JP7204999B1 - Lightning Strike Determination Control Device, Power Supply System, and Lightning Strike Determination Control Method - Google Patents

Abstract

A lightning strike determination control device (10) includes an acquisition unit (11) that acquires lightning discharge waveform data detected by a lightning sensor (15), and a lightning discharge waveform data acquired by the acquisition unit (11). a detection unit (12) for detecting a predischarge before the main discharge occurs; a determination unit (13) for determining that a lightning strike is received when the predischarge of lightning is detected by the detection unit (12); and a control unit (14) for closing a grounding device (26) connected to the ground line (25) before main discharge of lightning occurs when the unit (13) determines that a lightning strike occurs.

Description

The present disclosure relates to a lightning strike determination control device, a power supply system, and a lightning strike determination control method.

Patent Literature 1 discloses a technique for detecting a lightning strike based on an electric field generated by the main discharge of lightning.

JP-A-4-9792

Here, aircraft, wind power generation facilities, and the like may be damaged by lightning strikes. When the technology disclosed in Patent Document 1 is applied to such an aircraft and wind power generation equipment, even if a lightning strike can be detected at the interface between the aircraft and the wind power generation equipment, the current of the lightning strike is There is a risk of intrusion into those power systems.

Specifically, some aircraft have fuselages manufactured using insulating or high resistance materials, such as carbon fiber reinforced plastics. Such an aircraft has a lower shielding effect against electromagnetic fields than an aircraft having a metal airframe. Therefore, if an aircraft is struck by lightning, the current from the lightning strike may enter the power system within the aircraft and damage the power system.

Some aircraft also include generators, motors, and propulsion fans. This aircraft obtains propulsion by driving a motor using electric power generated by a generator, and driving the motor to rotate a propulsion fan. In such an aircraft, since an opening is formed in the fuselage facing the propulsion fan, the shielding effect against the electromagnetic field is reduced. Therefore, if an aircraft is struck by lightning, the current from the lightning strike may enter the power system in the aircraft via the fan and the motor directly connected thereto, and damage the power system.

If a wind power generation facility is struck by lightning, the current from the lightning strike may enter the power system in the facility via the windmill and the generator and damage the power system.

SUMMARY OF THE INVENTION The present disclosure has been made to solve the above problems, and an object of the present disclosure is to provide a lightning strike determination control device capable of causing a lightning current to flow through a ground wire before the main discharge of a lightning strike occurs. and

A lightning strike determination control device according to the present disclosure includes an acquisition unit that acquires discharge waveform data of a lightning strike on an aircraft, which is detected by a lightning sensor provided on the aircraft , and the lightning discharge waveform data acquired by the acquisition unit. a detection unit for detecting a predischarge before the main discharge of a lightning strike and a main discharge that occurs immediately after the predischarge; and a circuit that supplies power from the power supply to the motor to obtain the propulsion force of the aircraft before the main discharge of the lightning strike occurs when the determination unit determines that the lightning strike has occurred. and a control unit that closes an earthing device that is connected to the earthing wire and causes current caused by a lightning strike that has entered the circuit to flow through the earthing wire .

According to the present disclosure, since it is configured as described above, it is possible to cause the lightning current to flow through the ground line before the main discharge of the lightning strike occurs.

1 is a circuit diagram showing a configuration of an aircraft power supply system to which a lightning strike determination control device according to Embodiment 1 is applied; FIG. 3 is a diagram showing the configuration of a power supply; FIG. 1 is a block diagram showing the configuration of a lightning strike determination control device according to Embodiment 1; FIG. FIG. 4 is a diagram showing a discharge waveform (electric field intensity waveform) of a lightning strike; 1 is a diagram showing a configuration of an aircraft to which a power supply system according to Embodiment 1 is applied; FIG. 1 is a circuit diagram showing a configuration of a power supply system having multiple load devices; FIG. 4 is a flowchart showing a lightning strike determination control method according to Embodiment 1; 8A and 8B are diagrams showing an example of the hardware configuration of the lightning strike determination control device according to Embodiment 1. FIG. FIG. 10 is a circuit diagram showing the configuration of an aircraft power supply system to which a lightning strike determination control device according to a second embodiment is applied; FIG. 11 is a circuit diagram showing the configuration of an aircraft power supply system to which a lightning strike determination control device according to a third embodiment is applied; FIG. 10 is a diagram showing the configuration of an aircraft to which a power supply system according to Embodiment 3 is applied; FIG. 10 is a diagram showing the configuration of an aircraft to which a lightning strike determination control device according to Embodiment 4 is applied; FIG. 10 is a diagram showing the configuration of an earthing switch in an aircraft power supply system to which a lightning strike determination control device according to Embodiment 5 is applied; FIG. 12 is a diagram showing the configuration of an earthing switch in an aircraft power supply system to which a lightning strike determination control device according to a sixth embodiment is applied; It is a principal part enlarged view of an earthing|grounding switch. FIG. 15A is a diagram showing a state in which fixed-side electrodes and movable-side electrodes are not connected. FIG. 15B is a diagram showing a state in which fixed-side electrodes and movable-side electrodes are connected. FIG. 12 is a diagram showing the configuration of a wind power generation facility to which a lightning strike determination control device according to Embodiment 7 is applied; FIG. 13 is a circuit diagram showing the configuration of a power supply system for wind power generation equipment to which a lightning strike determination control device according to Embodiment 7 is applied; FIG. 12 is a circuit diagram showing the configuration of a power supply system for wind power generation equipment to which a lightning strike determination control device according to an eighth embodiment is applied;

Hereinafter, in order to describe the present disclosure in more detail, embodiments for carrying out the present disclosure will be described with reference to the accompanying drawings.

Embodiment 1.
A lightning strike determination control device 10 according to Embodiment 1 will be described with reference to FIGS. 1 to 8. FIG.

FIG. 1 is a circuit diagram showing the configuration of an aircraft power supply system to which a lightning strike determination control device 10 according to Embodiment 1 is applied. FIG. 2 is a diagram showing the configuration of the power supply 21. As shown in FIG. FIG. 3 is a block diagram showing the configuration of the lightning strike determination control device 10 according to Embodiment 1. As shown in FIG. FIG. 4 is a diagram showing a discharge waveform (electric field strength waveform) of a lightning strike. FIG. 5 is a diagram showing the configuration of an aircraft to which the power supply system according to Embodiment 1 is applied.

As shown in FIG. 1, the aircraft power supply system includes a lightning strike determination control device 10, a lightning sensor 15, a power source 21, a load device 22, a switch 23, a current path 24, a ground wire 25, a grounding device 26, and a grounding device. A circuit 27 is provided. The energization path 24 is, for example, a cable or the like. The switch 23 and the grounding device 26 are, for example, mechanical switches.

The power source 21 and the load device 22 are connected via a switch 23 and an electricity path 24 . The load device 22 is a device to which power is supplied, and operates by receiving current from the power supply 21 via the switch 23 and the conduction path 24 . The switch 23 connects the power supply 21 and the current path 24 by closing. Moreover, the switch 23 cuts off between the power source 21 and the energization path 24 by opening.

The grounding device 26 connects the conducting path 24 and the grounding wire 25 . The grounding switch 26 connects the current-carrying path 24 to the grounding line 25 by closing. In addition, the grounding device 26 insulates the conducting path 24 from the grounding wire 25 by opening.

FIG. 1 shows a state in which the switch 23 is closed and the earthing switch 26 is open. In such a state, power output from power supply 21 is supplied to load device 22 .

The ground circuit 27 connects the power supply 21 and the ground line 25 . Here, the current supplied from the power supply 21 to the load device 22 may be AC or DC. For example, when the current supplied from the power supply 21 to the load device 22 is three-phase alternating current, the three-phase neutral point is connected to the ground circuit 27 .

As shown in FIG. 2, the power supply 21 has, for example, a housing 21a, an internal circuit 21b, and a stray capacitance 21c. An internal circuit 21b and a stray capacitance 21c are provided inside the housing 21a. A stray capacitance 21c exists between the inner surface of the housing 21a and the internal circuit 21b. The internal circuit 21 b is connected to one end of the switch 23 . The floating capacitance 21c is connected to the ground circuit 27. FIG.

The lightning strike determination control device 10 is connected to the lightning sensor 15 , the switch 23 and the grounding device 26 . The lightning sensor 15 detects data on lightning discharge waveforms. The lightning sensor 15 also outputs the detected lightning discharge waveform data to the lightning strike determination control device 10 . The lightning strike determination control device 10 controls opening/closing of the switch 23 and opening/closing of the grounding switch 26 based on the acquired lightning discharge waveform data.

In place of the lightning sensor 15, the power supply system may be an antenna for measuring electric field intensity or a current sensor for detecting current flowing through the airframe 20 of the aircraft.

As shown in FIG. 3 , the lightning strike determination control device 10 has an acquisition unit 11 , a detection unit 12 , a determination unit 13 , and a control unit 14 .

The obtaining unit 11 obtains discharge waveform data of lightning detected by the lightning sensor 15 .

Here, the lightning discharge waveform data detected by the lightning sensor 15 is sent to the acquisition unit 11 moment by moment. FIG. 4 shows the discharge waveform of the lightning. The vertical axis in FIG. 4 indicates the electric field intensity, and the horizontal axis in FIG. 4 indicates time. A lightning discharge waveform can be divided into a first half waveform W1 and a second half waveform W2. The waveform W1 in the first half indicates the predischarge, and the waveform W2 in the second half indicates the main discharge. A predischarge is a precursor phenomenon of a lightning strike and occurs before a lightning strike occurs. A main discharge is generated when a lightning strike occurs.

The detection unit 12 detects a lightning precursor discharge and a main discharge from the lightning discharge waveform data acquired by the acquisition unit 11 .

The determination unit 13 determines that a lightning strike is received when the detection unit 12 detects the predischarge of lightning.

When the determination unit 13 determines that the lightning strike occurs, the control unit 14 cuts off the current to the target device before the lightning generates the main discharge, and the energization path 24 through which the current flows to the target device is grounded. Close the grounding device 26 that connects with line 25 . More specifically, when the determination unit 13 determines that lightning strikes, the control unit 14 opens the switch 23 and closes the earthing switch 26 before the lightning causes the main discharge.

Further, after a predetermined period of time has passed since the detection unit 12 detected the main discharge of lightning, the control unit 14 causes the current to flow to the target device and opens the grounding device 26 . More specifically, when the main discharge of lightning ends, the control unit 14 closes the switch 23 and opens the grounding switch 26 .

Specifically, as shown in FIG. 4, a lightning sensor 15 is provided at the tip of the airframe 20 of the aircraft. The lightning sensor 15 sends the detected lightning discharge waveform data to the lightning strike determination control device 10 from time to time.

Then, when the lightning strike determination control device 10 determines that the detected electric field strength value exceeds a preset threshold value in the time period in which the waveform W1 corresponding to the predischarge occurs, the switch 23 and the ground It outputs an operation start command to the device 26 . The time zone in which the waveform W1 corresponding to the precursor discharge is generated is, for example, 2 to 3 ms before the start time of generation of the waveform W2 corresponding to the main discharge.

In response to this, the switch 23 starts the opening operation. On the other hand, the earthing switch 26 starts closing operation. The switch 23 and the grounding switch 26 complete their operation by the time the lightning main discharge occurs. Completion of the operation of the switch 23 indicates the time when the current supplied from the power supply 21 is cut off after receiving the operation start command from the lightning strike determination control device 10 . Completion of the operation of the earthing switch 26 indicates the time when the contacts are closed after receiving an operation start command from the lightning strike determination control device 10 . At this time, after the opening operation of the switch 23 is started, the closing operation of the grounding device 26 is started. That is, the period of 2 to 3 ms is a period required until the opening operation of the switch 23 and the closing operation of the grounding switch 26 are completed.

Further, when the main discharge of lightning has finished occurring, the lightning strike determination control device 10 restores the circuit of the power supply system to the original state before the occurrence of lightning. That is, the lightning strike determination control device 10 outputs a return command to the switch 23 and the grounding device 26 . In response to this, the switch 23 starts closing operation. On the other hand, the earthing switch 26 starts opening operation. At this time, the opening operation of the switch 23 is started after the opening operation of the earthing switch 26 is started.

Further, as shown in FIG. 5 , when the airframe 20 is struck by lightning, the lightning current flows from the front to the tail of the airframe 20 or from the tail to the head of the airframe 20 . At this time, if the fuselage 20 is covered with a metal skin, the lightning current flows along the outer surface of the skin. Since the metal skin is effective in electromagnetic shielding, it is considered that the lightning current has little electromagnetic influence on the interior of the fuselage 20 .

However, in recent years, some aircraft have outer skins made of carbon fiber reinforced plastic. In such an aircraft, the lightning current flows along the outer surface of the skin or along the metal fuselage frame that forms the skeleton of the fuselage 20, causing dielectric breakdown. Therefore, an aircraft whose skin is made of carbon fiber reinforced plastic has a lower electromagnetic shielding effect than an aircraft whose skin is made of a metal material, and may cause electromagnetic induction inside the fuselage 20 .

For example, as shown in FIG. 4, a lightning current flows with the occurrence of a main discharge with a sharp change in magnetic field strength. Since the discharge waveform of lightning is a triangular pulse waveform, a voltage is generated in the conducting path 24 due to electromagnetic induction from the current of the lightning, and an induced current flows through the conducting path 24 . This induced current flows to the ground line 25 via the ground circuit 27 and stray capacitance 21c of the power supply 21. At this time, if the power supply 21 is destroyed by the induced current, or if the power supply 21 suffers from insulation failure, After the occurrence, the power supply 21 may be destroyed due to the follow-on of the induced current becoming a short-circuit current.

Generally, lightning induced currents can be suppressed by lightning arresters using zinc oxide elements. Therefore, when the outer skin of an aircraft is made of carbon fiber reinforced plastic, the induced current of lightning increases, so a lightning arrester with a large current carrying capacity is required. In addition, since the lightning arrester operates after the main discharge of lightning occurs, there are cases where a high voltage is temporarily generated in the aircraft. Therefore, aircraft require lightning arresters with greater current-carrying capacity to reduce it.

On the other hand, the lightning strike determination control device 10 according to the first embodiment grounds the circuit of the power supply system before the main discharge of the lightning strike occurs when the airframe 20 of the aircraft is likely to be struck by lightning. ing. Therefore, the lightning strike determination control device 10 can cause the lightning induced current to flow through the ground wire 25 , and can suppress application of a high voltage to the load device 22 . Further, when the lightning strike determination control device 10 and a lightning arrester are used together, the lightning arrester has a small current carrying capacity. Therefore, the lightning strike determination control device 10 can reduce the size and weight of the lightning arrester.

6 is a circuit diagram showing the configuration of a power supply system having a plurality of load devices 22. As shown in FIG. As shown in FIG. 6, in the power supply system, when a plurality of load devices 22 are provided for one power source 21, the circuit includes branch lines 28, for example. The branch lines 28 correspond to the number of load devices 22 and are connected to the power supply 21 . A switch 23 and a grounding device 26 are connected to the tip of the branch line 28 in pairs. At this time, the lightning strike determination control device 10 is connected to the switches 23 and grounding devices 26 of each set (for each branch). The lightning strike determination control device 10 can control each set of switches 23 and grounding switches 26 at the same time. FIG. 6 shows a configuration example of a power supply system having two load devices 22. As shown in FIG.

Next, a lightning strike determination control method according to Embodiment 1 will be described with reference to FIG. FIG. 7 is a flow chart of the lightning strike determination control method according to the first embodiment.

As shown in FIG. 7, in step ST11, the acquisition unit 11 acquires discharge waveform data of lightning detected by the lightning sensor 15. FIG.

In step ST<b>12 , the detection unit 12 detects a precursor discharge before the main discharge of lightning occurs from the lightning discharge waveform data acquired by the acquisition unit 11 .

In step ST<b>13 , when the detector 12 detects a lightning predischarge, the determination unit 13 determines that lightning strikes.

In step ST14, when the determination unit 13 determines that the lightning strikes, the control unit 14 closes the grounding device 26 before the lightning generates the main discharge. Then, the lightning strike determination control method ends.

Next, the hardware configuration of the lightning strike determination control device 10 will be described using FIG. 8A and 8B are diagrams showing an example of the hardware configuration of the lightning strike determination control device 10 according to Embodiment 1. FIG.

As shown in FIG. 8A, the lightning strike determination control device 10 is configured by a computer, and the computer has a processor 91 and a memory 92 . The memory 92 stores programs for causing the computer to function as the acquisition unit 11 , the detection unit 12 , the determination unit 13 , and the control unit 14 . The functions of the acquisition unit 11, the detection unit 12, the determination unit 13, and the control unit 14 are realized by the processor 91 reading and executing the programs stored in the memory 92. FIG.

Moreover, as shown in FIG. 8B, the lightning strike determination control device 10 may be configured by a processing circuit 93 . In this case, the processing circuit 93 may implement the functions of the acquisition unit 11 , the detection unit 12 , the determination unit 13 , and the control unit 14 .

Furthermore, the lightning strike determination control device 10 may be configured by a processor 91, a memory 92, and a processing circuit 93 (not shown). In this case, some of the functions of the acquisition unit 11, the detection unit 12, the determination unit 13, and the control unit 14 are implemented by the processor 91 and the memory 92, and the remaining functions are implemented by the processing circuit 93. It can be anything.

The processor 91 uses, for example, a CPU (Central Processing Unit), a GPU (Graphics Processing Unit), a microprocessor, a microcontroller, or a DSP (Digital Signal Processor).

The memory 92 uses, for example, a semiconductor memory or a magnetic disk. More specifically, the memory 92 includes RAM (Random Access Memory), ROM (Read Only Memory), flash memory, EPROM (Erasable Programmable Read Only Memory), EEPROM (Electrically Erasable Programmable Read Only Memory), SD (Electrically Erasable Programmable Solid-On Memory). State Drive), HDD (Hard Disk Drive), or the like is used.

The processing circuit 93 is, for example, ASIC (Application Specific Integrated Circuit), PLD (Programmable Logic Device), FPGA (Field-Programmable Gate Array), SoC (System-on-a-Chip), or system LSI (Large-Scale Integration).

As described above, the lightning strike determination control device 10 according to the first embodiment includes the acquisition unit 11 that acquires the lightning discharge waveform data detected by the lightning sensor 15, and the lightning discharge waveform data acquired by the acquisition unit 11. a detection unit 12 for detecting a predischarge before the main discharge occurs; a determination unit 13 for determining that a lightning strike is received when the detection unit 12 detects a lightning predischarge; and the determination unit 13 receives the lightning strike. and a control unit 14 that closes the grounding device 26 connected to the grounding wire 25 until the main discharge of lightning occurs when it is determined. Therefore, the lightning strike determination control device 10 can cause the lightning current to flow through the ground wire 25 before the main discharge of the lightning strike occurs.

In the lightning strike determination control device 10, the detection unit 12 detects the main discharge of lightning from the lightning discharge waveform data, and the control unit 14 detects the main discharge of lightning for a predetermined period after the detection unit 12 detects the main discharge of lightning. After the passage of time, the grounding switch 26 is opened. Therefore, the lightning strike determination control device 10 can easily restore the current circuit state to the original circuit state before the lightning strike after the lightning main discharge occurs.

Embodiment 2.
A power supply system according to Embodiment 2 will be described in detail with reference to FIG. FIG. 9 is a circuit diagram showing the configuration of an aircraft power supply system to which the lightning strike determination control device 10 according to the second embodiment is applied.

As shown in FIG. 9, the load device 22 in the power supply system according to the second embodiment includes a current converter 31, a motor 32, and a fan 33. As shown in FIG. This load device 22 is configured by connecting a current converter 31, a motor 32, and a fan 33 in this order.

Current converter 31 controls the magnitude of the current supplied from power supply 21 . The rotation speed of the motor 32 is controlled according to the magnitude of the current controlled by the current converter 31 . The fan 33 is directly connected to the rotating shaft 32 a of the motor 32 and rotates together with the rotating shaft 32 a of the motor 32 . Therefore, the aircraft obtains propulsive force by rotating the fan 33 .

If the motor 32 is synchronized with the frequency of the power supply 21, the current converter 31 can be omitted from the power supply system.

The switch 23 connects the power supply 21 and the current converter 31 by closing. Moreover, the switch 23 cuts off between the power supply 21 and the current converter 31 by opening.

The grounding device 26 connects the conducting path 24 and the grounding wire 25 . The grounding switch 26 connects the current-carrying path 24 to the grounding line 25 by closing. In addition, the grounding device 26 insulates the conducting path 24 from the grounding wire 25 by opening.

As described above, the power supply system according to the second embodiment includes the motor 32 to which power is supplied from the power supply 21, the current converter 31 that controls the magnitude of the current supplied to the motor 32, the power supply 21 and the current converter. a switch 23 connected between the switch 23 and the current converter 31, an earthing device 26 having one end connected between the switch 23 and the current converter 31 and the other end connected to the ground wire 25, the switch 23 and the earthing device and a lightning strike determination control device 10 having a control unit 14 connected to 26 . Therefore, the power supply system can cause the lightning current to flow through the ground line 25 before the main discharge of the lightning strike occurs.

Embodiment 3.
A power supply system according to Embodiment 3 will be described with reference to FIGS. 10 and 11. FIG. FIG. 10 is a circuit diagram showing the configuration of an aircraft power supply system to which the lightning strike determination control device 10 according to the third embodiment is applied. FIG. 11 is a diagram showing the configuration of an aircraft to which the power supply system according to Embodiment 3 is applied.

The power supply system according to the third embodiment shown in FIG. 10 has the same components as the power supply system according to the second embodiment shown in FIG. The connection destination is different.

As shown in FIG. 10, one end of the grounding device 26 is connected to a connection line connecting the current converter 31 and the motor 32 . Also, the other end of the grounding device 26 is connected to the grounding wire 25 . An output terminal of the lightning strike determination control device 10 is connected to the grounding device 26 and the current converter 31 . That is, the lightning strike determination control device 10 outputs an operation start command and a return command to the grounding device 26 and the current converter 31 .

When the current converter 31 receives an operation start command from the control unit 14 of the lightning strike determination control device 10 , the current converter 31 stops normal current conversion operation and stops energizing the motor 32 . The earthing switch 26 starts the closing operation when receiving an operation start command from the control unit 14 of the lightning strike determination control device 10 . The earthing switch 26 and the current transformer 31 complete their operation by the time the lightning main discharge occurs. At this time, the closing operation of the grounding device 26 is started after the current converter 31 is started to be deenergized.

Further, when the current converter 31 receives a return command from the control unit 14 of the lightning strike determination control device 10 , the current converter 31 performs a normal current conversion operation and starts energizing the motor 32 . The grounding device 26 starts opening operation when receiving a return command from the control unit 14 of the lightning strike determination control device 10 . At this time, the energization operation of the current converter 31 is started after the opening operation of the earthing device 26 is started.

The switching operation between energization and energization stoppage in the current converter 31 is performed by the opening/closing operation of a switch using a semiconductor. Therefore, the switching operation of the current converter 31 is performed at a higher speed than the switching operation of the switch 23, which is a mechanical switch.

As shown in FIG. 11, when the fan 33 provided in the tail of the aircraft is struck by lightning, the lightning current mainly flows toward the skin of the aircraft (thick solid line). , some (thin solid lines) intrude into the circuit via the fan 33 as they are. At this time, even if the lightning current is shunted into the circuit, the current converter 31 stops energizing and the earthing switch 26 is closed. , and flows toward the ground line 25 . Therefore, the power supply 21 and the current converter 31 are not damaged by the lightning current.

On the other hand, when the lightning strike determination control device 10 is not provided, the lightning current diverted from the fan 33 into the circuit flows from the motor 32 to the current converter 31 and the power supply 21 as indicated by the dotted line in FIG. through the ground line 25 . Therefore, the power supply 21 and the current converter 31 are damaged by the lightning current.

As described above, the power supply system according to Embodiment 3 includes the motor 32 to which the current is supplied from the power supply 21, the current converter 31 that controls the magnitude of the current supplied to the motor 32, and the current converter 31 that has one end. and the motor 32 , the other end of which is connected to the ground wire 25 ; Therefore, the power supply system can cause the lightning current to flow through the ground line 25 before the main discharge of the lightning strike occurs.

Embodiment 4.
A power supply system according to Embodiment 4 will be described with reference to FIG. FIG. 12 is a diagram showing the configuration of an aircraft to which the lightning strike determination control device 10 according to the fourth embodiment is applied.

A power supply system according to Embodiment 4 shown in FIG. For this reason, when the power supply system includes the current converter 31, the motor 32, and the fan 33 as the target devices, the lightning sensor 15 is provided on the rotation shaft 32a of the motor 32 to detect lightning current in the circuit. It becomes easier to catch direct intrusions into As a result, the lightning strike determination control device 10 can improve the accuracy of determining the presence or absence of a lightning strike.

As described above, in the power supply system according to the fourth embodiment, the motor 32 has the rotating shaft 32a connected to the fan 33, and the lightning sensor 15 is provided on the rotating shaft 32a. Therefore, it is possible to detect the direct intrusion of current into the circuit.

Embodiment 5.
A lightning strike determination control device 10 according to Embodiment 5 will be described with reference to FIG. FIG. 13 is a diagram showing the configuration of an earthing switch 26 in an aircraft power supply system to which the lightning strike determination control device 10 according to the fifth embodiment is applied.

As shown in FIG. 13, the grounding switch 26, which is a mechanical switch, is composed of a fixed portion and a movable portion. The fixed part and the movable part are arranged coaxially.

The fixed portion of the grounding device 26 is composed of a fixed electrode 41A, a buffer member 42, an insulator 43, a fixed member 44, a flexible conductor 45, and a conductor 46. As shown in FIG. The fixed-side electrode 41A is fixed to a fixed member 44 with a buffer member 42 and an insulator 43 interposed therebetween. The cushioning member 42 is made of, for example, an elastic material. The fixed member 44 is supported by the fuselage 20 . The conductor 46 is connected through the flexible conductor 45 to the fixed electrode 41A.

The movable portion of the earthing device 26 is composed of a movable electrode 51A, an insulator 52, a drive source 53, a flexible conductor 54, and a conductor 55. As shown in FIG. The tip of the movable electrode 51A and the tip of the fixed electrode 41A face each other. The movable-side electrode 51A is fixed to a drive source 53 via an insulator 52 . The drive source 53 is supported by the body 20 .

The drive source 53 moves the movable electrode 51A together with the insulator 52 in its axial direction. The drive source 53 moves the movable-side electrode 51A in its axial direction, and attaches and detaches the tip to/from the tip of the fixed-side electrode 41A. The grounding device 26 is closed when the movable electrode 51A presses the fixed electrode 41A, and is opened when the movable electrode 51A is separated from the fixed electrode 41A.

Here, when the grounding device 26 is opened and closed at high speed, the movable electrode 51A collides with the fixed electrode 41A with great force. Therefore, the movable-side electrode 51A may move away from the fixed-side electrode 41A due to the recoil of the collision with the fixed-side electrode 41A.

Therefore, in the grounding device 26 according to the present invention, the fixed electrode 41A is fixed to the fixed member 44 via the buffer member 42, so that the impact force from the movable electrode 51A to the fixed electrode 41A is It is gradually attenuated and absorbed by the buffer member 42 . Therefore, in the grounding switch 26, the buffer member 42 is compressed while the main discharge of lightning is occurring, so that the fixed electrode 41A and the movable electrode 51A do not come into contact with each other.

As described above, in the lightning strike determination control device 10 according to the fifth embodiment, the earthing device 26 includes the fixed side electrode 41A fixed via the buffer member 42 and the movable side electrode 41A which is detachably movable with respect to the fixed side electrode 41A. and an electrode 51A. Therefore, the lightning strike determination control device 10 can gradually attenuate and absorb the impact force generated when the earthing switch 26 is closed. As a result, the lightning strike determination control device 10 can maintain contact between the fixed electrode 41A and the movable electrode 51A while the lightning main discharge is occurring.

Embodiment 6.
A lightning strike determination control device 10 according to Embodiment 6 will be described with reference to FIGS. 14 and 15. FIG. FIG. 14 is a diagram showing a configuration of an earthing switch 26 in an aircraft power supply system to which the lightning strike determination control device 10 according to the fifth embodiment is applied. FIG. 15 is an enlarged view of the main part of the grounding switch 26. As shown in FIG.

In contrast to the grounding device 26 according to the fifth embodiment shown in FIG. 13, the grounding device 26 according to the sixth embodiment shown in FIG. It is replaced with the movable side electrode 51B. The tip of the fixed electrode 41B and the tip of the movable electrode 51B can be fitted to each other.

FIG. 15A shows a state in which the fixed side electrode 41B and the movable side electrode 51B are not fitted to each other. Such a state is the open state of the earthing switch 26 . FIG. 15B shows a state where the fixed side electrode 41B and the movable side electrode 51B are fitted to each other. Such a state is the closed state of the earthing switch 26 .

Therefore, in the earthing device 26, the fixed side electrode 41A and the movable side electrode 51A do not come into contact with each other while the main discharge of lightning is occurring.

As described above, in the lightning strike determination control device 10 according to Embodiment 6, the tip of the fixed-side electrode 41B and the tip of the movable-side electrode 51B can be fitted. Therefore, the lightning strike determination control device 10 can reliably bring the fixed electrode 41B and the movable electrode 51B into contact while the lightning main discharge is occurring.

Embodiment 7.
A power supply system according to Embodiment 7 will be described with reference to FIGS. 16 and 17. FIG. FIG. 16 is a diagram showing the configuration of a wind power generation facility to which the lightning strike determination control device 10 according to Embodiment 7 is applied. FIG. 17 is a circuit diagram showing the configuration of a power supply system for wind power generation equipment to which the lightning strike determination control device 10 according to Embodiment 7 is applied.

As shown in FIG. 16 , the wind power generation facility includes an electricity path 24 , a wind turbine 61 , a power generation section 62 , a transformer section 63 , a transmission line 64 , a tower body 65 and a ground line 66 .

The power generation section 62 is provided at the upper end of the tower body 65 . The windmill 61 is rotatably supported by the power generation section 62 . The transformer section 63 is provided at the bottom of the tower body 65 . The power generation unit 62 and the power transformation unit 63 are connected by the power supply path 24 . The current-carrying path 24 is provided inside the tower body 65 . A ground line 66 is connected to the power generation unit 62 . This ground wire 66 connects between the power generating section 62 and the ground. A transmission line 64 is also connected to the transformer section 63 . This transmission line 64 is connected to an external system.

Therefore, in the wind power generation facility, when the windmill 61 rotates, the power generation unit 62 generates power. Electric power generated by the power generation unit 62 is sent to the power transformation unit 63 via the power supply path 24 . Moreover, the electric power sent to the transformer unit 63 is further sent to the external system via the transmission line 64 .

As shown in FIG. 17 , in the power supply system for the wind power generation facility, the power generation section 62 has a grounding device 26 , a current converter 31 and a power generator 67 . The windmill 61 is supported by a rotating shaft 67 a of a generator 67 . The lightning sensor 15 is provided on the rotating shaft 67 a of the generator 67 .

The current converter 31 converts the power generated by the generator 67 into direct current or alternating current of another frequency. Also, one end of the grounding device 26 is connected to a connection line that connects the current converter 31 and the generator 67 . The other end of the grounding device 26 is connected to the grounding line 66 .

The substation section 63 has a switch 23 and a substation device 68 serving as a target device. The switch 23 connects between the energization path 24 and the transformer 68 . The transformer device 68 converts the power sent from the current converter 31 into a different voltage or smoothes it. Also, the substation device 68 sends electric power to the external grid via the transmission line 64 . This transforming device 68 is connected to the ground line 66 through the ground circuit 27 .

An input terminal of the lightning strike determination control device 10 is connected to the lightning sensor 15 . An output terminal of the lightning strike determination control device 10 is connected to the grounding device 26 and the current converter 31 .

Therefore, the lightning sensor 15 detects lightning discharge waveform data in the windmill 61 and sends the lightning discharge waveform data to the lightning strike determination control device 10 . This lightning strike determination control device 10 outputs an operation start command to the grounding device 26 and the current converter 31 based on the lightning discharge waveform.

As described above, the power supply system according to Embodiment 7 includes the generator 67 that generates power using rotational force, the transformer 68 that is supplied with current from the generator 67, and the magnitude of the current that is supplied to the transformer 68. and a switch 23 connected between the current converter 31 and the transformer 68, one end of which is connected between the switch 23 and the current converter 31, and the other end of which is a ground line 66. and a lightning strike determination control device 10 having a control unit 14 connected to the grounding device 26 and the current converter 31 . Therefore, the power supply system can cause the lightning current to flow through the ground line 66 before the main discharge of the lightning strike occurs.

Further, in the power supply system according to Embodiment 7, the generator 67 has a rotating shaft 67a connected to the windmill 61, and the lightning sensor 15 is provided on the rotating shaft 67a. Therefore, the power supply system can detect the direct intrusion of lightning current into the circuit, and thus can improve the accuracy of determining the presence or absence of a lightning strike.

Embodiment 8.
A power supply system according to Embodiment 8 will be described with reference to FIG. FIG. 18 is a circuit diagram showing the configuration of a power supply system for wind power generation facilities to which the lightning strike determination control device 10 according to the eighth embodiment is applied.

The power supply system according to Embodiment 8 shown in FIG. 18 has the same components as the power supply system according to Embodiment 7 shown in FIG. .

As shown in FIG. 18 , one end of the grounding device 26 is connected to a connection line that connects the switch 23 and the current converter 31 . Also, the other end of the grounding device 26 is connected to the grounding line 66 .

As described above, the power supply system according to the eighth embodiment includes the generator 67 that generates power using rotational force, the transformer 68 that is supplied with current from the generator 67, and the magnitude of the current that is supplied to the transformer 68. and a switch 23 connected between the current converter 31 and the transformer 68, one end of which is connected between the switch 23 and the current converter 31, and the other end of which is a ground line 66. and a lightning strike determination control device 10 having a control unit 14 connected to the grounding device 26 and the current converter 31 . Therefore, the power supply system can cause the lightning current to flow through the ground line 66 before the main discharge of the lightning strike occurs.

In addition, within the scope of the disclosure, the present disclosure can freely combine each embodiment, modify any component of each embodiment, or omit any component in each embodiment. .

The lightning strike determination control device according to the present disclosure closes the earthing device connected to the ground wire before the main discharge of lightning occurs. It can be flowed and is suitable for use in lightning strike determination control devices and the like.

10 lightning strike determination control device, 11 acquisition unit, 12 detection unit, 13 determination unit, 14 control unit, 15 lightning sensor, 20 fuselage, 21 power supply, 21a housing, 21b internal circuit, 21c stray capacitance, 22 load device, 23 opening and closing device, 24 energization path, 25 grounding wire, 26 grounding device, 27 grounding circuit, 28 branch line, 31 current converter, 32 motor, 32a rotating shaft, 33 fan, 41A, 41B fixed side electrode, 42 buffer member, 43 insulation body, 44 support member, 45 flexible conductor, 46 conductor, 51A, 51B movable side electrode, 52 insulator, 53 drive device, 54 flexible conductor, 55 conductor, 61 windmill, 62 power generation section, 63 substation section, 64 transmission Electric wire, 65 tower body, 66 ground wire, 67 generator, 67a rotary shaft, 68 substation, 91 processor, 92 memory, 93 processing circuit, W1, W2 waveforms.

Claims (9)

an acquisition unit that acquires discharge waveform data of a lightning strike on the aircraft, which is detected by a lightning sensor provided on the aircraft;
a detection unit that detects a pre-discharge before a main discharge of a lightning strike and a main discharge that occurs immediately after the pre-discharge from the discharge waveform data of the lightning strike acquired by the acquisition unit;
a determination unit that determines that the aircraft is subject to a lightning strike due to a main discharge when the detection unit detects a predischarge of a lightning strike;
A grounding device that connects a circuit for supplying power from a power supply to a motor for obtaining the propulsion force of the aircraft and a ground wire before the main discharge of the lightning strike occurs when the determination unit determines that the lightning strike occurs. and a control unit that closes the circuit and causes a current due to a lightning strike that has entered the circuit to flow through the ground line . 2. The lightning strike determination control device according to claim 1, wherein the controller opens the earthing switch after a predetermined period of time has passed since the detection of the main discharge of the lightning strike by the detector. The acquisition unit
2. The lightning strike determination control device according to claim 1, wherein discharge waveform data of a lightning strike flowing through the airframe of the aircraft whose skin is made of carbon fiber reinforced plastic is acquired. The earthing device is
a stationary electrode fixed via a buffer member;
The lightning strike determination control device according to claim 1, further comprising a movable electrode that moves detachably with respect to the fixed electrode. 5. The lightning strike determination control device according to claim 4, wherein the tip of the fixed electrode and the tip of the movable electrode are fittable. the motor to which current is supplied from the power supply through the circuit ;
a current converter for controlling the magnitude of the current supplied to the motor;
a switch connected between the power supply and the current converter;
the grounding device, one end of which is connected between the current converter and the switch, and the other end of which is connected to the grounding wire;
A power supply system comprising: the lightning strike determination control device according to claim 1, wherein the control unit is connected to the switch and the grounding device. the motor to which current is supplied from the power supply through the circuit ;
a current converter for controlling the magnitude of the current supplied to the motor;
the grounding device, one end of which is connected between the motor and the current converter and the other end of which is connected to the ground wire;
A power supply system comprising: the lightning strike determination control device according to claim 1, wherein the control unit is connected to the current converter and the earthing device. the motor has a rotating shaft connected to the fan,
8. The power supply system according to claim 6, wherein the lightning sensor is provided on the rotating shaft. an acquisition unit acquiring discharge waveform data of a lightning strike on the aircraft detected by a lightning sensor provided on the aircraft;
A detection unit detects a predischarge before a main discharge of a lightning strike and a main discharge that occurs immediately after the predischarge from the discharge waveform data of the lightning strike acquired by the acquisition unit;
a determination unit determining that the aircraft is subject to a lightning strike due to a main discharge when the detection unit detects a pre-discharge of a lightning strike;
When the control unit determines that the determination unit receives a lightning strike , a circuit for supplying power from a power source to the motor for obtaining the propulsion force of the aircraft and a ground wire before the main discharge of the lightning strike occurs. Close the grounding device to be connected , and allow the current due to the lightning strike that has entered the circuit to flow through the grounding wire.
A lightning strike determination control method characterized by:

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