JP7586740B2 - Aircraft Lighting - Google Patents

Description

The present invention relates to the technical field of aircraft lighting equipment that is attached to the fuselage of an aircraft.

Some aircraft lighting fixtures have a light source disposed inside a lighting fixture outer casing that is made up of a cover and a lamp housing (see, for example, Patent Documents 1, 2, and 3).

There are various types of such aircraft lighting fixtures depending on the purpose of use. Examples of exterior lighting include collision prevention lights to prevent collisions between aircraft, aviation lights that indicate the aircraft's flight attitude and direction, landing lights that illuminate the runway during takeoff and landing, and logo lights that illuminate the logos of airlines and the like inscribed on the aircraft.

JP 2010-33840 A JP 2010-33841 A JP 2020-119636 A

In aircraft lighting fixtures such as those described above, high visibility is required for pilots of other aircraft, and therefore at least the cover is exposed to the air from the aircraft body, making the internal space an enclosed space. However, when an aircraft is flying, the flight environment is prone to large fluctuations, such as large changes in air pressure and temperature. Therefore, there is a risk that moisture may unintentionally enter the internal space due to these flight conditions.

However, in the unlikely event that moisture does enter the internal space of aircraft lighting fixtures, it is necessary to prevent moisture from adhering to the control board that controls the turning on and off of the light source, thereby ensuring a stable operating state of the control circuit.

The aircraft lighting fixture of the present invention aims to prevent moisture from adhering to the control board that controls the turning on and off of the light source regardless of changes in the aircraft's flight environment.

First, the aircraft lighting fixture of the present invention comprises a lighting fixture outer casing having a lamp housing and a cover that are joined together to form a lamp chamber inside, a board mounting member that has an opening at one end and an internal space that forms an arrangement space and is arranged in the lamp chamber, a light source board that is attached to the outer periphery of the board mounting member and has a light source mounted thereon, a control board that controls the turning on and off of the light source, and a board mounting base that is attached to the control board and arranged in the lamp chamber, and the control board is positioned in the arrangement space when the board mounting base is attached to the board mounting member from the opening side and the board mounting base is attached to the board mounting member.

As a result, the board mounting member and board mounting base are arranged in the lamp chamber formed by combining the lamp housing and the cover, and the control board is positioned in the arrangement space when the board mounting base is attached to the board mounting member, so that the control board is positioned in the arrangement space, which is the inner space of the lamp chamber that has a double structure.

Secondly, in the aircraft lighting device according to the present invention described above, it is preferable that a plurality of the light source boards are provided, and the plurality of light source boards are attached to the board attachment member in a line or spaced apart manner in the circumferential direction.

This makes it possible to emit light from the light source in the circumferential direction.

Thirdly, in the aircraft lighting device according to the present invention described above, a flexible printed circuit board is provided that connects the control board and the plurality of light source boards, and it is preferable that the flexible printed circuit board has an attachment portion that is attached to the outer circumferential surface of the board attachment member and a plurality of connection portions that protrude from the attachment portion and are respectively connected to the plurality of light source boards.

As a result, with the mounting portion attached to the outer peripheral surface of the board mounting member, multiple light source boards are connected to the control board by a single flexible printed wiring board.

Fourthly, in the aircraft lighting device according to the present invention described above, it is desirable that the board mounting member and the board mounting base are both formed as heat sinks from metal materials.

As a result, heat generated on the light source board is transferred to the board mounting member formed as a heat sink, and heat generated on the control board is transferred to the board mounting base formed as a heat sink, allowing heat dissipation.

Fifthly, in the aircraft lighting device according to the present invention described above, it is preferable that the board mounting base is provided with a base portion that is attached to the board mounting member and a component mounting portion that protrudes from the base portion, the control board has a first board and a second board, and the first board and the second board are attached to both sides of the component mounting portion.

This splits the control board into a first board and a second board, both of which are attached to the board mounting portion.

According to the present invention, the board mounting member and the board mounting base are arranged in the lamp chamber formed by combining the lamp housing and the cover, and the control board is positioned in the arrangement space when the board mounting base is attached to the board mounting member. Therefore, the control board is positioned in the arrangement space, which is the inner space of the lamp chamber having a double structure, and the control board is protected regardless of changes in the flight environment of the aircraft, and the adhesion of moisture to the control board can be prevented.

FIG. 1 is a perspective view showing an aircraft. FIG. 2 is a perspective view of an aircraft lighting device. 3 is a perspective view showing the aircraft lighting device as viewed from a different direction than that shown in FIG. 2. FIG. 2 is an exploded perspective view of an aircraft lighting device. FIG. 2 is a cross-sectional view of an aircraft lighting device. 2 is a perspective view showing a part of a board mounting member and a part of a flexible printed wiring board. FIG.

Below, the embodiment of the aircraft lighting device of the present invention will be described with reference to the attached drawings.

Aircraft lighting fixtures have a light source placed inside the lighting fixture outer casing, which has a lamp housing and a cover. In the following explanation, the direction in which the lamp housing and cover are joined is referred to as the up-down direction, with the cover at the top and the lamp housing at the bottom, and the directions indicated are front-back, up-down, left-right.

Note that the directions of front, back, up, down, left and right shown below are for convenience of explanation, and the implementation of the present invention is not limited to these directions.

Below is an example of the aircraft lighting device of the present invention being applied to an anti-collision light, which is an external light, but the scope of application of the present invention is not limited to anti-collision lights, and may be applied to other external lights used on aircraft.

The aircraft lighting device 1 is used, for example, as a collision prevention light for external lighting, and is attached to the airframe 101 of the aircraft 100, for example, to the upper or lower part of the fuselage 102 (see FIG. 1). Note that the aircraft lighting device 1 may also be attached to both sides of the wing, for example, the vertical stabilizer 103.

When the aircraft lighting device 1 is attached to the fuselage 102, a recessed arrangement not shown is formed in the fuselage 102. A portion of the aircraft lighting device 1 is placed in the recessed arrangement, and the other portion is exposed from the fuselage 102.

Aircraft lighting fixture 1 comprises a lamp housing 2 that opens upward and a cover 3 that opens downward, with the upper end of the lamp housing 2 and the lower end of the cover 3 being joined (see Figures 2 to 5). The portion of aircraft lighting fixture 1 below the joint between the lamp housing 2 and the cover 3 is placed in a placement recess in the fuselage 102, and the remaining portion is exposed from the fuselage 102. The lamp housing 2 and the cover 3 form the lighting fixture outer casing 4, and the space inside the lighting fixture outer casing 4 is formed as the lamp chamber 5.

The lamp housing 2 is made of a metal material with high heat dissipation properties, such as aluminum, and each part is integrally formed. The lamp housing 2 has a cylindrical peripheral portion 6 with an axial direction extending vertically, and a flange portion 7 that projects outward from the upper end of the peripheral portion 6. The peripheral portion 6 has inner protrusions 6a, 6a, ... that protrude inward from the inner peripheral surface and are spaced apart in the circumferential direction. The inner peripheral portion of the flange portion 7 is formed as a concave receiving portion 7a that opens upward and inward.

The cover 3 is made of a transparent resin material, with each part being integrally formed. The cover 3 has a cap-shaped cover part 8 that opens downwards and a pressed part 9 that protrudes outward from the lower end of the cover part 8.

The lamp housing 2 and cover 3 are joined together by having the cover 3's retained portion 9 pressed from above by a ring-shaped lens retainer 10 made of a metal material and pressed from below by the inner circumference of the flange portion 7 of the lamp housing 2, and the lens retainer 10 being fixed to the flange portion 7 by screws or the like.

In this way, the cover 3 is held in place by the lens retainer 10 and the flange portion 7 with the pressed portion 9 pressed from above and below, preventing the cover 3 from falling off the lamp housing 2 and ensuring a stable positioning of the cover 3.

When the lens retainer 10 is fixed to the flange portion 7, a first annular gasket 11 is interposed between the two. In addition, the connecting portion of the lens retainer 10 and the flange portion 7 of the lamp housing 2 and the cover 3 is fixed to the body 102 or the like by screws or the like, and at this time a second gasket 12 is interposed between the underside of the flange portion 7 and the body 102.

The first gasket 11 provides waterproofing to the lamp chamber 5, and the second gasket 12 prevents the aircraft lamp 1 from rattling against the fuselage 102 and provides waterproofing to the placement recess formed in the fuselage 102.

A board mounting member 13 is disposed in the lamp chamber 5, and is attached to the lamp housing 2 by means of screws or the like. The board mounting member 13 is made of a metal material with high heat dissipation properties, such as aluminum, and each part is integrally formed. As the board mounting member 13 is made of a metal material with high heat dissipation properties, it also functions as a heat sink.

The board mounting member 13 has a generally circular annular portion 14 with an axial direction extending vertically, a generally cylindrical board mounting portion 15 whose lower end is connected to the inner periphery of the annular portion 14, a generally disk-shaped mounting plate portion 16 whose outer periphery is connected to the upper end of the board mounting portion 15, and coupling protrusions 17, 17, ... that protrude downward from the outer periphery of the annular portion 14 and are positioned at intervals in the circumferential direction.

The board mounting member 13 is formed with an open shape at the bottom, with an opening 13a at the bottom end, and the internal space is formed as the arrangement space 13b.

The annular portion 14 has a wiring board insertion hole 14a that penetrates vertically (see Figure 6).

The outer peripheral surface of the board mounting portion 15 is, for example, divided equally into nine portions, and each of the nine portions is formed as a planar board mounting surface 15a, 15a, ... (see Figures 4 and 5).

Positioning pins 16a, 16a protruding upward are provided on the outer periphery of the mounting plate portion 16, and the positioning pins 16a, 16a are provided on approximately opposite sides of the center of the mounting plate portion 16.

Light source boards 19, 19, ... are attached to the board mounting surfaces 15a, 15a, ... of the board mounting member 13 by gluing, screwing, etc. via first heat dissipation sheets 18, 18, ..., respectively. The first heat dissipation sheet 18 and the light source board 19 are formed, for example, in a vertically elongated rectangular shape, and three light sources 20, 20, 20 are mounted on the outer surface of the light source board 19, spaced apart in the longitudinal direction, for example. As the light sources 20, for example, light emitting diodes (LEDs) are used.

As described above, the light source boards 19, 19, ... are attached to the board mounting surfaces 15a, 15a, ... of the board mounting member 13, respectively, so that the light source boards 19, 19, ... are attached to the board mounting member 13 side by side or spaced apart in the circumferential direction. This makes it possible to emit light from the light sources 20, 20, ... in all circumferential directions (radiation directions), improving the functionality of the aircraft lamp 1 when used as a marker light.

A flexible printed circuit board 21 is connected to the light source substrates 19, 19, ... (see Figures 4 to 6). The flexible printed circuit board 21 is composed of an attachment portion 21a extending in a predetermined direction, connection portions 21b, 21b, ... protruding from the attachment portion 21a in a direction perpendicular to the longitudinal direction of the attachment portion 21a, and a relay portion 21c protruding from the attachment portion 21a in the opposite direction to the protruding direction of the connection portion 21b. The connection portions 21b, 21b, ... are provided in the same number as the light source substrates 19, and are positioned at a distance in the longitudinal direction of the attachment portion 21a.

The flexible printed wiring board 21 has the relay portion 21c inserted from above into the wiring board insertion hole 14a formed in the annular portion 14 of the board mounting member 13, and the mounted portion 21a is attached to the lower end of the board mounting portion 15 of the board mounting member 13 by gluing or the like in a state in which it is bent into a substantially arc shape, and the connection portions 21b, 21b, ... are each joined to the lower end of the light source boards 19, 19, ... by soldering or the like. However, the mounted portion 21a may be attached to the board mounting portion 15 without using adhesive.

The board mounting member 13 has its board mounting portion 15 and mounting plate portion 16 inserted from below into the peripheral surface portion 6 of the lamp housing 2, and the annular portion 14 is attached to the inner protrusions 6a, 6a, ... by screwing or the like (see Figures 4 and 5). At this time, a second annular heat dissipation sheet 22 is interposed between the annular portion 14 and the inner protrusions 6a, 6a, ..., and the annular portion 14 is attached to the inner protrusions 6a, 6a, ... via the second heat dissipation sheet 22. When the board mounting member 13 is attached to the lamp housing 2, approximately the upper half of the board mounting portion 15 and the mounting plate portion 16 protrude upward from the lamp housing 2.

As described above, in the aircraft lighting device 1, the light source board 19 is attached to the board mounting surface 15a of the board mounting member 13 via the first heat dissipation sheet 18, and the annular portion 14 is attached to the inner protrusions 6a, 6a, ... via the second heat dissipation sheet 22. Therefore, heat generated in the light source board 19 and the light source 20 when the light source 20 is driven is transferred from the first heat dissipation sheet 18 to the board mounting member 13, and then from the board mounting member 13 to the lamp housing 2 and released from the lamp housing 2 to the outside, thereby suppressing the temperature rise of the light source board 19 and the light source 20, and ensuring a good on/off state of the light source 20.

A board mounting base 23 is disposed in the lamp chamber 5, and is attached to the board mounting member 13 from the opening 13a side by screws or the like. The board mounting base 23 is formed integrally from various parts of a metal material with high heat dissipation properties, such as aluminum. The board mounting base 23 has a substantially disk-shaped base portion 24 facing the vertical direction, and a member mounting portion 25 protruding upward from the base portion 24. The board mounting base 23 also functions as a heat sink as it is formed from a metal material with high heat dissipation properties.

A connector 26 is attached to the base portion 24, with a portion of the connector 26 inserted into the base portion 24 and a lower portion protruding downward from the base portion 24 (see Figures 3 to 5). A cable connected to a power supply circuit (not shown) arranged inside the aircraft body 101 is connected to the portion of the connector 26 protruding downward from the base portion 24 when the aircraft lamp 1 is attached to the fuselage 102. A screw hole 24a is formed in the base portion 24, penetrating vertically.

The member mounting portion 25 is formed in a generally rectangular, vertically elongated, generally flat plate shape, and is positioned between the connector 26 and the screw hole 24a (see Figures 4 and 5). The two largest surfaces of the member mounting portion 25 are formed as mounting surfaces 25a, 25a, each of which faces horizontally.

A control board 27 is attached to the board mounting base 23. The control board 27 is equipped with electronic components (not shown). The control board 27 has a function of controlling the on/off of the light sources 20, 20, ... mounted on the light source boards 19, 19, ..., and is divided into two boards, a first board 28 and a second board 29, which are connected by wiring. The control board 27 has the first board 28 attached to one mounting surface 25a and the second board 29 attached to the other mounting surface 25a. The control board 27 has the relay portion 21c of the flexible printed wiring board 21 connected to the first board 28, and the second board 29 connected to the connector 26 by a connection line 30.

In the aircraft lighting device 1, current is supplied from the power supply circuit to the second board 29 via the connector 26 and the connection line 30, and is then supplied from the second board 29 to the first board 28 via the flexible printed wiring board 21 and the light source boards 19, 19, ... to the light sources 20, 20, .... At this time, the first board 28 and the second board 29 control the turning on and off of the light sources 20, 20, .... In the aircraft lighting device 1, for example, turning on and off control is performed in which all the light sources 20, 20, ... are turned on or off simultaneously and flashed.

As described above, in the aircraft lighting device 1, the control board 27 has a first board 28 and a second board 29, and the first board 28 and the second board 29 are attached to both sides of the component mounting portion 25.

As a result, the control board 27 is divided into a first board 28 and a second board 29, both of which are attached to the component mounting portion 25, reducing the space required for arranging the control board 27 and enabling the aircraft lighting device 1 to be made more compact.

The aircraft lighting device 1 also includes a flexible printed circuit board 21 that connects the control board 27 to the multiple light source boards 19, 19, ..., and the flexible printed circuit board 21 has an attachment portion 21a that is attached to the outer circumferential surface of the board mounting member 13, and multiple connection portions 21b, 21b, ... that protrude from the attachment portion 21a and are connected to the light source boards 19, 19, ..., respectively.

Therefore, with the mounting portion 21a attached to the outer peripheral surface of the board mounting member 13, the multiple light source boards 19, 19, ... are connected to the control board 27 by one flexible printed wiring board 21, so that the multiple light source boards 19, 19, ... can be easily connected to the control board 27 while ensuring space saving.

In addition, since there is no need to connect the multiple light source boards 19, 19, ... and the control board 27 separately with connecting wires, the number of steps required for wiring work is reduced, improving workability and shortening work time.

Furthermore, since multiple connection lines are not required to connect the multiple light source boards 19, 19, ... and the control board 27, the space required for wiring is small, and the aircraft lighting device 1 can be made smaller.

An O-ring 31 made of rubber or the like is attached to the outer periphery of the base portion 24 of the board mounting base 23.

The board mounting base 23 is inserted into the peripheral surface 6 of the lamp housing 2 from below, and the upper surface of the base portion 24 is butted against the lower surface of the joining protrusions 17, 17, ... of the board mounting member 13. At this time, a cushion 32 is placed between the upper surface of the member mounting portion 25 of the board mounting base 23 and the lower surface of the mounting plate portion 16 of the board mounting member 13, and the member mounting portion 25 is pressed against the mounting plate portion 16 via the cushion 32. Therefore, the cushion 32 can prevent the board mounting base 23 from rattling relative to the board mounting member 13.

When the board mounting base 23 is inserted from below into the peripheral portion 6 of the lamp housing 2, the O-ring 31 attached to the base portion 24 is tightly attached to the inner peripheral surface of the peripheral portion 6. This provides waterproofing to the arrangement space 13b, which is the internal space in the board mounting member 13.

The base portion 24 of the board mounting base 23 is attached to the connecting protrusions 17, 17, ... by screwing or the like. When the board mounting base 23 is attached to the board mounting member 13, the control board 27 is positioned in the arrangement space 13b of the board mounting member 13.

As described above, the first board 28 and the second board 29 are attached to the mounting surfaces 25a, 25a of the member mounting portion 25, but they may also be attached to the mounting surfaces 25a, 25a via heat dissipation sheets. By attaching the first board 28 and the second board 29 to the mounting surfaces 25a, 25a via heat dissipation sheets, the heat generated when the first board 28 and the second board 29 are driven is transferred from the first board 28 and the second board 29 to the board mounting base 23, and from the board mounting base 23 to the lamp housing 2 via the board mounting member 13, and is released to the outside from the lamp housing 2. Therefore, the temperature rise of the first board 28 and the second board 29 is suppressed, and the good driving state of the first board 28 and the second board 29 can be ensured.

As described above, the board mounting member 13 and the board mounting base 23 are both formed as heat sinks from metal materials, so that heat generated on the light source board 19 is transferred to the board mounting member 13 formed as a heat sink, and heat generated on the control board 27 is transferred to the board mounting base 23 formed as a heat sink, enabling heat dissipation. Therefore, the temperature rise of the light source 20 mounted on the light source board 19 and the electronic components mounted on the control board 27 is suppressed, and a stable operating state of the light source 20 and the electronic components can be ensured.

When the board mounting base 23 is attached to the board mounting member 13, a control member 33 having a threaded portion is threaded into the threaded hole 24a formed in the base portion 24. The control member 33 contains a functional material that is permeable to air but not to moisture. Therefore, while the aircraft 100 is in flight, the control member 33 allows air to flow inside and outside the aircraft lighting device 1, suppressing fluctuations in internal pressure. In addition, the provision of the control member 33 prevents moisture from entering the interior of the aircraft lighting device 1 through the threaded hole 24a, protecting each part arranged in the lamp chamber 5.

An inner lens 34 is disposed in the lamp chamber 5, and the inner lens 34 is attached to the board mounting member 13 by means of screws or the like. The inner lens 34 is made of a transparent resin material with each part integrally formed.

The inner lens 34 has a generally disk-shaped blocking portion 35 that faces the vertical direction, a cover portion 36 whose upper end is connected to the outer periphery of the blocking portion 35, and a protruding portion 37 that protrudes outward from the lower end of the cover portion 36.

The blocking portion 35 has positioning holes 35a, 35a that penetrate vertically, and the positioning holes 35a, 35a are formed at positions approximately opposite each other across the center of the blocking portion 35.

The cover portion 36 is formed in a generally cylindrical shape that is one size larger than the board mounting portion 15 of the board mounting member 13, and its axial length is shorter than the axial length of the board mounting portion 15. The cover portion 36 is provided with control lens portions 38, 38, 38 in succession above and below. The control lens portion 38 is formed in a generally annular shape, and its longitudinal cross section is generally semicircular and convex outward.

The inner lens 34 is positioned on the board mounting member 13 by inserting the positioning pins 16a, 16a into the positioning holes 35a, 35a of the blocking portion 35. A screw hole (not shown) is formed in the mounting plate portion 16 of the board mounting member 13, and a screw insertion hole (not shown) is formed in the blocking portion 35 of the inner lens 34. With the inner lens 34 positioned on the board mounting member 13 as described above, the blocking portion 35 is attached to the mounting plate portion 16 by inserting a mounting screw (not shown) through the screw insertion hole and screwing it into the screw hole.

When the inner lens 34 is attached to the board mounting member 13, the control lens units 38, 38, 38 are positioned facing the light sources 20, 20, ... mounted on the light source boards 19, 19, ... (see Figure 5). That is, the upper control lens unit 38 is positioned facing the light sources 20, 20, ... positioned on the upper row, the middle control lens unit 38 is positioned facing the light sources 20, 20, ... positioned on the middle row, and the lower control lens unit 38 is positioned facing the light sources 20, 20, ... positioned on the lower row.

Therefore, the light emitted from the light sources 20, 20, ... located in the upper row is controlled by the control lens unit 38 of the upper row, passes through the cover 3 and is irradiated to the outside, the light emitted from the light sources 20, 20, ... located in the middle row is controlled by the control lens unit 38 of the middle row, passes through the cover 3 and is irradiated to the outside, and the light emitted from the light sources 20, 20, ... located in the lower row is controlled by the control lens unit 38 of the lower row, passes through the cover 3 and is irradiated to the outside.

As described above, when the inner lens 34 is attached to the board mounting member 13, the protrusion 37 engages with the receiving portion 7a of the flange portion 7 in the lamp housing 2, ensuring a stable positioning of the inner lens 34 in the lamp chamber 5.

As described above, in the aircraft lighting device 1, the board mounting base 23 is attached to the board mounting member 13 from the opening 13a side, and when the board mounting base 23 is attached to the board mounting member 13, the control board 27 is positioned in the arrangement space 13b.

Therefore, the board mounting member 13 and the board mounting base 23 are arranged in the lamp chamber 5 formed by combining the lamp housing 2 and the cover 3, and the control board 27 is positioned in the arrangement space 13b when the board mounting base 23 is attached to the board mounting member 13. As a result, since the control board 27 is positioned in the arrangement space 13b, which is the inner space of the lamp chamber 5 having a double structure, moisture is less likely to adhere to the control board 27 even if moisture unintentionally enters the lamp chamber 5 due to large fluctuations in the flight environment such as changes in air pressure and temperature during the flight of the aircraft 100, and the control board 27 is protected regardless of the fluctuations in the flight environment of the aircraft 100, and adhesion of moisture to the control board 27 can be prevented. In addition, in the aircraft lamp 1, a silicone agent or the like is filled between the positioning hole 35a of the inner lens 34 and the positioning pin 16a of the board mounting member 13, between the protruding portion 37 of the inner lens 34 and the receiving portion 7a of the lamp housing 2, and between the control member 33 and the screw hole 24a of the board mounting base 23 to waterproof the arrangement space 13b.

In addition, when the aircraft lighting device 1 is attached to the fuselage 102 or the like, the first board 28 and the second board 29 of the control board 27 are both oriented in a direction other than the vertical (up-down direction), for example, in the horizontal direction. Therefore, even if the water vapor present inside the aircraft lighting device 1 turns into water droplets and adheres to the first board 28 or the second board 29 due to changes in air pressure or temperature while the aircraft 100 is flying, the water droplets will flow down from the first board 28 and the second board 29, preventing the moisture from adhering to the first board 28 and the second board 29, and ensuring a stable operating state of the control board 27.

Furthermore, in the aircraft lighting device 1, the board mounting portion 15 of the board mounting member 13 is formed in a cylindrical shape.

As a result, the light source boards 19, 19, ... are attached to the cylindrical board attachment portion 15 in a line or spaced apart in the circumferential direction, making it possible to emit light from the light sources 20, 20, ... all around, ensuring high visibility of the aircraft lighting device 1 and improving the functionality of the aircraft lighting device 1.

Furthermore, the inner lens 34 is provided with a blocking portion 35 that blocks one axial end of the cover portion 36, and the board mounting member 13 is provided with a mounting plate portion 16 that blocks one axial end of the board mounting portion 15, and the blocking portion 35 is attached to the mounting plate portion 16 when the board mounting portion 15 is positioned inside the cover portion 36.

Therefore, by attaching the blocking portion 35 to the mounting plate portion 16, the positioning of the light source board 19 relative to the inner lens 34 and the connection between the inner lens 34 and the board mounting member 13 are performed, so that the various parts of the aircraft lighting device 1 can be easily assembled with high precision.

In addition, a board mounting base 23 is provided, on which a control board 27 is attached, and which is disposed in the lamp chamber 5, and the control board 27 is positioned inside the board mounting member 13.

As a result, the control board 27 attached to the board mounting base 23 is positioned inside the board mounting member 13, and the light source board 19 attached to the board mounting member 13 is positioned inside the inner lens 34, so that the light source board 19 and the control board 27 are positioned inside the inner lens 34, and the aircraft lighting fixture 1 can be made smaller by improving space efficiency.

1...aircraft lighting fixture, 2...lamp housing, 3...cover, 4...lamp outer casing, 5...lamp chamber, 13...board mounting member, 13a...opening, 13b...arrangement space, 19...light source board, 20...light source, 21...flexible printed wiring board, 21a...mounted portion, 21b...connection portion, 23...board mounting base, 24...base portion, 25...component mounting portion, 27...control board, 28...first board, 29...second board

Claims (3)

a lamp housing and a cover that are joined together to form a lamp chamber therein;
a board mounting member having an opening at one end, an internal space being formed as an arrangement space, and the board mounting member being disposed in the lamp chamber;
a light source substrate attached to an outer peripheral surface of the substrate mounting member and having a light source mounted thereon;
A control board for controlling the turning on and off of the light source;
a board mounting base disposed in the lamp chamber and on which the control board is mounted;
the board mounting base is attached to the board mounting member from the opening side, and the control board is positioned in the arrangement space in a state where the board mounting base is attached to the board mounting member ;
A plurality of the light source substrates are provided,
A plurality of the light source boards are attached to the board attachment member in a circumferential direction, side by side or spaced apart from each other,
a flexible printed wiring board is provided to connect the control board and the plurality of light source boards;
The flexible printed wiring board has a mounting portion that is mounted on an outer peripheral surface of the board mounting member, and a plurality of connection portions that protrude from the mounting portion and are connected to the plurality of light source boards, respectively.
Aircraft lighting fixtures. a lamp housing and a cover that are joined together to form a lamp chamber therein;
a board mounting member having an opening at one end, an internal space being formed as an arrangement space, and the board mounting member being disposed in the lamp chamber;
a light source substrate attached to an outer peripheral surface of the substrate mounting member and having a light source mounted thereon;
A control board for controlling the turning on and off of the light source;
a board mounting base disposed in the lamp chamber and on which the control board is mounted;
the board mounting base is attached to the board mounting member from the opening side, and the control board is positioned in the arrangement space in a state where the board mounting base is attached to the board mounting member;
the board mounting base is provided with a base portion to be attached to the board mounting member and a member mounting portion protruding from the base portion;
the control board has a first board and a second board;
The first substrate and the second substrate are attached to both sides of the member attachment portion.
Aircraft lighting fixtures. The board mounting member and the board mounting base are both formed as heat sinks using a metal material.
3. An aircraft lighting device according to claim 1 or 2 .

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