JP5562473B1 - Aircraft failure light failure detection system and failure detection method - Google Patents

Abstract

An aircraft obstacle light failure detection system and failure detection method capable of improving the failure detection accuracy of an aircraft obstacle light are provided.
Imaging means for imaging an aviation obstacle light provided at a predetermined position, position information relating to the distance and direction from the imaging means to the aviation obstacle light, and a threshold value of the emission intensity of the aviation obstacle light are recorded in advance. And at least the direction and focus of the imaging unit based on the position information recorded on the recording unit, and the imaging unit is controlled so as to obtain a determination image used for determining the failure of the aviation obstacle light Imaging control means for performing, emission intensity calculating means for calculating the emission intensity for determination of the aviation obstacle light from the image for determination, failure determination means for comparing the emission intensity for determination and the threshold value to determine a failure of the aviation obstacle light, Have.
[Selection] Figure 2

Description

  The present invention relates to an aircraft obstacle light failure detection system and failure detection method.

  Aviation obstruction lights are provided on power transmission towers, buildings, bridge piers, etc. according to their heights. If the aviation obstruction light is turned off due to a failure such as disconnection, it is necessary to replace the aviation obstruction light at an early stage. For this reason, it is required to constantly monitor the failure of the aviation obstacle light. As a failure detection method for an aviation obstacle light, a method for detecting a failure of an aviation obstacle light by detecting a light emission state or an energization state of the aviation obstacle light is used (see, for example, Patent Documents 1 to 4).

JP 09-128515 A JP 2008-071629 A JP 2008-293775 A JP 2008-293776 A

  However, in the methods described in Patent Documents 1 to 4 described above, there is a possibility that a failure of the aviation obstacle light is misidentified.

  An object of the present invention is to provide a failure detection system and a failure detection method for an aviation obstacle light that can improve the failure detection accuracy of the aviation obstacle light.

According to a first aspect of the invention,
Imaging means for imaging an aviation obstacle light provided at a predetermined position;
Recording means for pre-recording position information relating to the distance and direction from the imaging means to the aviation obstacle light, and a threshold value of the emission intensity of the aviation obstacle light;
Based on the position information recorded in the recording unit, the imaging unit is controlled to adjust at least the direction and focus of the imaging unit to obtain a determination image used for determining the failure of the aviation obstacle light. Imaging control means for
Emission intensity calculating means for calculating emission intensity for determination of the aviation obstacle light from the image for determination;
A failure determination means for comparing the determination light emission intensity with the threshold to determine a failure of the aviation obstacle light;
An aircraft obstacle light failure detection system is provided.

According to a second aspect of the invention,
The imaging control means includes
Before determining the failure of the aviation obstacle light by the failure determination means, the imaging means is controlled to image the aviation obstacle light by adjusting at least the direction and focus of the imaging means, and the imaging control means The failure detection system for an aviation obstacle light according to the first aspect is provided, wherein the adjusted setting information of the direction and focus of the imaging unit is recorded in the recording unit as the position information.

According to a third aspect of the invention,
The recording means includes
An area within one field of view when the imaging means images the aviation obstacle light, and records in advance an area including at least a light emitting portion of the aviation obstacle light as a light emission area,
The emission intensity calculating means includes
The failure detection system for an aviation obstacle light according to the first or second aspect, wherein the determination light emission intensity is calculated only from within the light emission region of the determination image, is provided.

According to a fourth aspect of the invention,
A first object located at a distance a (however a> 0) from the imaging means and a second object located at a distance b (where b> a) from the imaging means are imaged by the imaging means, Visibility calculation means for calculating that the visibility is a when the first object can be observed and the second object cannot be observed;
Visibility determining means for determining whether or not the aviation obstacle light is located within the visibility;
An aircraft fault light failure detection system according to any one of the first to third aspects is provided.

According to a fifth aspect of the present invention,
The failure determination means includes
When the visibility determining means determines that the aviation obstacle light is not located within the visibility, the failure of the aviation obstacle light is not determined,
The failure detection system for an aviation obstacle light according to a fourth aspect, wherein the aviation obstacle light determines that the aviation obstacle light has failed when the visibility determination means determines that the aviation obstacle light is located within the visibility.

According to a sixth aspect of the present invention,
The imaging control means includes
When the visibility determination means determines that the aviation obstacle light is not located within the visibility, the image pickup means does not acquire the determination image of the aviation obstacle light,
The aviation obstacle light according to the fourth aspect, wherein the imaging means is controlled to acquire the determination image of the aviation obstacle light when the visibility judgment means judges that the aviation obstacle light is located within the visibility. A fault detection system is provided.

According to a seventh aspect of the present invention,
In the recording means,
The threshold value of the emission intensity is determined in advance for at least one of an R value, a G value, and a B value in the color image of the aviation obstacle light acquired by the imaging unit,
The failure determination means includes
The aviation obstacle light is calculated by comparing at least one of the R value, G value, and B value for determination calculated as the light emission intensity for determination for each pixel of the image for determination with the threshold value. An aircraft fault light failure detection system according to any one of the first to sixth aspects is provided.

According to an eighth aspect of the present invention,
In the recording means,
The threshold value of the emission intensity is predetermined for a linear sum of R value, G value, and B value in the color image of the aviation obstacle light acquired by the imaging means,
The failure determination means includes
First to first determination of failure of the aviation obstacle light by comparing a linear sum for determination of R value, G value and B value calculated as the light emission intensity for determination for each pixel of the image for determination with the threshold value An aircraft fault light failure detection system according to any of the sixth aspects is provided.

According to a ninth aspect of the present invention,
In the recording means,
The threshold value of the light emission intensity is a hue ratio that is a ratio of another value to at least one of the R value, the G value, and the B value in the color image of the aviation obstacle light acquired by the imaging unit. Pre-determined for
The failure determination means includes
The determination hue ratio calculated as the determination emission intensity for each pixel of the determination image and corresponding to the threshold is compared with the threshold to determine a failure of the aviation obstacle light. An aircraft obstacle light failure detection system according to any one of the above is provided.

According to a tenth aspect of the present invention,
10. The system according to claim 1, further comprising a warning unit that issues a failure warning indicating that the aviation obstacle light has failed when the light emission for determination of the aviation obstacle light is lower than the threshold. An aircraft fault light failure detection system is provided.

According to an eleventh aspect of the present invention,
The threshold value of the emission intensity has a first threshold value and a second threshold value higher than the first threshold value,
The failure determination means includes
Predicting a failure of the aviation obstacle light when the light emission for determination of the aviation obstacle light is equal to or higher than the first threshold and lower than the second threshold;
The failure detection of the aviation obstacle light according to any one of the first to tenth aspects, wherein it is determined that the aviation obstacle light has failed when the determination emission intensity of the aviation obstacle light is lower than the first threshold value. A system is provided.

According to a twelfth aspect of the present invention,
The aviation obstacle light according to the eleventh aspect, further comprising warning means for issuing a prediction warning indicating that a failure of the aviation obstacle light is predicted when the failure determination means predicts a failure of the aviation obstacle light. A fault detection system is provided.

According to a thirteenth aspect of the present invention,
A first object located at a distance a (however a> 0) from the imaging means and a second object located at a distance b (where b> a) from the imaging means are imaged by the imaging means, Visibility calculation means for calculating that the visibility is a when the first object can be observed and the second object cannot be observed,
In the recording means,
The threshold value of the emission intensity is determined differently depending on the visibility,
The failure determination means includes
The failure detection system for an aviation obstacle light according to any one of the first to twelfth aspects, wherein the failure of the aviation obstacle light is determined based on the threshold value corresponding to the visibility calculated by the visibility calculation means. .

According to a fourteenth aspect of the present invention,
A pre-recording step for pre-recording position information related to the distance and direction from the image sensor that images the aviation obstacle light provided at a predetermined position to the aviation obstacle light, and a threshold value of the emission intensity of the aviation obstacle light;
An imaging step of adjusting at least the direction and focus of the imaging device based on the position information to obtain a determination image used for determining the failure of the aviation obstacle light;
A determination step of determining a failure of the aviation obstacle light by comparing the light emission intensity for determination of the aviation obstacle light calculated based on the image for determination and the threshold;
A fault detection method for an aviation obstacle light is provided.

  ADVANTAGE OF THE INVENTION According to this invention, the failure detection system and failure detection method of an aviation obstacle light which can improve the failure detection accuracy of an aviation obstacle light are provided.

It is the schematic which shows the structure of the failure detection system of the aviation obstacle light which concerns on 1st Embodiment of this invention. It is a schematic block diagram of the controller of the failure detection system used suitably for 1st Embodiment of this invention. It is a figure which shows the flow of the pre-recording process which concerns on 1st Embodiment of this invention. It is a schematic diagram when recording the light emission area | region of an aviation obstacle light in a prior recording process. It is a figure which shows the flow of the failure detection process which concerns on 1st Embodiment of this invention. It is a figure which shows the flow of the visibility calculation process which concerns on 1st Embodiment of this invention. It is a schematic diagram when calculating the visibility at the time of monitoring in the visibility calculation process which concerns on 1st Embodiment of this invention. It is a figure which shows the flow of the failure detection method which concerns on 2nd Embodiment of this invention. It is a schematic diagram when calculating the present visibility in the visibility calculation process which concerns on 2nd Embodiment of this invention.

<One Embodiment of the Present Invention>
Hereinafter, an embodiment of the present invention will be described with reference to the drawings.

(1) Schematic Configuration of Failure Detection System First, an aircraft obstacle light failure detection system 10 according to an embodiment of the present invention will be described with reference to FIG. FIG. 1 is a schematic diagram showing a configuration of an aircraft obstacle light failure detection system 10 according to an embodiment of the present invention.

  The failure detection system 10 of the aviation obstacle light according to the present embodiment is configured to periodically detect the aviation obstacle light 300 and detect a failure of the aviation obstacle light 300. The “failure” of the aviation obstacle light 300 means a non-lighting state or a reduced brightness state of the aviation obstacle light 300 including the disconnection or deterioration of the aviation obstacle light 300, the power trouble of the aviation obstacle light 300, and the like. In the following, “at the time of monitoring” means a time when a failure of the aviation obstacle light 300 is determined.

  Specifically, the failure detection system 10 for an aviation obstacle light according to this embodiment includes an ITV (Industrial Television) camera (imaging means) 100 that images the aviation obstacle light 300 provided at a predetermined position, and an aviation obstacle light 300. And a controller (control means) 120 that controls the ITV camera 100 to take an image and determines the state of the aviation obstacle light 300.

  An example of the flow of the failure determination of the aviation obstacle light 300 in this embodiment is shown. (However, the present invention is not limited to this example as will be described later.) First, the controller (control means) 120 is based on the information etc. previously input from the input / output unit 121j and recorded in the recording device 121i, etc. The ITV control signal is transmitted to the ITV camera 100 through the ITV control unit 121c. An image signal and / or ITV state information captured by the ITV camera 100 based on this signal is transmitted to the image processing unit 121b through the transmission unit 121a. The image processing unit 121b performs a noise removal process, which will be described later, based on the received information and the like. The main control unit 121d calculates the visibility by the visibility calculation unit 121g based on the information and the like, and determines the aviation obstacle light 300 for which the failure determination is performed by the visibility determination unit 121h. If necessary, the main control unit 121d again captures the aviation obstacle light 300 or the like to be monitored by the ITV camera 100 via the ITV control unit 121c and the transmission unit 121a, and if necessary, an image processing unit. Image processing is performed by 121b. The main control unit 121d causes the emission intensity calculation unit 121e to calculate the emission intensity of the aviation obstacle light 300 to be monitored based on the obtained image signal and ITV state information, and causes the failure determination unit 121f to calculate the aviation obstacle light 300. Make a failure judgment. When necessary, the main control unit 121d displays a failure or the like with the alarm unit 121k or the like. During this time, the main control unit 121d appropriately stores various types of information in the recording device 121i as necessary. Below, each structure etc. are explained in full detail in order.

  As shown in FIG. 1, for example, a plurality of power transmission towers 200 are provided at different predetermined positions. For example, the 1st power transmission tower 201, the 2nd power transmission tower 202, and the 3rd power transmission tower 203 are each arrange | positioned in the position spaced apart. Hereinafter, the “power transmission tower 200” is an arbitrary power transmission tower provided with a aviation obstacle light to be monitored, or a generic name thereof.

  Each of the plurality of power transmission towers 200 is provided with an aviation obstacle light 300. For example, the first power transmission tower 201, the second power transmission tower 202, and the third power transmission tower 203 include a first aviation obstacle light 301, a second aviation obstacle light 302, and a third aviation obstacle light, respectively. 303 is provided. Hereinafter, the “aviation obstacle light 300” is a generic name including the aviation obstacle light to be monitored or all of them.

  Here, the first power transmission tower 201, the second power transmission tower 202, and the first air navigation obstacle light 301, the second aircraft obstacle light 302, and the third aircraft obstacle light 303, which are monitoring targets, are provided. The area including the third power transmission tower 203 is set to, for example, “first area”, “second area”, and “third area”, respectively, in the aviation obstacle light failure detection system 10 in the present embodiment. Here, the monitoring target area is set, for example, from the first area to the Nth area where the Nth aviation obstacle light (not shown) is provided (where N is a natural number).

  Further, the emission color, brightness, light emission period, number of installations, arrangement, etc. of each aviation obstacle light 300 are the height of the building such as the power transmission tower 200 where the aviation obstacle light 300 is installed, and the aviation obstacle light 300 is attached to the building. It is set according to the installation location. Further, the aviation obstacle light 300 is configured to be constantly lit or blinking. Specifically, the aviation obstacle light 300 is classified into a high-light aviation trouble light, a medium-light white aviation trouble light, a medium-light red aviation trouble light, a low-light aviation trouble light, and the like according to laws and regulations. Further, for example, the aviation obstacle light 300 is configured by a halogen lamp, a xenon lamp, an LED (Light Emitting Diode), or the like.

  The ITV camera 100 as the imaging means (or imaging device) according to the present embodiment is configured to acquire full-color still images or moving images of a plurality of areas including the aviation obstacle light 300, for example. For example, the ITV camera 100 acquires a still image when the aviation obstacle light 300 lights up, and acquires a moving image when the aviation obstacle light 300 blinks. When the ITV camera 100 acquires a moving image of the aviation obstacle light 300, for example, the aviation obstacle light 300 is imaged at 25 to 30 frames / second.

  The ITV camera 100 is disposed at a position where the first to Nth aircraft obstacle lights 300 to be monitored can be imaged. The maximum distance (monitoring maximum radius) from the ITV camera 100 to the monitored aviation obstacle light 300 is, for example, not less than 1 km and not more than 30 km, for example, not less than 9 km and not more than 12. Specifically, for example, one transmission tower 200 is provided every 300 m, one aviation obstacle light 300 is provided on the transmission tower 200, and the maximum distance from the ITV camera 100 to the monitored aviation obstacle light 300 is When it is 9 km or more and 12 km or less, the number of the aviation obstacle lights 300 to be monitored by one ITV camera 100 is 30 or more and 40 or less × the number of tracks.

  The ITV camera 100 also has, for example, a focus function, a zoom function, a pan / tilt function, and an iris adjustment function (F value adjustment function). The “focus function” is automatically set by, for example, a focus function that operates based on setting information received from the ITV control unit 121c described later or setting information specifically input by a person, and a function built in the ITV camera 100. And an autofocus function in which the focus is adjusted. The ITV camera 100 may have a blur correction function. The ITV camera 100 is configured to pick up images of the first to Nth aviation obstacle lights with at least a focus function, a zoom function, a pan / tilt function, an iris adjustment function, and the like.

  The ITV camera 100 is connected to a controller 120 that controls the ITV camera 100 so as to monitor the aviation obstacle light 300 as will be described later. Specifically, the ITV camera 100 is connected to a transmission unit 121a as a transmission means in the controller 120 as will be described later. Further, for example, the controller 120 is provided at a position separated from the ITV camera 100, and transmits and receives various signals (image signal, ITV state information) to and from the ITV camera 100 via the transmission unit 121a. Details of the controller 120 will be described later.

  Mainly, the ITV camera 100 and the controller 120 constitute an aircraft obstacle light failure detection system 10.

(2) Configuration of Controller Next, the configuration of the controller 120 as a control unit (control unit) according to the present embodiment will be described with reference to FIG. FIG. 2 is a schematic configuration diagram of the controller 120 of the failure detection system 10 that is preferably used in one embodiment of the present invention.

  The controller 120 of the present embodiment includes a recording device (recording unit) 121 i that records in advance position information related to the distance and direction from the ITV camera 100 to the aviation obstacle light 300 and a threshold value of the emission intensity of the aviation obstacle light 300. Based on the position information recorded in the recording device 121i, at least the direction and focus of the ITV camera 100 are adjusted, and the ITV camera 100 is controlled so as to obtain a determination image used for determining the failure of the aviation obstacle light 300. Comparison between the ITV control unit (imaging control unit) 121c that performs determination, the emission intensity calculation unit (emission intensity calculation unit) 121e that calculates the determination emission intensity of the aviation obstacle light 300 from the determination image, and the determination emission intensity and the threshold value And a failure determination unit (failure determination means) 121f that determines a failure of the aviation obstacle light 300. Details will be described below.

(Transmission part)
As illustrated in FIG. 2, the controller 120 includes a transmission unit 121 a that transmits and receives signals and the like to and from the ITV camera 100. The transmission unit 121a is connected to the ITV camera 100, transmits an ITV control signal for controlling the ITV camera 100 to the ITV camera 100, and the ITV camera 100 captures an image signal (also simply referred to as “image”). ) And “ITV status information” including the focus state, zoom state, pan / tilt state, iris adjustment state, etc. of the ITV camera 100 are received from the ITV camera 100.

(Image processing unit)
Based on the image signal received from the ITV camera 100, the transmission unit 121a is connected to an image processing unit (image processing means) 121b that processes the “judgment image (image for monitoring)” of the aviation obstacle light 300. ing. The “determination image” referred to here is an image that is acquired by the ITV camera 100 during monitoring and is used for failure determination of the aviation obstacle light 300. For example, the image processing unit 121b corrects “blur” caused by vibration of the ITV camera 100 when the aviation obstacle light 300 is imaged, a process of removing noise from an image obtained by imaging the aviation obstacle light 300, or A smoothing process is performed. When the ITV camera 100 itself has a similar processing function, or when the imaging performance of the ITV camera 100 is high, an image (still image and / or non-processed image) obtained from the ITV camera 100 is used. (Or a moving image) can be used as a “determination image” as it is. In this case, the determination image can be directly transferred to each unit described later without passing through the image processing unit 121b.

(ITV control unit)
In addition, an ITV control unit (imaging control unit) 121c that controls the ITV camera 100 is connected to the transmission unit 121a. For example, the ITV control unit 121c adjusts at least the direction (pan / tilt) and focus of the ITV camera 100 according to the aviation obstacle light 300 based on the “ITV status information” received from the ITV camera 100 by the transmission unit 121a. It is configured to

  Here, “position information” relating to the distance and direction from the ITV camera 100 to the aviation obstacle light 300 is recorded in advance in the recording device 121i described later. In this embodiment, the ITV control unit 121c adjusts at least the direction and focus of the ITV camera 100 with respect to the aviation obstacle light 300 before determining the failure of the aviation obstacle light 300 (before the failure detection process). The ITV camera 100 is controlled so as to capture the obstacle light 300, and the “position information” of the aviation obstacle light 300 described above is adjusted to the direction (pan / tilt) of the ITV camera 100 adjusted for each aviation obstacle light 300. In addition, “setting information” such as focus, zoom, and iris is recorded in a recording device 121i described later. Further, the ITV control unit 121c adjusts at least the direction and focus of the ITV camera 100 based on the setting information of the ITV camera 100 recorded in advance in the recording device 121i in the failure detection process of the aviation obstacle light described later, The ITV camera 100 is configured to acquire a “determination image” used to determine the aviation obstacle light 300.

(Main control unit)
The controller 120 performs a light emission intensity calculation unit 121e, a failure determination unit 121f, a visibility calculation unit 121g, which will be described later, so as to perform a failure determination of the aviation obstacle light 300 periodically or when a predetermined condition (date and time) is met. It has a main control part (main control means) 121d for controlling the visibility determination part 121h. The main control unit 121d is connected to, for example, the image processing unit 121b and the ITV control unit 121c. A failure determination unit 121f described later may also serve as the main control unit 121d.

(Luminescence intensity calculator)
The controller 120 also includes a light emission intensity calculation unit 121e that calculates the light emission intensity of the aviation obstacle light 300 from the determination image acquired from the ITV camera 100 via the image processing unit 121b.

Here, the emission intensity of the aviation obstacle light 300 is obtained as, for example, a linear sum of hue values (R value, G value, and B value) in the color image of the aviation obstacle light 300 captured by the ITV camera 100. The “linear sum of R value, G value, and B value” here is “L” for linear sum, “R” for R value, “G” for G value, “B” for B value, x, y , Z are arbitrary positive numbers,
L = xR + yG + zB
Given in. Note that a specific hue value can be weighted by setting x, y, and z to different values.

Note that the recording device 121i described later has a light emission intensity threshold (TH _L ) as a reference value for determining a failure or the like for each aviation obstacle light 300 or for any group having the same luminescence type as the aviation obstacle light 300. Are previously recorded (stored). Further, in the recording device 121i described later, the above-described linear sum in the color image of the aviation obstacle light 300 acquired by the ITV camera 100 is previously determined (recorded).

  The emission intensity calculation unit 121e is configured to calculate “determination emission intensity” of the aviation obstacle light 300 from the determination image acquired by the ITV camera 100. Specifically, the emission intensity calculation unit 121e calculates a “determination linear sum” of the R value, the G value, and the B value calculated as the determination emission intensity for each pixel of the color determination image. It is configured to be “judgment emission intensity”. The determination linear sum as the determination light emission intensity is compared with the above-described threshold value of the light emission intensity, and is used when determining the failure of the aviation obstacle light.

  Further, in the recording apparatus 121i described later, an area within one field of view when the ITV camera 100 captures the aviation obstacle light 300, and an area including at least the “light emission portion” of the aviation obstacle light 300 is referred to as a “light emission area”. Are recorded in advance. Here, the “light emitting portion” refers to a portion having the light emitting function of the aviation obstacle light 300, and specifically refers to an element portion such as at least a halogen lamp, a xenon lamp, or an LED. The “light emitting area” is composed of, for example, four pixel coordinates that divide a rectangular area in an image.

The threshold value TH _L of the light emission intensity is the value of the linear sum of the R value, G value, and B value of each pixel in the “light emission area” in the image of the aviation obstacle light 300. It is predetermined with respect to the value integrated over the pixels.

  The light emission intensity calculation unit 121e is configured to calculate a determination linear sum as the determination light emission intensity only from within the light emission region of the determination image acquired by the ITV camera 100. The determination light emission intensity calculated only from the light emission area of the determination image is compared with a light emission intensity threshold value determined only within the same light emission area, and is used when determining a failure of the aviation obstacle light 300.

(Failure determination unit)
The controller 120 also includes a failure determination unit (failure determination means) 121f that determines the state of the aviation obstacle light 300. Here, the “state of the aviation obstacle light 300” includes, for example, a light emission type of the aviation obstacle light 300, a state in which the failure of the aviation obstacle light 300 is predicted, a state in which the aviation obstacle light 300 has failed, and the like.

  For example, the failure determination unit 121f is configured to determine the “light emission type” of the aviation obstacle light 300 based on an image acquired from the ITV camera 100 via the image processing unit 121b. The “light emission type” is a general term for the light emission characteristics of the aviation obstacle light 300 including at least one of the emission color, the luminance, the light emission period, etc. when the aviation obstacle light 300 normally emits light.

  In addition, the failure determination unit 121f compares the emission intensity for determination obtained from the determination image acquired by the ITV camera 100 with the threshold value recorded in the recording device 121i in the failure detection process of the aviation obstacle light described later. The failure lamp 300 is configured to determine a failure.

  Moreover, in the recording device 121i described later, a first threshold value and a second threshold value higher than the first threshold value are recorded in advance as threshold values relating to the emission intensity of the aviation obstacle light 300.

  The failure determination unit 121f is configured to compare the light emission intensity for determination of the aviation obstacle light 300 with the first threshold value or the second threshold value, and determine the state of the aviation obstacle light 300 according to each threshold value. Moreover, the failure determination part 121f transmits the warning signal according to the state of the aviation obstacle light 300 to the alarm part 121k described later.

  Details of the determination process by the failure determination unit 121f will be described later.

(Visibility calculation part)
In addition, the controller 120 includes a visibility calculation unit (visibility calculation means) 121 g that calculates the visibility of the ITV camera 100. “Visibility” refers to the maximum distance at which an object can be clearly observed by the ITV camera 100. It should be noted that the visibility can change due to changes in weather during monitoring, changes in the environment around the aviation obstacle light 300, and the like. The visibility calculation unit 121g is configured to calculate the visibility that can be captured by the ITV camera 100 during monitoring based on the result of observing the object by the ITV camera 100. Details of the visibility calculation processing by the visibility calculation unit 121g will be described later.

(Visibility determination part)
In addition, the controller 120 includes a visibility determination unit (visibility determination means) 121h that determines whether the aviation obstacle light 300 is located within the visibility based on the visibility calculated by the visibility calculation unit 121g. Details of the visibility determination processing by the visibility determination unit 121h will be described later.

(Recording device)
The controller 120 has a recording device (recording means, storage means) 121i for storing various data. The recording device 121i includes image data after image processing of the aviation obstacle light 300 is performed by the image processing unit 121b, ITV state information of the ITV camera 100 from the ITV control unit 121c, and information from the ITV camera 100 to the aviation obstacle light 300. Position information related to the distance and direction, direction information (pan / tilt) of the ITV camera 100 adjusted with respect to the aviation obstacle light 300 by the ITV control unit 121c, setting information such as focus, zoom, and iris, light emission of the aviation obstacle light 300 Intensity threshold values (first threshold value and second threshold value), light emission type of the aviation obstacle light 300, object information in the visibility calculation step described later, image information regarding the shape of the object, visibility of the ITV camera 100, aviation obstacle light 300 Failure determination period, the distance from the ITV camera 100 to the setting information of the ITV camera 100 And it is configured to record the determined table, intermediate value on the function or various calculations and the like.

  These data recorded in the recording device 121i are stored so as to be readable by the ITV control unit 121c, the light emission intensity calculation unit 121e, the failure determination unit 121f, the visibility calculation unit 121g, the visibility determination unit 121h, and the main control unit 121d. Has been.

(I / O device)
The controller 120 also includes an input / output unit (input / output means) 121j that inputs various data to the controller 120 and outputs various data from the controller 120. For example, the input / output unit 121j includes any one of a touch panel, a mouse, a keyboard, an operation terminal, and the like. In addition, the controller 120 may include a display unit (not shown) that outputs various data and a determination result by the failure determination unit 121f. Note that the display unit may be included in the input / output unit 121j.

(Alarm part)
In addition, the controller 120 includes an alarm unit (alarm unit) 121k that issues a warning based on a result determined by the failure determination unit 121f. Note that the display unit described above may also serve as the alarm unit 121k. In addition, the alarm unit 121k may use, for example, a notification by sound, or may display warning contents in order at predetermined time intervals with respect to a plurality of arbitrarily defined terminals. In addition, the alarm unit 121k may have a function of notifying a warning individually about failures of a plurality of aviation obstacle lights 300 in the same area arbitrarily defined, for example.

  As described above, the controller 120 is mainly configured by the ITV control unit 121c, the main control unit 121d, the light emission intensity calculation unit 121e, the failure determination unit 121f, the visibility calculation unit 121g, and the visibility determination unit 121h. Note that the controller 120 may include the transmission unit 121a, the recording device 121i, the image processing unit 121b, the input / output unit 121j, and the alarm unit 121k.

  Note that the ITV control unit 121c, the main control unit 121d, the light emission intensity calculation unit 121e, the failure determination unit 121f, the visibility calculation unit 121g, the visibility determination unit 121h, and the like in the controller 120 may not be hardware independent of each other. At least one of the ITV control unit 121c, the main control unit 121d, the light emission intensity calculation unit 121e, the failure determination unit 121f, the visibility calculation unit 121g, the visibility determination unit 121h, and the like is, for example, a general-purpose computer and a main control unit. , A program (software) that functions as a unit corresponding to at least one of the emission intensity calculation unit, the failure determination unit, the visibility calculation unit, and the visibility determination unit. In this case, the controller 120 is a computer having a CPU (Central Processing Unit), a RAM (Random Access Memory), an HDD (Hard Disk Drive) or flash memory as a recording device 121i, and an I / O port as a transmission unit 121a. Composed.

  Furthermore, in the image processing unit 121b, a part of the processing of the image processing unit 121b may be hardware, and a processing of the other part of the image processing unit 121b may be a program.

(3) Aviation Obstruction Light Failure Detection Method Next, an aviation obstruction light failure detection method according to the present embodiment will be described.

  The aviation obstacle light failure detection method of this embodiment is a position related to the distance and direction from the ITV camera (imaging device or imaging means) 100 that images the aviation obstacle light 300 provided at a predetermined position to the aviation obstacle light 300. Information and a pre-recording step for preliminarily recording the emission intensity threshold value of the aviation obstacle light 300, and at least the direction and focus of the ITV camera 100 are adjusted based on the position information to determine the failure of the aviation obstacle light 300 An imaging step of acquiring a determination image to be used, and a determination step of determining a failure of the aviation obstacle light 300 by comparing the emission intensity for determination of the aviation obstacle light 300 calculated based on the determination image with a threshold value; Have. Details will be described below. In the following description, each step of the aircraft fault light failure detection method is controlled by each unit of the controller 120.

(Pre-recording step S110)
First, the pre-recording step S110 will be described with reference to FIG. 1, FIG. 3, and FIG. FIG. 3 is a diagram showing a flow of a pre-recording process according to the present embodiment. FIG. 4 is a schematic diagram when the light emitting area of the aviation obstacle light is recorded in the pre-recording step.

  The pre-recording step S110 is performed, for example, when the aviation trouble light failure detection system 10 is installed, when a newly monitored aviation trouble light 300 is installed, or when the failure detection system 10 is maintained.

  Here, as shown in FIG. 1, for example, a plurality of power transmission towers 200 having aviation obstacle lights 300 are provided at different predetermined positions. The ITV camera 100 is installed in a position where the aviation obstacle light 300 installed in N areas can be imaged in advance.

  In the pre-recording step S110, for example, the aviation obstacle light 300 is imaged in advance by the ITV camera 100 as described below, and various data used for determining a failure of the aviation obstacle light 300 is recorded in advance.

(Direction and focus adjustment step S111)
As shown in FIG. 3, the ITV control unit 121 c adjusts at least the direction and focus of the ITV camera 100 with respect to the aviation obstacle light 300 to be monitored so that the aviation obstacle light 300 is imaged. 100 is controlled. The ITV control unit 121c may control the ITV camera 100 so as to capture the aviation obstacle light 300 by adjusting the zoom and iris of the ITV camera 100.

  For example, as illustrated in FIG. 1, the ITV control unit 121 c controls the ITV camera 100 so that all the first aviation obstacle lights 301 provided in the first power transmission tower 201 are in the same field of view. .

(Recording step S112)
Next, for example, as shown in FIG. 1, the ITV control unit 121 c sets an area in which all the first aviation obstacle lights 301 are in the same field of view as a “first area”, and an ITV camera. As position information related to the distance and direction from the aviation obstacle light 300 of the first area to the first area, for example, setting information of the direction and focus of the ITV camera 100 adjusted to the first aviation obstacle light 301 of the first area is recorded. 121i is recorded in advance. In other words, the ITV control unit 121c replaces the information corresponding to the spatial position coordinates (the horizontal coordinate and the height coordinate) of the aviation obstacle light 300 (or together with these information) with the ITV camera. 100 mechanical setting information is recorded in the recording device 121i in advance.

  When the first aviation obstacle light 301 is imaged using the zoom function and the iris adjustment function of the ITV camera 100, the ITV control unit 121c includes the zoom information, the iris information, and the like in the setting information described above. In addition, it may be recorded in advance on the recording device 121i. In addition, when another aviation obstacle light 300 provided in another power transmission tower 200 is adjacent to the first power transmission tower 201 and the ITV camera 100 can capture an image within the same field of view without changing the direction, It may be set as the “first area” including the aviation obstacle light 300. In this case, in the recording device 121i, an information table for managing the mechanical setting information of the ITV camera 100 for each area and an information table indicating to which area each aviation obstacle light 300 belongs are managed in advance. May be recorded.

  Here, as shown in FIG. 4, in the recording step S112, the ITV control unit 121c adjusts the ITV camera 100 with respect to the kth aviation obstacle lights 304a to 304d in the kth area as an arbitrary area, for example. (K is a natural number from 1 to N). FIG. 4 schematically shows an image of one field of view in the k-th area.

  Within this field of view, the portions other than the “light emitting portion” of the kth aviation obstacle lights 304 a to 304 d to be monitored are portions that are not directly related to the failure determination of the aviation obstacle light 300. In addition, a part other than the light emitting part of the k-th aviation obstacle light 304a to 304d to be monitored may cause an erroneous determination in the failure detection process of the aviation obstacle light. For example, if light other than the aviation obstacle light 300 (light from a car or airplane, or reflected light from these buildings) is detected from a part other than the light emission part of the kth aviation obstacle lights 304a to 304d, an error occurs. It may cause judgment.

  Therefore, for example, the light emission intensity calculation unit 121e is an area within one field of view when the ITV camera 100 captures the kth area, and includes an area including at least the light emission part of the kth aviation obstacle lights 304a to 304d. The light emitting areas 404a to 404d "are recorded in advance in the recording device 121i. When at least the focus conditions of the ITV camera 100 are different in each of the light emitting areas 404a to 404d, the ITV control unit 121c sets the detailed settings of the ITV camera 100 for each of the light emitting areas 404a to 404d associated with each aviation obstacle light 300. Information is recorded in advance in the recording device 121i. In the determination step described later, the light emission intensity of only this “light emission region” is used for the determination.

  In the recording step S112, the light emission type of each aviation obstacle light 300 is recorded in the recording device 121i in advance.

  For example, as shown in FIG. 4, in the recording step S112, the ITV control unit 121c records the setting information of the ITV camera 100 by imaging the kth aviation obstacle light 304a in the kth area. The failure determination unit 121f determines the “light emission type” of the k-th aviation obstacle light 304a based on the pre-recorded image acquired from the ITV camera 100 via the image processing unit 121b. 121i is recorded. The “light emission type” is determined for all the aviation obstacle lights 300 in the kth area and recorded in the recording device 121i.

  Further, in the recording step S112, a threshold value of light emission intensity determined for each aviation obstacle light 300 is recorded in the recording device 121i in advance.

  For example, in the recording step S112, the light emission intensity calculation unit 121e records the initial light emission intensity of each aviation obstacle light 304 in the kth area in the recording device 121i in advance based on the pre-recorded image in the kth area. In the determination step described later, for example, a threshold value obtained by multiplying the above-described initial light emission intensity by a predetermined ratio is used according to the above-described “light emission type”.

  Further, in the recording step S112, the ITV control unit 121c determines whether or not the ITV camera 100 is observable in the visibility calculation step described later within one field of view when the ITV camera 100 captures the k-th area, for example. Things "are recorded in the recording device 121i in advance. At this time, the initial image of the object and setting information such as the direction and focus of the ITV camera 100 adjusted to the object are recorded in the recording device 121i in advance.

  The “object (landmark)” here is an object that is observed in order to calculate the visibility. Specifically, the “object” is, for example, an arbitrary building, or a structure, signboard, or chimney installed in an arbitrary building. Preferably, the “object” emits light, and is, for example, lighting installed in an arbitrary building, aviation obstacle light, or the like. It should be noted that the aviation obstacle light as an object for visibility calculation is not limited to whether or not it is a monitoring target. The details of the visibility calculation step will be described later.

  The above-mentioned “direction and focus adjustment S111” and “recording step S112” are performed on all the aviation obstacle lights 300 in the respective areas from the first to the Nth areas set as monitoring targets. Thereby, for example, setting information of the ITV camera 100 for each area from the first to the Nth area set as a monitoring target, a light emission area for the aviation obstacle light 300 in each area, and setting information of the ITV camera 100 for the light emission area , And the light emission type of the aviation obstacle light 300 are recorded in the recording device 121i in advance.

(Failure detection process)
Next, the failure detection process of the aviation obstacle light will be described with reference to FIGS. FIG. 5 is a diagram illustrating a flow of a failure detection process according to the present embodiment. FIG. 6 is a diagram illustrating a flow of the visibility calculation process according to the present embodiment. FIG. 7 is a schematic diagram when the visibility at the time of monitoring is calculated in the visibility calculation step according to the present embodiment.

  Here, a case where the kth aviation obstacle light 304 in the kth area is monitored in the failure detection process of the aviation obstacle light will be described. For example, the main control unit 121d controls the light emission intensity calculation unit 121e, the failure determination unit 121f, the visibility calculation unit 121g, and the visibility determination unit 121h so as to perform failure determination (monitoring) of the aviation obstacle light 300 at a predetermined cycle. . For example, the failure detection step is performed once a day at a predetermined time.

(Visibility calculation step S120)
First, as shown in FIG. 5, for example, the visibility calculation step S120 is performed as follows. In the visibility calculation step S120, the visibility calculation unit 121g includes a first object located at a distance a (provided a> 0) from the ITV camera 100 and a second object located at a distance b (provided b> a) from the ITV camera 100. The object is imaged by the ITV camera 100, and when the first object can be observed and the second object cannot be observed, the visibility is calculated as a. The visibility determining unit 121h determines whether or not the aviation obstacle light 300 is located within the visibility. Hereinafter, in the visibility calculation step S120, as an example, the visibility calculation unit 121g performs the monitoring when the aviation obstacle light 300 is monitored from a plurality of predetermined objects in the k-th area (initially k = 1). A case will be described in which visibility is calculated by searching for objects corresponding to the first object and the second object.

  First, the ITV control unit 121c controls the ITV camera 100 by reading setting information regarding at least the direction and focus for the kth area from the recording device 121i. Thereby, the ITV camera 100 is adjusted so as to image the k-th area.

(First object setting S121a)
As shown in FIG. 6, the visibility calculation unit 121g, for example, selects an arbitrary object from among a plurality of predetermined objects within the same field of view as the aviation obstacle light 304 in the kth area. “1 object” is set and recorded in the recording device 121i.

(First Object Observation S122)
Next, for example, the ITV control unit 121c, in a state where the ITV camera 100 is adjusted based on the setting information of the kth area, the “first object” in the same field of view as the aviation obstacle light 304 in the kth area. The ITV camera 100 is controlled so as to observe.

(First object judgment S123)
Next, as shown in FIG. 6, the visibility calculation unit 121 g determines whether or not the first object can be observed.

  At this time, the determination as to whether or not an object such as the first object is observable is, for example, the ITV status information of the ITV camera 100 acquired by the ITV control unit 121c or the image processing unit 121b from the ITV camera 100. For example, as follows.

  First, the visibility calculation unit 121g extracts an edge portion of the object in the image at the time of monitoring via the image processing unit 121b, and the shape of the object in the image at the time of monitoring and the shape of the object recorded in advance. Is determined to be 90% or more (first image determination). Next, the visibility calculation unit 121g has a diagonal line between the upper left point and the lower right point, and the upper right point and the lower left point in the edge portion of the object extracted from the image at the time of monitoring. Find the diagonal. The visibility calculation unit 121g is based on two diagonal lines at the time of monitoring, a diagonal line formed by the upper left point and the lower right point of the edge portion of the object recorded in advance, and an upper right point and a lower left point. It is determined whether the matching rate with the diagonal is 90% or more (second image determination). When the conditions for the first image determination and the second image determination are satisfied (that is, when the AND determination condition is satisfied), it is determined that the object is observable.

(First object setting S121b)
When the first object is not observable (No in S123), for example, the visibility calculation unit 121g newly adds the current first target to the ITV camera 100 in the same field of view as the aviation obstacle light 304 in the kth area. An arbitrary object closer to the object is set and recorded as the “first object” in the recording device 121i. Further, the ITV control unit 121c controls the ITV camera 100 to observe the updated “first object” (S122), and the visibility calculation unit 121g can observe the “first object”. It is determined whether or not (S123).

(Second object setting S125a)
On the other hand, when the first object is observable (Yes in S123), the visibility calculation unit 121g records the “first object” determined to be observable as it is in the recording device 121i. In the same field of view as the aviation obstacle light 304 in the k-th area, an arbitrary object located farther from the ITV camera 100 than the first object is selected as a “second object” from among a plurality of predetermined objects. Set "in the recording device 121i and record.

(Second Object Observation S126)
Next, as illustrated in FIG. 6, for example, the ITV control unit 121 c controls the ITV camera 100 to observe the “second object” in the same field of view as the aviation obstacle light 304 in the k-th area. To do.

(Second object judgment S127)
Next, the visibility calculation unit 121g determines whether or not the second object can be observed. Depending on whether or not the second object is observable, the visibility calculation step S120 proceeds as follows.

(First object setting S121c)
When the second object is observable (Yes in S127), the visibility calculation unit 121g determines that the old first object previously determined to be observable is the current second object determined to be observable later. The current second object is newly set as the “first object”, and is recorded in the recording device 121i. As described above, the “first object” is updated as an object located farthest from the ITV camera 100 among the objects determined to be observable.

(Second object setting S125b)
Next, the visibility calculation unit 121g newly starts the current second object (the current second object replaced with the first object) from the ITV camera 100 in the same field of view as the aviation obstacle light 304 in the kth area. An arbitrary object located farther than is set as the “first object” in the recording device 121i and recorded. Further, the ITV control unit 121c controls the ITV camera 100 to observe the updated “second object” (S126), and the visibility calculation unit 121g can observe the “second object”. It is determined whether or not (S127).

(Visibility calculation S128)
On the other hand, when the second object is not observable (No in S127), the visibility calculation unit 121g records the “second object” determined to be unobservable as it is in the recording device 121i. For example, visibility calculation is performed as follows.

  Here, as shown in FIG. 7, for example, in the same field of view as the aviation obstacle light 304 in the kth area, the first object 500a and the ITV camera 100 farther from the first object 500a. It is assumed that it is determined that the first target object 500a can be observed and the second target object 500b cannot be observed by imaging the second target object 500b with the ITV camera 100.

  At this time, for example, in the recording device 121i, a table or a function for obtaining a distance from the ITV camera 100 is recorded in advance for setting information such as a focus function or a zoom function of the ITV camera 100. When the distance calculation unit 121g obtains the distances of the first object 500a and the second object 500b from the ITV camera 100, the visibility calculation unit 121g uses the table and the like described above based on setting information such as the focus function or the zoom function of the ITV camera 100. refer.

  For example, the visibility calculation unit 121g refers to the table based on the setting information of the ITV camera 100 when the first object 500a is imaged, and the distance a (where a> 0) of the first object 500a from the ITV camera 100. ) Is calculated. The visibility calculation unit 121g refers to the table based on the setting information of the ITV camera 100 when the second object 500b is imaged, and the distance b of the second object 500b from the ITV camera 100 (where b> a ) Is calculated. In this case, since the ITV camera 100 cannot focus on the second object 500b, the distance b may not be calculated. Alternatively, for example, the distance b is calculated based on setting information of the second object 500b recorded in advance.

  As described above, the visibility calculation unit 121g calculates that the current visibility that the ITV camera 100 can capture is “distance a” when the first object 500a can be observed and the second object 500b cannot be observed. As described above, the relationship between the first object 500a that is farthest from the ITV camera 100 among the observable objects and the second object 500b that is located farther than the first object 500a and could not be observed. Based on the above, the visibility at the time of monitoring is calculated.

  For example, when all objects in the k-th area are observable on a clear day with good visibility, the visibility at the time of monitoring is the maximum value in the k-th area (for example, the specifications of the ITV camera 100). The maximum value of the subject distance at) or infinity. On the other hand, for example, when all objects in the kth area cannot be observed, such as a day when rain or snow falls and visibility is poor, the visibility at the time of monitoring is set to be less than the minimum value in the kth area or set to zero. .

(Imaging process S130)
Next, as shown in FIG. 5, the ITV control unit 121 c adjusts the ITV camera 100 based on the setting information of the ITV camera 100 for the k-th area to determine the failure of the aviation obstacle light 304. The ITV camera 100 is controlled to acquire the determination image to be used. In addition, the ITV control unit 121c adjusts the ITV camera 100 while using detailed setting information of the ITV camera 100 with respect to the light emission areas of the respective aviation obstacle lights 304 when necessary, and displays a determination image for each light emission area. The ITV camera 100 is controlled to acquire.

  At this time, the visibility calculation unit 121g calculates the distance of the aviation obstacle light 304 from the ITV camera 100 by referring to the table based on the setting information of the ITV camera 100 when the aviation obstacle light 304 in the light emitting area is imaged.

  In addition, when the ITV camera 100 acquires an image for determining the aviation obstacle light 304, the image processing unit 121b performs processing for correcting “blurring” caused by vibration of the ITV camera 100, and an image obtained by imaging the aviation obstacle light 304. Noise removal processing or smoothing processing is performed.

(Visibility determination step S140)
Next, the visibility determining unit 121h determines whether or not the aviation obstacle light 304 in each light emitting area in the kth area is located within the visibility based on the visibility calculated by the visibility calculating unit 121g.

  When the aviation obstacle light in the light emitting area in the k-th area is not located within the visibility (in the case of No in S140), the failure determination unit 121f performs the aviation obstacle light described later on the aviation obstacle light 304 in the light emission area. The failure determination process 304 is not performed.

  For example, in the example of FIG. 7, the aviation obstacle light 304 is located at a distance c (where c> b) farther than a certain distance b where the second object 500b that could not be observed. That is, the aviation obstacle light 304 is not located within the visibility set as the distance a. Therefore, when the failure determination unit 121f determines a failure of the aviation obstacle light 304, there is a high possibility that the determination will be wrong. The determination process is not performed.

  On the other hand, when the aviation obstacle light 304 in the light emission area of the k-th area is located within the visibility (in the case of Yes in S140), the failure determination unit 121f is described later with respect to the aviation obstacle light 304 in the light emission area. The failure determination step S150 of the aviation obstacle light 304 is performed.

  Similarly, the visibility determination unit 121h performs a visibility determination step S140 on the aviation obstacle lights 304 in all the light emitting areas of the kth area.

(Determination step S150)
First, the emission intensity calculation unit 121e obtains “determination emission intensity” of the aviation obstacle light 304 in the k-th area determined to be within visibility in the visibility determination step S140, for example, as follows.

  For example, the light emission intensity calculation unit 121e uses linearity of R value, G value, and B value in each pixel in the light emission areas 404a to 404d of the kth area from the image for determination of the kth area acquired by the ITV camera 100. Find the sum value. Next, the light emission intensity calculation unit 121e adds a value obtained by integrating the linear sum of the R value, G value, and B value of each pixel for all the pixels in the light emitting regions 404a to 404d only in the light emitting regions 404a to 404d. Is calculated as “judgment emission intensity” of the aviation obstacle light 304 in FIG. As a result, light from the outside of the light emitting areas 404a to 404d, that is, light other than the aviation obstacle light 304 is detected, so that the failure determination unit 121f is prevented from erroneously determining the failure of the aviation obstacle light 304.

  Next, the failure determination unit 121f compares the emission intensity for determination of the aviation obstacle light 304 obtained from the determination image of the aviation obstacle light 304 with a threshold value determined for each aviation obstacle light 304 in advance, and compares the aviation obstacle light 304 Determine the failure. The threshold value used here is selected according to the light emission type of the aviation obstacle light 304 as described above.

  Further, for example, in the recording device 121i, a first threshold value and a second threshold value higher than the first threshold value are recorded in advance as threshold values relating to the emission intensity of the aviation obstacle light 304.

  For example, when the emission intensity of only one aviation obstacle light 300 among the plurality of aviation obstacle lights 300 installed in the same power transmission tower 200 is lower than the first threshold, the failure determination unit 121f Judged to be “failed”. In addition, the failure determination unit 121f supplies power to the aviation obstacle light 300 installed in the power transmission tower 200 when all the emission intensities of the plurality of aviation obstacle lights 300 installed in the same power transmission tower 200 are lower than the first threshold. Is determined to have failed.

  The failure determination unit 121f predicts a failure of the aviation obstacle light 304 when, for example, the light emission for determination of the aviation obstacle light 304 is equal to or higher than the first threshold and lower than the second threshold. Here, “prediction of failure of aviation obstacle light” means that the aviation obstacle light 304 may break down after a predetermined period of time due to, for example, the determination emission intensity of the aviation obstacle light 304 being lower than the second threshold. Is to predict. The “second threshold value” of the emission intensity of the aviation obstacle light is, for example, a half value with respect to the initial emission intensity of the aviation obstacle light.

  The failure determination unit 121f transmits a prediction warning signal indicating that a failure of the aviation obstacle light 304 is predicted to the alarm unit 121k when the determination light emission intensity is equal to or higher than the first threshold value and lower than the second threshold value. . The warning unit 121k issues a prediction warning indicating that a disconnection (failure) of the aviation obstacle light is predicted based on the prediction warning signal.

  On the other hand, the failure determination unit 121f determines that the aviation obstacle light 304 has failed when the determination light emission intensity is lower than the first threshold. The “first threshold value” of the emission intensity of the aviation obstacle light is, for example, a predetermined value equal to or lower than the minimum luminance of the aviation obstacle light 300 at the time of non-failure, a background value (noise value) observed at normal time, or these numerical values. Is a value obtained by adding a margin.

  The failure determination unit 121f transmits a failure warning signal indicating that the aviation obstacle light 304 has failed to the alarm unit 121k when the determination light emission intensity is lower than the first threshold. The warning unit 121k issues a failure warning indicating that the aviation obstacle light 304 has failed based on the failure warning signal.

  In consideration of the case where there is an aviation obstacle light 300 that has not been subjected to the determination step S150 among the aviation obstacle lights 300 registered in advance, the input / output unit 121j determines whether each aviation obstacle light 300 is a determination target. Whether or not may be displayed. In addition, the input / output unit 121j may display information about the aviation obstacle light 300, etc., which is determined to be normal, and the numerical value relating to the calculated emission intensity of each aviation obstacle light 300, etc. May be displayed.

(End determination S160)
Next, the main control unit 121d determines whether or not the steps from the visibility calculation step S120 to the determination step S150 have been performed for the first to Nth areas (k = N).

(Area number update S170)
If these steps are not performed up to the Nth area (No in S160), the area number k is updated to k + 1. Further, the visibility calculation process S120 to the determination process S150 are performed for the next k + 1 area.

  On the other hand, when these steps are performed up to the Nth area (Yes in S160), the failure detection step of the aviation obstacle light is finished.

(4) Effects according to the present embodiment According to the present embodiment and its modifications, the following one or more effects can be achieved.

(A) According to the present embodiment, position information related to the distance and direction from the ITV camera 100 to the aviation obstacle light 300 and the threshold value of the emission intensity of the aviation obstacle light 300 are recorded in advance. In the aviation obstacle light failure detection step, the ITV control unit 121c acquires a determination image used to determine the aviation obstacle light 300 failure based on the position information of the aviation obstacle light 300 recorded in the recording device 121i. The ITV camera 100 is controlled. The emission intensity calculation unit 121e calculates the determination emission intensity of the aviation obstacle light 300 from the determination image. The failure determination unit 121f determines the failure of the aviation obstacle light by comparing the emission intensity for determination of the aviation obstacle light 300 with a predetermined threshold value. Thereby, by always imaging the aviation obstacle light 300 based on the same position information of the aviation obstacle light 300, the emission intensity for determination of the aviation obstacle light 300 varies due to the adjustment of the ITV camera 100 during monitoring. It is suppressed. That is, the reproducibility of measuring the determination light emission intensity is improved, and the failure detection accuracy of the aviation obstacle light 300 is improved. Further, since the ITV camera 100 can be provided at a position away from the aviation obstacle light 300, the ITV camera 100 can be installed at a place where the power source can be easily obtained.

(B) According to the present embodiment, the ITV control unit 121c determines at least the direction of the ITV camera 100 with respect to the monitored aviation obstacle light 300 before determining the failure of the aviation obstacle light 300 by the failure determination unit 121f. In addition, the ITV camera 100 is controlled so that the aviation obstacle light 300 is imaged by adjusting the focus, and positional information regarding the distance and direction from the ITV camera 100 to the aviation obstacle light 300 is used for each aviation obstacle light 300. The setting information such as the direction (pan / tilt) and focus of the ITV camera 100 adjusted in this manner is recorded in the recording device 121i. As a result, the aviation obstacle light 300 is always imaged based on the setting information of the same ITV camera 100, thereby suppressing the determination emission intensity of the aviation obstacle light 300 from varying. That is, the reproducibility of measuring the determination light emission intensity is improved, and the failure detection accuracy of the aviation obstacle light 300 is improved.

(C) According to the present embodiment, the recording apparatus 121i includes at least one of the kth aviation obstacle lights 304a to 304d, which is an area within one field of view when the ITV camera 100 captures the kth area, for example. An area including the light emitting portion is recorded in advance as “light emitting areas 404a to 404d”. The light emission intensity calculation unit 121e calculates the light emission intensity for determination only from within the light emission areas 404a to 404d of the image for determination. As a result, light from the outside of the light emitting areas 404a to 404d, that is, light other than the aviation obstacle light 304 is detected, so that the failure determination unit 121f is prevented from erroneously determining the failure of the aviation obstacle light 304.

(D) According to the present embodiment, the visibility calculation unit 121g is located at a distance a (provided a> 0) from the ITV camera 100 and at a distance b (provided b> a) from the ITV camera 100. The second object located is imaged by the ITV camera 100, and when the first object can be observed and the second object cannot be observed, the visibility is calculated as a. The visibility determination unit 121h determines whether or not the aviation obstacle light 300 is located within the visibility based on the visibility calculated by the visibility calculation unit 121g. Thereby, it is possible to determine whether or not the failure determination of the aviation obstacle light 300 is possible according to the visibility at the time of monitoring. For example, when the visibility at the time of monitoring is short, erroneous determination of a failure of the aviation obstacle light 300 is suppressed.

(E) According to the present embodiment, the failure determination unit 121f does not determine the failure of the aviation obstacle light 300 when the aviation obstacle light 300 is not within the visibility, and the aviation obstacle light 300 is within the visibility. Then, the failure of the aviation obstacle light 300 is determined. Accordingly, it is possible to prevent the failure determination unit 121f from erroneously determining a failure due to the short visibility by determining whether to perform the failure determination of the aviation obstacle light according to the visibility at the time of monitoring. can do.

(F) According to the present embodiment, the ITV control unit 121d controls the ITV camera 100 to image the first object 500a and the second object 500b in the same field of view as the aviation obstacle light 300. The visibility determination unit 121h determines whether or not the aviation obstacle light 300 is located within the visibility based on the visibility calculated by the visibility calculation unit 121g. By calculating the visibility using the first object 500a and the second object 500b within the same field of view as the aviation obstacle light 300, the visibility based on the environment close to the monitored aviation obstacle light 300 can be calculated.

<Modification of this embodiment>
In the above-described embodiment, the threshold value of the light emission intensity is predetermined for the linear sum of the R value, the G value, and the B value in the color image of the aviation obstacle light 300 captured by the ITV camera 100, and the failure determination unit 121f. In the above description, the determination linear failure is compared with the threshold value for each pixel from the determination image to determine the failure of the aviation obstacle light. However, the present invention is not limited to this.

  The following modified example of the present embodiment is different from the above-described present embodiment in the threshold value of light emission intensity and the method of comparison with the threshold value. Hereinafter, in this modification, only elements different from the present embodiment will be described, and description of elements that are substantially the same as those described in the present embodiment will be omitted.

In the first modification, for example, the threshold value of the light emission intensity (TH _R , TH _G , TH _B ) is set to at least one of the R value, the G value, and the B value in the color image of the aviation obstacle light imaged by the ITV camera. Alternatively, it may be determined in advance. Specifically, for example, the threshold TH _{B of the} light emission intensity is predetermined for the B value. The failure determination unit compares at least one of the determination R value, G value, and B value corresponding to the threshold value for each pixel of the color determination image acquired by the ITV camera with the threshold value. Determine failure. Specifically, for example, the failure determination unit determines the failure of the aviation obstacle light by comparing the B value for determination with the threshold value TH _B for each pixel from the image for determination. Thereby, for example, it is possible to determine a failure of the aviation obstacle light by setting a threshold value to a hue value (for example, B value) in which the light emission deterioration of the aviation obstacle light is remarkable.

In the second modification, for example, the emission intensity threshold (TH _ratio ) is different from at least one of the R value, the G value, and the B value in the color image of the aviation obstacle light captured by the ITV camera 100. It may be predetermined for a hue ratio that is a ratio of one value. Specifically, for example, the threshold TH _{ratio of the} light emission intensity is predetermined with respect to the ratio of R value / B value. The failure determination unit determines the failure of the aviation obstacle light by comparing the determination hue ratio corresponding to the threshold value with the threshold value TH _ratio for each pixel of the color determination image acquired by the ITV camera 100. Thereby, for example, it is possible to determine a failure of an aviation obstacle light by setting a threshold value to a hue value (for example, B value) that is significantly deteriorated compared to other hue values.

<Second Embodiment of the Present Invention>
The second embodiment of the present invention will be described below. This embodiment is different from the first embodiment in that imaging of the aviation obstacle light itself is not performed when the aviation obstacle light to be monitored is not located within the visibility. Hereinafter, only elements different from those of the first embodiment will be described, and elements substantially the same as those described in the first embodiment are denoted by the same reference numerals and description thereof will be omitted.

(1) Aviation Obstruction Light Failure Detection Method The aviation obstruction light failure detection method according to the present embodiment will be described with reference to FIGS. 8 and 9. FIG. 8 is a diagram illustrating a flow of the failure detection method according to the present embodiment. FIG. 9 is a schematic diagram when the current visibility is calculated in the visibility calculation step according to the present embodiment.

(Pre-recording process)
First, also in the present embodiment, a pre-recording step S110 similar to that in the first embodiment is performed in advance. For example, setting information of the ITV camera 100 for each of the first to Nth areas set as monitoring targets, a light emitting area for the aviation obstacle light 300 in each area, setting information of the ITV camera 100 for the light emitting area, and aerial The light emission type of the obstacle light is recorded in the recording device 121i in advance.

  In the present embodiment, as shown in FIG. 9, in the pre-recording process, the ITV control unit 121 c selects a plurality of “objects 500” at arbitrary positions around the ITV camera 100 at an angle of 360 °. Recording in advance on the recording device 121i. At this time, the initial image of the object 500 and setting information such as the direction and focus of the ITV camera 100 adjusted to the object 500 are recorded in the recording device 121i in advance.

  The visibility calculation unit 121g refers to a table or function for obtaining a distance from the ITV camera 100 based on setting information such as a focus function or a zoom function of the ITV camera 100, and from the ITV camera 100 of the aviation obstacle light 300 in each area. And the distance of each object 500 from the ITV camera 100 is calculated. The distance from the ITV camera 100 of the aviation obstacle light 300 in each area is recorded in advance in the recording device 121i.

(Failure detection process)
Next, as shown in FIG. 8, a failure detection step is performed as follows.

(Visibility calculation step S220)
For example, as shown in FIG. 9, the ITV control unit 121 c determines the target object 500 at an arbitrary position at an angle of 360 ° around the ITV camera 100 before determining the failure of the aviation obstacle light 300. The ITV camera 100 is controlled to take an image. Here, the object 500 need not be located in the same field of view as the aviation obstruction light 300 in a predetermined area to be monitored next.

  The visibility calculation unit 121g sets an object that can be observed from any object 500 as a "first object", and an object that is located farther than the first object and cannot be observed as a "second object". Set to calculate visibility during monitoring.

(Visibility determination step S230)
Next, the visibility determining unit 121h determines whether the aviation obstacle light 300 in the k-th area to be monitored is located within the visibility based on the position information of the aviation obstacle light 300 recorded in the recording device 121i. . Specifically, the visibility determination unit 121h compares, for example, the distance from the ITV camera 100 of the aviation obstacle light 300 in the k-th area to be monitored obtained in the pre-recording process and the visibility at the time of monitoring. Then, it is determined whether or not the aviation obstacle light 300 in the k-th area to be monitored is located within the visibility.

  When the visibility determining unit 121h determines that the aviation obstacle light 300 in the k-th area is not located within the visibility (No in S230), the ITV control unit 121c acquires an image for determining the aviation obstacle light 300 using the ITV camera 100. I won't let you. The failure determination unit 121f performs the visibility determination step S230 on the aviation obstacle light in the next area (k + 1 area).

(Judgment process S250)
On the other hand, when the visibility determining unit 121h determines that the aviation obstacle light 300 is located within the visibility (Yes in S230), the ITV control unit 121c acquires the determination image of the aviation obstacle light 300 in the kth area. The camera 100 is controlled. The failure determination unit 121f compares the emission intensity of the aviation obstacle light 300 obtained from the determination image of the aviation obstacle light 300 determined to be within visibility with a threshold value determined for each aviation obstacle light 300 in advance. The failure of the obstacle light 300 is determined.

(End determination S260)
Next, the failure determination unit 121f determines whether or not the steps from the visibility determination step S230 to the determination step S250 have been performed up to the Nth area.

(Area Number Update S270)
If these steps are not performed up to the Nth area (No in S260), the area number k is updated to k + 1. Further, the visibility determination process S230 to the determination process S250 are performed for the next k + 1 area.

  On the other hand, when these steps are performed up to the Nth area (Yes in S260), the failure detection step of the aviation obstacle light is finished.

(2) Effects According to the Present Embodiment According to the present embodiment, the ITV control unit 121c causes the ITV camera 100 to image the target object 500 at an arbitrary position before determining the failure of the aviation obstacle light 300. Control. The visibility determining unit 121h determines whether the aviation obstacle light 300 in the k-th area to be monitored is located within the visibility based on the position information of the aviation obstacle light 300 recorded in the recording device 121i. The ITV control unit 121c causes the ITV camera 100 to acquire a determination image of the aviation obstacle light 300 based on the result determined by the visibility determination unit 121h based on the visibility. Thereby, it is possible not only to suppress the erroneous determination of the failure of the aviation obstacle light due to the short visibility, but also to shorten the time related to the failure detection process.

<Other Embodiments of the Present Invention>
As mentioned above, although embodiment of this invention was described concretely, this invention is not limited to the above-mentioned embodiment, It can change variously in the range which does not deviate from the summary.

  In the above-described embodiment, the case where the controller 120 includes the transmission unit 121a that transmits and receives signals to and from the ITV camera 100 has been described, but the present invention is not limited to this. The controller 120 may not have the transmission unit 121a. In addition to the transmission unit, an amplification transmission unit that amplifies the signal may be further provided between the ITV camera 100 and the controller 120.

  In the above-described embodiment, before determining the failure of the aviation obstacle light 300 (in the pre-recording step S110), the failure determination unit 121f applies the pre-recorded image acquired from the ITV camera 100 via the image processing unit 121b. Based on the above description, the “light emission type” of the aviation obstacle light 300 is determined and recorded in the recording device 121i. However, the present invention is not limited to this. For example, the light emission type of the aviation obstacle light 300 may be directly recorded in the recording device 121i.

  Further, in the above-described embodiment, the ITV control unit 121c adjusts at least the direction and focus of the ITV camera 100 and images the aviation obstacle light 300 before imaging the aviation obstacle light 300 before determining the failure of the aviation obstacle light 300. Although the control and the setting information of the direction and focus of the ITV camera 100 adjusted with respect to the aviation obstacle light 300 as the position information of the ITV camera 100 have been described in the recording device 121i, the present invention is not limited thereto. It is not limited. Without recording the setting information of the ITV camera 100 obtained by imaging the aviation obstacle light 300, for example, the recording device 121i may directly record the position information of the aviation obstacle light 300 by numerical input or the like. .

  In the first embodiment described above, in the pre-recording process, the ITV control unit 121c preliminarily displays a plurality of objects in the visibility calculation process within one field of view when the ITV camera 100 captures the k-th area, for example. Although the case of recording in the recording device 121i has been described, the present invention is not limited to this. The object for which it is determined whether or not observation is possible in the visibility calculation step may be any object searched within the same field of view each time monitoring is performed.

  In the second embodiment described above, in the pre-recording step, the ITV control unit 121c records in advance the plurality of objects 500 at arbitrary positions with an angle of 360 ° around the ITV camera 100 in the recording device 121i. Although the case has been described, the present invention is not limited to this. The object for which it is determined whether or not observation is possible in the visibility calculation step may be an arbitrary object searched at an angle of 360 ° each time during monitoring.

  In the above-described embodiment, the determination as to whether or not the object is observable is performed by determining the coincidence rate with the shape of the object (first image determination) and the diagonal coincidence rate of the object (second image determination). However, the present invention is not limited to this. The visibility calculation unit may determine that “the object is observable” when the object is focused on the object by the auto-focus function of the ITV camera.

  In the first embodiment, the visibility calculation unit 121g captures the object or the aviation obstacle light 300 in the visibility calculation step S120 or the imaging step S130 based on the setting information of the ITV camera 100 based on the setting information of the ITV camera 100. Although the case where the actual distance of the object from the ITV camera 100 or the aviation obstacle light 300 is calculated with reference to the table for obtaining the distance of the aviation obstacle light 300 has been described, the present invention is not limited to this. The visibility calculated by the visibility calculation unit in the visibility calculation process or the imaging process or the distance of the aviation obstacle light 300 from the ITV camera 100 may not be an actual distance. For example, the focus function or the zoom function of the ITV camera is set. It suffices if the relative positional relationship in the kth area can be grasped from the information. Specifically, for example, when the first object can be observed and the second object cannot be observed, the visibility calculation unit does not need to use a table or a function for obtaining the distance from the ITV camera. You may calculate (determine) relatively that it is in a state farther than the first object and closer to the second object. In the imaging process, it is not necessary to use a table or a function for obtaining the distance from the ITV camera. In the visibility determination process, the visibility determination unit includes setting information of the ITV camera when the visibility calculation unit calculates the visibility, Visibility determination may be made by relatively comparing the setting information of the ITV camera for the aviation obstacle light in each light emitting area in the kth area.

  Similarly, in the above-described second embodiment, from the ITV camera 100 based on the setting information of the ITV camera 100 when the visibility calculation unit 121g images the object or the aviation obstacle light 300 in the pre-recording step and the visibility calculation step. The case of calculating the object from the ITV camera 100 or the actual distance of the aviation obstacle light 300 has been described with reference to a table for obtaining the distance of the aviation obstacle light 300, but the present invention is not limited to this. . Specifically, for example, in the pre-recording step, it is not necessary to use a table or a function for obtaining the distance from the ITV camera. In the visibility determination step, the visibility determination unit calculates the ITV when the visibility calculation unit calculates the visibility. Visibility determination may be made by relatively comparing the setting information of the camera and the setting information of the ITV camera for the aviation obstacle light in each light emitting area in the k-th area.

  In the above-described embodiment, the first object 500a that can be observed and the second object 500b that cannot be observed are searched in the visibility calculation step S120, and the visibility calculation unit 121g calculates the visibility each time. However, the present invention is not limited to this. A candidate object may be set in advance on a day with good visibility, and the distance of the object from the ITV camera may be calculated and recorded in the storage device. In the visibility calculation step, the visibility calculation unit calculates the visibility at the time of monitoring by reading the distance of the object from the ITV camera based on the result of whether or not the object set as a candidate can be observed in advance. Also good.

  In the above-described embodiment, the case where the ITV control unit sets an object located at an arbitrary distance from the ITV camera 100 as the “first object” and starts observation in the visibility calculation step S120 has been described. However, the present invention is not limited to this. In the visibility calculation step, the ITV control unit may set an object located closest to the ITV camera as a “first object” and start observation. In this case, when the first object cannot be observed, this corresponds to the fact that all objects cannot be observed, and the visibility during monitoring is set to the minimum value. Alternatively, in the visibility calculation step, the ITV control unit may set an object located farthest from the ITV camera as a “first object” and start observation. In this case, when the first object can be observed, this corresponds to the fact that all objects can be observed, and the visibility at the time of monitoring is set to the maximum value.

  In the first embodiment, the case where the imaging step S130 is performed before the visibility determination step S140 is described. In the second embodiment, the case where the imaging step S240 is performed before the visibility determination step S220 is described. However, the present invention is not limited to this. The visibility determination process may be performed simultaneously with at least a part of the imaging process.

  In the above-described embodiment, the case where the threshold used for failure detection is constant regardless of the visibility at the time of monitoring has been described, but the present invention is not limited to this. For example, in the recording device, a different value is set for the emission intensity threshold according to the visibility, and the failure determination unit changes the threshold according to the visibility calculated by the visibility calculation unit. A failure of the obstacle light may be determined. For example, when the visibility is short, such as a day with bad weather, even if the aviation obstacle light is normal, the emission intensity of the detected aviation obstacle light may be reduced. Therefore, when the visibility is short as described above, the threshold used for detecting the failure of the aviation obstacle light may be set low.

10. Aircraft obstacle light failure detection system 100 ITV camera (imaging means)
120 controller (control means)
120a Transmission unit (transmission means)
120b Image processing unit (image processing means)
121c ITV control unit (imaging control means)
121d Main control unit (main control means)
121e Luminescence intensity calculation unit (luminescence intensity calculation means)
121f Failure determination unit (failure determination means)
121g Visibility calculation unit (visibility calculation means)
121h Visibility determination unit (visibility determination means)
121i Recording device (recording means)
121j Input / output unit 121k Alarm unit 200-204 Transmission tower 300-304, 304a-304d Aviation obstruction light 404a-404d Light emitting area 500, 500a, 500b Object S110 Pre-recording step S111 Direction and focus adjustment S112 Recording step S120 Visibility calculation step S130 Imaging step S140 Visibility determination step S150 Determination step S160 End determination S121 First object observation S122 First object determination S123 First object setting S124 Second object observation S127 Second object setting S220 Visibility calculation step S230 Visibility determination Step S240 Imaging step S250 Determination step S260 End determination

Claims (15)

Imaging means for imaging an aviation obstacle light provided at a predetermined position;
Recording means for pre-recording position information relating to the distance and direction from the imaging means to the aviation obstacle light, and a threshold value of the emission intensity of the aviation obstacle light;
Based on the position information recorded in the recording unit, the imaging unit is controlled to adjust at least the direction and focus of the imaging unit to obtain a determination image used for determining the failure of the aviation obstacle light. Imaging control means for
Emission intensity calculating means for calculating emission intensity for determination of the aviation obstacle light from the image for determination;
A failure determination means for comparing the determination light emission intensity with the threshold to determine a failure of the aviation obstacle light;
A first object located at a distance a from the imaging means and a second object located at a distance b longer than the distance a from the imaging means are imaged by the imaging means, and the first object is Visibility calculation means for calculating that the visibility is the distance a when the second object cannot be observed;
Visibility determining means for determining whether or not the aviation obstacle light is located within the visibility;
Aviation obstruction light failure detection system. The imaging control means includes
Before determining the failure of the aviation obstacle light by the failure determination means, the imaging means is controlled to image the aviation obstacle light by adjusting at least the direction and focus of the imaging means, and the imaging control means The failure detection system for an aviation obstacle light according to claim 1, wherein the adjusted setting information of the direction and focus of the imaging unit is recorded in the recording unit as the position information. The recording means includes
An area within one field of view when the imaging means images the aviation obstacle light, and records in advance an area including at least a light emitting portion of the aviation obstacle light as a light emission area,
The emission intensity calculating means includes
The failure detection system for an aviation obstacle light according to claim 1 or 2, wherein the determination light emission intensity is calculated only from within the light emission region of the determination image. The failure determination means includes
When the visibility determining means determines that the aviation obstacle light is not located within the visibility, the failure of the aviation obstacle light is not determined,
The failure detection system for an aviation obstacle light according to any one of claims 1 to 3, wherein when the visibility determination unit determines that the aviation obstacle light is located within the visibility, a failure of the aviation obstacle light is determined. The imaging control means includes
When the visibility determination means determines that the aviation obstacle light is not located within the visibility, the image pickup means does not acquire the determination image of the aviation obstacle light,
The said imaging means is controlled to any one of Claim 1 to 3 which acquires the said image for determination of the said aviation obstacle light when the said visibility judgment means judges that the said aviation obstacle light is located in the said visibility The failure detection system for aviation obstacle lights as described. In the recording means,
The threshold value of the emission intensity is determined in advance for at least one of an R value, a G value, and a B value in the color image of the aviation obstacle light acquired by the imaging unit,
The failure determination means includes
The aviation obstacle light is calculated by comparing at least one of the R value, G value, and B value for determination calculated as the light emission intensity for determination for each pixel of the image for determination with the threshold value. The failure detection system for an aviation obstacle light according to any one of claims 1 to 5 , wherein the failure is determined. In the recording means,
The threshold value of the emission intensity is predetermined for a linear sum of R value, G value, and B value in the color image of the aviation obstacle light acquired by the imaging means,
The failure determination means includes
2. The failure of the aviation obstacle light is determined by comparing a linear sum for determination of R value, G value, and B value calculated as the light emission intensity for determination for each pixel of the image for determination with the threshold value. The failure detection system for an aviation obstacle light according to any one of 1 to 5 . In the recording means,
The threshold value of the light emission intensity is a hue ratio that is a ratio of another value to at least one of the R value, the G value, and the B value in the color image of the aviation obstacle light acquired by the imaging unit. Pre-determined for
The failure determination means includes
Wherein the determination color ratio corresponding to the threshold value is calculated as the determination luminous intensity for each pixel of the determination image, any of determining claims 1 to 5 a failure of the obstacle lights compared with the threshold value The failure detection system for an aviation obstacle light according to item 1. According to any one of claims 1 to 8 having a warning means for the determination luminous intensity of the obstacle lights to alarm failure warning indicating said that obstacle lights fails when lower than the threshold value Aircraft fault light failure detection system. The threshold value of the emission intensity has a first threshold value and a second threshold value higher than the first threshold value,
The failure determination means includes
Predicting a failure of the aviation obstacle light when the light emission for determination of the aviation obstacle light is equal to or higher than the first threshold and lower than the second threshold;
The failure detection of the aviation obstacle light according to any one of claims 1 to 9 , wherein the aviation obstacle light is determined to have failed when the light emission for determination of the aviation obstacle light is lower than the first threshold value. system. 11. The aviation obstacle light according to claim 10, further comprising a warning means for issuing a prediction warning indicating that a failure of the aviation obstacle light is predicted when the failure determination means predicts a failure of the aviation obstacle light. Fault detection system. In the previous type recording means,
The threshold value of the emission intensity is determined differently depending on the visibility,
The failure determination means includes
The failure detection system for an aviation obstacle light according to any one of claims 1 to 11 , wherein a failure of the aviation obstacle light is determined based on the threshold value corresponding to the visibility calculated by the visibility calculation means. A pre-recording step for pre-recording position information related to the distance and direction from the image sensor that images the aviation obstacle light provided at a predetermined position to the aviation obstacle light, and a threshold value of the emission intensity of the aviation obstacle light;
A first object located at a distance a from the image sensor and a second object located at a distance b longer than the distance a from the image sensor are imaged by the image sensor, and the first object is A visibility calculation step of calculating that the visibility is the distance a when the second object cannot be observed;
Visibility determination step for determining whether or not the aviation obstacle light is located within the visibility;
An imaging step of adjusting at least the direction and focus of the imaging device based on the position information to obtain a determination image used for determining the failure of the aviation obstacle light;
A determination step of determining a failure of the aviation obstacle light by comparing the light emission intensity for determination of the aviation obstacle light calculated based on the image for determination and the threshold;
A fault detection method for aviation obstruction lights. In the determination step,
If it is determined in the visibility determination step that the aviation obstacle light is not located within the visibility, a failure of the aviation obstacle light is not determined,
When it is determined in the visibility determination step that the aviation obstacle light is located within the visibility, a failure of the aviation obstacle light is determined.
The fault detection method of the aviation obstacle light according to claim 13. In the imaging step,
In the visibility determination step, when it is determined that the aviation obstacle light is not located within the visibility, the determination image of the aviation obstacle light is not acquired by the imaging device,
When it is determined in the visibility determination step that the aviation obstacle light is located within the visibility, the image for determination of the aviation obstacle light is acquired by the imaging device.
The fault detection method of the aviation obstacle light according to claim 13.

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