JP5130144B2 - Aircraft lights - Google Patents

Description

  The present invention relates to an aircraft lamp in which a light source and a reflector are housed in a housing mounted on an aircraft body.

Conventionally, external lights equipped outside the aircraft, such as landing lights, taillights, logo lights, and searchlights, are known as this type of aircraft lamp. For example, Patent Literature 1 describes a searchlight in which a housing is mounted outside the fuselage of a helicopter or a two-wing aircraft, and a valve and a reflector are housed inside the housing.
JP 2001-266603 A

  By the way, since an aircraft lamp is lit for a long time, it is necessary to periodically inspect and repair or replace the light source and other parts. In addition, when the next flight schedule is imminent, it is necessary to perform maintenance work within a limited time. However, according to the conventional lamp, there is a problem in that it takes time to perform maintenance because it particularly takes time to disconnect and reconnect the electric wiring.

  The present invention has been made paying attention to the above-mentioned problems, and an object thereof is to provide an aircraft lamp capable of performing maintenance work easily and quickly.

  In order to solve the above-described problems, an aircraft lamp according to the present invention includes a housing that is mounted on an aircraft body, a translucent cover is attached to the front surface of the housing, a reflector is accommodated inside the housing, and the front surface of the reflector is accommodated. Fix the light source, project the electrode terminal of the light source on the back of the reflector, install the lamp socket with power supply terminal at the rear of the housing, attach and detach the reflector to the lamp socket, and electrically connect the electrode terminal to the power supply terminal It is characterized by contacting and separating.

  In addition, the aircraft lamp of the present invention includes a retainer for fastening the translucent cover to the housing so that the electrode terminal can be securely connected to the power supply terminal in the assembled state, and the reflector is interposed between the translucent cover and the lamp socket by the retainer. It is characterized by being pinched.

  A semiconductor light source such as a filament-type bulb or LED can be used as the light source, but a long-life discharge lamp having a long life can be preferably used as the light source of the external lamp. The aircraft lamp of the present invention uses a discharge lamp as a light source so that a predetermined area around the aircraft can be illuminated brightly, and the discharge lamp is disposed so that the arc tube is oriented laterally with respect to the attachment / detachment direction of the reflector. It is characterized by that.

  In particular, in the case of an aircraft external light that supplies high power (for example, 250 W), the igniter generates a high voltage pulse (starting voltage) of, for example, ± 18 KV. For this reason, it is desirable to equip the igniter with the lamp so that the starting voltage of the discharge lamp does not drop. An aircraft lamp according to the present invention is characterized in that an igniter for starting a discharge lamp is assembled in a housing, and a high-voltage electric wire of the lamp socket is electrically connected to a socket portion of the igniter.

  Here, the installation location of the igniter is not particularly limited, but it is desirable that the rear end of the housing be formed from the viewpoint of making the entire lamp compact. The aircraft lamp of the present invention is characterized in that a back cover is attached to the rear end of the housing, and an igniter is accommodated inside the back cover.

  According to the aircraft lamp of the present invention, the light source is integrated with the reflector, and the electrode terminal of the light source is connected to and separated from the power supply terminal of the lamp socket by attaching and detaching the reflector. There is an effect that the maintenance work can be performed easily and quickly.

  Hereinafter, embodiments of the present invention will be described with reference to the drawings. FIG. 1 shows the appearance of an aircraft lamp. FIG. 2 shows a state in which an aircraft lamp is installed on the fuselage. 3 and 4 show exploded main parts of the aircraft lamp. FIG. 5 shows a power feeding path from the igniter to the discharge lamp in the assembled state of the aircraft lamp.

  As shown in FIGS. 1 and 2, the aircraft lamp 1 of this embodiment includes a cup-shaped housing 2. A translucent cover 3 is attached to the front surface of the housing 2 by a retainer 4. A back cover 6 that accommodates the igniter 5 is attached to the rear end of the housing 2, and a power supply shield wire 7 is connected to the igniter 5. A pair of mounting portions 8 are provided on the outer surface of the housing 2, and the housing 2 is attached to the aircraft body 10 by screws 9 or bolts screwed to the mounting portions 8, and the plug 11 at the tip of the shield wire 7 is connected to the body 10. It is connected to an internal power supply circuit (not shown). The lamp 1 is used as an external lamp such as a landing lamp, a tail lamp, a recognition lamp, and a logo light, and a housing 2 is mounted at an appropriate position on the body 10 according to the type of the lamp 1. The housing 2 is formed of a metal material such as aluminum from the viewpoint of being able to be easily attached to the body 10 and ensuring sufficient strength.

  As shown in FIGS. 3 and 4, the inside of the housing 2 is partitioned forward and backward by a partition wall 13, and a glass reflector 15 is accommodated in the front light chamber 14. On the front surface of the reflector 15, a reflecting surface 16 formed of a rotating paraboloid or a free curved surface that opens toward the translucent cover 3 is formed. A discharge lamp 17 is disposed at a substantially focal position of the reflecting surface 16, and electrode terminals 18 are fixed to both ends in the longitudinal direction of the arc tube 17 a of the discharge lamp 17. The discharge lamp 17 is arranged such that the arc tube 17a is oriented laterally with respect to the attaching / detaching direction of the reflector 15 (in the illustrated example, perpendicular to the optical axis 15a of the reflector 15), and is fixed to the reflector 15 by the electrode terminal 18. Has been. A pair of seating portions 19 project from the back surface of the reflector 15, and electrode terminals 18 project from the back surface side of the reflector 15 through the seating portion 19. In some aircraft lamps such as a logo light, the reflector 15 can be mounted on the housing 2 so that the light emission direction (optical axis 15a) is inclined.

  A lamp socket 21 is disposed at the rear of the lamp chamber 14 and is fixed to the partition wall 13 with a plurality of screws 22. The lamp socket 21 is formed of an insulating material such as ceramic or resin in a block shape that is long in the same direction as the arc tube 17 a of the discharge lamp 17. At both ends of the lamp socket 21, a power supply terminal 23 is embedded, and a support portion 24 for supporting the redirector 15 is projected, and an insertion port 25 of the power supply terminal 23 is exposed on the upper surface of the support portion 24. . In maintenance of the lamp 1, the reflector 15 is attached to and detached from the lamp socket 21 with the translucent cover 3 removed, and the electrode terminal 18 of the discharge lamp 17 is electrically connected to and separated from the power supply terminal 23. Yes. In addition, uneven positioning portions 26 </ b> A and 26 </ b> B are provided on the relative surfaces of the housing 2 and the reflector 15 so that the electrode terminal 18 can be easily inserted into the insertion port 25.

  As shown in FIG. 5, in the assembled state of the lamp 1, the translucent cover 3 and the reflector 15 are held on the housing 2 by the retainer 4 in a state in which the respective peripheral edges are joined. A gasket 27 is attached to the peripheral portion of the translucent cover 3, and another gasket 29 is interposed between the reflector 15 and the flange portion 28 of the housing 2. The retainer 4 is formed in an annular shape surrounding the translucent cover 3, and is attached to the flange portion 28 with a plurality of screws 30. Then, the translucent cover 3 and the reflector 15 are fastened to the housing 2 by the retainer 4, the reflector 15 is sandwiched between the translucent cover 3 and the lamp socket 21, and the electrode terminal 18 is held in a connected state with the power supply terminal 23. Is configured to do.

  The electrode terminal 18 is fixed to the seating portion 19 of the reflector 15 with an insulating ceramic adhesive 32, and the exposed portion of the adhesive 32 is insulated and protected by a base 33. The power supply terminal 23 of the lamp socket 21 includes a connection portion 23a parallel to the arc tube 17a of the discharge lamp 17, an insertion port 25 of the electrode terminal 18 is formed at one end of the connection portion 23a, and a high pressure is provided at the other end of the connection portion 23a. The front end of the electric wire 34 is connected. The high-voltage electric wire 34 is covered with an insulating coating 34 a made of silicon rubber or the like, the front end portion of the insulating coating 34 a is embedded in the insulating material of the lamp socket 21, and the remaining portion is formed on the rear side of the partition wall 13. It protrudes to the air layer 35 for use. The electrode terminal 18, the power supply terminal 23, and the high-voltage electric wire 34 are all covered with an insulating material to ensure a long creepage distance in the power supply path to the discharge lamp 17 and between the metal member such as the housing 2 and the screw 9. It is possible to reliably prevent discharge leakage and improve the insulation performance around the discharge lamp 17.

  As shown in FIGS. 3 and 5, the igniter 5 for starting the discharge lamp 17 is housed inside the back cover 6, and the back cover 6 is attached to the rear end surface of the housing 2 (mounting surface of the igniter 5) with a plurality of screws 37. It is attached. A pair of insertion holes 38 is formed in the front surface of the igniter 5, and the leg portion 40 of the igniter socket 39 is detachably inserted into the insertion hole 38. The igniter socket 39 is made of an insulating material such as resin or ceramic, and has a socket portion 41 protruding from the air layer 35 on the side opposite to the leg portion 40. In the socket portion 41, a connection port 42 is formed in which the high-voltage electric wire 34 and the rear end portion of the insulating film 34 a are attached and detached, and a connection conductor 44 is embedded to connect the connection port 42 to the output terminal 43 of the igniter 5. ing. The portion of the high voltage electric wire 34 that passes through the air layer 35 is covered with an insulating film 34a, and a high degree of insulation is secured at the connection portion between the high voltage electric wire 34 and the igniter 5, and the electronic circuit (not shown) of the igniter 5 is The power supply terminal 23 of the lamp socket 21 is electrically connected.

Therefore, according to the aircraft lamp 1 configured as described above, the following operational effects can be obtained.
(A) Since the discharge lamp 17 is integrated with the reflector 15 and the reflector 15 is attached to and detached from the lamp socket 21, the electrode terminal 18 is brought into and out of contact with the power supply terminal 23, thereby eliminating the trouble of disconnecting and reconnecting the electrical wiring. In addition, maintenance work such as inspection and replacement of the discharge lamp 17 can be performed easily and quickly within a limited time.
(B) In the assembled state of the lamp 1, since the reflector 15 is sandwiched between the translucent cover 3 and the lamp socket 21 by using the retainer 4 which is a mounting part of the translucent cover 3, separate parts are used. Without this, the electrode terminal 18 can be easily and reliably connected to the power supply terminal 23.

(C) Since the discharge lamp 17 is disposed so that the arc tube 17a is transverse to the attaching / detaching direction of the reflector 15, the light of the discharge lamp 17 is reflected by the reflecting surface 16 of the reflector 15, and a predetermined area around the aircraft Can be brightly illuminated.
(D) Since the igniter 5 is assembled to the housing 2 and the high-voltage electric wire 34 of the lamp socket 21 is connected to the socket part 41 of the igniter 5, the discharge lamp 17 with a large amount of light can be reliably turned on without lowering the starting voltage. The igniter 5 can be easily separated from the lamp socket 21 for maintenance.
(E) Since the igniter 5 is accommodated in the back cover 6 at the rear end of the housing 2, the cover 6 can protect the igniter 5, and the igniter 5 is arranged in the same direction as the attachment / detachment direction of the reflector 15. Can be made compact.

The present invention is not limited to the above-described embodiments, and as illustrated below, the configuration of each part can be arbitrarily changed and implemented without departing from the spirit of the invention.
(1) The translucent cover 3 shown in FIG. 1 is appropriately deformed according to the type and application of the lamp 1, such as an oval, a rectangle, or a polygon.
(2) Use a colored glass or lens for the translucent cover 3.
(3) The igniter socket 39 is omitted from the igniter 5 shown in FIG. 3, and the socket portion 41 is integrally provided on the front surface of the igniter 5.

1 is an external perspective view of an aircraft lamp showing an embodiment of the present invention. It is a side view which shows the body installation form of this lamp. It is a perspective view which shows the decomposition | disassembly form of this lamp. It is sectional drawing which shows the decomposition | disassembly form of this lamp. It is a fragmentary sectional view which shows the assembly form of this lamp.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Aircraft lamp 2 Housing 3 Translucent cover 4 Retainer 5 Igniter 6 Back cover 10 Airframe 15 Reflector 17 Discharge lamp 18 Electrode terminal 21 Lamp socket 23 Power supply terminal 34 High voltage electric wire 41 Socket part

Claims (5)

  Equipped with a housing to be mounted on the aircraft body, a translucent cover is attached to the front of the housing, a reflector is accommodated inside the housing, a light source is fixed to the front of the reflector, and an electrode terminal of the light source is projected on the back of the reflector An aircraft lamp comprising: a lamp socket provided with a power supply terminal at a rear portion of the housing; the reflector is attached to and detached from the lamp socket; and the electrode terminal is electrically connected to and separated from the power supply terminal.   The aircraft lamp according to claim 1, further comprising a retainer for fastening the translucent cover to the housing, wherein the reflector is sandwiched between the translucent cover and the lamp socket by the retainer.   The aircraft lamp according to claim 1 or 2, wherein a discharge lamp is used as the light source, and the discharge lamp is disposed so that the arc tube thereof is transverse to the attaching / detaching direction of the reflector.   The aircraft lamp according to claim 1, 2, or 3, wherein an igniter for starting the discharge lamp is assembled to a housing, and a high-voltage electric wire of the lamp socket is electrically connected to a socket portion of the igniter.   The aircraft lamp according to claim 4, wherein a back cover is attached to a rear end portion of the housing, and the igniter is accommodated inside the back cover.

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