JPH11245896A - Lamp for helicopter takeoff/landing site and lighting system using the same - Google Patents

Abstract

PROBLEM TO BE SOLVED: To simplify a lighting system which allows helicopters dispatched in an emergency or the like to safely take off and land even during the night. SOLUTION: A lighting system for a helicopter takeoff/landing site is constructed using a lamp 11 fitted with at least a solar battery 17 placed on the outer surface of a casing 12, an electric double-layer capacitor 18 built into the casing 12 and charged by the solar battery 17, and a light-emitting diode 20 placed at the top of the casing 12 and turned on by a current supplied from the electric double-layer capacitor 18.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a lighting device for a helicopter landing / departure site for assisting a helicopter to be dispatched to a rescue operation or the like in an emergency such as an emergency or disaster so that it can safely take off and land at night. And a lighting system using the same.

[0002]

2. Description of the Related Art A helicopter is highly mobile and
Since it is a simple means of flight that can take off and land at relatively small takeoff and landing sites, it has demonstrated great power in emergency and disaster situations, especially in disaster relief activities such as earthquakes and high-rise building fires.

On the other hand, from the viewpoint of ensuring safe navigation of a helicopter, a place where helicopters can take off and land (hereinafter, referred to as "helicopter") Various restrictions are added to the "take-off and landing area."

[0004] That is, in the Civil Aeronautics Act, etc., there are four helicopter take-off and landing sites: "heliport (for public and non-public use)", "off-airfield take-off and landing site", "emergency take-off and landing site", and "emergency rescue space". In particular, as a field of application of the present invention, the relationship between “off-airfield landing / departure landing”, “emergency departure / departure landing”, and “emergency rescue space” becomes a problem.

[0005] Of these, the "off-airfield take-off and landing site" refers to an off-airfield take-off and landing site that requires a take-off and landing permission of the Minister of Transportation every time it is used, and can take off and land temporarily.
"Emergency takeoff and landing site" refers to a place (land or rooftop) that is applied only when taking off and taking off an emergency helicopter for disaster activities, etc. I can do it. further,
"Emergency rescue space" means a place that is only applied when hovering an emergency helicopter for disaster activities, etc., and that only special agencies can hover only during special hours during emergencies . In this case, it is necessary to apply for the “emergency take-off and landing site” and “emergency rescue space” as “off-airfield take-off and landing site” and obtain a landing permit each time it is used.

[0006] In addition, regarding the “off-airfield departure / departure landing”, “emergency departure / departure landing” and “emergency rescue space”, a permanent “heliport (public / non-public)” equipped with various safety facilities and equipment is provided. It is necessary to install various lighting equipment necessary to ensure safety, especially during night navigation.

[0007] Of these, the "emergency take-off and landing area" and "emergency rescue space" are at least "heliport lighthouse", "wind direction light", "landing area illumination light", "boundary guidance light", and "boundary light". It is said that it is necessary to set up. In addition, at the "off-airfield landing / departure", various lighting fixtures according to the "emergency departure / departure" or "emergency rescue space" will be installed each time it is used.

[0008] For this reason, the above-mentioned various lamps are installed at predetermined positions in advance with necessary wiring, and are turned on by manually operating a lighting control panel or by remote operation from a disaster prevention center or the like. It can be turned off.

Incidentally, since the above-mentioned various lighting devices are wired and controlled to be turned on and off by the lighting control panel, the installation work performed with the wiring becomes complicated, and the emergency response is promptly performed. He had the problem of lack of sex.

[0010] On the other hand, in view of such a problem, the "heliport lighthouse", the "wind direction light" and the "landing area illumination light" are individually equipped with light-equipped generators, and the "boundary light" and "boundary guide light"
A simple lighting system for a helicopter landing / departure site which eliminates the need for wiring by installing and configuring a rechargeable light has already been proposed.

[0011]

However, in the above-mentioned simple system, the "heliport lighthouse" and the "wind light" are used.
And the `` landing area lighting '' are replaced by generators with lights, so there is the complexity of having to start and prepare the engine in advance, as well as generating noise and exhaust gas when the engine is running. There is also a problem that the surrounding environment is adversely affected.

[0012] As for the "boundary light" and the "boundary guide light", a rechargeable light is used.
In addition to the fact that it is necessary to charge the battery in advance, the lighting time must be relatively short.

Further, in the case of a rechargeable light, a secondary battery such as a lead battery is used.
In the case of a stored battery, a sufficient battery function cannot be exhibited, and the battery may not operate when required. There is also a problem that the charging time is prolonged during use.

The present invention has been made in view of the above-mentioned problems in the prior art, and has been simplified in that a helicopter dispatched for rescue operations or the like in an emergency such as an emergency or disaster can safely take off and land even at night. It is an object of the present invention to provide a lighting device for a helicopter take-off and landing site that can form a supportive attitude and a lighting system using the same.

[0015]

DISCLOSURE OF THE INVENTION The present invention has been made to achieve the above object. Among them, the structural features of the lamp for a helicopter take-off and landing site according to the present invention are arranged on the outer surface of a casing. A solar cell provided, an electric double layer capacitor built in the casing and charged by the solar cell, and a light emitting diode disposed on the top of the casing and lit by a current supplied from the electric double layer capacitor. I have at least provided it.

The configuration of the helicopter take-off and landing lighting system according to the present invention is characterized by various types including a heliport lighthouse, a wind direction light, a landing area light, a boundary guidance light, and a boundary light installed at a predetermined position. In the lighting system for helicopter takeoff and landing field composed of lamps, the lamp composed of at least the boundary guide light and the boundary light, the solar cell disposed on the outer surface of the casing, and built in the casing An electric double layer capacitor charged by the solar cell and a light emitting diode disposed on the top of the casing and lit by a current supplied from the electric double layer capacitor are provided.

[0017]

FIG. 1 is an overall perspective view showing an example of a lamp for a helicopter take-off and landing site according to the present invention.
The entire lamp 11 includes a solar cell 17 disposed on the outer surface of the casing 12 and an electric double-layer capacitor 18 built in the casing 12 and charged by the solar cell 17.
And a light emitting diode 20 disposed at the top of the casing 12 and lit by a current supplied from the electric double layer capacitor 18.

This will be described in more detail with reference to FIG. 1. The casing 12 is provided with a swash plate portion 14 which is inclined at a predetermined angle with respect to a horizontal plane, and a top plate portion 15 on the top.
And a casing body 13 having a truncated pyramid shape such as a truncated pyramid shape, and the casing body 1
3 is formed on the lower side with a base 16 suspended on a prism.

The solar cell 17 is provided on the casing 12 by attaching one or more solar panels having an appropriate structure so as to cover the outer surface of each swash plate section 14 in the casing body section 13. Has been established.

Further, one or a plurality of electric double layer capacitors 18 are arranged in a well-balanced manner in a base portion 16 of the casing 12, and if necessary, the base portion 16 is provided.
A connection terminal 19 for connecting a power supply line (not shown) drawn from a vehicle-mounted battery of the vehicle is provided on an outer surface of the vehicle,
The electric double layer capacitor 18 can be freely charged via the connection terminal 19.

Further, one or a plurality of light emitting diodes 20 are arranged in a light-transmitting protective cover 20 covered by the top plate 15 of the casing 12.
In this case, it is preferable that the light emitting diode 20 is provided with a horizontal reflector 21 on the lower surface side.

Moreover, the lighting device 11 itself is formed to have a large weight so that it is not blown off by a wind pressure received from a helicopter when it is installed at a predetermined position, or the position is fixed using, for example, a magnetic force. It is desirable to provide an appropriate position fixing means such as fixing the position by inserting an anchor projecting from the base 16 into the ground. Moreover, you may have a handle for carrying.

FIG. 2 is a basic circuit diagram as an example for controlling the turning on and off of the light emitting diode 20 provided in the lighting device 11. The solar cell 17 and the solar cell 17 are shown in FIG.
Electric double layer capacitor 1 connected in parallel and charged
8 and at least a light emitting diode 20 that is turned on by a current supplied from the electric double layer capacitor 18.

A zener diode 23 for protecting the electric double layer capacitor 18 from overvoltage is connected to the solar cell 17 in parallel, and a backflow between the solar cell 17 and the electric double layer capacitor 18 is prevented. Diode 24 is provided.

Further, between the electric double layer capacitor 18 and the light emitting diode 20, there are provided a switch 25 for controlling the turning on and off of the light emitting diode 20 by manual operation, and a required resistor 26.

Further, in the above circuit, the solar cell 1
It is preferable that a connection terminal 19 connected in parallel with the power supply 7 is provided so that the electric double layer capacitor 18 can be rapidly charged from the vehicle-mounted battery via the connection terminal 19. Such a circuit is formed on a printed circuit board or the like and is disposed in the casing 12.

On the other hand, FIG. 3 is an explanatory diagram showing the illumination system for helicopter takeoff and landing according to the present invention applied to an “off-airfield takeoff and landing site” as an example.

According to the figure, a vertical side × a horizontal side is 13 m × 13
m and the outer edge 1 of the LZ 1
a total of eight boundary lights 3 installed at the four corners of the similar-shaped frame dashed line 2 located 0.5 m outside of a and the center of each of the vertical sides 2a and 2b, and each vertical line in the frame dashed line 2 Side 2a,
A total of six boundary guide lights, each consisting of a total of three, are arranged 0.5 m outside of the boundary lights 3 installed at the center of each of the 2b and the upper and lower positions 1.5 m apart from each other. 4 and each boundary light 3 located at the four corners of the dashed box 2
A variety of lighting fixtures 11 consisting of a total of four landing area illumination lights 5 installed 1.0 m outside from, and a heliport lighthouse 6 and wind direction lights 7 installed 13 m outside the upper right corner of the dashed box 2. Constitutes a helicopter take-off and landing lighting system.

In this case, at least the boundary light 3 and the boundary guide light 4 whose lamp quality is immobile light can be installed by using the lamp 11 shown in FIG.

If necessary, at least one of the wind direction light 7 and the landing area illuminating light 5 whose light quality is immobile light is disposed on the outer surface of the casing 12. A solar cell 17, one or more electric double-layer capacitors 18 disposed in the casing 12 and charged by the solar cell 17, and separately supplied from each electric double-layer capacitor 18 disposed on the top of the casing 12. One or more light emitting diodes 2 lit by the applied current
1 can be formed.

For the heliport lighthouse 6 whose light quality is flashing (flashing), for example, a control circuit having a flashing (flashing) circuit 27 as shown in FIG. 4 is used instead of the circuit shown in FIG. Thereby, the light quality of the light emitting diode 21 can be set to flash light. Further, a xenon lamp having a required luminous intensity may be used in place of the light emitting diode 21, and a lamp having the same other configuration as the lamp 11 may be used.

The lamp 11 for helicopter takeoff and landing in the present invention is lit by a solar cell 17, an electric double layer capacitor 18 charged by the solar cell 17, and a current supplied from the electric double layer capacitor 18. Since the light emitting diode 20 is provided, the electric double layer capacitor 18 is charged during daylight, so that the electric double layer capacitor 18 can be suitably used as the boundary light 3 or the boundary induction light 4 which does not require wiring at night.

In addition, the electric double layer capacitor 18 incorporated in the lamp 11 can store a large amount of energy in a short time and can withstand a long-term use at a practical level. Superior stability can be imparted.

Further, a casing body 13 constituting the casing 12 has a swash plate portion 14 inclined on a horizontal plane on each surface, and the solar cell 1 is placed on each swash plate portion 14.
In the case where 7 is provided, even if the altitude of the sun changes depending on the season, electric energy can be obtained by photoelectric conversion most efficiently.

Further, when the casing 12 has the connection terminal 19 for connecting the power supply line drawn from the vehicle-mounted battery, even when the lamp 11 has to be used suddenly, It can be used for use by fully charging quickly in a short time.

On the other hand, in the lighting system for helicopter take-off and landing field according to the present invention, the lighting device 11 shown in FIG. 1 can be used as at least the boundary light 3 and the boundary guide light 4. In addition to clearing electrical wiring from the surrounding area, installation work at a predetermined position can be performed quickly, and the switch 25 can be operated without any preparatory work such as charging before a helicopter comes in. It is possible to immediately prepare the receiving state only by closing and turning on the light emitting diode 21. Further, after the use as an “emergency take-off and landing place” or “emergency rescue space” for a helicopter, the withdrawal work can be performed extremely simply by simply collecting the lamps 11.

Further, a plurality of electric double layer capacitors 1
8 is built in the casing 12, and a plurality of light emitting diodes 21 illuminated by currents supplied separately from the electric double layer capacitors 18 are also provided. The helicopter lighthouse 6, the wind direction light 7, or the landing area illumination light 5 are provided. In the case where the lighting device 11 having a brightness that satisfies the required luminous intensity is formed, the lighting device 11 is used as the heliport lighthouse 6, the wind direction light 7 and the landing area lighting light 5 to cover a wider area. Since wiring related to electricity can be wiped out, maintenance of the receiving system including the installation and withdrawal after use can be performed more quickly.

[0038]

As described above, according to the lamp for a helicopter take-off and landing site according to the present invention, the electric double-layer capacitor is charged during the sunshine, so that the boundary which does not require electric wiring at night can be obtained. It can be suitably used as a lamp or a boundary guide lamp.

In addition, the electric double layer capacitor incorporated in the lamp can withstand standing and storage for many months, can store a large amount of energy in a short time, and has a long life per charge. Good stability can be imparted to the tool.

Further, when the casing body constituting the casing has a swash plate portion with a solar cell on each surface, photoelectric conversion can be performed efficiently to obtain electric energy. In addition, when the casing has a connection terminal connected to the vehicle-mounted battery, the electric double-layer capacitor can be fully charged in a short time, so that it is possible to immediately respond to a sudden use request. it can.

On the other hand, according to the helicopter take-off and landing lighting system of the present invention, since the lighting device of the present invention is used for at least the boundary lights and the boundary guide lights, the "emergency take-off and landing" or the "emergency rescue" Eliminating the electrical wiring around the LZ provided as a “space for use” can contribute to speeding up installation and withdrawal operations.

In the case where a lighting device which can obtain the brightness satisfying the luminous intensity required for the heliport lighthouse, the wind direction light or the landing area illumination light is formed, the lighting apparatus is changed to the heliport lighthouse, the wind direction light and the landing area illumination. Since it can also be used as a light, it is possible to wipe out the electrical wiring over a wider area centered on the landing zone, and to perform the installation work and the removal work more quickly. Further, by eliminating the need to use a generator, it is possible to eliminate the adverse effects on the surrounding environment caused by engine noise and exhaust gas.

[Brief description of the drawings]

FIG. 1 is an overall perspective view showing an example of a lamp for helicopter takeoff and landing according to the present invention.

FIG. 2 is a principle circuit diagram as an example for controlling turning on and off of a light emitting diode included in the lighting device shown in FIG.

FIG. 3 is an explanatory view showing an example of a lighting system for helicopter takeoff and landing according to the present invention.

FIG. 4 is a principle circuit diagram as an example for controlling flashing (flashing) of a light emitting diode included in a lamp used for a heliport lighthouse.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Landing belt 1a Outer edge 2 Outer dashed line 2a, 2b Vertical side 3 Boundary light 4 Boundary guidance light 5 Landing area illumination light 6 Heliport lighthouse 7 Wind light 11 Lighting fixture 12 Casing 13 Casing main body part 14 Swash plate part 15 Top plate part 16 Base 17 Solar cell 18 Electric double layer capacitor 19 Connection terminal 20 Light emitting diode 21 Protective cover 22 Reflector 23 Zener diode 24 Diode 25 Switch 26 Resistance 26 Flashing (flashing) circuit

 ──────────────────────────────────────────────────の Continuing on the front page (72) Inventor Masao Hikita 2-23-1, Nishigotanda, Shinagawa-ku, Tokyo Inside Eluna-Components Co., Ltd.

Claims (8)

[Claims] 1. A solar cell disposed on an outer surface of a casing, an electric double layer capacitor built in the casing and charged by the solar cell, and an electric double layer capacitor disposed on a top of the casing. A light for a helicopter take-off and landing field, comprising at least a light-emitting diode that is lit by a supplied current. 2. The casing according to claim 1, wherein the casing has a swash plate portion inclined on a horizontal plane on each surface, and has a top plate portion on the top and a truncated pyramid shape. And a base portion provided on a lower side portion, wherein a solar cell is provided on each swash plate portion of the casing main body portion, and a light emitting diode is provided on a top plate portion. A lighting device for a helicopter take-off and landing site according to claim 1. 3. The electric vehicle according to claim 2, wherein the casing has a connection terminal for connecting a power supply line drawn from a vehicle-mounted battery of the vehicle, and the electric double-layer capacitor is freely charged via the connection terminal. 3. A method according to claim 1, wherein
Lighting equipment for helicopter take-off and landing as described. 4. A helicopter take-off and landing lighting system comprising a variety of lights including a heliport lighthouse, a wind direction light, a landing area light, a boundary guidance light, and a boundary light installed at a predetermined position. A lighting device composed of a lamp and a boundary light includes a solar cell disposed on the outer surface of the casing, an electric double-layer capacitor incorporated in the casing and charged by the solar cell, and disposed on the top of the casing. And a light emitting diode which is lit by a current supplied from an electric double layer capacitor. 5. The at least one kind of lighting device constituting the wind direction light and the landing area illumination light, a solar cell disposed on an outer surface of a casing, and a solar cell incorporated in the casing and charged by the solar cell. One or more electric double-layer capacitors, and a lamp which is disposed on the top of the casing and is lit by a current supplied separately from each electric double-layer capacitor.
The helicopter landing and landing lighting system according to claim 4, wherein the lighting system comprises at least one light emitting diode. 6. A lighting device constituting the heliport lighthouse,
A solar cell disposed on the outer surface of the casing, one or more electric double-layer capacitors contained in the casing and charged by the solar cell, and each electric double-layer capacitor disposed on the top of the casing. 6. The helicopter landing / departure lighting system according to claim 4, wherein the lighting system comprises at least one light emitting diode which flashes and blinks by a current supplied separately. 7. A casing body having a swash plate portion inclined on a horizontal plane on each surface, a top plate portion at the top, and a truncated pyramid shape, and a casing having a truncated pyramid shape. And a base portion provided on a lower side portion, wherein a solar cell is provided on each swash plate portion of the casing main body portion, and a light emitting diode is provided on a top plate portion. The lighting system for a helicopter take-off and landing field according to any one of 4 to 6. 8. The electric vehicle according to claim 8, wherein the casing has a connection terminal for connecting a power supply line drawn from a vehicle-mounted battery of the vehicle, and the electric double-layer capacitor is freely charged via the connection terminal. 8. The method according to claim 4, wherein
The lighting system for a helicopter take-off and landing site according to any one of the above.