Unmanned aerial vehicle lighting device

Abstract

The utility model discloses an unmanned aerial vehicle lighting device which comprises a lamp panel, a lamp panel mounting seat, a quick-change plug, a quick-change socket, a steering engine, a transmission shaft, a first bevel gear and a second bevel gear. The lamp panels are installed on the lamp panel installation base side by side, one side of the lamp panel installation base is fixedly connected with the quick-change plug, the quick-change plug can be locked to the quick-change socket, the quick-change socket is installed on the two sides of the rotating shaft, a second bevel gear is installed in the middle of the transmission shaft, and the second bevel gear is mechanically matched with the first bevel gear. The first bevel gear is driven by a steering engine to rotate. According to the utility model, the angle can be overturned by + / -45 degrees in the pitching direction of the overturning device, so that the directivity of the illuminating lamp is enhanced, and the illuminating range is expanded; and moreover, a quick release structure is arranged, so that the illuminating lamp can be quickly disassembled and assembled.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane and application field, especially, it is a kind of unmanned plane lighting device. BACKGROUND

[0002] Due to the different functions and purposes of unmanned plane, unmanned plane is often used as carrier, and different devices such as holder, loudspeaker and lighting lamp are mounted to expand the use function of unmanned plane, and the lighting of unmanned plane is used in natural disaster rescue and crowd behavior processing.

[0003] The existing unmanned plane lighting device is mostly fixed on the bottom of unmanned plane and vertically downward irradiation, and the angle of unmanned plane flight needs to be adjusted when the angle of lighting needs to be changed, which increases the energy consumption of unmanned plane and reduces the endurance of unmanned plane, and increases the operation difficulty of unmanned plane pilot. UTILITY MODEL CONTENT

[0004] The utility model aims at providing a kind of unmanned plane lighting device to solve the problems in the above background.

[0005] To achieve the above object, the utility model provides the following technical scheme: a kind of unmanned plane lighting device, including lighting lamp mechanism and control unit;The control unit includes angle overturning device, and the control unit is used to change the angle of lighting when needed.

[0006] Preferably, the lighting lamp mechanism includes light-transmitting mirror, lamp plate, lamp plate mounting seat, first control panel, second control panel, quick-change plug and cover plate;

[0007] The front of the lamp plate mounting seat is divided into left and right cavities, and the back is a large area of heat sink, which can dissipate a large amount of heat.

[0008] Four lamp plates are installed in the left cavity, and four light-transmitting mirrors are covered on the lamp plates to ensure sufficient brightness and irradiation distance of the lighting lamp. The first control panel and the second control panel are installed in the right cavity, and the first control panel and the second control panel are electrically connected with the lamp plates through the wiring slot and the wire hole of the left cavity of the mounting seat. The right cavity of the lamp plate mounting seat is provided with a sealing groove for installing waterproof strip, and the cover plate is used to press the waterproof strip to ensure the sealing and waterproof of the cavity.

[0009] Preferably, the quick-change plug is installed on the right side of the lamp plate mounting seat.

[0010] Preferably, the mounting assembly includes lighting upper shell, L bracket, aviation plug and lighting lower shell.

[0011] Preferably, the angle turning device comprises a rudder rear support, a rudder, a rudder control panel, a first bevel gear, a rudder front support, a limiting block, a bearing, an end cover, a second bevel gear, a transmission shaft, a transition shaft and a quick-change socket; the left and right sides of the lighting lower shell are provided with bearings, the bearings are limited in the axial position by the end cover, and the transmission shaft is arranged in the inner hole of the bearing; the transmission shaft is a circular rod on both sides and a D-shaped section rod in the middle, the quick-change socket is arranged on the left and right end faces, the second bevel gear and the limiting block are arranged in the middle, the limiting block is limited by the limiting boss corresponding to the position of the lighting lower shell; the second bevel gear is meshed with the first bevel gear, the first bevel gear is connected with the output shaft of the rudder through the transition shaft, and the transition shaft is a D-shaped section.

[0012] Preferably, the front and rear positions of the rudder are provided with the rudder rear support and the rudder front support, and are fixed on the lighting lower shell.

[0013] Preferably, four L-shaped supports are arranged around the lighting lower shell and are used for being linked with the bottom of the unmanned aerial vehicle, the lighting upper shell is arranged on the top, and the rudder control panel is arranged in the inside and is used for driving the rudder to rotate.

[0014] Compared with the prior art, the angle turning device can realize the turning of 45 degrees in the pitch direction, the directivity of the lighting lamp is strengthened, and the lighting range is enlarged; and the quick-disassembly structure is arranged, so that the lighting lamp can be quickly disassembled and assembled. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 It is the isometric view of the utility model;

[0016] Figure 2 It is the lighting lamp mechanism explosion schematic view of the utility model;

[0017] Figure 3 It is the control unit explosion schematic view of the utility model;

[0018] Figure 4 It is the lighting lower shell limiting boss schematic view of the utility model;

[0019] Figure 5 It is the lamp plate mounting seat schematic view of the utility model;

[0020] In the drawing:

[0021] 100 lighting lamp mechanism: 101 light transmission mirror, 102 lamp plate, 103 lamp plate mounting seat, 104 first control panel, 105 second control panel, 106 quick-change plug, 107 cover plate;

[0022] 200 control unit: 201 lighting upper shell, 202 L support, 203 aviation plug, 204 lighting lower shell, 2041 limit boss, 205 rudder rear support, 206 rudder, 207 rudder control panel, 208 first bevel gear, 209 rudder front support, 210 limit block, 211 bearing, 212 end cover, 213 second bevel gear, 214 transmission shaft, 215 transition shaft, 216 quick-change socket;

[0023] 3 wiring slot, 4 heat sink, 5 wire hole, 6 sealing strip mounting groove. DETAILED DESCRIPTION

[0024] The technical solutions in the embodiments of the utility model will be described clearly and completely below in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the utility model.

[0025] Please refer to Figures 1-5 The utility model provides a technical scheme:

[0026] A unmanned plane lighting device, including lighting lamp mechanism 100, control unit 200.

[0027] Lighting lamp mechanism 100 includes: light mirror 101, lamp plate 102, lamp plate mounting seat 103, first control panel 104, second control panel 105, quick-change plug 106, cover plate 107.

[0028] The front of lamp plate mounting seat 103 is divided into left and right cavities, and the back is a large-area heat sink 5, which can dissipate a large amount of heat. Four lamp plates 102 are installed in the left cavity, and four light mirrors 101 are covered on the lamp plates 102 to ensure sufficient brightness and irradiation distance of the lighting lamp. The first control panel 104 and the second control panel 105 are installed in the right cavity, and the first control panel 104 and the second control panel 105 are connected with the lamp plates 102 through the wiring slot 3 and the wire hole 6 of the left cavity of the mounting seat 103, and glue is applied on these slots and wire holes to ensure that the left and right cavities of the mounting seat 103 are separate spaces. The right cavity of the lamp plate mounting seat 103 has a sealing groove for installing a waterproof strip, and the cover plate 107 is used to press the waterproof strip to ensure the airtightness and waterproofness of the cavity.

[0029] The quick-change plug 106 is installed on the right side of the lamp plate mounting seat 103.

[0030] The control unit 200 comprises: a lighting upper shell 201, an L support 202, an aviation plug 203, a lighting lower shell 204, a rudder rear support 205, a rudder 206, a rudder control board 207, a first bevel gear 208, a rudder front support 209, a limiting block 210, a bearing 211, an end cover 212, a second bevel gear 213, a transmission shaft 214, a transition shaft 215 and a quick-change socket 216.

[0031] The bearing 211 is arranged on the left and right sides of the lighting lower shell 204, the bearing 211 is limited in the axial position by the end cover 212, and the transmission shaft 214 is arranged in the inner hole of the bearing 211.

[0032] The transmission shaft 214 is a circular rod on both sides and a D-shaped section rod in the middle, the quick-change socket 216 is arranged on the left and right end faces, the second bevel gear 213 and the limiting block 210 are arranged in the middle through a top screw, the limiting block 210 is limited in the rotating angle by the limiting boss 2041 corresponding to the position of the lighting lower shell 204.

[0033] The second bevel gear 213 is meshed with the first bevel gear 208, the first bevel gear 208 is connected with the output shaft of the rudder 206 through the transition shaft 215, and the transition shaft 215 is a D-shaped section.

[0034] The front and back positions of the rudder 206 are fixed on the lighting lower shell 204 through the rudder rear support 205 and the rudder front support 209.

[0035] The four L supports 202 are arranged around the lighting lower shell 204 and are used for being linked with the bottom of the unmanned aerial vehicle, the lighting upper shell 201 is arranged on the top, and the rudder control board 207 is arranged in the inside and is used for driving the rudder to rotate.

[0036] The utility model discloses a control unit 200 is used to control the turning angle of the lighting lamp mechanism 100, and the specific implementation is as follows: the rudder 206 is driven, the output shaft of the rudder 206 is connected with the transition shaft 215 to drive the first bevel gear 208, the first bevel gear 208 is meshed with the second bevel gear 213, the second bevel gear 213 drives the transmission shaft 214 to rotate, and the lighting lamp mechanism can realize the turning of positive and negative 45 degrees in the pitching direction.

[0037] Although the embodiments of the utility model have been shown and described above, it can be understood that the above-mentioned embodiments are exemplary, and cannot be understood as the limitation of the utility model, and the ordinary skilled in the art can change, modify, replace and transform the above-mentioned embodiments within the scope of the utility model.

Claims

1. A lighting device for unmanned aerial vehicles (UAVs), characterized in that: It includes a lighting mechanism (100) and a control unit (200); the control unit (200) includes an angle flipping device, which is used to change the lighting angle when needed; the lighting mechanism (100) includes a light-transmitting mirror (101), a lamp panel (102), a lamp panel mounting base (103), a first control board (104), a second control board (105), a quick-change plug (106), and a cover plate (107); The lamp panel mounting base (103) is divided into left and right cavities on the front and a large heat sink on the back, which can dissipate a large amount of heat. Four lamp panels (102) are installed in the left cavity, and four light-transmitting lenses (101) are covered on the lamp panels (102) to ensure sufficient brightness and illumination distance of the lighting lamps. A first control board (104) and a second control board (105) are installed in the right cavity. The first control board (104) and the second control board (105) are electrically connected to the lamp panels (102) through the wiring groove and wiring hole of the left cavity of the mounting base (103). The right cavity of the lamp panel mounting base (103) is provided with a sealing groove for installing a waterproof strip. The cover plate (107) is used to press the waterproof strip to ensure the airtightness and waterproofness of the cavity. The quick-change plug (106) is installed on the right side of the lamp panel mounting base (103).

2. The UAV lighting device according to claim 1, characterized in that: It also includes a mounting assembly comprising an upper lighting housing (201), an L-bracket (202), an aviation plug (203), and a lower lighting housing (204).

3. The UAV lighting device according to claim 2, characterized in that: The angle-flipping device includes a servo rear bracket (205), a servo (206), a servo control board (207), a first bevel gear (208), a servo front bracket (209), a limiting block (210), a bearing (211), an end cover (212), a second bevel gear (213), a drive shaft (214), a transition shaft (215), and a quick-change socket (216); the lower lighting housing (204) is equipped with bearings (211) on its left and right sides, the bearings (211) are axially positioned by the end cover (212), and the drive shaft (214) is mounted on the shaft. The transmission shaft (214) is a round rod on both sides and a D-shaped cross-section rod in the middle. Quick-change sockets (216) are installed on the left and right end faces. A second bevel gear (213) and a limiting block (210) are installed in the middle. The lighting lower shell (204) corresponding to the limiting block (210) has a limiting boss. The second bevel gear (213) meshes with the first bevel gear (208). The first bevel gear (208) is connected to the output shaft of the servo motor (206) through a transition shaft (215). The cross-section of the transition shaft (215) is a D-shaped cross-section.

4. The UAV lighting device according to claim 3, characterized in that: The servo (206) is equipped with a rear servo bracket (205) and a front servo bracket (209) at the front and rear positions, and is fixed on the lower housing (204) of the lighting.

5. A drone lighting device according to claim 4, characterized in that: The lower illumination shell (204) is equipped with four L-shaped brackets (202) around its perimeter for connecting to the bottom of the UAV. The upper illumination shell (201) is installed on top, and a servo control board (207) is installed inside for driving the servo to rotate.

Images