Aircraft light-emitting device and aircraft

Abstract

The aircraft comprises a main machine and a plurality of rotor wing rods connected to the main machine, the aircraft light-emitting device comprises a shell provided with an installation groove and a light-transmitting area, a light-emitting circuit board of a light-emitting assembly is arranged on a groove opening of the installation groove in a covering mode, and the light-emitting circuit board and the shell are enclosed to form a sealing cavity. The lamp beads are contained in the sealing cavity, light emitted by the lamp beads is transmitted outwards through the light-transmitting area, the heat dissipation piece is attached to the plate face of the side, away from the shell, of the light-emitting circuit board, the elastic buckle of the installation assembly is connected to the light-emitting circuit board and detachably buckled to the rotor wing rod, and the fastening piece is connected to the opening end of the elastic buckle. And the elastic buckle is fixed on the rotor wing rod. According to the aircraft light-emitting device, different aircraft light-emitting devices can be used in a matched mode according to different use scenes. Meanwhile, the endurance time of the aircraft can be greatly prolonged.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, and particularly relates to an aircraft lighting device and an aircraft. Background Art

[0002] With the progress of technology, unmanned aerial vehicles (UAVs) are widely used in people's lives and work. Currently, most existing UAVs are quad-rotor UAVs.

[0003] At present, UAVs can be used for photography, light shows, cruise indication, etc. In the above application scenarios, lights are an important part. However, most existing UAV lighting modules are integrated with the UAV. On the one hand, it uses the power of the whole machine itself, which affects the battery life. On the other hand, in different usage scenarios, the quantity and types of lights are different, and the existing integrated lighting modules cannot well meet the usage requirements of different application scenarios. Summary of the Utility Model

[0004] The main purpose of the utility model is to provide an aircraft lighting device, aiming to make it well applied to UAVs to meet the usage requirements of different scenarios while improving the battery life.

[0005] To achieve the above purpose, the aircraft lighting device proposed by the utility model is applied to an aircraft. The aircraft includes a main body and a plurality of rotor rods connected to the main body. The aircraft lighting device includes:

[0006] A housing, provided with a mounting groove and a light-transmitting area arranged on the housing;

[0007] A lighting assembly, including a lighting circuit board, a plurality of lamp beads and a power supply. The lighting circuit board covers the opening of the mounting groove and encloses a sealed cavity with the housing. The plurality of lamp beads and the power supply are electrically connected and installed on the lighting circuit board and are accommodated in the sealed cavity. The light emitted by the plurality of lamp beads is transmitted outwards through the light-transmitting area;

[0008] A heat dissipation plate, attached to the surface of the lighting circuit board facing away from the housing; and

[0009] A mounting assembly, including at least one elastic buckle and at least one fastener. The elastic buckle is connected to the lighting circuit board and detachably buckles on the rotor rod. The fastener is connected to the open end of the elastic buckle to fix the elastic buckle on the rotor rod.

[0010] In an optional embodiment, the fastener includes a fastening screw and a fastening nut. The elastic buckle is provided with two opposite through holes. The fastening screw passes through the two through holes, and the fastening nut is screwed onto the fastening screw.

[0011] In an alternative embodiment, the mounting assembly includes a plurality of the elastic clasps and a plurality of the fasteners. The plurality of elastic clasps are arranged at intervals along the length direction of the light-emitting circuit board, and one fastener is connected to one elastic clasp.

[0012] In an alternative embodiment, the light-emitting circuit board is provided with a plurality of mounting holes penetrating through its opposite two plate surfaces. The elastic clasp is provided with a connection hole, and a mounting screw passes through any one of the mounting holes and the connection hole to connect and fix the elastic clasp and the light-emitting circuit board.

[0013] In an alternative embodiment, the light-emitting assembly further includes a plurality of light guide covers. The light guide covers are arranged in the sealing cavity and are in a flared shape toward the side of the light-transmitting area. One light guide cover is disposed around the outside of one lamp bead.

[0014] In an alternative embodiment, the housing includes a middle frame, a plurality of light-transmitting plates, and a pressing plate. One light-transmitting plate covers the opening end of one light guide cover and is provided with the light-transmitting area. The pressing plate is detachably connected to the middle frame to press the plurality of light-transmitting plates on the surface of the light guide cover.

[0015] In an alternative embodiment, a plurality of positioning posts are convexly formed on the surface of the middle frame, and the pressing plate is provided with a plurality of positioning grooves. The pressing plate is connected to the middle frame, and one positioning post is received in one positioning groove.

[0016] In an alternative embodiment, the housing further includes a plurality of sealing rings. One sealing ring is disposed on the surface of one light-transmitting plate facing away from the light guide cover and is elastically abutted against the pressing plate.

[0017] In an alternative embodiment, the light-emitting assembly further includes a charging interface. The charging interface is mounted on the light-emitting circuit board and is electrically connected to the power source.

[0018] The present utility model further provides an aircraft, including a main body and an aircraft light-emitting device. The aircraft light-emitting device includes the aircraft light-emitting device as described above. The main body is provided with a plurality of rotor rods, and the aircraft light-emitting device is detachably connected to any one of the rotor rods.

[0019] The aircraft lighting device of the utility model is applied to an aircraft, which includes a mainframe and a plurality of rotor rods connected to the mainframe, the aircraft lighting device includes a shell provided with a mounting groove and a light-transmitting area, the light-emitting circuit board cover of the light-emitting assembly is arranged in the notch of the mounting groove, and is enclosed with the shell to form a sealed cavity, a plurality of lamp beads are contained in the sealed cavity, and the light emitted by them is transmitted outward from the light-transmitting area, the heat sink is attached to the plate surface of the light-emitting circuit board away from the shell, the elastic buckle of the mounting assembly is connected to the light-emitting circuit board, the elastic buckle is detachably fastened to the rotor rod, and the fastener is connected to the open end of the elastic buckle to fix the elastic buckle to the rotor rod. In the present application, the elastic buckle and the fastener cooperate to fix the shell more stably on the rotor rod of the unmanned aerial vehicle, so that different aircraft lighting devices can be used in combination according to different usage scenarios. At the same time, the power supply supplies power to the plurality of lamp beads, and the light emitted by the plurality of lamp beads is transmitted outward from the light-transmitting area, which can be used for light performances, fixed-point cruise indication, etc. Since the power supply of the aircraft is not occupied, the endurance time can also be greatly improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0021] Figure 1 This is a schematic structural diagram of an embodiment of the aircraft of the utility model;

[0022] Figure 2 for Figure 1 A schematic diagram of the structure of the light-emitting device of the aircraft;

[0023] Figure 3 for Figure 2 An exploded view of the structure of the aircraft lighting device shown;

[0024] Figure 4 for Figure 2 A top view of the aircraft lighting device shown;

[0025] Figure 5 for Figure 4 A cross-sectional view of an aircraft lighting device along AA is shown.

[0026] Description of Figure Numbers:

[0027]

[0028]

[0029] The realization of the purpose, functional features and advantages of the utility model will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0030] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0031] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back...) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0032] In addition, the descriptions of "first", "second", etc. in the present utility model are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the technical solutions between the various embodiments can be combined with each other, but they must be based on the ability of ordinary technicians in this field to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present utility model.

[0033] Reference Figures 1 to 5 The utility model provides an aircraft lighting device 100. The aircraft lighting device 100 is applied to an aircraft 1, and the aircraft 1 includes a main engine 200 and a plurality of rotor rods 210 connected to the main engine 200. The aircraft lighting device 100 includes: a housing 10, which is provided with a mounting groove and a light-transmitting area 10b arranged on the housing 10; a light-emitting component 20, which includes a light-emitting circuit board 21, a plurality of lamp beads 22 and a power source. The light-emitting circuit board 21 is covered in the notch of the mounting groove and enclosed with the housing 10 to form a sealed cavity 10a. The plurality of lamp beads 22 and the power source are electrically connected and installed. The light emitting circuit board 21 is arranged in the sealed cavity 10a, and the light emitted by the multiple lamp beads 22 is transmitted outward from the light-transmitting area 10b; the heat dissipation plate 30 is attached to the board surface of the light emitting circuit board 21 away from the shell 10; the mounting assembly includes at least one elastic buckle 41 and at least one fastener (not shown in the figure), the elastic buckle 41 is connected to the light emitting circuit board 21, and is detachably buckled to the rotor rod 210, and the fastener is connected to the open end of the elastic buckle 41 to fix the elastic buckle 41 to the rotor rod 210.

[0034] In this application, the elastic buckle 41 cooperates with the fastener, and the housing 10 can be firmly fixed on the rotor rod 210 of the unmanned aerial vehicle. Thus, different aircraft lighting devices 100 can be used according to different usage scenarios. At the same time, the power supply powers multiple lamp beads 22, and the light emitted by the multiple lamp beads 22 is transmitted outward through the light-transmitting area 10b, which can be used for light shows, fixed-point cruise indication, etc. Since it does not consume the power of the aircraft 1, the battery life can be greatly improved to a large extent.

[0035] It can be understood that in this application, the main body 200 of the aircraft 1 is a commercially available quadcopter unmanned aerial vehicle. The technical features and key points of the quadcopter unmanned aerial vehicle will not be elaborated here. By providing the elastic buckle 41 in this application, the aircraft lighting device 100 can be installed on any rotor rod 210 of the main body 200, so that the aircraft 1 can be made to suit different usage scenarios to a large extent.

[0036] Furthermore, in this application, the elastic buckle 41 can be made of silicone or rubber material, or silicone or rubber is coated on the outer side of a metal sheet metal part. The elastic buckle 41 has a certain elastic deformation and can adapt to aircraft 1 with different rod diameters. The fastener includes a fastening screw and a fastening nut. The elastic buckle 41 is provided with two oppositely arranged through holes 41a by a forming process. In practical applications, the elastic buckle 41 is buckled on the outer side of the rotor rod 210, the fastening screw passes through the two through holes 41a, and the fastening nut is screwed onto the fastening screw to fix the elastic buckle 41 and the rotor rod 210, so as to avoid the situation that the aircraft lighting device 100 falls during flight.

[0037] Even further, the installation assembly includes multiple elastic buckles 41 and multiple fasteners. The multiple elastic buckles 41 are arranged at intervals along the length direction of the light-emitting circuit board 21, and one fastener is connected to one elastic buckle 41. By providing multiple elastic buckles 41 and multiple fasteners, the connection between the aircraft lighting device 100 and the rotor rod 210 can be made more stable.

[0038] Please refer to again Figure 2 , in this embodiment, the housing 10 includes a middle frame 11, multiple light-transmitting plates 12 and a pressing plate 13. Among them, the middle frame 11 and the pressing plate 13 can be formed by metal or plastic materials, and the light-transmitting plate 12 can be a transparent glass plate or a plastic plate. The light-emitting assembly 20 includes a light-emitting circuit board 21, multiple lamp beads 22, a power supply and a light guide cover 23. The light-emitting circuit board 21 includes a printed circuit board (PCB) and multiple electronic components soldered on the surface of the board body. The multiple lamp beads 22 and the power supply are also soldered on the board surface of the PCB by a soldering process. A light guide cover 23 is disposed around the outside of one lamp bead 22 and has a flared shape facing the light-transmitting area 10b side, that is, the light guide cover 23 is in a conical shape.

[0039] In actual assembly, the pressing plate 13 and the light-emitting circuit board 21 are respectively connected to the opposite sides of the middle frame 11 by screws. The light guide cover 23 is disposed around the outside of the lamp beads 22. The light-transmitting plate 12 covers the opening on the side of the light guide cover 23 facing away from the light-emitting circuit board 21 and abuts against the pressing plate 13. A plurality of avoidance holes penetrating through the opposite two plate surfaces of the pressing plate 13 are formed on the surface of the pressing plate 13. The light-transmitting plate 12 is exposed through the avoidance holes, so that the light-transmitting plate 12 forms a light-transmitting area 10b. The pressing plate 13, the light-transmitting plate 12, the middle frame 11 and the light-emitting circuit board 21 enclose to form a sealed cavity 10a. A part of the light-emitting circuit board 21 extends out of the sealed cavity 10a, and a plurality of mounting holes 21a penetrating through the opposite two plate surfaces are formed by machining. The elastic buckle 41 is provided with a connection hole. The mounting screw passes through any one of the mounting holes 21a and the connection hole to connect and fix the elastic buckle 41 and the light-emitting circuit board 21. The structures of the housing 10 and the elastic buckle 41 of the present application are simple and convenient for production and manufacturing.

[0040] Further, a plurality of positioning posts 111 are convexly formed on the surface of the middle frame 11. The pressing plate 13 is provided with a plurality of positioning grooves. The pressing plate 13 is connected to the middle frame 11, and one positioning post 111 is accommodated in one positioning groove. By providing the positioning grooves and the positioning posts 111, the pre-positioning installation of the pressing plate 13 and the middle frame 11 is facilitated.

[0041] Further, the housing 10 further includes a plurality of sealing rings 14. One sealing ring 14 is disposed on the surface of one light-transmitting plate 12 facing away from the light guide cover 23 and elastically abuts against the pressing plate 13. Among them, the sealing ring 14 is made of silica gel material. By providing the sealing ring 14, impurities or moisture in the air can be prevented from entering the sealed cavity 10a through the gap between the light-transmitting plate 12 and the pressing plate 13, thereby improving the service life of the lamp beads 22 and the light-emitting circuit board 21.

[0042] Furthermore, the light-emitting assembly 20 further includes a charging interface (not shown in the figure). The type of the charging interface can be interfaces such as USB and Type-C. The charging interface is installed on the light-emitting circuit board 21 by soldering technology and is electrically connected to the power supply. The charging interface can be connected to an external circuit to charge the power supply.

[0043] The present utility model also proposes an aircraft 1. The aircraft 1 includes a main engine 200 and an aircraft light-emitting device 100. The specific structure of the aircraft light-emitting device 100 refers to the above embodiments. Since the aircraft 1 adopts all the technical solutions of the above all embodiments, it has at least all the beneficial effects brought by the technical solutions of the above embodiments, which will not be elaborated herein one by one.

[0044] The above are only the preferred embodiments of the present utility model, and thus do not limit the patent scope of the present utility model. Any equivalent structural transformation made under the inventive concept of the present utility model by using the content of the specification and drawings of the present utility model, or any direct / indirect application in other related technical fields is included in the patent protection scope of the present utility model.

Claims

1. An aircraft lighting device, applied to an aircraft, the aircraft comprising a main engine and a plurality of rotor rods connected to the main engine, characterized in that: The aircraft lighting device comprises: A housing having a mounting groove and a light-transmitting area disposed on the housing; A light-emitting component, comprising a light-emitting circuit board, a plurality of lamp beads and a power source, wherein the light-emitting circuit board is covered in a notch of the mounting slot and is enclosed with the housing to form a sealed cavity, the plurality of lamp beads and the power source are electrically connected and installed on the light-emitting circuit board and accommodated in the sealed cavity, and the light emitted by the plurality of lamp beads is transmitted outward from the light-transmitting area; a heat dissipation plate, attached to a board surface of the light-emitting circuit board that is away from the housing; and The mounting assembly includes at least one elastic buckle and at least one fastener. The elastic buckle is connected to the light-emitting circuit board and is detachably buckled to the rotor rod. The fastener is connected to the open end of the elastic buckle to fix the elastic buckle to the rotor rod.

2. The aircraft lighting device according to claim 1, characterized in that: The fastener comprises a fastening screw and a fastening nut, the elastic buckle is provided with two oppositely arranged through holes, the fastening screw is passed through the two through holes, and the fastening nut is screwed onto the fastening screw.

3. The aircraft lighting device according to claim 1, characterized in that: The installation assembly includes a plurality of the elastic buckles and a plurality of the fasteners. The plurality of the elastic buckles are arranged at intervals along the length direction of the light-emitting circuit board, and one of the fasteners is connected to one of the elastic buckles.

4. The aircraft lighting device according to claim 1, characterized in that: The light-emitting circuit board is provided with a plurality of mounting holes penetrating two opposite board surfaces thereof, the elastic buckle is provided with a connecting hole, and a mounting screw is passed through any of the mounting holes and the connecting hole to connect and fix the elastic buckle and the light-emitting circuit board.

5. The aircraft lighting device according to any one of claims 1 to 4, characterized in that: The light emitting assembly further comprises a plurality of light guide covers, which are arranged in the sealed cavity and are in a flared shape facing one side of the light-transmitting area. One of the light guide covers is arranged around the outer side of one of the lamp beads.

6. The aircraft lighting device as claimed in claim 5, characterized in that: The shell includes a middle frame, a plurality of light-transmitting plates and a pressure plate. One of the light-transmitting plates covers an open end of the light guide cover and is provided with the light-transmitting area. The pressure plate is detachably connected to the middle frame to press the plurality of light-transmitting plates onto the surface of the light guide cover.

7. The aircraft lighting device according to claim 6, characterized in that: A plurality of positioning posts are formed on the surface of the middle frame, and a plurality of positioning grooves are provided on the pressure plate. The pressure plate is connected to the middle frame, and one of the positioning posts is accommodated in one of the positioning grooves.

8. The aircraft lighting device according to claim 6, characterized in that: The housing further comprises a plurality of sealing rings, one of the sealing rings being arranged on a surface of the light-transmitting plate away from the light-guiding cover and elastically abutting against the pressing plate.

9. The aircraft lighting device according to any one of claims 1 to 4, characterized in that: The light emitting assembly further comprises a charging interface, which is mounted on the light emitting circuit board and electrically connected to the power source.

10. An aircraft, characterized in that: It comprises a main machine and an aircraft light-emitting device, wherein the aircraft light-emitting device comprises the aircraft light-emitting device as claimed in any one of claims 1 to 8, the main machine is provided with a plurality of rotor rods, and the aircraft light-emitting device is detachably connected to any of the rotor rods.

Images