Composite wing unmanned aerial vehicle body

Abstract

The utility model discloses a composite wing unmanned aerial vehicle body, belongs to the technical field of unmanned aerial vehicles, and solves the problems that an existing unmanned aerial vehicle is inconvenient to disassemble and assemble and low in efficiency. And a plurality of first mounting holes matched with the first quick-release pins are formed in the machine body. A plurality of fourth mounting holes corresponding to the first mounting holes are formed in the central wing, and after the fuselage is connected with the central wing, a first quick-release pin is mounted in each first mounting hole and each fourth mounting hole in the corresponding position. The two ends of the central wing are each provided with an outer wing, and each outer wing is connected with the central wing through a second quick-release pin. And a power arm is arranged between each outer wing and the central wing. The two ends of the tail wing are each connected with a threaded sleeve, and each power arm is provided with threads matched with the corresponding threaded sleeve. The device is simple and reliable in structure, convenient to operate and low in difficulty, the composite wing unmanned aerial vehicle body can be disassembled and assembled without tools, and the disassembling and assembling efficiency is high.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle technology, and in particular to a composite wing unmanned aerial vehicle airframe. Background Technology

[0002] A drone is a reusable aircraft that is powered, unmanned, and relies on air for lift. During packaging, transportation, and storage, drones are required to be compact and easy to carry. Therefore, some drones currently use screws to detachably connect the fuselage and wing components. While this method allows for disassembly by removing the screws, it requires multiple forceful rotations with tools, making disassembly and assembly inconvenient and inefficient. Utility Model Content

[0003] This application provides a composite wing unmanned aerial vehicle (UAV) airframe, which solves the problems of inconvenient assembly and disassembly and low efficiency of existing UAVs.

[0004] This utility model provides a composite wing unmanned aerial vehicle (UAV) fuselage, which includes a fuselage, a central wing, a powered arm, outer wings, a tail fin, a first quick-release pin, a second quick-release pin, and a threaded sleeve. The fuselage has multiple first mounting holes that match the first quick-release pins. The central wing has multiple fourth mounting holes corresponding to the first mounting holes. When the fuselage and the central wing are connected, a first quick-release pin is installed in each corresponding first mounting hole and fourth mounting hole. An outer wing is provided at each end of the central wing, and each outer wing is connected to the central wing via a second quick-release pin. A powered arm is provided between each outer wing and the central wing. A threaded sleeve is connected to each end of the tail fin, and each powered arm has threads that mate with the threaded sleeve.

[0005] In one possible implementation, the composite wing UAV fuselage further includes a guide block; the guide block is mounted on the central wing; and the fuselage is provided with a guide groove that matches the guide block.

[0006] In one possible implementation, two first plug-in blocks are respectively provided at both ends of the central wing; each of the first plug-in blocks has a second mounting hole; the end of the outer wing is provided with two second plug-in blocks connected to the first plug-in blocks; each of the second plug-in blocks has a third mounting hole; when the first plug-in block is inserted into the second plug-in block, each of the second mounting holes corresponds to a fifth mounting hole; a second quick-release pin is installed in each corresponding second mounting hole and the fifth mounting hole.

[0007] In one possible implementation, the composite wing UAV body further includes a bushing; the bushing is installed within the second mounting hole.

[0008] In one possible implementation, the composite wing UAV fuselage also includes winglets on the wingtips; the winglets are located at the end of the outer wing opposite to the central wing.

[0009] In one possible implementation, the tail fin is an inverted V-shaped fixed tail support structure.

[0010] One or more technical solutions provided in the embodiments of this utility model have at least the following technical effects or advantages:

[0011] This utility model provides a composite-wing unmanned aerial vehicle (UAV) fuselage, comprising a fuselage, a central wing, powered arms, outer wings, a tail fin, a first quick-release pin, a second quick-release pin, and threaded sleeves. The fuselage has multiple first mounting holes that mate with the first quick-release pins. The central wing has multiple fourth mounting holes corresponding to the first mounting holes. When the fuselage and the central wing are connected, a first quick-release pin is installed in each corresponding first and fourth mounting hole. An outer wing is located at each end of the central wing, and each outer wing is connected to the central wing via a second quick-release pin. A powered arm is located between each outer wing and the central wing. A threaded sleeve is connected to each end of the tail fin, and each powered arm has threads that mate with the threaded sleeves. During drone installation, the central wing and fuselage are first connected via a first quick-release pin. Then, the power arms are fitted onto both ends of the central wing. Next, the outer wings and central wing are connected via a second quick-release pin. Finally, the tail wing and power arms are connected via a threaded sleeve. During drone disassembly, the first quick-release pin handle is operated to extend and retract the limit button, then the first quick-release pin is pulled out to disassemble the central wing. The second quick-release pin handle is then operated to extend and retract the limit button, then the second limit pin is pulled out to disassemble the outer wing. Finally, the threaded sleeve is rotated to disassemble the tail wing. This compound-wing drone fuselage allows for rapid disassembly, reducing storage space and transportation requirements. Furthermore, this application features a simple and reliable structure, is easy to operate, and requires no tools for assembly and disassembly, resulting in high efficiency. Attached Figure Description

[0012] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the description of the embodiments of this utility model will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0013] Figure 1 A schematic diagram of the structure of the composite wing UAV airframe provided in the embodiments of this application. Figure 1 ;

[0014] Figure 2 This is a schematic diagram of the fuselage structure provided in an embodiment of this application;

[0015] Figure 3 for Figure 2 Enlarged view of point A in the image;

[0016] Figure 4 A schematic diagram of the structure of the composite wing UAV airframe provided in the embodiments of this application. Figure 2 ;

[0017] Figure 5 for Figure 4 BB-direction sectional view in the middle;

[0018] Figure 6 for Figure 4 CC-direction section view;

[0019] Figure 7 for Figure 4 DD section view in the middle;

[0020] Figure 8 This is a schematic diagram of the structure of the central wing and the first plug-in block provided in an embodiment of this application;

[0021] Figure 9 for Figure 8 Enlarged view of point E in the image;

[0022] Figure 10 This is a schematic diagram of the structure of the power arm provided in an embodiment of this application;

[0023] Figure 11 This is a schematic diagram of the structure of the outer wing and the winglet at the wingtip provided in an embodiment of this application;

[0024] Figure 12 for Figure 11 Enlarged view of point F in the image;

[0025] Figure 13 This is a schematic diagram of the tail fin provided in an embodiment of this application.

[0026] Icons: 1-Fuselage; 1a-First mounting hole; 1b-Guide groove; 2-Center wing; 21-Fourth mounting hole; 3-Power arm; 4-Outer wing; 41-Fifth mounting hole; 42-Plug-in hole; 5-Tail fin; 6-First quick-release pin; 7-Second quick-release pin; 8-Threaded sleeve; 9-Guide block; 10-First plug-in block; 101-Second mounting hole; 11-Bushing; 12-Winglet; 13-Second plug-in block; 131-Third mounting hole; 14-Third quick-release pin. Detailed Implementation

[0027] 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, not all, of the embodiments of the present utility model. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present utility model.

[0028] In the description of the embodiments of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing the embodiments of this utility model and simplifying the description. They 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, and therefore should not be construed as a limitation of this utility model. The terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. In addition, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of two components. For those skilled in the art, the specific meaning of the above terms in the embodiments of this utility model can be understood according to the specific circumstances.

[0029] like Figures 1-13 As shown, this utility model embodiment provides a composite wing unmanned aerial vehicle (UAV) fuselage, which includes a fuselage 1, a central wing 2, a power arm 3, an outer wing 4, a tail fin 5, a first quick-release pin 6, a second quick-release pin 7, and a threaded sleeve 8. The central wing 2 of this application adopts a sealed structure, resulting in good overall sealing performance.

[0030] In this embodiment, the fuselage 1 has multiple first mounting holes 1a that match the first quick-release pins 6. The central wing 2 has multiple fourth mounting holes 21 corresponding to the first mounting holes 1a. When the fuselage 1 and the central wing 2 are connected, a first quick-release pin 6 is installed in each corresponding first mounting hole 1a and fourth mounting hole 21. An outer wing 4 is provided at each end of the central wing 2, and each outer wing 4 is connected to the central wing 2 by a second quick-release pin 7. A power arm 3 is provided between each outer wing 4 and the central wing 2. Specifically, the power arm 3 is sleeved on the central wing 2. When the outer wing 4 is installed on the central wing 2 by the second quick-release pin 7, the central wing 2 and the outer wing 4 limit and fix the power arm 3.

[0031] In practical applications, a threaded sleeve 8 is connected to each end of the tail fin 5, and each power arm 3 is provided with a thread that mates with the threaded sleeve 8. Specifically, the tail fin 5 is an integrated fixed tail support structure to reduce connecting mechanisms and improve assembly and disassembly efficiency. Furthermore, a third quick-release pin 14 is installed at the end of the tail support rod of the tail fin 5 to axially limit the threaded sleeve 8.

[0032] This utility model provides a composite wing unmanned aerial vehicle (UAV) fuselage, comprising a fuselage 1, a central wing 2, power arms 3, outer wings 4, a tail fin 5, a first quick-release pin 6, a second quick-release pin 7, and a threaded sleeve 8. The fuselage 1 has multiple first mounting holes 1a that match the first quick-release pins 6. The central wing 2 has multiple fourth mounting holes 21 corresponding to the first mounting holes 1a. When the fuselage 1 and the central wing 2 are connected, a first quick-release pin 6 is installed in each corresponding first mounting hole 1a and fourth mounting hole 21. An outer wing 4 is provided at each end of the central wing 2, and each outer wing 4 is connected to the central wing 2 via a second quick-release pin 7. A power arm 3 is provided between each outer wing 4 and the central wing 2. A threaded sleeve 8 is connected to each end of the tail fin 5, and each power arm 3 has threads that mate with the threaded sleeve 8. During drone installation, the central wing 2 and fuselage 1 are first connected via the first quick-release pin 6. Then, the power arm 3 is fitted onto both ends of the central wing 2. Next, the outer wing 4 is connected to the central wing 2 via the second quick-release pin 7. Finally, the tail wing 5 and power arm 3 are connected via the threaded sleeve 8. During drone disassembly, the first quick-release pin 6 is first operated to extend and retract the limit button, then pulled out to remove the central wing 2. Then, the second quick-release pin 7 is operated to extend and retract the limit button, then pulled out to remove the outer wing 4. Finally, the threaded sleeve 8 is rotated to remove the tail wing 5. This application features a simple and reliable structure, convenient and easy operation, and requires no tools for assembly and disassembly of the composite wing drone body, resulting in high efficiency. Furthermore, the composite wing drone body of this application can be quickly disassembled, reducing storage space and transportation requirements.

[0033] In this embodiment, the composite wing UAV body further includes a guide block 9. The guide block 9 is mounted on the central wing 2. The fuselage 1 is provided with a guide groove 1b that matches the guide block 9. During assembly of the central wing 2, the guide block 9 on the central wing 2 slides within the guide groove 1b on the fuselage 1 to prevent the central wing 2 from shifting, thereby ensuring quick and accurate installation of the central wing 2. Specifically, the guide block 9 is connected to the beam of the central wing 2 by screws to prevent the guide block 9 from rotating.

[0034] In this embodiment, two first plug-in blocks 10 are respectively provided at both ends of the central wing 2. Each first plug-in block 10 has a second mounting hole 101. The outer wing 4 has two second plug-in blocks 13 connected to the first plug-in blocks 10 at its ends. Each second plug-in block 13 has a third mounting hole 131. When the first plug-in block 10 is inserted into the second plug-in block 13, each second mounting hole 101 corresponds to a fifth mounting hole 41. A second quick-release pin 7 is installed in each corresponding second mounting hole 101 and fifth mounting hole 41. Specifically, when connecting the outer wing 4 and the central wing 2, the second plug-in blocks 13 and the first plug-in blocks 10 are plugged in, and then a second quick-release pin 7 is installed in each corresponding second mounting hole 101 and fifth mounting hole 41; when disassembling the outer wing 4 and the central wing 2, the second quick-release pin 7 is pulled out, and the second plug-in blocks 13 and the first plug-in blocks 10 are separated.

[0035] like Figure 6 As shown, the composite wing UAV fuselage also includes a bushing 11. The bushing 11 is installed inside the second mounting hole 101. Specifically, installing the bushing 11 inside the second mounting hole 101 can prevent the outer wing 4 from undergoing large deflection deformation.

[0036] like Figure 11 As shown, the composite wing UAV also includes winglets 12 at the wingtips. The winglets 12 are located at the end of the outer wing 4 opposite to the central wing 2. Specifically, the winglets 12 can reduce induced drag during the flight of the UAV.

[0037] like Figure 13 As shown, the tail fin 5 is an inverted V-shaped fixed tail boom structure. The inverted V-shaped fixed tail boom structure can reduce the disassembly and assembly process and improve disassembly and assembly efficiency.

[0038] The various embodiments in this specification are described in a progressive manner. For the same or similar parts between the various embodiments, please refer to each other. Each embodiment focuses on describing the differences from other embodiments.

[0039] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit this application. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of this application.

Claims

1. A composite-wing unmanned aerial vehicle (UAV) airframe, characterized in that, Includes fuselage (1), center wing (2), power arm (3), outer wing (4), tail (5), first quick release pin (6), second quick release pin (7) and threaded sleeve (8); The body (1) is provided with a plurality of first mounting holes (1a) that match the first quick release pin (6); The central wing (2) is provided with a plurality of fourth mounting holes (21) corresponding to the first mounting hole (1a). When the fuselage (1) and the central wing (2) are connected, a first quick-release pin (6) is installed in each of the first mounting holes (1a) and the fourth mounting holes (21) at each corresponding position. An outer wing (4) is provided at each end of the central wing (2), and each outer wing (4) is connected to the central wing (2) by the second quick-release pin (7); A power arm (3) is provided between each of the outer wings (4) and the central wing (2); The tail fin (5) is connected to a threaded sleeve (8) at each end, and each power arm (3) is provided with a thread that mates with the threaded sleeve (8).

2. The composite-wing UAV airframe according to claim 1, characterized in that, It also includes the guide block (9); The guide block (9) is mounted on the central wing (2); The fuselage (1) is provided with a guide groove (1b) that matches the guide block (9).

3. The composite-wing UAV airframe according to claim 1, characterized in that, Two first plug-in blocks (10) are respectively provided at both ends of the central wing (2); Each of the first plug-in blocks (10) is provided with a second mounting hole (101); The outer wing (4) has two second plug-in blocks (13) at its end that are connected to the first plug-in block (10); each of the second plug-in blocks (13) has a third mounting hole (131). When the first plug-in block (10) is inserted into the second plug-in block (13), each of the second mounting holes (101) corresponds to a fifth mounting hole (41). A second quick-release pin (7) is installed in each of the corresponding second mounting holes (101) and the fifth mounting holes (41).

4. The composite-wing UAV airframe according to claim 3, characterized in that, It also includes bushings (11); The bushing (11) is installed in the second mounting hole (101).

5. The composite-wing UAV airframe according to claim 1, characterized in that, It also includes the winglets on the wingtips (12); The winglet (12) is located at one end of the outer wing (4) away from the central wing (2).

6. The composite-wing UAV airframe according to claim 1, characterized in that, The tail fin (5) is an inverted V-shaped fixed tail support structure.

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