KR20130063158A - Apparrutus and method to inspect obstruction light for flight, and system using thereof - Google Patents

Abstract

PURPOSE: An apparatus and method for inspecting a flight obstruction light, and a flight obstruction light inspection system using the same are provided to enable a manager to inspect obstruction lights scattered in mountainous area easily, by providing a system which is able to inspect the obstruction light remotely. CONSTITUTION: A lamp monitoring part includes a current transformer(310), a current detection part(320), a failure determination part(330), a first communication module, a first power supply part(350) and an operation control part(360). The current transformer transforms a first current flowing in a flight obstruction light into a second current inversely proportional to the winding number of a coil. The current detection part detects the second current flowing in the current transformer. The failure determination part determines the failure of the obstruction light by using the second current detected in the current detection part. The first communication module transmits failure and operation state data to an upper server or a mobile terminal of a manager. The power supply part supplies a power source to each part. [Reference numerals] (310) Current transformer; (320) Current detection part; (330) Failure determination part; (360) Operation control part; (361) Solar cell plate; (362) Charging part; (363) Battery; (364) Over-charging detection part; (365) Over-discharging detection part

Description

Apparatus and method for inspecting aviation faults, and aviation fault inspection system using the same {APPARRUTUS AND METHOD TO INSPECT OBSTRUCTION LIGHT FOR FLIGHT, AND SYSTEM USING THEREOF}

The present invention relates to a aviation failure light inspection device and a aviation failure light inspection system and method using the same, and specifically monitors the aviation failure lights directly, by measuring the voltage and temperature of the power supply of the aviation failure lights, etc. An apparatus and system for determining the goodness of a supply.

Tall buildings, bridges, chimneys, pylons and tall structures, transmission towers and overhead lines in urban areas are equipped with aviation obstructions that flash red or white flashes. This is to prevent the accident by indicating the location of obstacles that may interfere with the flight of the aircraft or helicopter at night low light conditions. According to the aviation law, high-rise buildings, steel towers, and transmission towers are required to install aviation obstacle indicators that indicate the location of obstacles to pilots in flight to prevent accidents. Structures, transmission towers, and overhead ships are equipped with aviation obstacles that indicate the location of obstacles to aircraft or helicopter pilots.

However, due to the large number of transmission towers or overhead lines for aerial lines, they are difficult to inspect and troubleshoot, especially when they are installed on rugged terrain. There is this. Accordingly, there has been a need for a system that can remotely check for aviation disturbances.

In addition, there is a problem that the existing system needs to be reinstalled in order to convert the already installed aviation failure system into a remote system. In addition, when a separate circuit is implemented to detect faults such as aviation faults, there is a problem in that faults cannot be checked when a fault occurs in the circuit itself.

In order to solve the above problems, an object of the present invention is to provide an apparatus and system that can detect the current failure in the aviation failure lamp and check the aviation failure lamp. In addition, the present invention has another object to enable to check the aviation failures remotely through the aviation failure inspection device and system, and to create an environment that can check the aviation failures without implementing a separate circuit, the inspection system Another goal is to make it easy to take action in case something goes wrong. In addition, by establishing a device that can use the existing aviation failure lights system, there is another object to provide a aviation failure lights inspection device and system without replacing the existing aviation failure lights and aviation failure lights system.

The inventors of the present invention, such as aviation failure inspection device current transformer for flowing the primary current flowing in the aviation failure lamp to the secondary current; A detector for detecting the secondary current flowing in the current transformer; A failure determination unit which detects a change in at least one of a current value and a frequency of the secondary current to determine whether the aviation failure is defective; And a power supply unit supplying power to the current transformer, the detection unit, and the failure determination unit.

The power supply unit, the solar panel absorbs sunlight to generate electrical energy; A battery charging electrical energy generated by the solar panel; An overcharge detector for detecting whether the battery is overcharged during charging; And an over-discharge detector for detecting whether the battery is over-discharged during the discharging process of the battery.

The air traffic light inspection device further includes an operation control unit for controlling the operation to operate after sunset.

The operation control unit may compare the voltage of the solar panel with a preset reference voltage value to control the operation of the aviation failure inspection device.

The air traffic light inspection device further includes an operation control unit for controlling the operation to operate after the operation of the air traffic lights.

The operation control unit, by detecting the current flowing in the current transformer in accordance with the operation of the aviation failure lights, characterized in that for controlling the operation of the aviation failure inspection device.

The inventors aviation failure light inspection system is electrically connected to the aviation failure lights lamp monitoring unit for detecting a current flowing in the aviation failure lights; And a management server that detects a failure of the aviation fault by detecting a change in at least one of a current value and a frequency of the current flowing through the aviation fault received from the lamp monitoring unit.

The lamp monitoring unit includes a current transformer for converting the primary current flowing in the aviation obstacle, etc. into a secondary current; A detector for detecting the secondary current flowing in the current transformer; A first communication module for transmitting data on the secondary current to the management server; And a first power supply unit supplying power to the lamp monitoring unit.

The first power supply unit, the solar panel absorbs sunlight to generate electrical energy; A battery charging electrical energy generated by the solar panel; An overcharge detector for detecting whether the battery is overcharged during charging; And an over-discharge detector for detecting whether the battery is over-discharged during the discharging process of the battery.

The lamp monitoring unit further includes an operation control unit for controlling the operation of the lamp monitoring unit so that the lamp monitoring unit can operate after sunset.

The operation control unit may compare the voltage of the solar panel with a predetermined reference voltage value to control the operation of the lamp monitoring unit.

The lamp monitoring unit further includes an operation control unit for controlling the operation of the lamp monitoring unit to operate after the operation of the aviation obstacle.

The operation control unit, by detecting the current flowing in the current transformer in accordance with the operation of the aviation failure lights, characterized in that for controlling the operation of the aviation failure inspection device.

A second power supply unit supplying power to the aviation obstacle; A voltage measuring unit measuring a voltage of the second power supply unit; A second communication module for transmitting the measured voltage of the voltage measuring unit to the management server; And an aviation failure light control unit for adjusting the operation timing of the aviation failure lights so that the aviation lights can operate after sunset.

It further includes a temperature measuring unit for measuring the temperature of the second power supply.

The management server may determine the health of the second power supply unit based on a voltage of the voltage measuring unit or a temperature measurement result of the temperature measuring unit.

The management server is characterized in that for outputting a warning signal when a failure occurs in the aviation failure.

The aviation failure light control unit transmits the aviation failure light operation signal to the operation control unit when the operation of the aviation failure lights, the operation control unit is characterized in that for controlling the operation of the lamp monitoring unit based on the operation signal of the aviation failure lights.

The inventors of the present invention, the air fault check method comprises the steps of determining the operation of the air fault lights by the air fault lights control unit; Operating the lamp monitoring unit by the operation control unit; Detecting, by the lamp monitoring unit, current flowed by the current transformer; And comparing the current detected by the lamp monitoring unit with a reference current to determine whether the aviation failure has failed.

Measuring, by a power measuring unit, a voltage of a power supply unit supplying power to the aviation obstacle; Transmitting the voltage of the power supply unit to a management server; And determining, by the management server, the health of the power supply unit based on the received data.

A temperature measuring unit measuring an ambient environment and a temperature of the power supply unit; Transmitting the temperature of the power supply unit to a management server; And determining, by the management server, the health of the power supply unit based on the received data.

According to the present invention according to the above configuration, by providing a system that can remotely check the aviation failure, the administrator can easily check the aviation failure scattered on the mountain wallpaper. In addition, by detecting the current flowing through the aviation obstacle, etc. to determine whether the failure, it is possible to check the aviation failure, etc. without implementing a complicated failure inspection circuit. In addition, the present invention can be installed at the bottom of the aviation obstacle to the device for monitoring the aviation failure, and can fully use the existing aviation failure lighting system, it is possible to minimize the waste of goods in the construction of a remote inspection system, such as aviation failure. .

1 is a block diagram of a general aviation failure system,
2 is a block diagram of a device for checking a aviation failure according to an embodiment of the present invention,
3 is a detailed configuration diagram of a lamp monitoring unit according to an embodiment of the present invention;
4 is a detailed configuration diagram of a voltage / temperature measurement unit according to an embodiment of the present invention;
5 is a aviation failure inspection system using a aviation failure inspection apparatus according to an embodiment of the present invention,
6 is a flow chart of a method for checking a aviation failure, etc. according to an embodiment of the present invention;
7 is a flow chart of a method for checking a aviation obstacle, etc. according to another embodiment of the present invention, and
8 is a circuit diagram of a current transformer and a detector according to an embodiment of the present invention.

Hereinafter, exemplary embodiments of the present invention will be described with reference to the accompanying drawings. In the drawings, the same reference numerals are used to designate the same or similar components, and the same reference numerals will be used to designate the same or similar components. Detailed descriptions of known functions and configurations are omitted.

1 is a block diagram of a general aviation failure light system. According to Figure 1, the aviation failure light system is composed of aviation failure light 100, and aviation failure light control device 110. Aviation obstacle lamp 100 may be divided into a flashing light and a floating light according to the type, the flashing light means an aviation failure light that blinks at a predetermined time interval and the floating light means an aviation failure light that is continuously turned on during operation. Aviation obstacle light 100 operates according to the control signal of the aircraft failure light control device 110, and blinks or lights continuously for a predetermined time period, it can be informed that the obstacle is adjacent to the flight during the night flight. Aviation failure light control device 110 includes a power supply unit 350 (not shown) for supplying power to the aircraft failure light 100, the aircraft failure lights such that the aircraft failure lights 100 can operate after sunset. To control its operation.

When the aviation obstacle lamp 100 is installed in the transmission tower, it is generally 60 meters or more away from the ground, it is difficult to install the aviation obstacle lamp control device 110 together with the aviation obstacle lamp. Therefore, the aviation failure lamp 100 is located at the top of the transmission tower, the aviation failure lamp control device 110 is generally installed in the lower portion of the transmission tower so that the administrator can easily check.

Figure 2 is a block diagram of a aviation failure check system according to an embodiment of the present invention. According to FIG. 2, the aviation failure inspection apparatus includes a lamp monitoring unit 210 and a voltage / temperature measuring unit 220.

The lamp monitoring unit 210 is electrically connected to the aviation failure lamp 100 to detect a current flowing in the aviation failure lamp 100. The lamp monitoring unit is installed at the bottom of the steel tower and can be connected to the aviation obstacle lamp and the wire. The lamp monitoring unit 210 determines whether the aviation failure lamp 100 is broken by comparing the measured current with the current when the aviation failure lamp 100 operates normally. The lamp monitoring unit compares the detected current with the current value of the preset reference current and the frequency of the current, and determines that an abnormality has occurred in the aviation failure, etc. In the case of aviation obstacle lamp, it can be divided into flashing light and the flashlight. In the case of flickering light, the lamp monitoring unit is out of a certain range by comparing the current value and current frequency of current flowing through the aviation obstacle lamp with the current value and current frequency of the preset reference current. It is judged that an abnormality has occurred in aviation obstacles. Alternatively, when the aviation fault lamp is a flashlight, the current value of the current flowing through the aviation fault lamp is compared with the current value of the preset reference current, and if it is out of a certain range, it is determined that the fault occurs in the aviation fault lamp.

The voltage / temperature measuring unit 220 measures the voltage and temperature of the power supply source for supplying power to the aviation failure lamp 100 so that the aviation failure lamp 100 can operate. In general, the power supply source included in the aviation failure control device 110 is composed of a solar panel, a charging unit and a battery. During the day, the solar panel absorbs sunlight, and the voltage applied from the solar panel is charged by the battery after the voltage is adjusted in the charging unit. After sunset, the voltage charged in the battery is discharged and the aviation obstacle lamp 100 operates. At this time, the voltage / temperature measuring unit 220 measures the charging voltage of the solar panel to calculate the normal charging days of the solar panel. The manager can determine the health of the solar panels whether the solar panel is good or bad. In addition, the voltage / temperature measuring unit 220 measures the discharge voltage of the battery, thereby determining the battery life and the discharge capacity of the battery. The voltage / temperature measuring unit 220 measures the internal / external temperature of the power supply source to determine the normal charge / discharge of the battery.

The voltage / temperature measuring unit 220 is preferably included in the aviation failure control device 110, and the lamp monitoring unit 210 is integrally installed with the voltage / temperature measuring unit at the bottom of the steel tower to communicate with each other. No separate module is required. However, this does not exclude that the lamp monitoring unit and the voltage / temperature measuring unit are implemented as separate devices. In this case, the lamp monitoring unit 210 and the voltage / temperature measuring unit 220 may be connected by wire or wirelessly to communicate with each other. Can be.

3 is a detailed configuration diagram of a lamp monitoring unit according to an embodiment of the present invention.

According to FIG. 3, the lamp monitoring unit includes a current transformer 310, a current detector 320, a failure determining unit 330, a first communication module (not shown), a first power supply unit 350, and an operation control unit 360. do.

The circuit of the current transformer 310 and the current detector 320 is as shown in FIG. 8. The current transformer 310 may convert the primary current flowing in the aviation obstacle into a secondary current that is inversely proportional to the number of turns of the coil. Current transformer 310 and the aviation fault lamp is connected by using a wire and the current flowing in the aviation fault lamp is supplied as a primary current of the current transformer 310 through a wire connected to the current transformer 310 and the primary coil and 2 of the current transformer 310 The winding of the primary coil is inverted into a secondary current having a small value in inverse proportion to the number of turns.

The current detector 320 may detect the secondary current flowing in the current transformer 310. The current detector 320 may detect the secondary current by, for example, measuring a voltage between both ends of a resistor having an arbitrary value connected to the secondary coil of the current transformer 310. If the resistance connected to the secondary coil is, for example, 1 ohm, the voltage across the resistor becomes the secondary current, according to Ohm's law.

The failure determining unit 330 determines whether there is a failure such as an aviation failure by using the secondary current detected by the current detecting unit 320. In general, a small current flows when the aviation failure light is activated. The failure determination unit 330 detects an abnormal change in the current flowing through the aviation failure by using the value and frequency of the current detected by the current detection unit 320, and the aviation failure light. It is possible to determine whether or not. The failure determining unit 330 may compare the current flowing in the aviation obstacle with the current value of the preset reference current and the frequency of the current, and may determine that the aviation failure occurs when it is out of a predetermined range. The predetermined range of the current set value and frequency of the fault determination unit 330 may be set by an external administrator, or may detect a current such as a aviation failure that operates normally and set the current value and frequency of the current as a reference current. . The failure determining unit 330 may be integrally formed with the lamp monitoring unit or may be provided in the form of a separate server.

The first communication module is for communicating with the host server, and transmits data or an operation state, such as whether the aviation failure lamp 100 is broken, the current flowing through the aviation failure lamp 100, or the like to the mobile terminal of the host server or the administrator. In general, the first communication module may use a wired communication method or a wireless communication method.

The power supply unit 350 supplies power to each part so that the lamp monitoring unit 210 can operate. The power supply unit 350 includes a solar panel 361, a charging unit 362, a battery 363, an overcharge detector 364, and an overdischarge detector 365.

During the day, the solar panel 361 absorbs sunlight, and the voltage applied from the solar panel 361 is charged by the battery 363 after the voltage is adjusted in the charging unit 362. At this time, in the charging process, the overcharge detection unit 364 detects overcharge of the battery 363 and prevents the battery 363 from being overcharged. The lamp monitoring unit 210 operates by discharging the voltage charged in the battery 363 at night. At this time, the overdischarge detection unit 365 detects overdischarge of the battery 363 and prevents the battery 363 from overdischarging.

In order to prevent the lamp monitoring unit 210 from discharging the power supply unit 350 during the day, it is preferable that the lamp monitoring unit 210 operates after sunset or after the aviation failure lamp 100 operates to monitor the aviation failure lamp 100.

According to one embodiment of the present invention, the operation control unit 360 sets the reference voltage value and compares the reference voltage value and the voltage of the solar panel 361, so that the lamp monitor 210 can operate after sunset do. For example, when the reference voltage value is set and the voltage of the solar panel 361 is lower than the reference voltage value, the battery 363 may be discharged to allow the lamp monitoring unit 210 to operate. The lower the brightness of the solar panel 361 is, the less the amount of light is collected, so that a sufficient voltage cannot be output. Therefore, sufficient light cannot be obtained after sunset, and thus the output voltage is reduced. By using this, when the voltage of the solar panel 361 falls below a predetermined reference voltage, it is determined that the sunset and the lamp monitor 210 is operated.

4 is a detailed configuration diagram of a voltage / temperature measurement unit according to an embodiment of the present invention.

Referring to FIG. 4, the voltage / temperature measuring unit 220 includes a voltage measuring unit 410, a temperature measuring unit 420, a central processing unit 430, a second communication module 440, and a voltage / temperature measuring unit 220. And a power supply unit 450 for supplying power to operate the aviation fault lamp 100 and an aviation fault control unit 460 for adjusting the operation time of the aviation fault lamp so that the aviation fault light can operate after sunset. .

The voltage measuring unit 410 measures the output voltage of the solar panel 451 of the power supply unit 350 for supplying power to the aviation failure lamp 100, and the battery is charged through a voltage applied from the solar panel 451 The charging voltage and the discharge voltage of 453 are measured.

The temperature measuring unit 420 measures the temperature inside and outside the voltage / temperature measuring unit 220. The internal temperature of the voltage / temperature measuring unit 220 refers to the internal temperature of the enclosure in which the battery 453 is stored.

The central processing unit 430 is a voltage / temperature measurement value in the voltage measuring unit 410 and the temperature measuring unit 420, the measurement time and the current value of the aviation failure lamp 100 received by the second communication module 440 and The data is processed to transmit the frequency of the current to the management server through the second communication module 440, and the data is transmitted to the management server through the second communication module 440.

The second communication module 440 transmits data regarding voltage / temperature measurement values, measurement time points, and current of the aviation failure lamp 100 to the management server. The second communication module 440 may use wireless communication or wired communication, and when using wireless communication, any one of WI-FI, Wibro, D-TRS, WiMax, LTE, HSDPA, WLAN, (Binary) CDMA, and UWB In case of using wired communication, it may be one of OPGW optical communication, optical communication, ADSL, cable modem, and xDSL. Alternatively, one or more of the communication methods listed above may be used.

The power supply unit 450 serves to supply power to operate the voltage / temperature measuring unit 220 and the aviation obstacle lamp 100. The power supply unit 450 includes a solar panel 451, a charging unit 452, a battery 453, an overcharge detection unit 454, and an over discharge detection unit 455.

During the day, the solar panel 451 absorbs sunlight, and the voltage applied from the solar panel 451 is charged by the battery 453 after the voltage is adjusted in the charging unit 452. At this time, in the charging process, the overcharge detection unit 454 detects overcharge of the battery 453 and prevents the battery 453 from being overcharged. The light source supervisory value is operated by discharging the voltage charged in the battery 453 at night. At this time, the overdischarge detection unit 455 detects overdischarge of the battery 453 and prevents the battery 453 from overdischarging.

The aviation fault lamp control unit 460 sets the reference voltage value and compares the reference voltage value with the voltage of the solar panel 451, so that the aviation fault lamp 100 can operate after sunset. For example, when the reference voltage value is set and the voltage of the solar panel 451 is lower than the reference voltage value, the battery 453 may be discharged so that the aviation failure lamp 100 may operate. The lower the brightness of the solar panel 451, the smaller the amount of light collected, the insufficient voltage is not output, and thus, after sunset, sufficient light cannot be secured so that the output voltage decreases. By using this, when the voltage of the solar panel 451 falls below a predetermined reference voltage, it is determined that sunset and the aviation failure lamp 100 is operated. When the aviation failure lamp 100 operates, the aviation failure lamp control unit 460 may transmit a control signal to the lamp monitoring unit 210 through the second communication module 440 to operate the lamp monitoring unit 210. .

That is, the operation control unit 360 may receive a control signal from the flight failure control unit 460 and operate the lamp monitoring unit 210 based on the control signal. For example, the aviation failure light control unit 460 operates the aviation failure light 100 after sunset, and transmits a control signal to the operation control unit 360 when the aviation failure light 100 is operated. The operation controller 360 receiving the control signal may operate the lamp monitor 210 based on the control signal.

FIG. 5 is a diagram illustrating a system for checking a traffic light by using a system for checking a traffic light according to an embodiment of the present invention. Referring to FIG. 5, the aviation failure light inspection system using the aviation failure light inspection device includes a lamp monitoring unit 510 for detecting a current flowing in the aviation failure light 100 using the current transformer 310, and the aviation failure light 100. Receive data on the current flowing in the voltage / temperature measuring unit 520 and the aviation failure lamp 100 and the voltage and temperature information of the voltage supply source for measuring the voltage and temperature of the voltage source of the), based on the received data It includes a management server 530 to determine whether the failure of the aviation failure (100).

The lamp monitoring unit 210 is electrically connected to the aviation failure lamp 100 to detect a current flowing in the aviation failure lamp 100. The lamp monitoring unit is installed at the bottom of the steel tower and can be connected to the aviation obstacle lamp and the wire. Data related to the current of the aviation failure lamp detected by the lamp monitoring unit 510 is transmitted to the management server 530, it is used as the determination data of the failure of the aviation failure lamp 100.

The voltage / temperature measuring unit 520 measures the voltage and temperature of the voltage source (not shown) together with the measurement time point to examine the health of the voltage source for supplying the voltage for driving the aviation obstacle lamp 100. The management server 530 transmits.

The management server 530 detects the failure of the aviation failure lamp 100 through the current value and frequency of the current flowing through the aviation failure lamp 100, the voltage measurement value of the voltage supply source, the temperature measurement value and the measurement time. It is determined whether the aviation fault lamp 100 operates normally by comparing the current when the aviation fault lamp 100 operates normally with the current flowing in the aviation fault lamp 100. Alternatively, the aviation fault lamp compares the current value and frequency of the current preset through the external input with the current value and frequency of the aviation fault lamp received from the voltage / temperature measuring unit, and if the aviation fault lamp 100 is in a good range, the condition of the aviation fault lamp 100 is good. If it is determined that the deviation from the predetermined range, such as the aviation failure 100 is determined to be broken. Aviation obstacle lamps generally have a current value of several tens to several hundred mA and a current having a frequency of 60 Hz flows, but may be set to different values depending on the type and situation of the aviation obstacle lamp 100.

The management server 530 calculates the normal charging days after the solar panel normally charged the battery through the measured value of the solar panel output voltage, and determines the goodness of the solar panel based on the calculation result.

The management server 530 determines the voltage and the time when the battery starts to discharge, based on the measured voltage value of the battery, and determines the voltage and the time when the discharge is completed, the operation time and sunset of the aviation failure lamp 100. After that, check whether it works normally. In addition, the management server 530 analyzes the battery health, such as the performance of the battery, the remaining life of the battery through the result of the measurement of the voltage at the start of discharge of the battery, the voltage at the completion of discharge and the temperature measuring unit 520.

When a failure occurs in the aviation failure light 100 or when it is determined that the state of the solar panel or the battery is poor, the management server 530 outputs a warning signal such as an alarm sound or a warning message to inform the manager, and the management server 530. Alert signal is sent to the mobile terminal 540 of the user registered in the).

6 is a flow chart of a method for checking a aviation failure according to an embodiment of the present invention.

Referring to FIG. 6, first, the aviation failure lamp 100 determines whether the aviation failure lamp 100 is operated (S610). Aviation failure light control unit so that the flight failure light 100 does not operate during the day, and when the amount of ambient light is insufficient after sunset, the flight failure light 100 is set to operate. When the aviation failure lamp 100 is operated, the lamp monitoring unit is operated by the operation control unit 360 (S620). The current detector 320 of the lamp monitor detects a current flowing in the secondary coil of the current transformer 310 (S630). Based on the current detected by the current detector 320, the failure determination unit 330 determines whether the aviation failure lamp 100 is faulty according to whether or not out of a predetermined range compared with the current value and frequency of the preset reference current. It is determined (S640). If the aviation fault lamp is a flashing light, the current value and frequency of the aviation fault lamp may be set by using data values stored in a database when the aviation fault lamp operates normally, or by the administrator directly inputting the current value and frequency. The failure determination result of the aviation failure lamp 100 is transmitted to the upper server or the mobile terminal through the communication module (S650).

7 is a flow chart of a method for checking a fault in the air according to another embodiment of the present invention.

Referring to FIG. 7, first, the aviation failure lamp 100 determines whether the aviation failure lamp 100 is operated (S710). When the aviation failure lamp 100 is operated, the lamp monitoring unit is operated by the operation control unit 360 (S720). The current detector 320 of the lamp monitoring unit detects a current flowing in the secondary coil of the current transformer 310 electrically connected to the aviation obstacle lamp 100 (S730). The voltage / temperature measuring unit measures the voltage of the power supply unit 350 that supplies power to the aviation obstacle lamp 100, the surrounding environment, and the temperature of the power supply unit 350 (S740). The voltage / temperature measuring unit transmits the current value and frequency flowing through the aviation obstacle lamp 100, the measured voltage, the surrounding environment, and the temperature measurement result of the power supply unit 350 to the management server (S750). The management server determines whether or not the failure of the aviation failure lamp 100 and the health of the power supply unit 350 based on the data received from the voltage / temperature measuring unit (S760). As a result of the determination, when a failure occurs in the aviation failure lamp 100 or when the battery of the power supply unit 350 is defective, the management server outputs a warning signal to the manager (S770).

7 illustrates the current detection process S730 of the current detection unit 320 and the voltage / temperature measurement process S740 of the voltage / temperature measurement device in order to easily explain the operation process. The above processes are not necessarily performed sequentially but may be performed in parallel at the same time.

The terminology used in this application is used only to describe a specific embodiment and is not intended to limit the invention. Singular expressions include plural expressions unless the context clearly indicates otherwise.

Unless defined otherwise, all terms used herein, including technical or scientific terms, have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. Terms such as those defined in commonly used dictionaries are to be interpreted as having a meaning consistent with the contextual meaning of the related art and are to be interpreted as either ideal or overly formal in the sense of the present application Do not.

100: aviation obstacle lights 110: aviation failure lights control device
200: aviation failure inspection device 210: lamp monitoring unit
220: voltage / temperature measuring unit 310: current transformer
320: current detection unit 330: fault determination unit
350: power supply unit 360: operation control unit
410: voltage measuring unit 420: temperature measuring unit
430: central processing unit 440: second communication module
450: power supply unit 460: air failure control unit

Claims (20)

Current transformer for converting the primary current flowing in the aviation obstacle, etc. into secondary current;
A current detector for detecting the secondary current flowing in the current transformer;
A fault determination unit for determining whether the aviation failure is faulty by comparing the current value and frequency of the secondary current with a current value and frequency of a preset reference current; And
A power supply unit supplying power to the current transformer, the current detection unit and the fault determination unit
Aviation failure check device comprising a.
The method of claim 1,
The power supply unit,
Solar panels for absorbing sunlight to generate electrical energy;
A battery charging electrical energy generated by the solar panel;
An overcharge detector detecting whether the battery is overcharged during a charging process of the battery; And
An over-discharge detection unit for detecting whether over-discharge is performed during the discharge process of the battery
Aviation failure check device comprising a.
3. The method of claim 2,
Air traffic light inspection device further comprises an operation control unit for controlling the operation so that the air traffic light inspection device can operate after sunset.
The method of claim 3, wherein
The operation control unit,
Aviation failure light inspection device, characterized in that for controlling the operation of the aviation failure light inspection device by comparing the voltage of the solar panel with a predetermined reference voltage value.
The method of claim 1,
Air traffic light inspection device further comprises an operation control unit for controlling the operation so that the air traffic light inspection device can operate after the operation of the air traffic lights.
The method of claim 5, wherein
The operation control unit,
Aviation failure light inspection device, characterized in that for controlling the operation of the aviation failure light inspection device by detecting the current flowing in the current transformer according to the operation of the aviation failure lights.
A lamp monitoring unit electrically connected to an aviation obstacle lamp for detecting a current flowing in the aviation obstacle lamp; And
Management server to determine whether the failure of the aviation failure by comparing the current value and frequency of the current flowing in the aviation failure lamp received from the lamp monitoring unit with the current value and frequency of the preset reference current
Aviation failure check system comprising a.
The method of claim 7, wherein
The lamp monitoring unit,
Current transformer for converting the primary current flowing in the aviation obstacle, etc. into a secondary current;
A current detector for detecting the secondary current flowing in the current transformer;
A first communication module for transmitting data on the secondary current to the management server; And
A first power supply unit supplying power to the lamp monitoring unit
Aviation failure inspection system including
The method of claim 8,
The first power supply unit,
Solar panels for absorbing sunlight to generate electrical energy;
A battery charging electrical energy generated by the solar panel;
An overcharge detector for detecting whether the battery is overcharged during charging; And
And an over-discharge detector for detecting over-discharge during the discharge process of the battery.
The method of claim 8,
The lamp monitoring unit,
And an operation control unit for controlling the operation of the lamp monitoring unit so that the lamp monitoring unit can operate after sunset.
11. The method of claim 10,
The operation control unit,
And comparing the voltage of the solar panel with a predetermined reference voltage to control operation of the lamp monitoring unit.
The method of claim 8,
And an operation control unit for controlling the operation of the lamp monitoring unit so that the lamp monitoring unit can operate after the operation of the aviation failure lamp.
13. The method of claim 12,
The operation control unit,
According to the operation of the aviation failure lights, the aviation failure lights inspection system, characterized in that for controlling the operation of the aviation failure lights inspection device by detecting the current flowing in the current transformer.
The method of claim 7, wherein
A second power supply unit supplying power to the aviation obstacle;
A voltage measuring unit measuring a voltage of the second power supply unit;
Temperature measuring unit for measuring the temperature of the second power supply
A second communication module for transmitting the measured voltage of the voltage measuring unit and the measured temperature of the temperature measuring unit to the management server; And
Aviation obstacle light control unit for adjusting the operating time of the aviation obstacle lights so that the aviation failure lights operate after sunset
Aviation failure check system further comprising a.
15. The method of claim 14,
And the management server determines the health of the second power supply unit based on the measured voltage of the voltage measuring unit or the measured temperature of the temperature measuring unit.
The method of claim 7, wherein
The management server outputs a warning light warning system, characterized in that for outputting a warning signal when a failure occurs in the air failure light.
15. The method of claim 14,
The aviation failure light control unit transmits the aviation failure light operation signal to the operation control unit when the operation of the aviation failure lights, the operation control unit aviation failure characterized in that for controlling the operation of the lamp monitoring unit based on the operation signal of the aviation failure lights. Etc check system.
Determining, by the air traffic light control unit, whether or not the air traffic light operates;
Operating the lamp monitoring unit by the operation control unit;
Detecting, by the lamp monitoring unit, current flowed by the current transformer; And
Comparing the current value and the frequency of the current detected by the lamp monitoring unit with the current value and the frequency of the preset reference current to determine whether the aviation fault is faulty.
Checking methods such as aviation failures.
The method of claim 18,
Measuring, by a power measuring unit, a voltage of a power supply unit supplying power to the aviation obstacle;
Transmitting the voltage of the power supply unit to a management server; And
Determining, by the management server, the health of the power supply unit based on the received data.
Checking methods such as aviation failure further comprising.
The method of claim 18,
A temperature measuring unit measuring an ambient environment and a temperature of the power supply unit;
Transmitting the temperature of the power supply unit to a management server; And
Determining, by the management server, the health of the power supply unit based on the received data.
Checking methods such as aviation failure further comprising.

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