Unmanned aerial vehicle tear bomb launcher

Abstract

The utility model relates to the technical field of launchers, and discloses an unmanned aerial vehicle tear bomb launcher which comprises a base plate installed at the bottom of an unmanned aerial vehicle and a launcher body located on the lower portion of the base plate, the base plate is connected with the launcher body through a plurality of hinge structures, and a driving structure is installed at the end of the launcher body. The driving end of the driving structure is rotationally connected with a rotating assembly installed at the end of the base plate, and the driving structure is used for driving the emitter body to rotate and adjust. According to the utility model, the substrate and the emitter body are connected through the hinge structure; the emitter body can rotate on the base plate through the hinge structure; the launcher body can be rotationally adjusted according to the throwing position, and high flexibility is achieved; the driving structure and the rotating assembly are arranged between the base plate and the emitter body, and through cooperation of the driving structure and the rotating assembly, the emitter can be rotationally adjusted in an electric mode in the high-altitude work process.

Description

Technical Field

[0001] This utility model relates to the field of launcher technology, specifically a drone tear gas launcher. Background Technology

[0002] Tear gas is a non-lethal chemical weapon that contains a tear-inducing irritant and can be launched in the form of a jet or a grenade.

[0003] Currently, most tear gas launchers require the use of drones; however, current tear gas launchers are usually fixed directly to the bottom of the drone with bolts. If the tear gas is to be deployed, it cannot be adjusted according to the deployment position, resulting in poor effectiveness. In addition, the installation or removal of the launcher requires frequent adjustment of the fastening bolts, which is inconvenient for the staff.

[0004] Therefore, we propose a drone tear gas launcher to address the problems mentioned above. Utility Model Content

[0005] The purpose of this utility model is to solve the aforementioned technical problems.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: a drone tear gas launcher, comprising a base plate installed at the bottom of the drone and a launcher body located at the lower part of the base plate, wherein the base plate and the launcher body are connected by a plurality of hinge structures, and a drive structure is installed at the end of the launcher body, wherein the drive end of the drive structure is rotatably connected to a rotating component installed at the end of the base plate, and the drive structure is used to drive the launcher body to rotate and adjust.

[0007] Furthermore: the hinge structure includes a first rotating support fixed at the corner of the transmitter body and a second rotating support fixed at the bottom of the substrate. A first press-type hinge assembly is fixed on one side of the first rotating support, and a hinge hole for use with the first press-type hinge assembly is provided on the second rotating support.

[0008] Furthermore: the drive structure includes a rotating seat fixed to the end of the transmitter body, and a "U"-shaped rotating bracket is rotatably mounted on the rotating seat, and a drive rod is fixed on the rotating bracket, and a rotating sleeve is fixed to one end of the drive rod.

[0009] Furthermore: the rotating assembly includes a mounting base fixed to the end of the substrate, and a second press-type hinge assembly is mounted on the side of the mounting base, and the rotating sleeve is rotatably mounted inside the second press-type hinge assembly.

[0010] Furthermore: the first press-type hinge assembly includes a fixed sleeve fixed to the side of the first rotating support and a sliding sleeve slidably installed inside the fixed sleeve, and a compression spring is installed between the sliding sleeve and the inner sidewall of the fixed sleeve, and a hinge shaft extending to the outside of the fixed sleeve is fixed to one end of the sliding sleeve.

[0011] Furthermore: the inner sidewall of the fixed sleeve is fixed with a plurality of first limiting posts at equal intervals along the circumferential direction, and the outer surface of the sliding sleeve is fixed with a plurality of second limiting posts at equal intervals along the circumferential direction, and each second limiting post is slidably installed in the gap between two adjacent first limiting posts.

[0012] The beneficial effects of this utility model are:

[0013] The base plate and the transmitter body of this utility model are connected by a hinge structure; the transmitter body can rotate on the base plate through the hinge structure; the transmitter body can be rotated and adjusted according to the deployment position, which has strong flexibility; a drive structure and a rotating component are provided between the base plate and the transmitter body. Through the cooperation of the drive structure and the rotating component, the transmitter can be rotated and adjusted electrically when working at high altitudes, which has strong practicality and improves the use effect of the transmitter.

[0014] This utility model has a press-type connection component installed at the connection between the first rotating support and the second rotating support, and at the connection between the rotating bracket and the mounting base. The press-type connection component allows for quick disassembly of the transmitter body, thus providing convenience for the staff. Attached Figure Description

[0015] Figure 1 This is a three-dimensional structural schematic diagram of the present invention;

[0016] Figure 2 This is a three-dimensional structural diagram of the substrate in this utility model;

[0017] Figure 3 This is a three-dimensional structural diagram of the driving structure in this utility model;

[0018] Figure 4 This is a three-dimensional structural diagram of the transmitter body in this utility model;

[0019] Figure 5 This is a cross-sectional structural diagram of the first rotating support in this utility model;

[0020] Figure 6 This is a partial structural schematic diagram of the first press-type hinge assembly in this utility model.

[0021] The names corresponding to each mark in the diagram:

[0022] 1. Substrate; 2. Transmitter body; 3. Hinge structure; 301. First rotating support; 302. Second rotating support; 303. First press-type hinge assembly; 3031. Fixed sleeve; 3032. Sliding sleeve; 3033. Hinge shaft; 3034. First limiting post; 3035. Second limiting post; 304. Hinge hole; 4. Drive structure; 401. Rotating seat; 402. Rotating bracket; 403. Drive rod; 404. Rotating sleeve; 5. Rotating assembly; 501. Mounting seat; 502. Second press-type hinge assembly. Detailed Implementation

[0023] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art are within the protection scope of the present utility model.

[0024] A drone tear gas launcher includes a base plate 1 with a plurality of mounting holes 6 evenly spaced on the base plate 1. Typically, fixing bolts (not shown in the figure) pass through the mounting holes 6 and are threadedly connected to the bottom of the drone (not shown in the figure) to fix the base plate 1. Both ends of the base plate 1 are connected to the same launcher body 2 (the launcher body is already known prior art and will not be described in detail here) via hinge structures 3. The hinge structures 3 allow for rotational adjustment of the launcher body 2 according to the tear gas launch position, providing greater flexibility. A drive structure 4 is mounted at the end of the launcher body 2, and a rotating component 5 is mounted at the end of the base plate 1. One end of the drive structure 4 is rotatably connected to the rotating component 5. Through the cooperation of the drive structure 4 and the rotating component 5, the launcher body 2 can be electrically rotated and adjusted when operating at high altitudes, improving the launcher's effectiveness.

[0025] In detail: The hinge structure 3 includes a first rotating support 301 fixed at the top corner of the transmitter body 2 and a second rotating support 302 fixed at the bottom of the substrate 1. The second rotating support 302 is provided with a hinge hole 304. A first press-type hinge assembly 303 is installed on the side of the first rotating support 301. The hinge part of the first press-type hinge assembly 303 is rotatably mounted on the first press-type hinge assembly 303, so that the second rotating support 302 can rotate on the first rotating support 301 through the first press-type hinge assembly 303.

[0026] In detail: the drive structure 4 includes a rotating seat 401 fixed to the end of the transmitter body 2, and a rotating bracket 402 with a "U" shape structure is rotatably mounted on the rotating seat 401, and a drive rod 403 is fixed on the rotating bracket 402. The drive rod 403 is usually an electric telescopic rod, and a rotating sleeve 404 is fixed to one end of the drive rod 403.

[0027] In detail: The rotating component 5 includes a mounting base 501 fixed to the end of the substrate 1, and a second press-type transfer component 502 is mounted on one side of the mounting base 501. Normally, the rotating sleeve 404 is rotatably mounted on the second press-type transfer component 502. When the driving end of the driving rod 403 extends, the transmitter body 2 can rotate downward on the substrate 1 through the hinge structure 3, thereby playing an adjustment role.

[0028] It should be noted that the structures of the first press-type hinge assembly 303 and the second press-type junction assembly 502 are completely identical. For ease of description, this application only describes the structure of the first press-type hinge assembly 303 and the personnel involved.

[0029] More specifically: the first press-type hinge assembly 303 includes a fixed sleeve 3031 fixed to the side of a fixed sleeve 3031, and a sliding sleeve 3032 is slidably installed inside the fixed sleeve 3031 along the axial direction. It should be noted that: a plurality of first limiting posts 3034 are equidistantly fixed to the inner wall of the fixed sleeve 3031 along the circumferential direction, with a certain gap between adjacent first limiting posts 3034; a plurality of second limiting posts 3035 are equidistantly fixed to the outer surface of the sliding sleeve 3032 along the circumferential direction. Typically: each second limiting post 3035 is slidably installed on the adjacent... In the gap between the adjacent first limiting post 3034, the cooperation of the first limiting post 3034 and the second limiting post 3035 serves to limit the sliding sleeve 3032, preventing the sliding sleeve 3032 and the first limiting post 3034 from rotating in opposite directions; one end of the sliding sleeve 3032 is fixed with a hinge shaft 3033, and the hinge shaft 3033 is usually rotatably installed inside the hinge hole 304; a compression spring 3036 is installed between the inner end of the sliding sleeve 3032 and the inner end wall of the fixed sleeve 3031, and the compression spring 3036 serves to reset the hinge shaft 3033.

[0030] Before the drone fires tear gas, the launcher body 2 needs to be adjusted according to the location where the tear gas will be deployed: First, the drive rod 403 is activated, and the drive end of the drive rod 403 extends, so that the rotating sleeve 404 at the end of the drive rod 403 can rotate on the second pressing-type connecting assembly 502. The launcher body 2 can be rotated and adjusted on the second rotating support 302 through the cooperation of the first rotating support 301 and the first pressing-type hinge assembly 303. The launcher body 2 can be rotated and adjusted according to the location where the tear gas will be deployed, which has strong flexibility.

[0031] When the transmitter body 2 needs to be disassembled from the drone after use: pressure is applied to the hinge shafts 3033 on both sides. The hinge shafts 3033 move into the fixed sleeve 3031 through the sliding sleeve 3032 and apply pressure to the compression spring 3036, so that the compression spring 3036 changes from its original state to a compressed state. If the two hinge shafts 3033 are removed from the inside of the first limiting post 304, the initial disassembly is completed. Then, the second pressing hinge assembly 502 is operated in the same way as above. When the second pressing hinge assembly 502 disengages from the inside of the rotating sleeve 404, the disassembly of the transmitter body 2 is completed, which facilitates operation and provides convenience for the staff.

Claims

1. A drone tear gas launcher comprising a base plate (1) mounted at the bottom of a drone and a launcher body (2) located at the lower part of the base plate (1), characterized by: The substrate (1) and the transmitter body (2) are connected by several hinge structures (3). A drive structure (4) is installed at the end of the transmitter body (2), and the drive end of the drive structure (4) is rotatably connected to the rotating component (5) installed at the end of the substrate (1). The drive structure (4) is used to drive the transmitter body (2) to rotate and adjust.

2. The drone tear gas launcher of claim 1, wherein: The hinge structure (3) includes a first rotating support (301) fixed at the corner of the transmitter body (2) and a second rotating support (302) fixed at the bottom of the substrate (1). A first press-type hinge assembly (303) is fixed on one side of the first rotating support (301), and a hinge hole (304) is provided on the second rotating support (302) to cooperate with the first press-type hinge assembly (303).

3. A drone tear gas launcher according to claim 2, characterized in that: The drive structure (4) includes a rotating seat (401) fixed at the end of the transmitter body (2), and a "U"-shaped rotating bracket (402) is rotatably mounted on the rotating seat (401), and a drive rod (403) is fixed on the rotating bracket (402), and a rotating sleeve (404) is fixed at one end of the drive rod (403).

4. The drone tear gas launcher of claim 3, wherein: The rotating assembly (5) includes a mounting base (501) fixed to the end of the substrate (1), and a second press-type hinge assembly (502) is mounted on the side of the mounting base (501), and a rotating sleeve (404) is rotatably mounted inside the second press-type hinge assembly (502).

5. The drone tear gas launcher of claim 2, wherein: The first press-type hinge assembly (303) includes a fixed sleeve (3031) fixed to the side of the first rotating support (301) and a sliding sleeve (3032) slidably installed inside the fixed sleeve (3031). A compression spring (3036) is installed between the sliding sleeve (3032) and the inner wall of the fixed sleeve (3031). One end of the sliding sleeve (3032) is fixed with a hinge shaft (3033) extending to the outside of the fixed sleeve (3031).

6. The drone tear gas launcher of claim 5, wherein: The inner wall of the fixed sleeve (3031) is fixed with a plurality of first limiting posts (3034) at equal intervals along the circumferential direction, and the outer surface of the sliding sleeve (3032) is fixed with a plurality of second limiting posts (3035) at equal intervals along the circumferential direction. Each second limiting post (3035) is slidably installed in the gap between two adjacent first limiting posts (3034).

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