Aircraft power supply system

Abstract

To provide a technique for a power supply system of an aircraft, capable of supplying electric power to a power generation device while suppressing an increase in the number of components.SOLUTION: In a power supply system 22 of an aircraft, when supplying electric power from a power generation unit 28 to a drive unit 40, the power supply system 22 supplies the electric power from the power generation unit 28 to the drive unit 40 through a first power transmission path 52, and a voltage is applied to a second power transmission path 54 by a failure detection circuit 26 in a state in which the power generation unit 28 and the drive unit 40 are disconnected from the second power transmission path 54. When the power generation unit 28 is started, electric power in the failure detection circuit 26 is supplied to the power generation unit 28 in a state in which the power generation unit 28 is connected to the second power transmission path 54.SELECTED DRAWING: Figure 7

Description

[Technical Field]

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

[0002] Patent Document 1 listed below discloses a hybrid propulsion architecture for an electric aircraft. The electric aircraft has an electric motor that drives a propeller. The electric motor operates using power supplied from a power generation device or power supplied from a battery. The power generation device includes a gas turbine, a generator, and a converter. A diode is provided between the battery and the generator to prevent current from flowing from the battery to the generator. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] International Publication No. 2021 / 089948 Summary of the Invention [Problem to be solved by the invention]

[0004] The technology disclosed in the above-mentioned Patent Document 1 does not take into consideration the supply of power to a power generation device. Because the converter's capacitor needs to be charged before the generator starts, power needs to be supplied to the converter. Furthermore, power needs to be supplied to the generator to start the gas turbine.

[0005] It is conceivable to supply power to the power generation device from the battery that supplies power to the electric motor. In this case, a switching element or the like must be provided in parallel with the diode. Alternatively, it is conceivable to provide a battery that supplies power to the power generation device separately from the battery that supplies power to the electric motor. However, in either case, there is a problem that the number of parts increases.

[0006] The present invention aims to solve the above-mentioned problems. [Means for solving the problem]

[0007] An aspect of the present invention is an aircraft power supply system, the power supply system having a first transmission line that supplies power from one or more power generation devices to one or more load devices, a second transmission line that supplies power from one or more of the power generation devices to one or more of the load devices, and a fault detection circuit that applies a voltage to the second transmission line, wherein when power is supplied from the power generation device to the load device, power is supplied from the power generation device to the load device via the first transmission line, and when the power generation device and the load device are disconnected from the second transmission line, a voltage is applied to the second transmission line by the fault detection circuit, and when the power generation device is started, power from the fault detection circuit is supplied to the power generation device with the power generation device connected to the second transmission line. [Effects of the Invention]

[0008] According to the present invention, it is possible to supply electric power to a power generation device while suppressing an increase in the number of parts. [Brief explanation of the drawings]

[0009] [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 schematic diagram of the power supply circuit. [Figure 4] FIG. 4 is a schematic diagram of the power supply circuit. [Figure 5] FIG. 5 is a schematic diagram of the power supply circuit. [Figure 6] FIG. 6 is a schematic diagram of the power supply circuit. [Figure 7] FIG. 7 is a schematic diagram of the power supply circuit. [Figure 8] FIG. 8 is a schematic diagram of the power supply circuit. [Figure 9] FIG. 9 is a diagram showing the configuration of a power supply system of a comparative example. [Figure 10] FIG. 10 is a schematic diagram showing the configuration of a power supply system. [Figure 11] FIG. 11 is a schematic diagram showing the configuration of a power supply system. DETAILED DESCRIPTION OF THE INVENTION

[0010] [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.

[0011] 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.

[0012] 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.

[0013] The aircraft 10 has eight VTOL rotors 18. The eight VTOL rotors 18 are rotor 18FLa, rotor 18FLb, rotor 18RLa, rotor 18RLb, rotor 18FRa, rotor 18FRb, rotor 18RRa, and rotor 18RRb.

[0014] The rotating shaft of each VTOL rotor 18 extends in the vertical direction. 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, when transitioning from vertical takeoff to cruising, when transitioning from cruising to vertical landing, when vertical landing, when hovering in the air, etc. Each VTOL rotor 18 is also used during attitude control.

[0015] 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.

[0016] 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.

[0017] The rotating shaft of each cruise rotor 20 extends in the fore-and-aft direction. 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.

[0018] Cruise thrust is generated by controlling the thrust of each cruise rotor 20. Cruise thrust refers to thrust in the horizontal direction.

[0019] [Power supply system configuration] FIG. 2 is a schematic diagram showing the configuration of the power supply system 22. As shown in FIG.

[0020] The power supply system 22 includes a power supply circuit 24 , a fault detection circuit 26 , two power generation units 28 , and six batteries 30 .

[0021] The power supply circuit 24 supplies power from each of the two power generation units 28 to each of the six drive modules 32. Each drive module 32 operates using the power generated by each power generation unit 28. Each drive module 32 is supplied with power stored in each battery 30, in addition to the power generated by each power generation unit 28. Each drive module 32 operates using the power supplied from each battery 30.

[0022] Each power generating unit 28 has a gas turbine 34, a generator 36, and a power control unit (hereinafter referred to as PCU) 38. The gas turbine 34 drives the generator 36, which then generates electricity. The PCU 38 converts AC power generated by the generator 36 into DC power and outputs it to the power supply circuit 24. In other words, the PCU 38 functions as an AC / DC converter, and the PCU 38 has a capacitor. Each power generating unit 28 corresponds to a power generating device of the present invention.

[0023] When starting the gas turbine 34, the PCU 38 converts the DC power supplied from the power supply circuit 24 into AC power and outputs it to the generator 36. The generator 36 operates using the power input from the PCU 38, and the generator 36 drives the gas turbine 34.

[0024] Of the six drive modules 32, four drive modules 32 each have two drive units 40. The other two drive modules 32 each have one drive unit 40 and one converter 42. Each drive unit 40 drives one of the VTOL rotors 18 or cruise rotors 20.

[0025] Each drive unit 40 has an electric motor 44 and an inverter 46. The electric motor 44 is a three-phase motor. Each VTOL rotor 18 is connected to the output shaft of the respective electric motor 44. Each cruise rotor 20 is connected to the output shaft of the respective electric motor 44. The inverter 46 converts DC power supplied from the power supply circuit 24 into three-phase AC power and outputs it to the electric motor 44. The inverter 46 has a capacitor. Each drive unit 40 corresponds to a load device of the present invention.

[0026] The converter 42 reduces the voltage of the DC power supplied from the power supply circuit 24 and outputs it to devices that operate on DC power. Devices that operate on DC power include, for example, fans that cool the PCU 38, the inverter 46, etc. Devices that operate on DC power include, for example, an ECU (Electronic Control Unit) that controls the gas turbine 34, the PCU 38, the inverter 46, the power supply circuit 24, etc.

[0027] A battery 30 is connected to each drive module 32. A circuit breaker 48 is provided between each battery 30 and each drive module 32. Each circuit breaker 48 has a contactor 48a and a contactor 48b. The contactor 48a is provided on the positive wiring connecting each battery 30 and each drive module 32. The contactor 48b is provided on the negative wiring connecting each battery 30 and each drive module 32. A current sensor 50 is provided on the negative wiring connecting each battery 30 and each drive module 32.

[0028] Each interrupting device 48 switches between a conductive state and a cut-off state between each battery 30 and each drive module 32. The conductive state is a state in which electricity flows. The cut-off state is a state in which electricity does not flow. Each interrupting device 48 may have only one of the contactor 48a and the contactor 48b.

[0029] The power supply circuit 24 has a first power transmission line 52 and a second power transmission line 54. The first power transmission line 52 supplies power from each power generation unit 28 to each drive module 32. The second power transmission line 54 supplies power from each power generation unit 28 to each drive module 32.

[0030] The power supply circuit 24 has two circuit breakers 56. Each circuit breaker 56 is provided between the corresponding power generating unit 28 and the first power transmission line 52. Each circuit breaker 56 has a contactor 56a and a contactor 56b. Each contactor 56a is provided on the positive wiring connecting the corresponding power generating unit 28 and the first power transmission line 52. Each contactor 56b is provided on the negative wiring connecting the corresponding power generating unit 28 and the first power transmission line 52. A current sensor 58 is provided between each contactor 56a and the first power transmission line 52.

[0031] Each of the breaker devices 56 switches between a conductive state and a cutoff state between each of the power generating units 28 and the first power transmission line 52 .

[0032] The power supply circuit 24 has six circuit breakers 60. Each circuit breaker 60 is provided between each drive module 32 and the first power transmission line 52. Each circuit breaker 60 has a contactor 60a and a contactor 60b. Each contactor 60a is provided on the positive wiring connecting each drive module 32 and the first power transmission line 52. Each contactor 60b is provided on the negative wiring connecting each drive module 32 and the first power transmission line 52. A current sensor 62 is provided between each contactor 60a and the first power transmission line 52.

[0033] Each of the circuit breakers 60 switches between a conductive state and a cut-off state between the corresponding drive module 32 and the first power transmission line 52 .

[0034] The power supply circuit 24 has two circuit breakers 64. Each circuit breaker 64 is provided between the corresponding power generating unit 28 and the second power transmission line 54. Each circuit breaker 64 has a contactor 64a and a contactor 64b. Each contactor 64a is provided on the positive wiring connecting the corresponding power generating unit 28 and the second power transmission line 54. Each contactor 64b is provided on the negative wiring connecting the corresponding power generating unit 28 and the second power transmission line 54. A current sensor 66 is provided between each contactor 64a and the second power transmission line 54.

[0035] Each of the breaker devices 64 switches between a conductive state and a cutoff state between each of the power generating units 28 and the second power transmission line 54 .

[0036] The power supply circuit 24 has six breaker devices 68. Each breaker device 68 is provided between each drive module 32 and the second power transmission line 54.

[0037] Each of the interrupting devices 68 switches between a conductive state and a cut-off state between the corresponding drive module 32 and the second power transmission line 54. Each of the interrupting devices 68 may include only one of the contactor 68a and the contactor 68b.

[0038] A diode 72 is provided between each battery 30 and a contact point connected to both the first power transmission line 52 and the second power transmission line 54. Each diode 72 is provided on the positive wiring connecting each battery 30 to the contact point. The anode of each diode 72 is connected to the contact point, and the cathode is connected to each battery 30. Each diode 72 allows power to be supplied from the first power transmission line 52 and the second power transmission line 54 to each battery 30. Each diode 72 prevents power from being supplied from each battery 30 to the first power transmission line 52 and the second power transmission line 54.

[0039] As a result, each battery 30 is charged by power supplied from the power generation unit 28. Furthermore, if the first power transmission line 52 or the second power transmission line 54 is short-circuited, power from each battery 30 is prevented from flowing to the first power transmission line 52 or the second power transmission line 54. As a result, even if the first power transmission line 52 or the second power transmission line 54 is short-circuited, power can be supplied from each battery 30 to the drive unit 40 and the converter 42 in each drive module 32.

[0040] A fault detection circuit 26 is connected to the second power transmission line 54. The fault detection circuit 26 has a battery 74 and a circuit breaker 76. The circuit breaker 76 is provided between the battery 74 and the second power transmission line 54. The circuit breaker 76 has a contactor 76a, a contactor 76b, and a pre-charge circuit 76c. The contactor 76a is provided on the positive wiring connecting the battery 74 and the second power transmission line 54. The contactor 76b is provided on the negative wiring connecting the battery 74 and the second power transmission line 54. A current sensor 77 is provided between the contactor 76b and the second power transmission line 54. The pre-charge circuit 76c is provided in parallel with the contactor 76b. The pre-charge circuit 76c has a contactor 76d and a resistor 76e.

[0041] The circuit breaker 76 switches between a conductive state and a cut-off state between the battery 74 and the second power transmission line 54. In the conductive state, the circuit breaker 76 switches between a state in which electricity flows further via the precharge circuit 76c and a state in which electricity flows without passing through the precharge circuit 76c.

[0042] The interrupting device 76 may include only the contactor 76b and the precharge circuit 76c. The precharge circuit 76c may be provided in parallel with the contactor 76a. In this case, the interrupting device 76 may include only the contactor 76a and the precharge circuit 76c.

[0043] [Operation of the circuit breaker] Each of Figures 3 to 8 is a schematic diagram of the power supply system 22. The schematic diagrams of Figures 3 to 8 show the circuit configuration of the power supply circuit 24 between one power generation unit 28 and one drive module 32. The operation of each circuit breaker will be explained below with reference to Figures 3 to 8. Even if there are two or more power generation units 28 and two or more drive modules 32, the operation of each circuit breaker is the same as the operation explained below, except that the number of circuit breakers increases.

[0044] (When precharging a capacitor) When precharging the capacitors of the PCU 38 and the inverter 46, the power supply system 22 brings the circuit breaker 56, the circuit breaker 60, the circuit breaker 64, and the circuit breaker 76 into a conductive state, as shown in Fig. 3. The circuit breaker 76 is brought into a state in which electricity flows through the precharge circuit 76c (Fig. 2). The power supply system 22 brings the circuit breaker 48 and the circuit breaker 68 into a cut-off state.

[0045] As a result, power is supplied from the battery 74 to each of the PCU 38 and the inverter 46. The power supplied from the battery 74 charges the capacitors of the PCU 38 and the inverter 46.

[0046] (When starting a gas turbine) When starting the gas turbine 34, the power supply system 22 turns on each of the circuit breaker devices 48, 56, 60, 64, and 76 as shown in Fig. 4. The circuit breaker device 76 is set to a state in which electricity flows without passing through the precharge circuit 76c (Fig. 2). The power supply system 22 turns off the circuit breaker device 68.

[0047] As a result, power is supplied from the battery 74 to the generator 36. The generator 36 operates using the power supplied from the battery 74, and the generator 36 drives the gas turbine 34.

[0048] (When operating an electric motor (1)) When operating the electric motor 44, the power supply system 22 turns on each of the circuit breaker devices 48, 56, 60, and 76 as shown in Fig. 5. The circuit breaker device 76 is set to a state in which electricity flows through the precharge circuit 76c (Fig. 2). The power supply system 22 turns off each of the circuit breaker devices 64 and 68.

[0049] As a result, power is supplied from the generator 36 to each electric motor 44 via the first power transmission line 52. Power is also supplied from the battery 30 to each electric motor 44. Each electric motor 44 operates using the power supplied from the generator 36 and the battery 30, and each electric motor 44 drives the VTOL rotor 18.

[0050] The fault detection circuit 26 applies a voltage to the second power transmission line 54. However, since the breaker device 64 and the breaker device 68 are both in an interrupted state, no current flows through the second power transmission line 54.

[0051] (If the second transmission line is short-circuited) A voltage is applied to the unused second power transmission line 54. Therefore, if the second power transmission line 54 is short-circuited as shown in FIG. 6, a current flows between the fault detection circuit 26 and the short-circuited location. The flow of current can be determined based on the current value detected by the current sensor 77 (FIG. 2). This makes it possible to detect a short circuit in the second power transmission line 54 even when the second power transmission line 54 is not in use.

[0052] Since the circuit breaker 64 and the circuit breaker 68 are in the disconnected state, the influence of a short circuit in the second power transmission line 54 on other parts of the power supply circuit 24 can be suppressed.

[0053] (If the first transmission line is short-circuited) If the first power transmission line 52 is short-circuited, an overcurrent flows between the power generation unit 28 and the first power transmission line 52. The flow of an overcurrent can be determined based on the current value detected by the current sensor 58 (FIG. 2). If the first power transmission line 52 is short-circuited, a protective device (not shown) stops the gas turbine 34 and the generator 36.

[0054] When the first power transmission line 52 is short-circuited, the power supply system 22 switches the circuit breaker 56 and the circuit breaker 60 to an interrupted state, as shown in Fig. 7. This makes it possible to suppress the influence of the short-circuit in the first power transmission line 52 on other parts of the power supply circuit 24.

[0055] When the first power transmission line 52 is short-circuited, the circuit breaker 48 maintains a conductive state. Therefore, the electric motors 44 are operated by the power supplied from the battery 30, and the electric motors 44 drive the VTOL rotors 18.

[0056] Thereafter, when the gas turbine 34 is to be restarted, the power supply system 22 sets the circuit breaker 64 to a conductive state while keeping the circuit breaker 56 and the circuit breaker 60 in a circuit breaker state, as shown in Fig. 7. This causes power to be supplied from the battery 74 to the generator 36. The generator 36 operates using the power supplied from the battery 74, and drives the gas turbine 34.

[0057] (When operating an electric motor (2)) When the electric motor 44 is operated in a state in which the first power transmission line 52 is short-circuited, the power supply system 22 sets each of the circuit breaker 48, the circuit breaker 64, and the circuit breaker 68 to a conductive state, as shown in Fig. 8. The power supply system 22 sets each of the circuit breaker 56, the circuit breaker 60, and the circuit breaker 76 to a disconnected state.

[0058] As a result, power is supplied from the generator 36 to each electric motor 44 via the second power transmission line 54. Power is also supplied from the battery 30 to each electric motor 44. Each electric motor 44 operates using the power supplied from the generator 36 and the battery 30, and each electric motor 44 drives the VTOL rotor 18.

[0059] [Action and effect] 9 is a diagram showing the configuration of a power supply system 100 of a comparative example. The power supply system 100 of the comparative example differs from the power supply system 22 of this embodiment shown in FIG.

[0060] First, in the power supply system 100 of the comparative example, a transistor 78 is provided in parallel with each diode 72. Second, in the power supply system 100 of the comparative example, the interrupter 48 has a precharge circuit 48c. The precharge circuit 48c is provided in parallel with the contactor 48b. The precharge circuit 48c has a contactor 48d and a resistor 48e. Third, in the power supply system 100 of the comparative example, the interrupter 76 of the fault detection circuit 26 does not have a precharge circuit 76c.

[0061] When charging the capacitor of each PCU 38 or starting the gas turbine 34, the power supply system 22 in the comparative example power supply system 100 turns on the transistor 78. This causes power to be supplied from each battery 30 to each power generating unit 28, bypassing the diode 72. In the comparative example power supply system 100, the fault detection circuit 26 only applies voltage to the second power transmission line 54 that is not in use.

[0062] In the power supply system 22 of this embodiment, when charging the capacitor of each PCU 38 or starting the gas turbine 34, power from the battery 74 of the fault detection circuit 26 is supplied to the power generation unit 28. In the power supply system 22 of this embodiment, the fault detection circuit 26 also applies voltage to the unused second power transmission line 54. As a result, the power supply system 22 of this embodiment can eliminate the transistor 78 provided in the power supply system 100 of the comparative example. Therefore, in the power supply system 22 of this embodiment, the number of parts constituting the power supply circuit 24 can be reduced. Furthermore, the reliability of the power supply system 22 can be improved.

[0063] Second Embodiment FIG. 10 is a schematic diagram showing the configuration of the power supply system 22. As shown in FIG.

[0064] In this embodiment, the fault detection circuit 26 is connected to both the first power transmission line 52 and the second power transmission line 54. The fault detection circuit 26 includes a switching device 80. The switching device 80 switches between a state in which the fault detection circuit 26 applies a voltage to the first power transmission line 52 and a state in which the fault detection circuit 26 applies a voltage to the second power transmission line 54.

[0065] The power supply system 22 switches between a state in which power is supplied from each power generation unit 28 to each drive module 32 via a first power transmission line 52 and a state in which power is supplied from each power generation unit 28 to each drive module 32 via a second power transmission line 54. When the first power transmission line 52 is not in use, the power supply system 22 uses the switching device 80 to set the fault detection circuit 26 to a state in which a voltage is applied to the first power transmission line 52. When the second power transmission line 54 is not in use, the power supply system 22 uses the switching device 80 to set the fault detection circuit 26 to a state in which a voltage is applied to the second power transmission line 54.

[0066] [Action and effect] The power supply system 22 of this embodiment includes a switching device 80 that switches between a state in which the fault detection circuit 26 applies a voltage to the first power transmission line 52 and a state in which the fault detection circuit 26 applies a voltage to the second power transmission line 54.

[0067] This allows a single fault detection circuit 26 to detect a short circuit in the first power transmission line 52 when the first power transmission line 52 is not in use, and to detect a short circuit in the second power transmission line 54 when the second power transmission line 54 is not in use.

[0068] Third Embodiment FIG. 11 is a schematic diagram showing the configuration of the power supply system 22. As shown in FIG.

[0069] In the power supply system 22 of this embodiment, a battery that supplies power to an accessory device 82 is used as the battery 74 in the fault detection circuit 26. A converter 84 is provided between the battery 74 and the circuit breaker 76. The converter 84 boosts the voltage of the DC power supplied from the battery 74 and outputs it to the circuit breaker 76.

[0070] The accessory device 82 is, for example, an air conditioner installed in the body 12. The accessory device 82 is, for example, a refrigerator installed in the body 12.

[0071] [Action and effect] In the power supply system 22 of the present embodiment, a battery that supplies power to the accessory device 82 is used as the battery 74 of the failure detection circuit 26. This allows the power supply system 22 of the present embodiment to reduce the number of parts that make up the failure detection circuit 26.

[0072] 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.

[0073] The power supply system 22 of the first to third embodiments supplies power from each of two power generation units 28 to each of ten drive units 40. However, the number of power generation units 28 may be one or more. The number of drive units 40 may be one or more.

[0074] [Inventions Obtained from the Embodiments] The invention that can be understood from the above embodiment will be described below.

[0075] A power supply system (22) for an aircraft (10) includes a first power transmission line (52) that supplies power from one or more power generators (28) to one or more load devices (40), a second power transmission line (54) that supplies power from the one or more power generators to the one or more load devices, and a fault detection circuit (26) that applies a voltage to the second power transmission line, wherein when power is supplied from the power generators to the load devices, power is supplied from the power generators to the load devices via the first power transmission line, and when the power generators and the load devices are disconnected from the second power transmission line, a voltage is applied to the second power transmission line by the fault detection circuit, and when the power generators are started, power from the fault detection circuit is supplied to the power generators with the power generators connected to the second power transmission line. This reduces the number of components and improves the reliability of the power supply system.

[0076] In the above-described aircraft power supply system, the fault detection circuit may include a switching device (80) that switches between a state in which a voltage is applied to the first power transmission line and a state in which a voltage is applied to the second power transmission line. This allows a single fault detection circuit to detect a short circuit in the first power transmission line when the first power transmission line is not in use, and to detect a short circuit in the second power transmission line when the second power transmission line is not in use.

[0077] The above-described aircraft power supply system may further include a power storage device (30) connected to the load device, and a diode (72) that allows power to be supplied from the first power transmission line and the second power transmission line to the power storage device and inhibits power supply from the power storage device to the first power transmission line and the second power transmission line. This prevents power from the power storage device from flowing to the first power transmission line or the second power transmission line when the first power transmission line or the second power transmission line is short-circuited. As a result, power can be supplied from the power storage device to the load device even when the first power transmission line or the second power transmission line is short-circuited.

[0078] In the above-described aircraft power supply system, a battery that supplies power to an accessory device 82 installed in the aircraft fuselage 12 may be used as the battery of the failure detection circuit, thereby reducing the number of components constituting the failure detection circuit. [Explanation of symbols]

[0079] 10...Aircraft 22...Power supply system 26...Fault detection circuit 28...Power generation unit (power generation device) 30... Battery (electricity storage device) 40... Drive unit (load device) 52...1st power transmission line 54...2nd power transmission line 72...Diode 80...Switching device 82...Accessory device

Claims

1. 1. An aircraft power supply system, comprising: a first transmission line that supplies electric power from one or more power generation devices to one or more load devices; a second power transmission line that supplies electric power from one or more of the power generation devices to one or more of the load devices; a fault detection circuit that applies a voltage to the second power transmission line; and When power is supplied from the power generation device to the load device, power is supplied from the power generation device to the load device via the first power transmission line, and in a state where the power generation device and the load device are disconnected from the second power transmission line, a voltage is applied to the second power transmission line by the fault detection circuit; When starting the power generation device, the power generation device is connected to the second power transmission path and power from the fault detection circuit is supplied to the power generation device.

2. 2. The aircraft power supply system according to claim 1, The power supply system of an aircraft, wherein the fault detection circuit has a switching device that switches between a state in which a voltage is applied to the first power transmission line and a state in which a voltage is applied to the second power transmission line.

3. 3. The aircraft power supply system according to claim 1 or 2, a power storage device is connected to the load device; a diode that allows power to be supplied from the first power transmission line and the second power transmission line to the power storage device and inhibits power supply from the power storage device to the first power transmission line and the second power transmission line.

4. The power supply system for an aircraft according to any one of claims 1 to 3, An aircraft power supply system, wherein a battery that supplies power to an accessory device installed in the fuselage of the aircraft is used as the battery of the failure detection circuit.

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