Individual portable composite wing unmanned aerial vehicle

Abstract

The utility model relates to an individual portable composite wing unmanned aerial vehicle, which comprises a vehicle body, fixed wings, movable wings and rotor wing supports, the fixed wings are arranged on the left side and the right side of the vehicle body, the movable wings are detachably connected to the fixed wings, first conductive terminals are arranged on the fixed wings, and second conductive terminals are arranged on the movable wings. The front side and the rear side of the movable wing are detachably connected with rotor wing supports, the movable wing is provided with a first conductive column, the first conductive column is electrically connected with a second conductive terminal through a wire, the rotor wing supports are provided with second conductive columns and rotor wing motors, and the output ends of the rotor wing motors are provided with rotor wings. Through the modular design, the modules are detachably connected, such as the matching of the connecting blocks and the connecting grooves, the fixing of the fixing pins and the threaded connection of the connecting pipes and the rotor wing brackets, so that the unmanned aerial vehicle can be conveniently disassembled and assembled, and the unmanned aerial vehicle is greatly convenient to carry by an individual soldier and rapidly deploy in a battlefield.

Description

Technical Field

[0001] This utility model relates to the field of compound wing unmanned aerial vehicle (UAV) technology, specifically a portable compound wing UAV for individual soldiers. Background Technology

[0002] Compound-wing UAVs are aircraft that integrate fixed-wing and rotor structures. Their core design involves configuring a rotor system on a fixed-wing base to achieve vertical takeoff and landing (VTOL) and hovering capabilities, while retaining the high-speed cruise, long endurance, and high payload capacity of a fixed-wing aircraft. These UAVs can switch flight modes—relying on rotor power during VTOL and switching to the optimal aerodynamic efficiency mode for fixed-wing flight during level flight. With the development of modern and information-based infantry equipment, UAVs have been widely deployed in the military, and individual soldier UAVs have become an important piece of equipment for infantry operations. Currently, the most commonly used individual soldier UAVs are rotorcraft UAVs and compound-wing UAVs, both of which possess VTOL capabilities, facilitating flight in complex environments. Compound-wing UAVs, however, are relatively large and not easily carried by individual soldiers; therefore, they require convenient disassembly and assembly. Utility Model Content

[0003] The technical problem to be solved by this utility model is to provide a portable composite wing unmanned aerial vehicle for individual soldiers, addressing the above-mentioned shortcomings.

[0004] To solve the above technical problems, the present invention adopts the following technical solution:

[0005] A portable compound-wing unmanned aerial vehicle (UAV) for individual soldiers includes a fuselage, fixed wings, movable wings, and rotor supports. Fixed wings are located on both the left and right sides of the fuselage. Movable wings are detachably connected to the fixed wings. Each fixed wing has a first conductive terminal electrically connected to a battery in the fuselage via a wire. Each movable wing has a second conductive terminal, which is electrically connected when the movable wing is mounted on the fixed wings. Rotor supports are detachably connected to both the front and rear sides of the movable wing. Each movable wing has a first conductive post electrically connected to a second conductive terminal via a wire. Each rotor support has a second conductive post, which contacts the movable wing when mounted on the movable wing. A rotor motor is mounted on the rotor support, and a rotor is mounted at the output end of the rotor motor. The second conductive post is electrically connected to the power supply terminal of the rotor motor via a wire.

[0006] Furthermore, the connecting end of the movable wing is provided with a connecting block, the upper and lower surfaces of the connecting block are both arc surfaces, a semi-annular groove is provided around the outer side of the connecting block, and a connecting groove adapted to the structure of the connecting block is provided on the fixed wing.

[0007] Furthermore, the first conductive terminal is located inside the connecting groove and is horizontally arranged. The front end face of the first conductive terminal is an inclined surface. The front end face of the connecting block is provided with a mating groove that cooperates with the first conductive terminal. The second conductive terminal extends horizontally from the inside of the movable wing to the inside of the mating groove. The front end face of the second conductive terminal is an inclined surface that is adapted to the front end face of the first conductive terminal. When the connecting block is installed in the connecting groove, the first conductive terminal is embedded in the mating groove and contacts the second conductive terminal.

[0008] Furthermore, a fixing pin for fixing the connecting block is detachably connected to the fixed wing, and the fixing pin can pass through the connecting groove and the connecting block from top to bottom.

[0009] Furthermore, the movable wing is provided with a connecting pipe that runs through both the front and rear ends of the movable wing. Both ends of the connecting pipe can be threaded to the rotor support. The inner side of the connecting pipe is provided with two first conductive posts for electrical connection with the two rotor supports. The first conductive post is L-shaped, and the working end of the first conductive post is a convex hemispherical arc surface. The first conductive post is provided with an insulating sheet. A spring is provided on the inner side of the connecting pipe between the two first conductive posts. The spring is used to push the two first conductive posts toward the corresponding second conductive posts on the rotor support. The side of the connecting pipe has two through holes on the inner side of the wing. The connecting ends of the first conductive posts extend through the through holes to the inner side of the wing. The connecting ends of the first conductive posts are electrically connected to the connecting ends of the second conductive terminals through wires.

[0010] Furthermore, the working end face of the second conductive post is a concave hemispherical arc surface that is adapted to the working end face of the first conductive post.

[0011] Compared with the prior art, the present invention, by adopting the above technical solution, has the following advantages:

[0012] This invention employs a modular design, disassembling the UAV into independent modules such as the fuselage, fixed wings, movable wings, and rotor support. These modules are connected by detachable mechanisms, including the mating of connecting blocks and grooves, the fixing of pins, and the threaded connection between connecting pipes and rotor support. This allows for convenient disassembly and assembly of the UAV, greatly facilitating individual soldier carrying and rapid battlefield deployment. Electrical connection structures are provided at the connections between the movable and fixed wings, and between the rotor support and the movable wing, respectively, for first and second conductive terminals and first and second conductive posts. The design of these conductive terminals / posts, such as the fit of inclined surfaces and the contact of hemispherical arc surfaces, ensures reliable electrical contact during connection, guaranteeing unimpeded power transmission and signal communication between the various components of the UAV.

[0013] The present invention will now be described in detail with reference to the accompanying drawings and embodiments. Attached Figure Description

[0014] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0015] Figure 2 A three-dimensional structural diagram of the fixed wing connection slot;

[0016] Figure 3 A three-dimensional structural diagram of the connecting plate section of the movable wing;

[0017] Figure 4 This is a cross-sectional view of the connection structure between the connecting pipe and the rotor support.

[0018] The attached diagram lists the components represented by each number as follows:

[0019] 1. Fuselage; 2. Fixed wing; 3. Movable wing; 4. Rotor support; 5. First conductive terminal; 6. Second conductive terminal; 7. First conductive post; 8. Second conductive post; 9. Rotor motor; 10. Rotor; 11. Connecting block; 12. Semi-annular groove; 13. Connecting groove; 14. Fitting groove; 15. Fixing pin; 16. Connecting pipe; 17. Insulating sheet; 18. Spring. Detailed Implementation

[0020] The principles and features of this utility model are described below with reference to the accompanying drawings. The examples given are only for explaining this utility model and are not intended to limit the scope of this utility model.

[0021] In the description of this utility model, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", "clockwise", "counterclockwise", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0022] like Figure 1-4As shown, a portable compound-wing unmanned aerial vehicle (UAV) for individual soldiers includes a fuselage 1, fixed wings 2, movable wings 3, and a rotor support 4. Fixed wings 2 are located on both the left and right sides of the fuselage 1. Movable wings 3 are detachably connected to the fixed wings 2. A first conductive terminal 5 is provided on each fixed wing 2, and the first conductive terminal 5 is electrically connected to the battery of the fuselage 1 via a wire. A second conductive terminal 6 is provided on each movable wing 3. When the movable wing 3 is mounted on the fixed wings 2, the first conductive terminal 5 and the second conductive terminal 6 are electrically connected. The movable wing 3 has detachable rotor brackets 4 on both its front and rear sides. The movable wing 3 is provided with a first conductive post 7, which is electrically connected to a second conductive terminal 6 via a wire. The rotor bracket 4 is provided with a second conductive post 8. When the rotor bracket 4 is installed on the movable wing 3, the first conductive post 7 and the second conductive post 8 are in contact. The rotor bracket 4 is provided with a rotor motor 9, and the output end of the rotor motor 9 is provided with a rotor 10. The second conductive post 8 is electrically connected to the power supply end of the rotor motor 9 via a wire.

[0023] In one embodiment, the connecting end of the movable wing 3 is provided with a connecting block 11. The upper and lower surfaces of the connecting block 11 are both arc surfaces. A semi-annular groove 12 is provided around the outer side of the connecting block 11. A connecting groove 13 adapted to the structure of the connecting block 11 is provided on the fixed wing 2.

[0024] In one embodiment, the first conductive terminal 5 is located inside the connecting groove 13 and is horizontally arranged. The front end face of the first conductive terminal 5 is an inclined surface. The front end face of the connecting block 11 is provided with a mating groove 14 that cooperates with the first conductive terminal 5. The second conductive terminal 6 extends horizontally through the inner side of the movable wing 3 and extends to the inner side of the mating groove 14. The front end face of the second conductive terminal 6 is an inclined surface that is adapted to the front end face of the first conductive terminal 5. When the connecting block 11 is installed in the connecting groove 13, the first conductive terminal 5 is embedded in the mating groove 14 and contacts the second conductive terminal 6.

[0025] In one embodiment, a fixing pin 15 for fixing the connecting block 11 is detachably connected to the fixed wing 2, and the fixing pin 15 can pass through the connecting groove 13 and the connecting block 11 from top to bottom.

[0026] In one embodiment, the movable wing 3 is provided with a connecting pipe 16 that runs through both the front and rear ends of the movable wing 3. Both the front and rear ends of the connecting pipe 16 can be threaded to the rotor support 4. The inner side of the connecting pipe 16 is provided with two first conductive posts 7 for electrical connection with the two rotor supports 4 respectively. The first conductive post 7 is L-shaped, and the working end of the first conductive post 7 is a convex hemispherical arc surface. The first conductive post 7 is provided with an insulating sheet 17. The inner side of the connecting pipe 16 is provided between the two first conductive posts 7. The spring 18 is used to push the two first conductive posts 7 toward the corresponding second conductive posts 8 on the rotor support 4. The side of the connecting pipe 16 is provided with two through holes on the inner side of the wing. The connecting ends of the first conductive posts 7 extend through the through holes to the inner side of the wing. The connecting ends of the first conductive posts 7 are electrically connected to the connecting ends of the second conductive terminals 6 through wires.

[0027] In one embodiment, the working end face of the second conductive post 8 is a concave hemispherical arc surface that is adapted to the working end face of the first conductive post 7.

[0028] In this invention, the first conductive terminal 5, the second conductive terminal 6, the first conductive post 7, and the second conductive post 8 are all made of copper, and the non-working surfaces of the first conductive terminal 5, the second conductive terminal 6, the first conductive post 7, and the second conductive post 8 are all covered with an insulating coating.

[0029] The working process of this utility model is as follows: First, the connecting block 11 of the movable wing 3 is inserted into the connecting groove 13 of the fixed wing 2. After the connecting block 11 is inserted into the connecting groove 13, the first conductive terminal 5 is located inside the fitting groove 14. The working end face of the first conductive terminal 5 is in contact with the working end face of the second conductive terminal 6 and is fixed by the fixing pin 15. Then, the rotor bracket 4 is threadedly connected to the movable wing 3 through the connecting tube 16. After the rotor bracket 4 is installed, under the push of the spring 18, the working end face of the first conductive post 7 is in contact with the working end face of the second conductive post 8. The power output from the battery passes through the first conductive terminal 5, the second conductive terminal 6, the first conductive post 7 and the second conductive post 8 in sequence and enters the rotor motor 9, ensuring that the fuselage 1 can stably supply power to the rotor 10.

[0030] The above description provides examples of the preferred embodiments of this utility model. Any aspects not detailed herein are common knowledge to those skilled in the art. The scope of protection of this utility model is determined by the claims. Any equivalent modifications based on the technical teachings of this utility model are also within the scope of protection of this utility model.

Claims

1. A portable composite-wing unmanned aerial vehicle for single soldiers, characterized in that, The system includes a fuselage (1), fixed wings (2), movable wings (3), and rotor support (4). Fixed wings (2) are provided on both the left and right sides of the fuselage (1). Movable wings (3) are detachably connected to the fixed wings (2). A first conductive terminal (5) is provided on the fixed wings (2), and the first conductive terminal (5) is electrically connected to the battery of the fuselage (1) via a wire. A second conductive terminal (6) is provided on the movable wings (3). When the movable wings (3) are mounted on the fixed wings (2), the first conductive terminal (5) and the second conductive terminal (6) are electrically connected. The rotor bracket (4) can be detachably connected to both the front and rear sides. The movable wing (3) is provided with a first conductive post (7). The first conductive post (7) is electrically connected to the second conductive terminal (6) through a wire. The rotor bracket (4) is provided with a second conductive post (8). When the rotor bracket (4) is installed on the movable wing (3), the first conductive post (7) and the second conductive post (8) are in contact. The rotor bracket (4) is provided with a rotor motor (9). The output end of the rotor motor (9) is provided with a rotor (10). The second conductive post (8) is electrically connected to the power supply end of the rotor motor (9) through a wire.

2. The portable compound-wing unmanned aerial vehicle for single soldiers according to claim 1, characterized in that, The connecting end of the movable wing (3) is provided with a connecting block (11). The upper and lower surfaces of the connecting block (11) are both arc surfaces. A semi-annular groove (12) is provided around the connecting block (11) on the outer side. A connecting groove (13) adapted to the structure of the connecting block (11) is provided on the fixed wing (2).

3. The portable compound-wing unmanned aerial vehicle for single soldiers according to claim 2, characterized in that, The first conductive terminal (5) is located inside the connecting groove (13) and is horizontally arranged. The front end face of the first conductive terminal (5) is an inclined surface. The front end face of the connecting block (11) is provided with a fitting groove (14) that cooperates with the first conductive terminal (5). The second conductive terminal (6) extends horizontally from the inside of the movable wing (3) to the inside of the fitting groove (14). The front end face of the second conductive terminal (6) is an inclined surface that is adapted to the front end face of the first conductive terminal (5). When the connecting block (11) is installed in the connecting groove (13), the first conductive terminal (5) is embedded in the fitting groove (14) and contacts the second conductive terminal (6).

4. A portable compound-wing unmanned aerial vehicle for single soldiers according to claim 3, characterized in that, The fixed wing (2) is detachably connected to a fixing pin (15) for fixing the connecting block (11), and the fixing pin (15) can pass through the connecting groove (13) and the connecting block (11) from top to bottom.

5. A portable compound-wing unmanned aerial vehicle for single soldiers according to claim 1, characterized in that, The movable wing (3) is provided with a connecting pipe (16) that runs through both the front and rear ends of the movable wing (3). Both the front and rear ends of the connecting pipe (16) can be threaded to the rotor support (4). The inner side of the connecting pipe (16) is provided with two first conductive posts (7) for electrical connection with the two rotor supports (4). The first conductive post (7) is L-shaped and the working end of the first conductive post (7) is a convex hemispherical arc surface. The first conductive post (7) is provided with an insulating sheet (17). The inner side of the connecting pipe (16) is provided between the two first conductive posts (7). The spring (18) is used to push the two first conductive posts (7) toward the corresponding second conductive post (8) on the rotor support (4). The side of the connecting pipe (16) is provided with two through holes on the inner side of the wing. The connecting ends of the first conductive posts (7) extend through the through holes to the inner side of the wing. The connecting ends of the first conductive posts (7) are electrically connected to the connecting ends of the second conductive terminals (6) through wires.

6. A portable compound-wing unmanned aerial vehicle for single soldiers according to claim 5, characterized in that, The working end face of the second conductive post (8) is a concave hemispherical arc surface that is adapted to the working end face of the first conductive post (7).

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