JP2000260202A - Obstacle light - Google Patents

Abstract

PROBLEM TO BE SOLVED: To reduce cost by facilitating manufacturing with the reduced number of parts, to facilitate handling by reducing weight, and to reduce maintenance cost and power consumption. SOLUTION: A plurality of LEDs(light-emitting diodes) 4 are placed along a cylindrical surface. At the whole of each belt-like region of a globe 5 corresponding to each row of LEDs 4 aligned on a circle about an O-axis, Fresnel lenses are formed, respectively, for controlling light distribution in an O-axis direction of light emitted from the LEDs 4 of each row to the outside. Each Fresnel lens has a shape such as is generated by rotating a given cross-sectional profile about the O-axis, and its focus position is in the vicinity of the corresponding LEDs 4. These Fresnel lenses make up a light distribution control part 6 which controls, for a desired light distribution, the light distribution in the O-axis direction of the light emitting from the LEDs 4 to the outside through the globe 5.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an aviation obstacle light, and more particularly to an aviation obstacle light having a large number of light emitting elements as light sources.

[0002]

2. Description of the Related Art Aviation obstruction lights are lights installed on buildings such as high-rise buildings, power transmission towers, and large chimneys to notify aircraft of the existence of obstacles. The aviation obstruction light is configured to emit a main beam having a predetermined luminous intensity (for example, 30 cd) or more in a direction above a horizontal by a predetermined angle (for example, 7.5 °).

Conventionally, for example, Japanese Utility Model Laid-Open No. 4-102113
As disclosed in Japanese Unexamined Patent Application Publication No. H11-264, an aviation obstruction light including a large number of LEDs arranged along a cylindrical surface and a globe provided to cover the large number of LEDs is known. .

In such an aircraft obstruction light, an extremely large number of LEDs are used in order to secure a sufficient luminance, and each LE
D is disposed so as to extend from the horizontal in the direction above the predetermined angle.

In such a conventional aviation obstruction light, it is considered that a large number of LEDs arranged along a cylindrical surface constitute a surface light source as a whole, and the globe is a simple cylindrical transparent member. It was composed of

[0006]

However, in the conventional aviation obstruction light, the entire light emitted from each LED is
It has not been effectively used to form the light intensity distribution required for aviation obstruction lights, and a significant portion of the light emitted from each LED is either unnecessary or does not require much luminosity as aviation obstruction lights It was also released in an upward or downward direction.

For this reason, in the conventional aviation obstacle lights, LED
Unless the number is extremely large, the light intensity distribution required for an aviation obstacle light cannot be obtained. Since the number of LEDs is very large, the number of parts increases, and the production is troublesome and expensive. When many LEDs are used, it is necessary to efficiently radiate the heat generated from the LEDs to the outside in order to extend the life of the LEDs. However, since the number of LEDs is large and the amount of heat generated is large, the heat radiation structure The weight of the aviation obstruction light is increased due to the increase in the weight of the aviation obstacle light and the number of parts. Furthermore, since the number of LEDs is very large, power consumption is large, and maintenance costs such as electricity costs are large,
It was uneconomic.

The present invention has been made in view of such circumstances, and has a small number of parts and is easy and inexpensive to manufacture.
It is an object of the present invention to provide an aviation obstruction light that can be reduced in weight and is easy to handle, consumes less power, and reduces maintenance costs.

[0009]

According to a first aspect of the present invention, there is provided an aviation obstruction light, comprising: a plurality of light emitting elements disposed along a cylindrical surface; In the aviation obstacle light provided with a globe provided so as to cover the light, it is desired that the light emitted from the plurality of light-emitting elements to the outside via the globe be distributed in the direction of the axis of the cylindrical surface. A light distribution control unit for controlling the light distribution is formed on the globe or provided on the globe.

According to the first aspect, since the light distribution control unit is formed or provided on the globe, the light distribution control unit transmits the light distribution of the light emitted from the light emitting element to the airplane. It can be adjusted according to the light intensity distribution required for the obstacle light. Therefore, as compared with the related art, light emitted from each light emitting element can be used more effectively to form a light intensity distribution required for an aircraft obstacle light. Therefore, a light intensity distribution required for an aviation obstacle lamp can be obtained with a smaller number of light emitting elements than in the related art, and the number of light emitting elements can be significantly reduced.

As described above, according to the first aspect, the number of light emitting elements can be greatly reduced, so that the number of components is reduced, the manufacture is easy, and the cost is reduced. Further, since the number of light emitting elements is reduced and the amount of heat generated is reduced, the weight of the heat radiating structure can be reduced. It is easy to handle such as when installing to the. Further, since the number of light emitting elements is reduced, power consumption is reduced, and maintenance costs such as electricity bills are reduced, which is economical.

An aviation obstruction light according to a second aspect of the present invention comprises:
In the aviation obstruction light according to the first aspect, the plurality of light-emitting elements are arranged so as to form a row arranged on a circle around the axis of the cylindrical surface and a plurality of the rows are arranged, The light distribution control unit controls the light distribution in the direction of the axis of the cylindrical surface of the light emitted to the outside from the light emitting elements in the row on the entire or a part of each band-shaped area of the globe corresponding to each row. Is provided.

This second aspect is a light distribution in the case where a large number of light emitting elements are arranged in a line arranged on a circle centered on the axis of the cylindrical surface, and a plurality of such lines are arranged. As an example of the control unit, an example in which the light distribution control unit is configured by an individual light distribution control unit corresponding to each column of the light emitting elements is described. However, in the first aspect, when the large number of light emitting elements are not arranged in such a manner, the light distribution control unit may be appropriately changed according to the arrangement.

An aviation obstruction light according to a third aspect of the present invention comprises:
In the aviation obstruction light according to the second aspect, the individual light distribution control unit is a Fresnel lens having a shape such that a predetermined cross-sectional shape is generated by rotating around an axis of the cylindrical surface.

An aviation obstacle light according to a fourth aspect of the present invention comprises:
In the aviation obstacle light according to the second aspect, the individual light distribution control unit is a prism or a prism array having a shape such that a predetermined cross-sectional shape is generated by rotating around an axis of the cylindrical surface. is there.

In the third and fourth aspects, specific examples of the individual light distribution control unit are given, but the specific configuration of the individual light distribution control unit is not limited to these. For example, in the second aspect, the individual light distribution control unit may be a normal lens having a thicker cross section but a semi-cylindrical shape instead of a Fresnel lens. When the individual light distribution control unit is a Fresnel lens or a lens, for example, each row of the light emitting elements is arranged at a position near the focal point of the corresponding individual light distribution control unit.

[0017]

DESCRIPTION OF THE PREFERRED EMBODIMENTS [First Embodiment]

Hereinafter, an aviation obstacle light according to a first embodiment of the present invention will be described with reference to FIGS.

FIG. 1 shows an aviation obstacle light 1 according to the present embodiment.
It is the schematic front view which notched the left part which shows this. FIG.
FIG. 2 is an enlarged view in which a part in FIG. 1 is enlarged.

The aviation obstruction light 1 according to the present embodiment includes a base 2 having a tubular portion 3 and having thermal conductivity and a tubular surface (in the present embodiment, an outer peripheral surface of the tubular portion 3). LED4 as a large number of light emitting elements arranged along and a globe 5 provided to cover these LEDs4. In the present embodiment, the axis of the cylindrical surface is the axis O of the cylindrical portion 3 of the substrate 2.

In this embodiment, the base 2 is made of a metal material. The cylindrical portion 3 constituting a part of the base 2 is formed in a cylindrical shape that tapers slightly upward.
The base body 2 includes, in addition to the cylindrical portion 3, a flange portion 7 formed at a lower portion of the cylindrical portion 3, a radiation fin 8 formed to protrude downward from the flange portion 7, A projecting portion 9 formed continuously at the upper end of the tubular portion 3 so as to define the internal space A from the outside. Heat radiation fins 8
Are provided intermittently in the circumferential direction and are provided in two rows at intervals in the radial direction, but are not limited to such a configuration. Near the lower end of the protruding portion 9 that is continuous with the upper end of the cylindrical portion 3, a step is formed for engaging the upper horizontal portion of the globe 5. A male screw portion 9a into which a nut 13 described later is screwed is formed on the outer periphery near the lower end of the protruding portion 9.

One or a plurality of rows of LEDs 4 arranged vertically are mounted on each of the thermally conductive substrates 10 such as a strip-shaped aluminum substrate extending long in the vertical direction. A predetermined number are juxtaposed in the circumferential direction. Thus, the LEDs 4 are arranged in a row arranged on a circle centered on the axis O, and the rows are arranged in a plurality (11 rows in the illustrated example). The substrate 10 is fixed to the cylindrical portion 3 by screws 11. The substrate 10 is inclined at an angle of, for example, 7.5 degrees with respect to the vertical direction (the direction in which the axis O extends).
。It is oriented in the direction of inclining upward.

The globe 5 is made of, for example, a red transparent member made of resin, and is formed at a lower end of the cylindrical portion having a cylindrical portion slightly tapered upward and having a diameter larger than the cylindrical portion 3 of the base 2. And an upper horizontal portion directed inward from the upper end of the cylindrical portion. The upper horizontal portion is formed with an insertion hole through which the protruding portion 9 is inserted. As described above, the upper horizontal portion is engaged with the step near the upper end of the cylindrical portion 3 of the base 2. The upper horizontal portion of the globe 5 is sandwiched between the nut 13 and the step by screwing the nut 13 into the male screw portion 9a of the protrusion 9. Further, the flange portion of the lower end portion of the globe 5 is inserted into the flange portion and screwed to the flange portion 7 of the base body 2 (the screws are not shown). Is fixed to the part. The glove 5 and the base 2 are kept watertight by O-rings 14 and 15.

Below the cylindrical portion 3 of the base 2, a support 17 for supporting the base 2 is provided. The support member 17 is integrally formed of a metal material (thermally conductive material), and includes a cup-shaped upper support member 18 that opens upward and a space B that opens outward on the near side in FIG. And the lower support 19 having the shape of a quadrangular prism. The opening of the space B is closed in a watertight manner by a closing plate 26 fixed by screws 25 and a packing (not shown). The upper flange portion of the upper support 18 and the lower flange portion 7 of the base 2 are fixed by screws (not shown). Between these,
It is kept watertight by a ring-shaped packing 24.

At the lower part of the lower support 19, a flange portion 20 is provided.
Is formed, and a bolt insertion hole 21 is formed in the flange portion 20 so that it can be fixed to a pedestal or the like at a location where the aircraft obstruction light 1 is mounted. The space C inside the cup-shaped upper support 18 opened upward and the space B are communicated with each other through a communication hole 22. Space B
Communicates from the lower surface of the lower support 19 to the outside through the communication hole 23.

At a lower position in the space D between the globe 5 and the base 2, there is provided a relay board 31 on which components for relaying the wiring of the LEDs 4 are mounted. The space C is provided with a power supply circuit board 32 on which a power supply circuit (its components are not shown) is mounted. Further, a terminal block 33 is provided in the space B. At a predetermined position below the cylindrical portion 3 of the base 2, a long wiring hole 34 is formed to allow the space A and the space D to communicate with each other and to allow an electric wire to pass therethrough.

Although not shown in the drawing, the power supply line is connected to the terminal block 33 through the communication hole 23 from the outside, and the terminal block 33 and the power supply circuit board 32 are connected by electric wires. The relay board 31 is connected with an electric wire, and the relay board 31 and the board power supply circuit board 32 are connected with an electric wire via the elongated hole 34. Thus, a predetermined electric circuit is formed, and when a predetermined current flows through the LED 4, the LED 4 is turned on.

In this embodiment, FIGS. 1 and 2
As shown in the figure, the tapered cylindrical portion of the globe 5 has L
A light distribution control unit 6 that controls the light distribution in the direction of the axis O of the light emitted from the ED 4 to the outside through the globe 5 to a desired light distribution is formed.

In the present embodiment, the light distribution control unit 6
As shown in FIG. 2, LEs arranged on a circle centered on axis O
The entirety of each band-shaped area W of the globe 5 corresponding to each row of D4 (in the present embodiment, this band-shaped area W is a truncated cone-shaped band-shaped area around the axis O), and the LEs of the row are respectively provided.
It has an individual light distribution control unit 61 for controlling the light distribution in the direction of the axis O of the light emitted from D4 to the outside. In the present embodiment, as the individual light distribution control unit 61, the corresponding LED 4
A Fresnel lens having a focus near the position is formed. This Fresnel lens has a shape such that a predetermined cross-sectional shape as shown in FIG.

According to the aviation obstruction light 1 according to the present embodiment, the light emitted from the LED 4 passes through the individual light distribution control unit 61 formed as a Fresnel lens of the globe 5 and becomes substantially parallel light to the outside. , For example, 7.5 with respect to the horizontal direction.
出 射 Emitted in the direction inclined upward. As described above, the light distribution control unit 6 including the individual light distribution control units 61 formed according to each column adjusts the light distribution of the light emitted from the LED 4 to the light intensity distribution required for the aviation obstruction light. Will be adjusted. Therefore, a smaller LE than in the past
In D4, the light intensity distribution required for the aviation obstacle light can be obtained, and the number of LEDs 4 can be significantly reduced.

As described above, according to the present embodiment, LE
Since the number of D4s can be greatly reduced, the number of parts is reduced, manufacturing is easy, and the cost is low.

By the way, the heat generated from the LED 4 is mainly radiated to the outside from the radiating fin 8 through the tubular portion 3 of the substrate 2. In the present embodiment, the number of the LED 4 is reduced and the amount of heat generated is reduced. The weight of the aviation obstruction light 1 can be reduced by reducing the thickness by reducing the thickness of the tubular portion 3 and the radiating fins 8 constituting the radiating structure. It is easy to handle when installed at a high place.

Further, according to the present embodiment, since the number of LEDs 4 is reduced, power consumption is reduced, and maintenance costs such as electricity bills are reduced, which is economical.

[Second Embodiment]

Next, an aircraft obstacle light according to a second embodiment of the present invention will be described with reference to FIG.

FIG. 3 is an enlarged view showing a main part of the aviation obstruction light according to the present embodiment, and corresponds to FIG. In FIG. 3, the same or corresponding elements as those in FIGS. 1 and 2 are denoted by the same reference numerals, and redundant description will be omitted.

The aviation obstruction light according to the present embodiment is different from the aviation obstruction light 1 according to the above-described first embodiment in that the individual light distribution control section 61 configured as a Fresnel lens is replaced with the Fresnel lens. Individual light distribution control unit 62 configured as a prism array having a similar cross-sectional shape
Are formed only on the whole of each band-shaped region W of the globe 5.

According to the present embodiment, the parallelism of the light emitted from the LED 4 and transmitted through the individual light distribution control unit 62 is slightly lower than in the case of the first embodiment. The same advantage as that of the embodiment can be obtained.

[Third Embodiment]

Next, an aircraft obstacle light according to a third embodiment of the present invention will be described with reference to FIG.

FIG. 4 is an enlarged view showing a main part of the aviation obstacle light according to the present embodiment, and corresponds to FIG. In FIG. 4, the same or corresponding elements as those in FIGS. 1 and 2 are denoted by the same reference numerals, and redundant description will be omitted.

The aviation obstruction light according to the present embodiment is different from the aviation obstruction light 1 according to the above-described first embodiment in that the individual light distribution control is formed as a Fresnel lens over the entire band-shaped area W of the globe. An individual light distribution control unit 63 configured as a Fresnel lens in which the Fresnel lens of the individual light distribution control unit 61 is substantially reduced to the lower half instead of the unit 61
Is formed only in substantially the lower half of each band-shaped region W.

According to the present embodiment, of the light emitted from the LED 4 and transmitted through each band-shaped area W of the globe 5, the light distribution of the light transmitted above the band-shaped area W is not adjusted by the globe 5 at all. , The lower side of each band-shaped area W (that is,
Only the light transmitted through the individual light distribution control unit 62) is emitted to the outside as substantially parallel light.

According to the present embodiment, the intensity of light in a direction inclined upward by 7.5 ° with respect to the horizontal direction is slightly lower than that in the first embodiment. The same advantages as in the first embodiment can be obtained.

[Fourth Embodiment]

Next, an aircraft obstacle light according to a fourth embodiment of the present invention will be described with reference to FIG.

FIG. 5 is an enlarged view showing a main part of the aviation obstruction light according to the present embodiment, and corresponds to FIG. In FIG. 5, the same or corresponding elements as those in FIGS. 1, 2 and 4 are denoted by the same reference numerals, and redundant description will be omitted.

The difference between the aviation obstruction light according to the present embodiment and the aviation obstruction light 1 according to the second embodiment described above is that the individual light distribution control unit 63 configured as a Fresnel lens is replaced with the Fresnel lens. Individual light distribution control unit 64 configured as a prism array having a similar cross-sectional shape
However, the only point is that each is formed substantially in the lower half of each band-shaped region W of the globe 5.

According to this embodiment, advantages similar to those of the first embodiment can be obtained.

The embodiments of the present invention have been described above, but the present invention is not limited to these embodiments.

For example, in each of the above-described embodiments, the light distribution control unit 6 is formed on the outer surface of the globe 5, but the light distribution control unit 6 may be formed on the inner surface of the globe 5. Further, in each of the above-described embodiments, the light distribution control unit 6 is formed integrally with the globe 5 at the time of resin molding of the globe 5 or the like. Prepared separately from the glove 5
May be provided by sticking to the surface.

In the present invention, another light emitting element may be used instead of the LED 4.

Further, in the present invention, it goes without saying that the shape and size of the radiation fins 8 are not limited to the above-described example.

[0054]

As described above, according to the present invention,
The number of parts is small, the manufacturing is easy and inexpensive, the weight can be reduced, the handling is easy, and the power consumption is low and the maintenance cost can be reduced.

[Brief description of the drawings]

FIG. 1 is a schematic front view of a aviation obstruction light according to a first embodiment of the present invention, with a left portion cut away.

FIG. 2 is an enlarged view in which a part of FIG. 1 is enlarged.

FIG. 3 is an enlarged view showing a main part of an aviation obstacle light according to a second embodiment of the present invention.

FIG. 4 is an enlarged view showing a main part of an aviation obstruction light according to a third embodiment of the present invention.

FIG. 5 is an enlarged view showing a main part of an aviation obstacle light according to a fourth embodiment of the present invention.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Aviation obstruction light 2 Base 3 Cylindrical part 4 LED 5 Globe 6 Light distribution control part 8 Radiation fin 9 Projection part 10 Substrate 17 Support body 18 Upper support body 19 Lower member 61-64 Individual light distribution control part

Claims (4)

[Claims] An aviation obstruction light comprising: a plurality of light emitting elements disposed along a cylindrical surface; and a globe provided to cover the plurality of light emitting elements. A light distribution control unit that controls light distribution in the direction of the axis of the cylindrical surface of light emitted to the outside through the globe to a desired light distribution, is formed on the globe or provided on the globe. An aviation obstruction light characterized by being performed. 2. The light distribution control section, wherein the plurality of light emitting elements are arranged in a row arranged on a circle centered on an axis of the cylindrical surface, and the rows are arranged in plurality. Individual light distribution for controlling the light distribution in the direction of the axis of the cylindrical surface of light emitted to the outside from the light-emitting elements of the row on the entire or a part of each band-shaped area of the globe corresponding to each row. The aviation obstacle light according to claim 1, further comprising a control unit. 3. The individual light distribution control unit is a Fresnel lens having a shape such that a predetermined cross-sectional shape is generated by rotating around an axis of the cylindrical surface.
The aviation obstruction light described. 4. The prism according to claim 2, wherein the individual light distribution control unit is a prism or a prism array having a shape such that a predetermined cross-sectional shape is generated by rotating about an axis of the cylindrical surface. The aviation obstruction light described.