Aircraft lighting

Abstract

An aircraft lamp comprises: a lamp housing, which is composed of a lamp housing with an opening and a cover installed on the lamp housing in a state of closing the opening, the internal space of the lamp housing forming a first configuration space; and a lamp unit, which has a light source assembly provided with a light source, a mounting base on which the light source assembly is mounted, and a power receiving connector mounted on the mounting base and used for supplying power to the light source, the lamp unit being loadable and detachable relative to the lamp housing, a through hole connected to the first configuration space being formed in the lamp housing, and a configuration shell portion being provided in the lamp housing, the configuration shell portion having a second configuration space opening on the outer surface side of the lamp housing.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft lamps that are mounted on a fuselage of an aircraft and used. Background Art

[0002] Some aircraft lamps include a lamp housing including a cover and a lamp housing, and a lamp unit that radiates light emitted from a light source to the outside (for example, see Patent Documents 1 and 2).

[0003] There are various types of such aircraft lamps depending on their intended use. For example, there are anti-collision lights for preventing collisions between aircraft, aviation lights for indicating the flight posture and direction of the aircraft, landing lights for illuminating the taxiway during takeoff and landing, and identification lights for illuminating the logo of the airline company etc. recorded on the aircraft as external lighting.

[0004] Prior art literature

[0005] Patent Literature

[0006] Patent Document 1: Japanese Patent Application Publication No. 2010-33840

[0007] Patent Document 2: Japanese Patent Application Publication No. 2010-33841

[0008] Technical problem to be solved by the invention

[0009] In such aircraft lamps, it is desired to ensure a stable driving state of the light source and ensure a good lighting state of the light irradiated from the lamp unit. However, if a malfunction occurs in various parts of the lamp unit, it may not be possible to ensure a good driving state of the light source, and it is necessary to improve the maintainability of the lamp unit. Summary of the invention

[0010] Therefore, an object of the aircraft lamp of the present invention is to improve the maintainability of the lamp unit and to ensure a good lighting state of the light irradiated from the lamp unit.

[0011] In a first embodiment, an aircraft lamp of the present invention comprises: a lamp housing, the lamp housing being composed of a lamp housing having an opening and a cover mounted on the lamp housing in a state of closing the opening, the interior space of the lamp housing forming a first configuration space; and a lamp unit, the lamp unit comprising a light source assembly provided with a light source, a mounting base on which the light source assembly is mounted, and a power receiving connector mounted on the mounting base and used at least for supplying power to the light source, the lamp unit being loadable and detachable relative to the lamp housing, a through hole communicating with the first configuration space being formed in the lamp housing, a configuration housing portion being provided in the lamp housing, the configuration housing portion having a second configuration space opening on an outer surface side of the lamp housing, at least a portion of the light source assembly being arranged in the first configuration space in a state of being inserted in the through hole, and the power receiving connector being arranged in the second configuration space.

[0012] Thus, the lamp unit including the light source assembly, the mounting base, and the power receiving connector can be attached to and detached from the lamp housing from the outer surface side of the lamp housing.

[0013] In the second embodiment, in the above-mentioned aircraft lamp of the present invention, a substrate storage portion having a configuration recess and a shielding cover portion closing the configuration recess are preferably provided on the mounting base, a control substrate for controlling the lighting and extinguishing of the light source is arranged in the configuration recess, and the power receiving connector is installed on the surface of the shielding cover portion on the opposite side of the configuration recess.

[0014] Thus, the power receiving connector and the control board are located on opposite sides with the shielding cover portion interposed therebetween, and therefore the power receiving connector and the control board do not interfere with each other.

[0015] In a third embodiment, in the above-mentioned aircraft lamp of the present invention, preferably, the mounting base is provided with an inclined surface portion inclined relative to the cover and a heat sink protruding from one surface in the thickness direction of the inclined surface portion, the light source assembly has a substrate carrying a plurality of the light sources, and the light source assembly is mounted on the other surface in the thickness direction of the inclined surface portion.

[0016] Thus, the substrate and the light source are arranged in a state of being inclined with respect to the cover, and the heat sink protrudes from the inclined surface portion to which the substrate is attached.

[0017] In a fourth aspect, in the aircraft lamp of the present invention described above, preferably, in a state where the lamp unit is mounted on the lamp housing, an outer peripheral portion of the mounting base is pressed toward the lamp housing by an annular heat conducting sheet.

[0018] Thus, heat generated in the lamp unit is released from the mounting base to the outside, and is transferred to the lamp housing via the heat conductive sheet and is further released from the lamp housing to the outside.

[0019] In the fifth embodiment, it is preferred that an anti-falling wire is provided in the above-mentioned aircraft lamp of the present invention, and when the lamp unit is removed from the lamp housing, the anti-falling wire prevents the lamp unit from falling off from the lamp housing, and the two ends of the anti-falling wire are respectively installed on the outer surface of the lamp housing and the outer surface of the lamp unit.

[0020] As a result, the power receiving connector and the anti-drop wire will not interfere with each other.

[0021] In the sixth aspect, another aircraft lamp of the present invention comprises: a lamp housing, which is composed of a lamp housing with an opening and a cover installed on the lamp housing in a state of closing the opening, and the internal space of the lamp housing is formed as a configuration space; and a lamp unit, which has a light source assembly provided with a light source, a mounting base on which the light source assembly is mounted, a power receiving connector installed on the mounting base and at least used for supplying power to the light source, and a control substrate installed on the mounting base and controlling the lighting and extinguishing of the light source, and the lamp unit can be loaded and unloaded relative to the lamp housing via the opening.

[0022] Thus, by removing the cover from the lamp housing, the lamp unit including the light source assembly, the mounting base, the power receiving connector, and the control substrate can be attached to and detached from the lamp housing.

[0023] In a seventh aspect, in the above-mentioned other aircraft lighting device of the present invention, it is preferable that the connecting connector is attachable to and detachable from the power receiving connector, and the attaching and detaching direction of the connecting connector from the power receiving connector is along the direction in which the light source unit moves.

[0024] Thus, during the operation of attaching and detaching the connecting connector to and from the power receiving connector, the connecting connector and the light source unit do not interfere with each other.

[0025] In an eighth aspect, in the above-mentioned other aircraft lamp of the present invention, preferably, a heat sink is provided on the mounting base, and heat generated in the light source unit and heat generated in the control substrate are radiated from the mounting base.

[0026] Thus, the heat generated in the light source unit and the heat generated in the control substrate are both released from the heat sink of the mounting base, so that no separate components are required for separately releasing the heat generated in the light source unit and the heat generated in the control substrate.

[0027] In the ninth mode, preferably in the above-mentioned other aircraft lamps of the present invention, the mounting base is formed with an outer peripheral surface opposite to the inner peripheral surface of the lamp housing and a mounting portion located on the inner side of the outer peripheral surface and mounted with the light source assembly, and the aircraft lamp is provided with an anti-falling wire, which prevents the cover from falling off from the lamp housing when the cover is removed from the lamp housing, and is located between the inner peripheral surface and the outer peripheral surface when the lamp unit is mounted on the lamp housing.

[0028] Thus, the light irradiated from the light source assembly will not be blocked by the anti-falling wire.

[0029] In the tenth embodiment, preferably, in the above-mentioned other aircraft lamps of the present invention, a part of the configuration space is a light path space, which becomes the path of the light irradiated from the light source assembly, and at least a part of the space for inserting a finger when loading and unloading the lamp unit relative to the lamp housing is consistent with the light path space.

[0030] This eliminates the need to additionally form a light path space serving as a path for light emitted from the light source unit and a work space for inserting fingers when attaching or detaching the lamp unit to or from the lamp housing.

[0031] Effects of the Invention

[0032] According to the present invention, a lamp unit having a light source assembly, a mounting base and a power receiving connector can be loaded and unloaded relative to the lamp housing from the outer surface side of the lamp housing. Therefore, the lamp unit can be removed from the lamp housing without removing the lamp housing and the cover from the aircraft, which can improve the maintainability of the lamp unit and ensure a good lighting condition of the light irradiated from the lamp unit. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 and Figures 2 to 6 This figure is a perspective view showing a part of an aircraft, together with a first embodiment of the aircraft lighting device according to the present invention.

[0034] Figure 2 It is a three-dimensional diagram of a lighting fixture for aircraft.

[0035] Figure 3 It is an exploded perspective view of an aircraft lamp.

[0036] Figure 4 It is a cross-sectional view of an aircraft lamp.

[0037] Figure 5 It is a three-dimensional diagram of the lamp unit.

[0038] Figure 6 So from Figure 2The perspective views of the aircraft lighting fixture are shown in different directions.

[0039] Figure 7 and Figures 8 to 11 The second embodiment of the aircraft lighting device according to the present invention is also shown. This figure is a perspective view showing an aircraft.

[0040] Figure 8 It is an exploded perspective view of an aircraft lamp.

[0041] Fig. 9 This is a perspective view of the aircraft lamp with the cover removed.

[0042] Fig.10 It is a cross-sectional view of an aircraft lamp.

[0043] Fig.11 It is a three-dimensional diagram of the lamp unit. DETAILED DESCRIPTION

[0044] Hereinafter, a mode for implementing the aircraft lamp of the present invention will be described with reference to the drawings.

[0045] <Aircraft lighting device according to the first embodiment>

[0046] First, the aircraft lighting device 1 according to the first embodiment will be described.

[0047] Hereinafter, an example is shown in which the aircraft lamp 1 of the present invention is applied to a marker light mounted on a horizontal tail as external lighting. However, the application scope of the present invention is not limited to marker lights, and can also be applied to other external lighting used in aircraft.

[0048] The lamp housing of the aircraft lamp 1 is composed of a lamp housing and a cover. In the following description, the direction of the lamp housing and the cover is set as the up-down direction, the cover is set as the top, and the lamp housing is set as the bottom, indicating the front-back, top-bottom, left-right directions. In addition, the aircraft lamp 1 is installed on the upper surface side of the horizontal tail, and the left-right direction is indicated by the vertical tail side as the inner side of the left-right direction and the top side of the horizontal tail as the outer side.

[0049] In addition, the front, back, up, down, left, and right directions shown below are for convenience of description, and the implementation of the present invention is not limited to these directions.

[0050] The aircraft lamp 1 is used as an external lighting, such as a logo lamp, and is installed on the fuselage of the aircraft 100, such as the horizontal tail 200 and 200 on both sides of the rear side, and has the function of illuminating the logo not shown attached to the vertical tail 300 (see Figure 1). Therefore, the light emitted from one aircraft lamp 1 is irradiated to one of the left and right surfaces of the vertical tail 300, and the light emitted from the other aircraft lamp 1 is irradiated to the other of the left and right surfaces of the vertical tail 300, and the left and right surfaces of the vertical tail 300 are irradiated surfaces 301, 301, respectively. A configuration recessed portion (not shown) that opens upward is formed in the horizontal tail 200.

[0051] The aircraft lamp 1 comprises: a lamp housing 2 having an opening at the upper end; and a cover 3 mounted on the lamp housing 2 in a state of closing the opening of the lamp housing 2 (see Figures 2 to 4 The lamp housing 2 and the cover 3 form a lamp housing 4 , and the inner space of the lamp housing 4 forms a first configuration space 5 .

[0052] The lamp housing 2 is formed integrally with each other using a metal material such as aluminum (see Figure 3 and Figure 4 The lamp housing 2 includes a bottom portion 6 facing in the vertical direction, a peripheral portion 7 protruding upward from the outer periphery of the bottom portion 6 except for a part thereof, and mounting pieces 8, 8, ... protruding outward from the upper end of the peripheral portion 7.

[0053] The lamp housing 2 is provided with a configuration housing portion 9 protruding upward relative to the bottom portion 6. The lower edge of one end portion of the configuration housing portion 9 in the left-right direction is continuous with the outer end edge in the left-right direction of the bottom portion 6, forming a box shape opening downward. The lower end opening of the configuration housing portion 9 is formed as a plug-in port 9a. The internal space of the configuration housing portion 9 is formed as a second configuration space 10. The configuration housing portion 9 is formed with a cable insertion hole 9b that connects the first configuration space 5 and the second configuration space 10.

[0054] The lamp housing 2 is provided with a hole forming portion 11, the lower end of which is continuous with the bottom surface portion 6 and inclined relative to the bottom surface portion 6. The hole forming portion 11 is inclined toward the outside in the left-right direction as it goes upward, and is located outside the configuration housing portion 9 in the left-right direction. The hole forming portion 11 is formed with an insertion hole 11a that connects the outside of the lamp housing 2 and the first configuration space 5. The insertion hole 11a is formed in a substantially rectangular shape, for example, in a portion of the hole forming portion 11 excluding the front and rear ends and the upper end.

[0055] The lamp housing 2 is provided with a mounting surface portion 12 which is continuous with the upper end portion of the hole forming portion 11 and faces in the up-down direction. The mounting surface portion 12 is located near the upper end of the peripheral surface portion 7 .

[0056] The connector 13 is installed in a through-state at the inner portion in the left-right direction of the peripheral surface portion 7. The connector 13 has a portion located on the outer surface side of the peripheral surface portion 7 and a portion located on the inner surface side of the peripheral surface portion 7. The portion located on the outer surface side of the peripheral surface portion 7 is connected to a power supply circuit (not shown) of the aircraft 100 via a connecting cord (not shown).

[0057] The cover 3 is formed in a flat plate shape and has a holding plate portion 14 formed of a metal material in a rectangular shape and a transparent cover portion 15 formed of a transparent material. The holding plate portion 14 is formed with a mounting hole 14a extending vertically therethrough, and the outer periphery of the transparent cover portion 15 is mounted on the opening edge of the mounting hole 14a.

[0058] The cover 3 is screwed to the mounting pieces 8, 8, ... of the lamp housing 2 via a gasket 16 having substantially the same size and shape as the upper end of the lamp housing 2. The gasket 16 is made of, for example, silicon material and has the function of ensuring airtightness between the lamp housing 2 and the cover 3.

[0059] In the aircraft lamp 1 , when the cover 3 is attached to the lamp housing 2 , the outer peripheral portion of the holding plate portion 14 of the cover 3 is fixed to the horizontal tail 200 by screwing or the like and is arranged in an arrangement recess formed in the horizontal tail 200 .

[0060] The lamp unit 17 can be attached to and detached from the lamp housing 2 (see Figure 3 and Figure 4 The lamp unit 17 includes a mounting base 18, a light source assembly 19, a control substrate 20, and a power receiving connector 21 (see Figures 3 to 6 ).

[0061] The mounting base 18 includes a main body 22 formed of a metal material such as aluminum, and a shielding cover 23 mounted on the main body 22 .

[0062] The main body 22 includes a board storage portion 24 formed in a box shape opening upward, an inclined surface portion 25 inclined with respect to the board storage portion 24 , and a mounted portion 26 continuous with an upper end portion of the inclined surface portion 25 .

[0063] The substrate storage portion 24 includes a bottom wall portion 27 that is substantially flat and faces the up-down direction, a peripheral wall portion 28 that protrudes upward from the outer peripheral portion of the bottom wall portion 27, and a flange portion 29 that protrudes outward from the upper end portion of the peripheral wall portion 28 except for a portion. The interior of the substrate storage portion 24 is formed so as to arrange a recessed portion 24a. Fin portions 30, 30, ... that protrude downward from the bottom wall portion 27 are arranged in a front-to-back arrangement in the substrate storage portion 24. Screw insertion holes 29a, 29a are formed in the flange portion 29 separated in the front-to-back direction.

[0064] The inclined surface portion 25 protrudes obliquely upward from the outer end portion in the left-right direction of the substrate storage portion 24, and the lower end portion is continuous with the upper end portion of the substrate storage portion 24. The inclined surface portion 25 is inclined in a state of being displaced outward in the left-right direction as it moves upward, and the inclined surface portion 25 is inclined relative to the cover 3 when the lamp unit 17 is mounted on the lamp housing 2. Heat sinks 31, 31, ... protruding obliquely downward from one surface 25a facing obliquely downward are arranged on the inclined surface portion 25 in a front-to-back manner.

[0065] Screw insertion holes 26 a , 26 a are formed in the mounted portion 26 so as to be separated front and rear.

[0066] The shield cover 23 is formed of, for example, a metal material in a flat plate shape facing the up-down direction. The shield cover 23 is attached to the substrate storage portion 24 by screwing or the like in a state of closing the arrangement recess 24a from above.

[0067] The light source unit 19 includes a substrate 32 on which a circuit pattern is formed, light sources 33 , 33 , . . . mounted on the substrate 32 , and an inner lens 34 for controlling light emitted from the light sources 33 , 33 , . . .

[0068] The substrate 32 is arranged on the other surface 25b of the inclined surface portion 25 in the mounting base 18 via a heat sink (not shown), and is mounted on the inclined surface portion 25 together with the inner lens 34 by screw fixing or the like. Therefore, the heat generated by the substrate 32 and the light sources 33, 33, ... is mainly transferred from the heat sink to the inclined surface portion 25, and is released from the heat sinks 31, 31, ... to the outside.

[0069] In this way, the heat generated by the substrate 32 and the light sources 33, 33, ... is transferred to the inclined surface 25 through the heat sink, thereby suppressing the temperature rise of the substrate 32 and the light sources 33, 33, ... and ensuring a good driving state of the substrate 32 and the light sources 33, 33, ...

[0070] For example, a light emitting diode (LED) is used as the light source 33. The light sources 33, 33, ... are regularly mounted on the substrate 32, for example, in a state of being separated at equal intervals in the front, back, left, and right directions.

[0071] The inner lens 34 is formed of a transparent resin or glass, and has a flat base surface 34a, and substantially hemispherical control lens portions 34b, 34b, ... protruding upward from the base surface 34a. The control lens portions 34b, 34b, ... are the same in number as the light sources 33, 33, ..., and are provided at positions corresponding to the light sources 33, 33, .... The control lens portions 34b, 34b, ... are, for example, convex lenses with free-form surfaces, and have the function of focusing and irradiating the light emitted from the light sources 33, 33, ..., respectively.

[0072] The inner lens 34 is arranged in a state where the base surface portion 34a and the control lens portions 34b, 34b, ... cover the substrate 32 and the light sources 33, 33, ... from above, and is attached to the inclined surface portion 25 by screw fixing or the like. Therefore, the substrate 32, the light sources 33, 33, ... and the inner lens 34 are arranged on the inclined surface portion 25.

[0073] As described above, since the substrate 32 on which the light sources 33 , 33 , . . . are mounted is disposed on the inclined surface portion 25 , the light emitted from the light sources 33 , 33 , . . . is irradiated from the light source unit 19 toward the oblique upper side.

[0074] As described above, the substrate 32 and the inner lens 34 of the light source unit 19 are mounted on the mounting base 18 by screwing or the like, and thus can be attached to and detached from the mounting base 18 .

[0075] Therefore, the light source assembly 19 can be replaced according to the model of the aircraft 100, and the light source assembly 19 corresponding to the different model of the aircraft 100 can be installed on the mounting base 18, thereby irradiating light according to the different model of the aircraft 100, and improving the versatility of the aircraft lamp 1.

[0076] The control substrate 20 has a function of controlling the lighting and extinguishing of the light sources 33, 33, ... in the light source assembly 19, and has a base substrate 20a facing the up and down direction, and electronic components 20b, 20b, ... mounted on the upper and lower surfaces of the base substrate 20a. The control substrate 20 is mounted on the shielding cover 23 via spacers 35, 35, ... by screw fixing or the like.

[0077] The control board 20 is located below the shielding cover 23. Therefore, when the shielding cover 23 is attached to the board storage portion 24, the control board 20 is arranged and stored in the arrangement recess 24a of the board storage portion 24 while being covered by the shielding cover 23 from above.

[0078] In this way, when the shield cover 23 is attached to the board storage portion 24 , the control board 20 is covered by the surface portions of the board storage portion 24 from directions other than above, and is also covered by the shield cover 23 from above.

[0079] Therefore, the control board 20 is housed inside the board housing portion 24 and covered by the board housing portion 24 and the shielding cover portion 23 , so that noise generated by the control board 20 is shielded by the board housing portion 24 and the shielding cover portion 23 .

[0080] A portion of the control board 20 contacts a portion of the board housing 24 via a heat transfer sheet (not shown). Therefore, the heat generated by the control board 20 is mainly transferred from the heat transfer sheet to the board housing 24, and the heat transferred to the board housing 24 is released to the outside from the fins 30, 30, ...

[0081] In this way, since the heat generated by the control substrate 20 is transferred to the substrate housing portion 24 via the heat transfer sheet, it is possible to suppress a temperature rise in the control substrate 20 and ensure a good driving state of the control substrate 20 .

[0082] The power receiving connector 21 is formed in a shape extending forward and backward, for example, and is attached to the upper surface of the shielding cover 23. One end of each of the first connection line 36 and the second connection line 37 is connected to the power receiving connector 21, the other end of the first connection line 36 is connected to the substrate 32, and the other end of the second connection line 37 is connected to the control substrate 20. One end of the third connection line 38 is connected to the power receiving connector 21, and the other end of the third connection line 38 is connected to the connector 13.

[0083] Therefore, the light sources 33, 33, ... are connected to the power circuit via the substrate 32, the first connection line 36, the power receiving connector 21, the third connection line 38 and the connector 13. In addition, the control substrate 20 is connected to the power circuit via the second connection line 37, the power receiving connector 21, the third connection line 38 and the connector 13.

[0084] The lamp unit 17 constructed as described above is mounted on the lamp housing 2 from below by mounting screws 50, 50, ... (see Figure 4 and Figure 6 ). The mounting screws 50, 50, ... are inserted from below into the screw insertion holes 26a, 26a, 29a, 29a formed in the mounting base 18, and are screwed into the bottom surface portion 6 and the mounting surface portion 12 of the lamp housing 2. Therefore, when the lamp unit 17 is mounted on the lamp housing 2, the substrate storage portion 24 and the shielding cover portion 23 of the main body 22 are located on the lower side of the bottom surface portion 6, the inclined surface portion 25 of the main body 22 is located on the lower side of the hole forming portion 11, the light source assembly 19 is inserted into the insertion hole 11a and arranged in the first arrangement space 5, and the mounted portion 26 of the main body 22 is located on the lower side of the mounting surface portion 12.

[0085] At this time, the power receiving connector 21 is arranged in the second arrangement space 10 formed in the arrangement case portion 9 of the lamp housing 2 via the insertion port 9a. Therefore, the third connection line 38 is inserted into the cable insertion hole 9b of the arrangement case portion 9, and the power receiving connector 21 and the connector 13 are connected.

[0086] When the lamp unit 17 is mounted on the lamp housing 2 from below, an annular heat conducting sheet 39 is arranged on the outer periphery of the mounting base 18 (see Figure 3 and Figure 4 ). Therefore, the mounting base 18 of the lamp unit 17 is pressed toward the lamp housing 2 from below via the heat conducting sheet 39 .

[0087] The heat conducting sheet 39 is formed into a shape corresponding to the outer peripheral portion of the upper surface of the mounting base 18 , and is arranged at a position straddling the substrate housing portion 24 , the inclined surface portion 25 , and the mounted portion 26 .

[0088] In this way, when the lamp unit 17 is installed in the lamp housing 2, the outer periphery of the mounting base 18 is pressed against the lamp housing 2 by the annular heat conductive sheet 39, so that the heat generated in the lamp unit 17 is released to the outside from the mounting base 18, and is transferred to the lamp housing 2 via the heat conductive sheet 39, and is also released to the outside from the lamp housing 2, which can effectively suppress the temperature rise of various parts in the lamp unit 17.

[0089] Furthermore, since the lamp unit 17 and the lamp housing 2 are in close contact with each other via the heat conductive sheet 39 , it is possible to improve the waterproof performance of the lamp unit 17 .

[0090] The lamp housing 2 and the lamp unit 17 are combined by the anti-drop wire 40. The two ends of the anti-drop wire 40 are installed on the outer surface of the lamp housing 2 and the outer surface of the lamp unit 17 by screw fixing, for example, the two ends are installed on the lower surface of the bottom portion 6 or the outer peripheral surface of the peripheral portion 7 in the lamp housing 2 and the lower surface or outer peripheral surface of the substrate storage portion 24 in the lamp unit 17.

[0091] In the aircraft lamp 1, the lamp unit 17 can be loaded and unloaded relative to the lamp housing 2. The lamp unit 17 can be removed from the lamp housing 2 by releasing the threaded state of the mounting screws 50, 50, ... relative to the lamp housing 2. However, when the lamp unit 17 is removed from the lamp housing 2, the lamp housing 2 and the lamp unit 17 are also connected by the anti-fall-off wire 40.

[0092] Therefore, the fall-off preventing wire 40 prevents the lamp unit 17 from falling when the lamp unit 17 is removed from the lamp housing 2 , thereby preventing the lamp unit 17 from being damaged or broken.

[0093] In addition, since the anti-drop wire 40 is located on the outer surface side of the lamp housing 2 and the lamp unit 17, the power receiving connector 21 will not interfere with the anti-drop wire 40. When the first connecting wire 36, the second connecting wire 37 and the third connecting wire 38 are connected to the power receiving connector 21, the anti-drop wire 40 will not become an obstacle, and the workability in the connection operation can be improved.

[0094] In addition, in the aircraft lamp 1, a washer (not shown) made of silicon or the like may be mounted on the screw shaft of the mounting screw 50 so that the mounting screw 50 will not fall off the lamp unit 17 when the lamp unit 17 is removed from the lamp housing 2.

[0095] In the aircraft lamp 1 constructed as described above, when light is emitted from the light sources 33, 33, ..., the emitted light is controlled by the control lens portions 34b, 34b, ... of the inner lens 34, respectively, and is irradiated onto the illuminated surface 301 of the vertical tail 300 to which the marking is attached.

[0096] As described above, in the aircraft lamp 1, the insertion hole 11a connected to the first configuration space 5 is formed in the lamp housing 2, and the configuration shell portion 9 is provided in the lamp housing 2. The configuration shell portion 9 has a second configuration space 10 opened on the outer surface side of the lamp housing 2, at least a portion of the light source assembly 19 is arranged in the first configuration space 5 in a state of being inserted through the insertion hole 11a, and a power receiving connector 21 is arranged in the second configuration space 10.

[0097] Therefore, the lamp unit 17 including the light source assembly 19, the mounting base 18, and the power receiving connector 21 can be attached to and detached from the lamp housing 2 from the outer surface side of the lamp housing 2. As a result, the lamp unit 17 can be removed from the lamp housing 2 without removing the lamp housing 2 and the cover 3 from the aircraft 100, and the maintainability of the lamp unit 17 can be improved, ensuring a good lighting state of the light irradiated from the lamp unit 17.

[0098] In addition, the mounting base 18 is provided with a substrate storage portion 24 having a configuration recess 24a and a shielding cover portion 23 that closes the configuration recess 24a. A control substrate 20 that controls the lighting and extinguishing of the light source 33 is arranged in the configuration recess 24a, and a power receiving connector 21 is mounted on the surface of the shielding cover portion 23 on the opposite side to the configuration recess 24a.

[0099] Therefore, the power receiving connector 21 and the control substrate 20 are located on opposite sides with the shield cover 23 interposed therebetween, so that the power receiving connector 21 and the control substrate 20 do not interfere with each other, and the control substrate 20 does not become an obstacle when the first connection line 36, the second connection line 37, and the third connection line 38 are connected to the power receiving connector 21, so that the workability in the connection operation can be improved, and miniaturization due to improved space efficiency can be achieved.

[0100] Furthermore, since the control board 20 is shielded by the shield cover 23 when the control board 20 is disposed in the disposition recess 24 a , it is possible to suppress the influence of noise generated by the control board 20 on various devices and instruments installed in the aircraft 100 .

[0101] In addition, an inclined surface portion 25 inclined relative to the cover 3 and heat sinks 31, 31, ... protruding from a surface 25a in the thickness direction of the inclined surface portion 25 are provided on the mounting base 18, and the light source assembly 19 has a substrate 32 carrying a plurality of light sources 33, which is mounted on another surface 25b in the thickness direction of the inclined surface portion 25.

[0102] Therefore, the substrate 32 and the light sources 33, 33, ... are arranged in a state inclined relative to the cover 3, and the heat sinks 31, 31, ... protrude from the inclined surface portion 25 on which the substrate 32 is mounted. Thus, the light emitted from the light sources 33, 33, ... can be easily irradiated in a direction inclined relative to the cover 3, and the heat generated by the substrate 32 and the light sources 33, 33, ... can be efficiently transferred to the heat sinks 31, 31, ...

[0103] In the above, an example is shown in which one light source unit 19 is provided in the lamp unit 17 , but the number of light source units 19 provided in the aircraft lamp 1 is not limited to one, and may be plural.

[0104] <Aircraft lighting device according to the second embodiment>

[0105] Next, an aircraft lighting device 51 according to a second embodiment will be described.

[0106] The following describes an example in which the aircraft lamp 51 of the present invention is applied to an ice detection lamp installed on an aircraft body as external lighting. However, the application scope of the present invention is not limited to ice detection lamps, and can also be applied to other external lighting such as identification lamps used in aircraft.

[0107] The aircraft lamp 51 is installed on the left and right side parts of the fuselage, for example, and the lamp housing is composed of a lamp housing and a cover. In the following description, the combination direction of the lamp housing and the cover is set as the left and right direction, the cover side is set as the outside of the side, and the lamp housing side is set as the inside of the side, indicating the front, back, up, down, left and right directions.

[0108] In addition, the front, back, up, down, left, and right directions shown below are for convenience of description, and the implementation of the present invention is not limited to these directions.

[0109] The aircraft lamp 51 is used as an external lighting, i.e., an ice detection lamp, and is respectively installed on the left and right side parts 101, 101 of the fuselage of the aircraft 100 (see Figure 7 The aircraft lighting device 51 is used to illuminate the main wings 400, 400 and the engines 500, 500 respectively mounted on the main wings 400, 400, and to check for adhesion of snow or ice to the engines 500, 500 and parts around the engines 500, 500.

[0110] The side surface portion 101 has a placement recessed portion (not shown) that opens laterally outward.

[0111] The aircraft lamp 51 includes a lamp housing 52 and a cover 53. The outer end of the lamp housing 52 is formed as an opening 52a, and the opening 52a is closed by the cover 53 (see FIG. Figures 8 to 10 The lamp housing 52 and the cover 53 constitute a lamp casing 54 , and an internal space of the lamp casing 54 is formed as a configuration space 55 .

[0112] The lamp housing 52 is integrally formed of metal materials such as aluminum. The lamp housing 52 has a bottom portion 56 facing the left and right direction, a peripheral portion 57 protruding laterally outward from the outer periphery of the bottom portion 56 , and a flange portion 58 extending from the top end of the peripheral portion 57 .

[0113] The lamp housing 52 has fastening projections 59 and 59 protruding laterally inward from the bottom surface 56 , and are separated from each other in the upper and lower parts. The fastening projections 59 and 59 are formed in a shape extending forward and backward. The inner surface of the peripheral surface 57 is formed as an inner peripheral surface 57a of the lamp housing 52 .

[0114] In the lamp housing 52, screw holes 52b, 52b, ... opened in the bottom portion 56 are formed in the portion from the bottom portion 56 to the fastening protrusions 59, 59, and two screw holes 52b, 52b, ... are formed separately on the left and right at positions corresponding to the fastening protrusions 59, 59.

[0115] The power supply terminal 60 is installed between the fastening protrusions 59, 59 in the bottom portion 56 in a penetrating state. The power supply terminal 60 has portions located inside and outside the lamp housing 52, and the portion located outside the lamp housing 52 is connected to a power supply circuit (not shown) of the aircraft 100 via a connecting cord (not shown).

[0116] One end of the power supply cord 61 is connected to a portion of the power supply terminal 60 that is located inside the lamp housing 52 . The other end of the power supply cord 61 is connected to a connection connector 62 .

[0117] The cover 53 includes a retaining ring 63 formed in an annular shape by a metal material such as aluminum, and a transparent cover portion 64 whose outer periphery is fixed to the inner periphery of the retaining ring 63. The cover 53 is coupled to the flange portion 58 of the lamp housing 52 by screw fixing or the like via a gasket 65 having the same size and shape as the outer periphery of the retaining ring 63. The gasket 65 is formed of, for example, a silicon material, and has a function of ensuring airtightness between the lamp housing 52 and the cover 53.

[0118] With the cover 53 and the flange 58 coupled together, the retainer 63 and the flange 58 are fixed to the side surface 101 of the aircraft 100 by screwing or the like, so that the aircraft lamp 51 is disposed in the placement recess formed in the side surface 101 .

[0119] The lamp unit 66 is attachable to and detachable from the lamp housing 52. The lamp unit 66 includes a mounting base 67, a light source unit 68, a control substrate 69, and a power receiving connector 70 (see Figures 8 to 11 ).

[0120] The mounting base 67 is formed of a metal material such as aluminum, and includes a board storage portion 71 formed in a box shape that is open to the side, and a component mounting portion 72 that protrudes to the side from the board storage portion 71 .

[0121] The substrate storage portion 71 includes a flat plate-shaped base portion 73 facing the left-right direction, and a peripheral wall portion 74 protruding laterally inward from the outer peripheral portion of the base portion 73. The interior of the substrate storage portion 71 is formed so as to be provided with a recessed portion 71a. The component mounting portion 72 protrudes from the base portion 73 except for a part thereof, and a portion of the base portion 73 on the rear side of the component mounting portion 72 is provided as a connector mounting plate portion 73a.

[0122] The mounting base 67 is provided with mounted pieces 75, 75, ... protruding from the inner side end of the lateral side of the peripheral wall portion 74 toward the outer surface. The mounted piece 75 is formed with a screw insertion hole 75a penetrating in the left-right direction.

[0123] The assembly mounting portion 72 protrudes outward from the base portion 73 to the side and is formed into a generally triangular prism shape whose front-to-rear width decreases as it moves outward to the side. The assembly mounting portion 72 is formed with a mounting portion 76 that is inclined obliquely to the rear side. The assembly mounting portion 72 is provided with a generally rectangular fin forming portion 77 that is continuous with the outer side edge of the mounting portion 76, and heat sinks 77a, 77a, ... are provided in the fin forming portion 77 separated from each other up and down (see FIG. 1 ). Fig.11 ) The outer surface of the fin forming portion 77 is a surface facing forward.

[0124] The outer peripheral surface 67a of the mounting base 67 is formed by the outer surface of the peripheral wall portion 74 and the outer surface of the fin forming portion 77. When the lamp unit 66 is arranged in the arrangement space 55, the outer peripheral surface 67a is arranged to face the inner peripheral surface 57a of the lamp housing 52.

[0125] The light source unit 68 includes a substrate 78 on which a circuit pattern is formed, light sources 79, 79, ... mounted on the substrate 78, and an inner lens 80 for controlling light emitted from the light sources 79, 79, ... (see FIG. 1 ). Figures 8 to 11 ).

[0126] As the light source 79 , for example, a light emitting diode (LED) is used. The light sources 79 , 79 , . . . are mounted on the substrate 78 in a regular pattern, for example.

[0127] The inner lens 80 is formed of a transparent resin or glass, and has a flat base surface 80a, and substantially hemispherical control lens portions 80b, 80b, ... protruding from the base surface 80a to the side opposite to the substrate 78. The control lens portions 80b, 80b, ... are the same in number as the light sources 79, 79, ..., and are provided at positions corresponding to the light sources 79, 79, .... The control lens portions 80b, 80b, ... are, for example, convex lenses with free-form surfaces, and have the function of controlling and illuminating the light emitted from the light sources 79, 79, ..., respectively.

[0128] The substrate 78 is disposed on the mounting portion 76 of the mounting base 67 via the heat sink 81, and the inner lens 80 is disposed on the mounting portion 76 via the spacer 82. The spacer 82 is formed in a ring shape slightly larger than the substrate 78 and the heat sink 81 and is located between the outer periphery of the base surface portion 80a and the mounting portion 76.

[0129] The inner lens 80 is arranged in a state where the base surface portion 80a and the control lens portions 80b, 80b, ... cover the substrate 78 and the light sources 79, 79, ... from the outside, and is mounted on the mounting portion 76 by screwing together with the substrate 78. The heat generated by the substrate 78 and the light sources 79, 79, ... is mainly transferred from the heat sink 81 to the mounting portion 76, and is released from the heat sinks 77a, 77a, ... to the outside.

[0130] In this way, since the heat generated by the substrate 78 and the light sources 79, 79, ... is transferred to the mounting portion 76 through the heat sink 81, the temperature rise of the substrate 78 and the light sources 79, 79, ... can be suppressed, thereby ensuring a good driving state of the substrate 78 and the light sources 79, 79, ...

[0131] As described above, since the substrate 78 on which the light sources 79 , 79 , . . . are mounted is arranged on the mounting portion 76 inclined obliquely to the rear side, the light emitted from the light sources 79 , 79 , . . . is irradiated obliquely to the rear side from the light source unit 68 .

[0132] Furthermore, as described above, the substrate 78 and the inner lens 80 are mounted on the mounting base 67 by screwing or the like, and therefore the light source unit 68 can be attached to and detached from the mounting base 67 .

[0133] Therefore, the light source assembly 68 can be replaced according to the model of the aircraft 100, and the light source assembly 68 corresponding to the aircraft 100 of different models can be installed on the mounting base 67, thereby irradiating light according to the aircraft 100 of different models, and improving the versatility of the aircraft lamp 51.

[0134] The control substrate 69 has a function of controlling the lighting and extinguishing of the light sources 79, 79, ... in the light source unit 68, and includes a base substrate 69a facing the front-back direction, and electronic components 69b, 69b, ... mounted on the left and right surfaces of the base substrate 69a. The control substrate 69 is mounted on the substrate storage portion 71 by screw fixing or the like in a state where the control substrate 69 is arranged in the arrangement recess 71a and stored in the substrate storage portion 71.

[0135] A portion of control board 69 contacts a portion of board housing 71 via a heat transfer sheet (not shown). Therefore, heat generated by control board 69 is mainly transferred from the heat transfer sheet to component mounting portion 72 via board housing 71 and released to the outside through heat sinks 77a, 77a, ...

[0136] In this way, the heat generated by the control substrate 69 is released from the heat dissipation fins 77 a , 77 a , . . . via the heat transfer sheet, so that the temperature rise of the control substrate 69 can be suppressed, and a good driving state of the control substrate 69 can be ensured.

[0137] As described above, the control board 69 is mounted on the mounting base 67 by screwing or the like, and thus can be attached to and detached from the mounting base 67 .

[0138] Therefore, the control board 69 can be replaced according to the model of the aircraft 100, and the control board 69 corresponding to the aircraft 100 of different models can be installed on the mounting base 67, thereby irradiating light according to the aircraft 100 of different models, and improving the versatility of the aircraft lamp 51.

[0139] The power receiving connector 70 is formed in a shape extending vertically, for example, and is mounted on the connector mounting plate portion 73a of the mounting base 67. The connecting connector 62 is attachable to and detachable from the power receiving connector 70 in the vertical direction. The attaching and detaching direction of the connecting connector 62 to the power receiving connector 70 is the vertical direction, which is the direction along which the light source unit 68 moves.

[0140] Therefore, the connection connector 62 is attached and detached relative to the power receiving connector 70 by moving along the light source unit 68, so the connection connector 62 does not interfere with the light source unit 68 during the attachment and detachment operation of the connection connector 62 relative to the power receiving connector 70. Thus, the workability during the attachment and detachment operation of the connection connector 62 relative to the power receiving connector 70 can be improved, and damage to the connection connector 62 and the light source unit 68 can be prevented.

[0141] One end of the first connection line 83 is connected to the power receiving connector 70, and the other end of the first connection line 83 is connected to the control board 69. In addition, the control board 69 and the board 78 of the light source unit 68 are connected by a second connection line 84.

[0142] Therefore, the light sources 79 , 79 , . . . are connected to the power circuit via the substrate 78 , the second connection line 84 , the control substrate 69 , the first connection line 83 , the power receiving connector 70 , the connection connector 62 , the power supply cord 61 , and the power supply terminal 60 .

[0143] In the lamp unit 66, the light source assembly 68 is located on the side of the control substrate 69, and the light source assembly 68 and the control substrate 69 are located on the left and right. Therefore, the configuration space of the light source assembly 68 and the control substrate 69 in the up-down direction and the front-back direction of the lamp unit 66 can be small, and the lamp unit 66 can be miniaturized.

[0144] In a state where the cover 53 is removed from the lamp housing 52, the lamp unit 66 constructed as described above is mounted to the lamp housing 52 through the opening 52a by means of mounting screws 90, 90, ... (see FIG. 1 ). Figures 8 to 10 The mounting screws 90, 90, ... are inserted into the screw insertion holes 75a, 75a, ... formed in the mounting pieces 75, 75, ... of the mounting base 67, and are screwed into the screw holes 52b, 52b, ... formed across the bottom surface 56 of the lamp housing 52 and the fastening protrusions 59, 59 to be mounted on the lamp housing 52.

[0145] When the lamp unit 66 is mounted on the lamp housing 52, the control substrate 69 stored in the substrate storage portion 71 is covered from the side by the bottom surface portion 56 of the lamp housing 52, and the control substrate 69 is shielded by the substrate storage portion 71 and the lamp housing 52. Therefore, it is possible to suppress the influence of noise generated by the control substrate 69 on various devices and instruments installed in the aircraft 100.

[0146] When the lamp unit 66 is mounted on the lamp housing 52, the lamp housing 52 and the cover 53 are connected by the anti-drop wire 85. The two ends of the anti-drop wire 85 are mounted on, for example, the inner surface of the bottom portion 56 in the lamp housing 52 and the inner surface of the retaining ring 63 in the cover 53. The anti-drop wire 85 is located between the inner circumferential surface 57a of the lamp housing 52 and the outer circumferential surface 67a of the lamp unit 66, and at least a part of it is located between the inner circumferential surface 57a of the lamp housing 52 and the fin forming portion 77 (refer to Fig.10 ).

[0147] In the aircraft lamp 51, the lamp unit 66 can be loaded and unloaded relative to the lamp housing 52. The lamp unit 66 can be removed from the lamp housing 52 by releasing the threaded state of the mounting screws 90, 90, ... relative to the screw holes 52b, 52b, ... of the lamp housing 52 when the cover 53 is removed from the lamp housing 52.

[0148] At this time, the lamp housing 52 and the cover 53 are connected by the anti-drop wire 85 (refer to Fig. 9 ), therefore, the anti-falling wire 85 prevents the cover 53 from falling when the cover 53 is removed from the lamp housing 52, thereby preventing the cover 53 from being damaged or broken.

[0149] In addition, the light source assembly 68 is mounted on the mounting portion 76 located on the inner side of the outer peripheral surface 67a of the lamp unit 66. When the lamp unit 66 is mounted on the lamp housing 52, the anti-drop wire 85 is located between the inner peripheral surface 57a of the lamp housing 52 and the outer peripheral surface 67a of the lamp unit 66 (see Fig.10 ).

[0150] Therefore, the light irradiated from the light source unit 68 is not blocked by the fall-off preventing wire 85 , and a good irradiation state of the light from the light source unit 68 can be ensured.

[0151] In particular, by positioning the anti-drop wire 85 between the inner peripheral surface 57 a of the lamp housing 52 and the fin forming portion 77 , the power receiving connector 70 and the anti-drop wire 85 are unlikely to interfere with each other, and the anti-drop wire 85 does not become an obstacle when the connecting connector 62 is mounted or removed relative to the power receiving connector 70 , thereby improving the workability of the connecting connector 62 relative to the power receiving connector 70 .

[0152] The anti-drop wire 85 has the following structure: the metal wire is covered with a resin tube, and the circular terminals provided at both ends electrically connect the guard ring 63 formed of a metal material and the lamp housing 52. In addition, the lamp housing 52 is electrically connected to a prescribed structural component provided in the aircraft, and is connected to the body of the aircraft through a ground wire. Therefore, in the event of a lightning strike near the cover 53, electricity can be released to the body of the aircraft via the anti-drop wire 85 and the lamp housing 52. Thus, the anti-drop wire 85 has the function of protecting the light sources 79, 79, ... of the light source assembly 68 and the electronic components 69b, 69b, ... of the control substrate 69 from the influence of surge voltage.

[0153] In the aircraft lamp 51 , a washer (not shown) made of silicon or the like may be installed on the screw shaft of the mounting screw 90 so that the mounting screw 90 will not fall off the lamp unit 66 when the lamp unit 66 is removed from the lamp housing 52 .

[0154] With such a structure, the mounting screw 90 does not fall from the lamp unit 66. Therefore, when the mounting screw 90 is released from the screw hole 52b, the mounting screw 90 and the lamp unit 66 do not fall from the lamp housing 52, thereby protecting the lamp unit 66. In addition, by removing the washer from the screw shaft of the mounting screw 90, the lamp unit 66 can be separated from the lamp housing 52 and removed.

[0155] When attaching and detaching the lamp unit 66 to and from the lamp housing 52, the operator inserts a jig such as a finger or a screwdriver into the placement space 55. Therefore, the placement space 55 also functions as a work space when attaching and detaching the lamp unit 66 to and from the lamp housing 52.

[0156] In the aircraft lamp 51 constructed as described above, when light is emitted from the light sources 79, 79, ..., the emitted light is controlled by the control lens portions 80b, 80b, ... of the inner lens 80, passes through a portion of the arrangement space 55 from the inner lens 80, and is transmitted through the transparent cover portion 64 of the cover 53 to illuminate the main wings 400, 400 and the engines 500, 500 respectively mounted on the main wings 400, 400 (see FIG. Figure 7 A portion of the configuration space 55 through which light emitted from the light sources 79, 79, ... passes is a light path space 55a, and at least a portion of the light path space 55a coincides with a working space when the lamp unit 66 is attached to and detached from the lamp housing 52.

[0157] By irradiating the main wings 400 , 400 and the engines 500 , 500 with light from the aircraft lighting device 51 , the operator of the aircraft 100 can visually check whether snow or ice is attached to the engines 500 , 500 and the surrounding parts of the engines 500 , 500 .

[0158] As described above, the aircraft lamp 51 includes: a lamp housing 54, which is composed of a lamp housing 52 and a cover 53, and the internal space is formed as a configuration space 55; and a lamp unit 66, which has a light source assembly 68, a mounting base 67, a power receiving connector 70 and a control substrate 69, and can be loaded and unloaded relative to the lamp housing 52 through the opening 52a.

[0159] Therefore, by removing the cover 53 from the lamp housing 52, the lamp unit 66 having the light source assembly 68, the mounting base 67, the power receiving connector 70 and the control substrate 69 can be loaded and unloaded relative to the lamp housing 52, thereby improving the maintainability of the lamp unit 66 and ensuring a good lighting state of the light irradiated from the lamp unit 66.

[0160] In addition, heat dissipation fins 77 a , 77 a , . . . are provided on the mounting base 67 , and heat generated in the light source unit 68 and heat generated in the control substrate 69 are dissipated from the mounting base 67 .

[0161] Therefore, the heat generated by the light source assembly 68 and the heat generated by the control substrate 69 are both released from the heat sinks 77a, 77a, ... of the mounting base 67. Therefore, there is no need for additional components for separately releasing the heat generated by the light source assembly 68 and the heat generated by the control substrate 69, thereby achieving an improvement in the heat dissipation efficiency while reducing the number of parts.

[0162] Furthermore, a portion of the configuration space 55 is an optical path space 55a that becomes a path of light emitted from the light source assembly 68 , and at least a portion of a working space, which is a space for inserting fingers when attaching or detaching the lamp unit 66 to or from the lamp housing 52 , coincides with the optical path space 55a .

[0163] Therefore, there is no need to form a separate optical path space 55a inside the lamp housing 52 that serves as a path for light emitted from the light source assembly 68 and a working space for inserting fingers when attaching or detaching the lamp unit 66 relative to the lamp housing 52, thereby miniaturizing the aircraft lamp 51.

[0164] In the above description, an example is shown in which one light source unit 68 is provided in the lamp unit 66 , but the number of light source units 68 provided in the aircraft lamp 51 is not limited to one, and may be plural.

[0165] Explanation of symbols

[0166] 1…aircraft lamp, 2…lamp housing, 3…cover, 4…lamp housing, 5…first configuration space, 9…configuration housing portion, 9b…cable insertion hole, 11a…insertion hole, 17…lamp unit, 18…mounting base, 19…light source assembly, 20…control board, 21…power receiving connector, 23…shielding cover portion, 24…board storage portion, 25…inclined surface portion, 25a…one surface, 25b…the other surface, 31…heat sink, 32…board, 33…light source, 39…heat conducting sheet , 40…anti-drop wire, 51…aircraft lamp, 52a…opening, 52…lamp housing, 53…cover, 54…lamp housing, 55…configuration space, 55a…light path space, 57a…inner circumference, 62…connecting connector, 66…lamp unit, 67…mounting base, 67a…outer circumference, 68…light source assembly, 69…control substrate, 70…power receiving connector, 76…mounting portion, 77a…heat sink, 79…light source, 85…anti-drop wire, 100…aircraft.

Claims

1. An aircraft lamp, characterized in that: have: A lamp housing, the lamp housing comprising a lamp housing having an opening and a cover mounted on the lamp housing in a state of closing the opening, wherein an inner space of the lamp housing forms a first configuration space; as well as A lamp unit, the lamp unit comprising a light source assembly provided with a light source, a mounting base on which the light source assembly is mounted, and a power receiving connector mounted on the mounting base and used at least to supply power to the light source, the lamp unit being attachable to and detachable from the lamp housing in a state where the light source assembly, the mounting base, and the power receiving connector are mounted to each other as an assembled body. The lamp housing has an insertion hole communicating with the first configuration space. The lamp housing is provided with a configuration housing portion having a second configuration space opened on the outer surface side of the lamp housing, At least a portion of the light source assembly is arranged in the first arrangement space in a state of being inserted into the insertion hole. The power receiving connector is arranged in the second arrangement space.

2. The aircraft lamp according to claim 1, characterized in that: The mounting base is provided with a substrate storage portion having a configuration recess and a shielding cover portion closing the configuration recess. A control substrate for controlling the lighting and extinguishing of the light source is arranged in the arrangement recess. The power receiving connector is mounted on a surface of the shielding cover on the opposite side from the placement recess.

3. The aircraft lamp according to claim 1, characterized in that: The mounting base is provided with an inclined surface portion inclined relative to the cover and a heat sink protruding from one surface in a thickness direction of the inclined surface portion. The light source unit includes a substrate on which the plurality of light sources are mounted, and is attached to the other surface in the thickness direction of the inclined surface portion.

4. The aircraft lamp according to claim 1, characterized in that: When the lamp unit is mounted on the lamp housing, the outer peripheral portion of the mounting base is pressed toward the lamp housing by the annular heat conducting sheet.

5. The aircraft lighting device according to any one of claims 1 to 4, wherein: The aircraft lamp is provided with an anti-drop wire, which prevents the lamp unit from dropping out of the lamp housing when the lamp unit is removed from the lamp housing. The two ends of the anti-falling wire are respectively installed on the outer surface of the lamp housing and the outer surface of the lamp unit.

6. An aircraft lamp, characterized in that: have: A lamp housing, the lamp housing comprising a lamp housing having an opening and a cover mounted on the lamp housing in a state of closing the opening, wherein an internal space of the lamp housing is formed as a configuration space; as well as A lamp unit, the lamp unit comprising a light source assembly provided with a light source, a mounting base on which the light source assembly is mounted, a power receiving connector mounted on the mounting base and used at least to supply power to the light source, and a control substrate mounted on the mounting base and controlling the lighting and extinguishing of the light source, the lamp unit being capable of being attached to and detached from the lamp housing via the opening in a state where the light source assembly, the mounting base, the power receiving connector and the control substrate are mounted to each other as an assembled body. The mounting base is formed with an outer peripheral surface opposite to the inner peripheral surface of the lamp housing and a mounting portion located inside the outer peripheral surface and mounted with the light source assembly. The aircraft lamp is provided with an anti-falling wire, which prevents the cover from falling off from the lamp housing when the cover is removed from the lamp housing. When the lamp unit is installed on the lamp housing, the anti-falling wire is located between the inner peripheral surface and the outer peripheral surface.

7. The aircraft lamp according to claim 6, characterized in that: The connecting connector can be attached to and detached from the power receiving connector. The attachment and detachment direction of the connecting connector relative to the power receiving connector is along the moving direction of the light source assembly.

8. The aircraft lamp according to claim 6, characterized in that: A heat sink is provided on the mounting base. Heat generated at the light source assembly and heat generated at the control substrate are released from the mounting base.

9. The aircraft lighting device according to any one of claims 6 to 8, characterized in that: A part of the configuration space is a light path space, and the light path space becomes a path of light emitted from the light source unit. At least a portion of a space into which a finger is inserted when attaching or detaching the lamp unit to or from the lamp housing coincides with the light path space.

Images