KR200261285Y1 - Apparatus for controlling obstruction lights for flight - Google Patents

Abstract

The present invention relates to a device for aviation failure lamp, the lamp monitoring unit for detecting the failure of the aviation failure lamp, the charge monitoring unit for detecting the abnormality of the charging control unit and the storage battery, and whether the voltage level applied to the aviation failure, etc. A power monitoring unit for sensing, a control unit for checking the failure state of each component through the monitoring unit and periodically storing the inspection result, and converts the inspection result request control signal received in the form of a mobile communication frequency signal into a wired signal. And a mobile communication data transmission / reception unit for inputting the control unit and converting the check result data stored in the control unit into a mobile communication frequency signal under the control of the control unit.

The present invention, by checking the lighting state of the aviation failure lamp and whether the components for driving the failure itself and transmits the check result to the management server through communication, the aviation failure lights and components from a remote location without a person instantaneous They can always monitor the status of their failures and their status.

Description

Apparatus for controlling obstruction lights for flight}

The present invention relates to a aviation failure lamp device, and more particularly to a aviation failure lamp device that can monitor the failure of the aviation failure lamp and its components for remote operation at all times.

In general, it is stipulated by law (for example, Korean Aviation Act) to install aviation obstacles in order to ensure the safety of airplanes at night and when the clock is not secured in structures above a certain height (for example, 60 meters) from the surface and the surface of the water. .

In other words, the owners of all structures above the prescribed height that may interfere with the safe operation of the aircraft shall, by law, install and manage low and low light aviation lights.

In order to turn on and turn off such aviation lights and to flash them according to the law, there are control devices that control not only the lights but also the power supply means and lights. It is called a device.

The aviation fault lamp device is a solar cell aviation fault lamp device that receives power from a solar cell, the conventional solar cell aviation fault lamp device, as shown in FIG. The solar cell 10 generated and the control box 20 charging and boosting the output power generated by the solar cell and the aviation obstacle lamps 30 and 31 that are turned on by the power applied from the control box 20. It is composed of

As shown in FIG. 2, the control box 20 includes a storage battery 21 for storing power generated by the solar cell 10, a charging control unit 22 for controlling current charging of the storage battery 21, and According to the control of the control unit 25 to be described later, the boosting unit 23 for boosting the power stored in the battery 21 and applying it to the aviation obstacle lamps 30 and 31, and sensing the intensity of light and correspondingly According to the optical sensor 24 for outputting the detection signal and the detection signal applied from the optical sensor 24, during the day when the illuminance is higher than a predetermined illuminance, the storage battery 21 and the booster 23 are controlled to control the aviation fault lamp 30 and 31. It is composed of a control unit 25 for turning off the lights and lighting the air traffic lights (30, 31) in the evening or at night below a certain illuminance.

The above-described aviation fault lighting device has a disadvantage in that it is not possible to control the lighting or turning off at a remote place, and the improvement that can turn on and off the aviation fault lighting device at a remote place by using a radio call signal among the conventional aviation fault lighting devices. There was a aviation failure lamp device, which is configured as shown in FIG.

3, the aviation failure light device shown in FIG. 3 includes a solar cell 40 generating power using sunlight and a control box 50 for charging the power generated by the solar cell and then boosting and outputting the same. And aeronautical failure lamps 60 which are turned on by the electric power applied from 50).

The control box 50 may include a storage battery 51 for storing power generated by the solar cell 40, a charging control unit 52 for controlling current charging of the storage battery 51, and a controller 56 to be described later. According to the control step-up unit 53 for boosting the power stored in the storage battery 51 to apply to the aviation failure lamp 60, and the optical sensor 54 for detecting the intensity of the light and outputs a corresponding detection signal It includes.

In addition, the control box 50 receives a radio call signal transmitted from a radio call repeater or the like, identifies a control command in the radio call signal received, and outputs a control signal corresponding to the identified control command ( 55) and control the battery 51 and the booster 53 during the day when the illuminance is greater than a certain illuminance according to the detection signal applied from the optical sensor 54 to turn off the aviation fault lamp 60 and in the evening or at night which is below the illuminance. When the aviation failure light 60 is turned on but the control signal indicating lighting from the wireless call signal receiver 55 is applied, the aviation failure light 60 is turned on and the radio call is made irrespective of the illuminance detected by the optical sensor 54. It is configured to include a control unit 56 for extinguishing the aviation obstacle lamp 60 when the control signal for instructing the extinguishing from the signal receiving unit 55 is applied.

The air fault lighting apparatus of FIG. 3 configured as described above is used for forcibly turning on or off the air fault lighting by a manager in a special situation such as a protection training.

The maintenance work on the devices such as the conventional aviation obstacles is generally performed by the inspector on a regular basis based on the service life of the device components determined by the manufacturer or by the statistics of the maintenance management company performing maintenance. Instantly inspect the structure. As a result of the instantaneous inspection by the inspector, if the aviation fault is found not to be turned on or blinking at the time that should be turned on, a repair agent is dispatched to the site to perform the repair.

As such, conventional devices such as aviation failures can be identified only by human inspection, so if a failure occurs at a time other than the inspection period, it is left unattended until inspection and threatens aviation safety, as well as maintenance personnel. There was a problem in that it took a long time to go to this direct site to check the fault condition, so that the repair and repair could not be performed immediately.

The present invention has been made to solve the problems of the prior art as described above, by checking the lighting state of the aviation failure light and the failure of the components for driving the self and by sending the check result to the management server through communication The object of the present invention is to provide a device for aviation failure lamp that can monitor the status and failure of the aviation failure lamp and its components at a remote location without the need for human instantaneous visit.

1 is a schematic diagram of a conventional general aviation obstacle light device,

FIG. 2 is a schematic block diagram of the control box shown in FIG. 1;

3 is a schematic block diagram of another conventional aviation obstacle device,

Figure 4 is a schematic block diagram of a remote monitoring system, such as aviation failure applied to the present invention,

Figure 5 is a schematic block diagram of a aviation fault lighting apparatus according to a preferred embodiment of the present invention.

<Explanation of symbols for main parts of the drawings>

100: aviation failure device 101: solar cell

102: storage battery 103: boosting unit

104: aviation failure light 105: charging control unit

106: light sensor 110: charge monitoring unit

120: power monitoring unit 130: lamp monitoring unit

140: control unit 150: mobile communication data transmission and reception unit

200: mobile communication relay unit 300: wireless data communication network

410: gateway 420: management server

430: manager terminal

Aviation failure lamp device according to the present invention for achieving the above object, the power supplied from a predetermined power supply means charges the storage battery by the charge control unit and the power charged in the storage battery to the amount of light detected through the light sensing means. In accordance with the present invention, the aviation fault lamp device is configured to be boosted by the booster and applied to an aviation fault lamp, the aviation fault lamp device comprising: a lamp monitoring unit for sensing a current flowing in the aviation fault lamp, and the booster unit according to the amount of light detected by the light sensing means Performs a control operation to apply or cut off the boosted power to the aviation fault lamp, and if the current is detected through the lamp monitoring unit while supplying power to the aviation fault lamp, checks the normal state. Control unit for periodically storing the received and in the form of mobile communication frequency signal And a mobile communication data transceiving unit for converting the inspection result request control signal into a wired signal, inputting the control signal to the controller, and converting the inspection result data stored in the controller into a mobile communication frequency signal according to the control of the controller. It is characterized by.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings.

4 is a schematic block diagram of a remote monitoring system for aviation failure light to which the present invention is applied. As can be seen from the same diagram, the aviation failure lighting remote monitoring system to which the present invention is applied includes at least one aviation failure lighting device ( 100) and at least one mobile communication repeater 200, a wireless data communication network 300, a management company gateway 410, the management server 420 and the manager terminal 430.

The aviation failure light device 100 lights up the aviation failure light according to the ambient illuminance, and constantly checks the aviation failure light and its driving components by itself and manages the checked contents in the form of a mobile communication frequency signal. 420).

The mobile communication repeater 200 transmits a control signal transmitted from the management server 420 via the wireless data communication network 300 to the aviation failure light device 100 in the form of a mobile communication frequency signal, and the aviation failure. The mobile communication frequency signal received from the device 100 is transmitted to the management server 420 via the wireless data communication network 300 as data.

The wireless data communication network 300 is a communication network for transmitting data between a mobile communication data transmission and reception means and an online server and a terminal, and connects the mobile communication repeater 200 and the management server 420 to the mobile communication repeater 200. Mediates data transmission between the server and management server 420.

The gateway 410 is a computer device for communication in which the management server 420 connects to the wireless data communication network 300 and mediates the wireless data communication network 300 to transmit and receive data with the mobile communication repeater 200. And a network connection device 70 such as a channel service unit (CSU) or a digital service unit (DSU) and a router.

The management server 420 to the aviation failure light device 100 via the wireless data communication network 300 and the mobile communication repeater 200 in accordance with the administrator's command command or a predetermined control value transmitted from the manager terminal 430. In addition to transmitting a control signal for requesting the check result, and stores the check result data received from the aviation failure light device 100 and transmits to the manager terminal 430.

In addition, the management server 420 mediates the wireless data communication network 300 and the mobile communication repeater 200 to control signals for forcibly turning on or turning off the aviation fault lamp according to an instruction command of the manager transmitted from the manager terminal 430. It transmits to the aviation failure light device 100.

The manager terminal 430 transmits an instruction command input by the manager to the management server 420 and displays the check result data transmitted from the management server 420.

Here, as shown in FIG. 5, the aviation failure lamp device 100 includes a solar cell 101, a storage battery 102, a booster unit 103, an aviation failure lamp 104, a charge control unit 105, and an optical light. The sensor 106, the charge monitoring unit 110, the power monitoring unit 120, the lamp monitoring unit 130, the control unit 140, and a mobile communication data transmission / reception unit 150 are included.

The solar cell 101 generates power by using sunlight, and the storage battery 102 accumulates power generated by the solar cell 101 under the control of the charging control unit 105, and the boosting unit 103. According to the control of the controller 140, the voltage level is increased to the power stored in the battery 102 and applied to the aviation failure lamp 104.

When the power generated by the solar cell 101 is greater than or equal to a predetermined value, the charging control unit 105 applies the charge to the storage battery 102 and charges the light sensor 106. The detection signal is input to the controller 140.

The charge monitoring unit 110 detects the current value output from the solar cell 101 and the current value output from the charge control unit 105 to the storage battery 102 to determine whether the charge control unit 105 is in normal operation. In addition to inputting the signal to the control unit 140, and detects the current value and the voltage level of the battery 102 to detect whether the overcharge and overvoltage, respectively, and inputs a detection signal corresponding to the detection result to the control unit 140.

The power monitoring unit 120 detects the voltage level of the power input from the battery 102 to the boosting unit 103 and the voltage level of the power output from the boosting unit 103 to the aviation fault lamp 104, respectively. This is compared with the set voltage and the comparison signal corresponding to the comparison result is input to the controller 140.

The lamp monitoring unit 130 monitors whether the aviation fault lamp 104 operates normally. The lamp monitoring unit 130 feeds back and detects a current in the power supply circuit between the booster 103 and the aviation fault lamp 104. The current detection signal corresponding thereto is applied to the controller 140.

The controller 140 controls the storage battery 102 and the booster 103 during the day when the illuminance is greater than a predetermined illuminance according to the detection signal applied from the optical sensor 106, so that the air traffic lights 104 are turned off and the illuminance is lower than the predetermined illuminance. At night, the aviation fault lamp 104 is turned on. Of course, it is also possible to periodically blink the aviation failure lamp 104 in accordance with the set control value.

In addition, the controller 140 checks whether the charge control unit 105 is normally operated and whether the battery 102 is overcharged or overvoltageed according to a signal input from the charge monitor 110, and then, from the power monitor 120. It is checked whether power of a proper voltage level is normally supplied from the boosting unit 103 to the aviation fault lamp 104 by the input signal, and the aviation fault lamp 104 is received by the signal input from the lamp monitoring unit 130. It checks whether it works normally, and if an abnormality or failure occurs as a result of the check, information about it is stored in a memory device (not shown).

In addition, when the request signal for the inspection result is input from the mobile communication data transmission / reception unit 150, the control unit 140 may check the mobile communication data transmission / reception unit 150 to check whether there is an abnormality in the device such as an aviation failure stored in the storage device. )

In addition, when the control signal for turning on or off the aviation obstacle lamp 104 is input from the mobile communication data transmission / reception unit 150, the controller 140 may be configured to have a storage battery (regardless of the ambient illumination sensed by the optical sensor 106). 102 and the booster 103 are controlled to turn on or turn off the aviation fault lamp 104.

An operation example of the present invention configured as described above will now be described in detail with reference to the accompanying drawings.

First, when light is emitted from a light source such as sunlight or an artificial light source (for example, a lamp) and the light is radiated to the solar cell 101, power is generated in the solar cell 101 and is generated in the solar cell 101. The electric power is charged in the storage battery 102 by the charging control section 105 when the current value is more than the set value.

In addition, a detection signal corresponding to the light intensity of the place where the optical sensor 106 is installed is generated from the optical sensor 106 and input to the controller 140, and the controller 140 is provided from the optical sensor 106. When the detected illuminance is less than the set illuminance by detecting the ambient illuminance by the input detection signal, the battery 102 and the booster 103 are controlled to apply power to the aviation obstacle lamp 104.

If the ambient illuminance detected by the sensing signal input from the optical sensor 106 is greater than or equal to the set illuminance, the controller 140 controls the storage battery 102 and the booster 103 to be applied to the aviation obstacle lamp 104. Cut off the power.

At this time, the charge monitoring unit 110 senses the current value output from the solar cell 101 and the current value output from the charge control unit 105 to the storage battery 102, respectively, the current value output from the solar cell 101 is equal to or greater than the set current value. When the current output from the charging control unit 105 to the battery 102 is sensed in the state, the sensing signal indicating that the charging control unit 105 is in normal operation is input to the controller 140 while the storage battery ( If the current output to the 102 is not sensed, a detection signal indicating that the charge control unit 105 is broken is input to the controller 140.

In addition, the charge monitoring unit 110 detects the current value and the voltage level of the battery 102, respectively, and compares the detected current value of the battery cell 102 with a preset reference current value. Inputting a detection signal indicating charging or overcharging to the controller 140 and comparing the detected voltage level of the battery 102 with a preset reference voltage level and generating a normal voltage or an overvoltage of the battery 102 according to the comparison result. The detection signal indicating the input to the control unit 140.

The power monitoring unit 120 detects the voltage level of the power input from the battery 102 to the boosting unit 103 and the voltage level of the power output from the boosting unit 103 to the aviation fault lamp 104, respectively. Next, this is compared with the set voltage, and according to each comparison result, the normal voltage detection signal is input to the controller 140 when the detected voltage is higher than the set voltage, and the undervoltage detection signal is input to the controller 140 when the detected voltage is lower than the set voltage.

In addition, the lamp monitoring unit 130 detects the current in the power supply circuit between the boosting unit 103 and the aviation obstacle lamp 104 and applies a current detection signal corresponding thereto to the control unit 140.

The controller 140 checks the failure state of each part by signals input from the charge monitoring unit 110, the power monitoring unit 120, and the lamp monitoring unit 130.

That is, the controller 140 checks whether the charge monitoring unit 110 is broken and whether the battery 102 is overcharged or overvoltageed by the detection signal input from the charge monitoring unit 110, and the power monitoring unit 120. The voltage level of the power input from the battery 102 to the booster unit 103 and the voltage level of the power output from the booster unit 103 to the aviation fault lamp 104 are normal. If the current detection signal is input from the lamp monitoring unit 130 while controlling the battery 102 and the booster 103 to apply power to the aviation fault lamp 104, the aviation fault lamp ( If the current detection signal is not input while the 104 is checked to be in normal operation, it is checked that a failure has occurred in the aviation fault lamp 104.

The control unit 140 periodically stores the check result in a storage device (not shown), and when a request signal for the check result is input from the mobile communication data transmission / reception unit 150, the check result stored in the storage device. Output to the mobile communication data transmission and reception unit 150.

Data of the check result output from the control unit 140 is converted into a mobile communication frequency signal in the mobile communication data transmission and reception unit 150 is transmitted to the mobile communication relay unit 200, the wireless by the mobile communication relay unit 200 The data communication network 300 is transmitted to the gateway 410 of the management company via the wireless data communication network 300 as a medium.

The check result data transmitted from the mobile communication data transmission / reception unit 150 through the mobile communication relay unit 200 and the wireless data communication network 300 are relayed by the gateway 410 and transmitted to the management server 420. In addition, the management server 420 stores the check result received through the gateway 410 in a storage device (not shown) and transmits the result to the manager terminal 430.

The inspection result transmitted from the management server 420 is displayed on the display screen of the manager terminal 430, through which the administrator can check whether there is a failure with respect to the aviation failure device 100.

In addition, the manager may transmit a control command for instructing to turn on or off the aviation failure light forcibly to the desired aviation failure light device 100, the control command input by the administrator from the manager terminal 100 to the management server 420. ) And is transmitted by the management server 420 to the aviation failure light device 100 via the gateway 410, the wireless data communication network 300, and the mobile communication relay unit 200.

The control command transmitted from the management server 420 is received by the mobile communication data transmission and reception unit 150 in the form of a mobile communication frequency signal and restored to the original control command by the mobile communication data transmission and reception unit 150 to control the controller 140. ), The controller 140 controls the storage battery 102 and the booster 103 regardless of the illuminance of the surroundings detected by the optical sensor 106 to turn on or turn off the aviation fault lamp 104.

The present invention is described by illustrating a specific embodiment, but the present invention is not limited to the above embodiment. Those skilled in the art can easily make various changes and modifications to the present invention, and it should be noted that such variations or modifications are included in the scope of the present invention as long as they use the features of the present invention.

As described above, the present invention, by checking the lighting state of the aviation failure lamp and the components of the components for driving it by itself, and transmits the check result to the management server through communication, the aviation failure lights from a remote place without a person instantaneous And there is an effect that can constantly monitor the status of the components and their failure.

In addition, it is possible to systematically store and manage the inspection results of a plurality of air traffic light devices through a database in the management server, through which the management, maintenance and history management of the air traffic light devices can be easily performed.

Claims (6)

Aviation obstacle configured to charge the power supplied from the predetermined power supply means to the storage battery by the charging control unit and to boost the power charged in the storage battery according to the amount of light detected by the light sensing means and apply it to the aviation fault lamp and turn it on. In the back device, Lamp monitoring unit for detecting the current flowing in the aviation failure lamp, When a current is sensed through the lamp monitoring unit while performing a control operation of applying or cutting off the power boosted from the boosting unit to the aviation obstacle lamp according to the amount of light detected by the light sensing means and supplying power to the aviation obstacle lamp. A control unit for checking in a normal state and checking in a fault state if not detected and periodically storing the check result; The mobile terminal converts the check result request control signal received in the form of a mobile communication frequency signal into a wired signal and inputs it to the control unit, and converts and transmits the check result data stored in the control unit to a mobile communication frequency signal under the control of the control unit. Aviation failure light device, characterized in that configured to include a communication data transmission and reception. The method of claim 1, wherein the current value output from the power supply means and the current value output from the charge control unit to the storage battery are respectively sensed and the current value output from the power supply means is greater than or equal to a set current value to the storage battery. If the output current is not detected further comprises a charge monitoring unit for inputting a detection signal to the control unit indicating that the charge control unit failure, And the control unit is further configured to perform a control operation of checking whether a failure of the charging control unit is caused by a detection signal input from the charging monitoring unit and storing the check result. The battery control apparatus of claim 1, further comprising a charge monitoring unit configured to detect a current value of the battery and compare it with a set current value and to input a detection signal indicating an overcharge state of the battery to the controller when the detected current value exceeds the set current value. and, And the control unit is further configured to perform a control operation of checking whether the battery is overcharged by a detection signal input from the charge monitoring unit and storing the check result. The charging method of claim 1, wherein the voltage level of the battery is detected and compared with the set voltage level, and when the detected voltage level exceeds the set voltage level, a charging signal for inputting a detection signal indicating an overvoltage of the battery to the controller is set. Further includes a monitoring unit, And the control unit is further configured to perform a control operation of checking whether an overvoltage of the storage battery is generated by a detection signal input from the charging monitoring unit and storing the check result. According to any one of claims 1 to 4, Detecting the level of the voltage applied from the storage battery to the boosting unit and compares it with a set voltage and if the detected voltage level is less than the set voltage detected as a result of the detection Further comprising a power monitoring unit for inputting a signal to the control unit, The control unit is configured to further perform a control operation for storing the check result by checking whether the voltage applied to the aviation failure light by the detection signal input from the power monitoring unit. The method according to any one of claims 1 to 4, wherein the voltage sensed from the boosting unit detects a level of the voltage applied to the aviation obstacle, and compares it with a set voltage. Further comprising a power monitoring unit for inputting the detection signal to the control unit, The control unit is configured to further perform a control operation for storing the check result by checking whether the voltage applied to the aviation failure light by the detection signal input from the power monitoring unit.