unit 44 having an inverter 50, a converter 46, as well as elements such as sensors, fuses, relays, breakers, diodes, transistors, resistors, coils, and capacitors.

[0107] The main power supply circuit 32 may include a shared bus 54, a circuit breaker 56, a circuit breaker 58, a current sensor 62, and a current sensor 63, as well as elements such as sensors, fuses, relays, breakers, diodes, transistors, resistors, coils, and capacitors.

[0108] In addition to the interrupter 60 and the current sensor 65, the auxiliary power supply circuit 34 may include elements such as sensors, fuses, relays, breakers, diodes, transistors, resistors, coils, and capacitors.

[0109] In addition to the current sensor 64, the load circuit 36 ​​may include elements such as sensors, fuses, relays, breakers, diodes, transistors, resistors, coils, and capacitors.

[0110] [Inventions Obtained from the Embodiments] The invention that can be understood from the above embodiment will be described below.

[0111] The power supply system (22) includes one or more main power supply units (26) that supply power to one or more load devices (30), auxiliary power supply units (28) provided for each of the load devices and that supply power to the respective load devices, a main power supply circuit (32) connected to the one or more main power supply units, an auxiliary power supply circuit (34) provided for each of the auxiliary power supply units and connected to each of the auxiliary power supply units, load circuits (36) provided for each of the load devices, connected to the main power supply circuit and the auxiliary power supply circuit at a junction where a current flowing through the main power supply circuit and a current flowing through the auxiliary power supply circuit join, and connected to each of the load devices, main power supply current sensors (62, 63) that detect a current flowing through the main power supply circuit, an auxiliary power supply current sensor (65) that detects a current flowing through the auxiliary power supply circuit, and a load current sensor (64) that detects a current flowing through the load circuit. This configuration can reduce the weight of the power supply system and the manufacturing costs of the power supply system.

[0112] In the above power supply system, each of the main power supply devices supplies power to a plurality of the load devices, and the main power supply circuit has a shared bus (54) for transmitting power from each of the main power supply devices to the plurality of the load devices, and the main power supply current sensors include a first main power supply current sensor (62) provided between the main power supply device and the shared bus and a second main power supply current sensor (63) provided between the shared bus and each of the junctions, and a failure determination unit (80) for determining whether any of the first main power supply current sensor, the second main power supply current sensor, the auxiliary power supply current sensor, and the load current sensor has failed, and the failure determination unit determines whether any of the first main power supply current sensor, the second main power supply current sensor, the auxiliary power supply current sensor, and the load current sensor has failed, and In a state where power is being supplied to all of the load devices, it may be determined whether or not one of the first main power supply current sensor and the second main power supply current sensor has failed based on the currents detected by each of the first main power supply current sensor, the second main power supply current sensor, the auxiliary power supply current sensor, and the load current sensor. In a state where power supply from the main power supply device to only some of the load devices has been stopped, it may be determined whether or not one of the auxiliary power supply current sensor and the load current sensor has failed based on the currents detected by each of the first main power supply current sensor, the second main power supply current sensor, the auxiliary power supply current sensor, and the load current sensor. This makes it possible to suppress an increase in the weight of the power supply system and an increase in the manufacturing cost of the power supply system.

[0113] In the power supply system, each of the auxiliary power supplies may have a battery (52) and a battery monitoring unit (78) that monitors the SOC (State Of Charge) of each of the batteries, and the failure determination unit may stop supplying power to some of the load devices when the SOC of the battery in the auxiliary power supply corresponding to some of the load devices is below a predetermined value, thereby preventing overcharging of the battery.

[0114] In the power supply system, when the supply of power to some of the load devices is stopped, the failure determination unit may increase the output power of the other load devices compared to when power is being supplied to some of the load devices. This makes it possible to compensate for the decrease in output power of some of the load devices by increasing the output power of the other load devices. [Explanation of symbols]

[0115] 22...Power supply system 26...Main power supply unit 28... Auxiliary power supply unit 30... Load module (load device) 32…Main power circuit 34…Auxiliary power circuit 36...Load circuit 52...Battery 54...Shared bus 62...Current sensor (main power supply current sensor, first main power supply current sensor) 63...Current sensor (main power supply current sensor, second main power supply current sensor) 64...Current sensor (load current sensor) 65...Current sensor (auxiliary power supply current sensor) 78... Battery monitoring unit 80... Failure determination unit

Claims

1. one or more main power supplies that provide power to one or more load devices; an auxiliary power supply unit provided corresponding to each of the load devices and supplying power to each of the load devices; a main power circuit connected to one or more of said main power devices; an auxiliary power supply circuit provided for each of the auxiliary power supplies and connected to each of the auxiliary power supplies; a load circuit provided corresponding to the load device, connected to the main power supply circuit and the auxiliary power supply circuit at a junction where a current flowing through the main power supply circuit and a current flowing through the auxiliary power supply circuit join, and connected to each of the load devices; a main power supply current sensor for detecting a current flowing through the main power supply circuit; an auxiliary power supply current sensor that detects a current flowing through the auxiliary power supply circuit; a load current sensor for detecting a current flowing through the load circuit; and each of the main power supplies supplies power to a plurality of the load devices; the main power supply circuit includes a shared bus for transmitting power from each of the main power supplies to a plurality of the load devices; the main power supply current sensors include a first main power supply current sensor provided between the main power supply device and the shared bus, and a second main power supply current sensor provided between the shared bus and each of the junction points; a failure determination unit that determines whether any of the first main power supply current sensor, the second main power supply current sensor, the auxiliary power supply current sensor, and the load current sensor has failed; The failure determination unit determining whether or not one of the first main power supply current sensor and the second main power supply current sensor has failed based on currents detected by the first main power supply current sensor, the second main power supply current sensor, the auxiliary power supply current sensor, and the load current sensor while power is being supplied from the main power supply device to all of the plurality of load devices; a power supply system that determines whether the auxiliary power supply current sensor or the load current sensor has failed based on the currents detected by the first main power supply current sensor, the second main power supply current sensor, the auxiliary power supply current sensor, and the load current sensor when the supply of power from the main power supply device to only some of the plurality of load devices has been stopped;

2. 2. The power supply system according to claim 1, Each of the auxiliary power supplies includes a battery; a battery monitoring unit that monitors the SOC (State Of Charge) of each of the batteries; The power supply system is configured such that, when the SOC of the battery in the auxiliary power supply device corresponding to the part of the load devices is less than a predetermined value, the failure determination unit stops the supply of power to the part of the load devices.

3. 3. The power supply system according to claim 1, A power supply system in which, when the supply of power to some of the load devices is stopped, the failure determination unit increases the output power of the other load devices compared to when power is being supplied to some of the load devices.

Images