KR200266641Y1 - Aircraft warning light systems - Google Patents

Abstract

Aviation obstacle lamp 10 installed on the same structure as the transmission tower 1 is supplied from the solar cell module 20, the solar cell module having a light receiving plate 21 for producing electricity by the light of the sun. Light emitting unit 40 having a plurality of LEDs 46 for emitting light by using the supplied power, and a control box to store the power supplied from the solar cell module to supply to the light emitting unit and to control the light emitting time and flashing of the light emitting unit 30, wherein one end of the solar cell module is rotatably connected to the top of the control box.

Description

Aviation failure light {AIRCRAFT WARNING LIGHT SYSTEMS}

The present invention relates to an aviation obstacle lamp, and more particularly, to generate an electric power with a solar cell installed integrally with the control box, and to an aviation obstacle lamp that emits light through a light emitting unit made of LED.

In general, aviation obstacles are installed on obstacles in the air route to avoid collisions of aircrafts, and are mainly installed on pylons, transmission lines or projection terrain obstacles of high-voltage lines crossing mountains or rivers. Such aviation obstacle lights are turned on at night so that they can be easily distinguished from flying objects, and are supplied by supplying lighting power from the outside or by installing solar panels as described in Korean Utility Model Publication No. 87-1036. In addition, there is also a form that can adjust the angle of the solar panel as described in Utility Model Registration No. 1991-5747 as a more advanced form.

Such a conventional aviation obstacle lamp uses a lamp such as an incandescent bulb or a halogen bulb, which may be broken, It consumes more than 200W and requires an inverter to operate, so the overall weight is so high that the entire machine usually weighs more than 200kg. In addition, the aviation failure lamp using such a conventional lamp is difficult to install and repair, short life has the disadvantage that the cost of additional purchase and replacement of the lamp increases.

In order to overcome this disadvantage, Korean Patent Publication No. 2001-19967, "Aircraft Disturbance Lamp," discloses a technology that minimizes power loss by using a light emitting diode having the maximum luminous power with the smallest power as a lamp for an airplane failure lamp. It is.

However, such a conventional aviation obstacle is a short life as a general storage battery is generally used solar cells, solar cells and control boxes for driving and controlling them are installed to be separated from each other. In general, the solar cell is installed in a high position to receive sunlight, and the control box is installed in a low position because the weight is high. However, when the solar cell and the control box are separated from each other, the wires for the electrical connection between them are used essentially, and these wires are exposed to the outside, which may cause a failure due to wear or disconnection. In addition, when the solar cells and the control box are installed independently of each other, they are installed in high towers with strong air currents, such as aviation obstacles, so that the installation state may become unstable or a large load may be generated on the wires connecting them. have.

The present invention was devised to solve the above problems, the purpose of which is to reduce power consumption by using LED and to provide a more structurally robust aviation failure by configuring a solar cell and a control box in one piece.

The following drawings attached to this specification are illustrative of the preferred embodiments of the present invention, and together with the detailed description of the present invention to serve to further understand the technical spirit of the present invention, the present invention is a matter described in such drawings It should not be construed as limited to.

1 is a schematic view showing a state in which the aviation obstacle lights installed in the structure according to the present invention.

Figure 2 is a perspective view showing a solar cell module and a control box, such as aviation obstacles according to the present invention.

3 is a cross-sectional view showing a solar cell module and a control box of FIG.

Figure 4 is a block diagram showing the internal configuration of a control box, such as aviation obstacles according to the present invention.

5 is a front view showing a light emitting unit used in the aviation obstacle lamp of the present invention.

<Explanation of symbols for important parts of the drawing>

1 .. Structure 10. Aviation failure, etc. 20. Solar cell module

21. Receiving plate 24. Connecting member 25. Pivot

26. Joiner 28. Joiner 30. Control box

40. Light emitting part 41. Pipe passage 42. Lower case

43. Transmitter 44. Upper case 46. LED

In order to achieve the above object, the aviation obstacle lamp according to the present invention is installed to be identified from an aircraft in a structure such as a transmission tower, and supplied from a solar cell module and a solar cell module having a light receiving plate that produces electricity by solar light. Light emitting unit having a plurality of LEDs for emitting light by using the provided power, and a control box for storing the power supplied from the solar cell module to supply to the light emitting unit, and controls the emission time and flashing of the light emitting unit, the solar cell One end of the module is rotatably connected to the top of the control box.

At this time, preferably, the connecting member 24 is rotatably installed on the upper part of the control box, a plurality of coupling holes 26 are installed in the solar cell module, and the other end of the connecting member is fixed to one of the coupling holes. It is configured to fix the light receiving plate of the battery module at a specific angle.

The light emitting unit may include a lower case having a wiring passage for electrically connecting the LED to the control box, and one end of which is rotatably connected to the lower case, and the other end of which may be detachably attached to the lower case. It includes an upper case made of a material, a plurality of LED is preferably installed in the upper and lower cases in a stacked structure.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings. Prior to this, the terms or words used in this specification and claims should not be construed as being limited to their usual or dictionary meanings, and the inventors will properly describe the concept of terms in order to best explain their own design. Based on the principle that it can be defined, it should be interpreted as meaning and concept corresponding to the technical idea of the present invention. Therefore, the embodiments described in the specification and the drawings shown in the drawings are only one of the most preferred embodiments of the present invention and do not represent all of the technical ideas of the present invention, various modifications that can be replaced at the time of the present application It should be understood that there may be equivalents and variations.

1 is a view showing the configuration of the aviation failure lights according to the present invention. Referring to the drawings, the aviation obstacle lamp 10 of the present invention is installed on a high structure 1 such as a steel tower, and includes a solar cell module 20 and a control box 30 coupled to one side of each other, approximately, The light emitting part 40 for emitting light to warn the pilot of the aircraft may be installed at a position away from them.

2 shows a solar cell module 20 and a control box 30 used in the aviation failure lamp of the present invention. In the present invention, unlike the conventional installation of the solar cell module and the control box separately, the solar cell module 20 and the control box 30 is configured in one piece. In general, since the control box 30 is bulky and heavy, it can sufficiently support the solar cell module 20. In addition, in the case of manufacturing the solar cell module 20 and the control box 30 in this way, since only the control box 30 is fixed to the structure without the hassle of reassembling separate parts, product transportation and installation It has the advantage of being very simple.

Referring to FIG. 2, the control box 30 has a substantially rectangular parallelepiped shape, and an opening / closing door 31 for inspecting and replacing internal parts and circuits is installed at one side. The internal module of the control box 30 will be described later in detail.

The solar cell module 20 is installed above the control box 30. The solar cell module 20 includes a panel 22 made of a rigid material, and a light receiving plate 21 for receiving sunlight is installed on an upper surface of the panel 22. The solar cell module 20 is rotatably connected to one side end of the upper end of the control box 30, the other side is free to rotate around the connection point.

In addition, as shown in Figure 3, the upper end of the control box 30, the connecting member 24 is rotatably installed by the pivot (25). In addition, a coupling hole 26 is installed at a predetermined position in the panel 22 of the solar cell module 20, and is coupled to the other end of the connection member 24. At this time, it is preferable that a plurality of coupling holes 26 are formed so that the panel 22 of the solar cell module 20 can be fixed at various angles. In addition, the fastener 28 is used to fix the connecting member 24 to the coupling hole 26, the fastener 28 is preferably used in the form of easy separation, such as pins, bolts and nuts.

According to this configuration, the operator moves the solar cell module 20 to have an appropriate inclination, and then optimizes the solar cell module 20 by coupling the connection member 24 to the coupling hole 26 corresponding to the position. Can be installed at an angle of.

Control box 30 is a built-in various parts and circuits for controlling the overall operation, such as aviation obstacles according to the present invention, the function of generating electricity by using the solar light obtained through the solar cell module 20 and It converts electricity and supplies the light to the light emitting unit 40, and controls the operating time and operation method of the light emitting unit 40.

An internal configuration of the control box 30 is illustrated in FIG. 4. Referring to FIG. 4, the control box 30 includes a storage battery 32 to store electricity generated from the solar cell module 20. Do it. The storage battery 32 may be of any type commonly used, and the capacity of the storage battery 32 may operate the light emitting unit 46 for a sufficient time in consideration of the number and power of LEDs used in the light emitting unit 40. It is preferable to be provided to the extent possible.

The control box 30 is also equipped with an electromotive force switch 34. The electromotive force switch 34 serves to automatically transfer electricity stored in the storage battery 32 to the light emitting unit 40 when the electromotive force of the solar cell module 20 is less than or equal to the reference value. However, when the electromotive force of the solar cell module 40 is greater than the reference value, the sunlight is sufficient, so that the structure can be visually identified, so the electromotive force switch 34 is an electrical flow between the solar cell module 20 and the light emitting unit 40. To block. Therefore, during the day when the sunlight is sufficient, the solar cell module 20 collects electricity in the storage battery 32, and the electricity stored in the storage battery 32 when the sunlight is not sufficient, such as on a cloudy day or during rainy weather or at sunset and after sunset. By using the light emitting unit 40 to emit light.

In this case, the electromotive force switch 34 may be configured using a bypass circuit using a transistor or the like. However, the present invention is not limited thereto, and the electromotive force of the solar cell module 20 may be measured using a separate electromotive force sensor in the control box 30.

In addition, the control box 30 may include an amplifier 36 between the solar cell module 20 and the light emitting unit 40 to amplify the electricity delivered to the light emitting unit 40. The amplifier 36 is preferably disposed between the electromotive force switch 34 and the light emitting portion 40. The amplifier 36 has a concept of a control circuit and may be composed of several active or passive elements such as diodes, transistors, and resistors.

In addition, the control box 30 may be provided with a separate flashing circuit 38 to cause the light emitting unit 40 to flicker. As the flashing circuit 38, all kinds of conventional materials may be used, and the present invention is not limited to a specific example.

5 shows a light emitting unit 40 used in the aviation obstacle lamp according to the present invention. Referring to the drawings, the light emitting unit 40 has a lower case 42 and an upper case 44, one side of which is pivotably connected by a pivot 45, and a plurality of LEDs 46 are installed in each case. do. The lower case 42 is fixed to the structure, and a wiring passage 41 for electrically connecting the LED 46 to the control box 30 is formed inside the lower case 42. In addition, the upper case 44 is at least a portion, preferably at least half of the upper portion is made of a material that transmits light, so that when the LED 46 emits light it is configured to identify it from the outside. The part made of a light transmitting material is called a light transmitting part 43.

The LED 46 has a structure in which a plurality of LEDs 46 are stacked on a support 47 having a predetermined shape, and are preferably disposed to cover both the side and the top of the support 47. The supporter 47 is detachably installed at the inner center position of the lower case 42. As such, when the LED is used as the light emitting means, it emits very bright light but consumes little power, so there is little concern about power depletion, long lifespan, and less heat generation during the light emitting process.

One end of the lower case 42 and the upper case 44 of the light emitting unit 40 is pivotally coupled to each other, but the other end is detachably coupled to each other. As an example of such a configuration, as shown, through holes 48a and 48b are formed on the outer circumferential surface of the lower case 42 and the upper case 44 opposite to the pivot 45, and each through hole 48a and 48b. Each case may be fixed by inserting a coupling member 49 such as a bolt-nut or a pin through). Alternatively, it is also possible to use a clamp or the like as another alternative.

As described above, although the present invention has been described by way of limited embodiments and drawings, the present invention is not limited thereto and is intended by those skilled in the art to which the present invention pertains. Various modifications and variations can be made within the equivalent scope of the utility model registration claims to be described.

Aviation obstacle lamp according to the present invention configured as described above is easy to transport and install since the solar cell module and the control box are integrated, and one end of the solar cell module is rotatably installed on the top of the control box to optimize the solar cell module. There is an advantage that can be placed at an angle of.

In addition, since the aviation obstacle lamp of the present invention uses a plurality of LEDs as light emitting means, it is possible to provide bright light with little power, there is no fear of fixing due to overheating, and there is an advantage that the product life is long.

Claims (3)

In the aviation obstacle lamp 10 which is installed to be identified from the aircraft in the same structure as the transmission tower 1, Solar cell module 20 having a light receiving plate 21 for producing electricity by the light of the sun; A light emitting unit 40 having a plurality of LEDs 46 for emitting light by using the power supplied from the solar cell module; And It includes a control box 30 for storing the power supplied from the solar cell module to supply to the light emitting unit and to control the light emitting time and flashing of the light emitting unit, One end of the solar cell module aviation obstacle, characterized in that rotatably connected to the upper portion of the control box. The method of claim 1, The connection member 24 is rotatably installed on the upper portion of the control box, a plurality of coupling holes 26 are installed in the solar cell module, and the other end of the connection member is fixed to one of the coupling holes. Aviation obstacle light, characterized in that for fixing the light receiving plate of the battery module at a specific angle. The method of claim 1, wherein the light emitting unit, A lower case 42 having a wiring passage 41 formed therein for electrically connecting the LED to the control box, and An upper case 44 having one end rotatably connected to the lower case and the other end detachably configured at the lower case, and at least a portion of which is made of a material transmitting light; The plurality of LEDs are aviation failure lights, characterized in that installed in the upper and lower cases in a stacked structure.