Unmanned aerial vehicle body

Abstract

The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle fuselage which comprises a fuselage body, the fuselage body comprises a first frame and a second frame, the first frame and the second frame are both triangular frames, and the first frame and the second frame are fixedly connected and arranged in the axial direction of the fuselage body. The end corner of the first frame and the end corner of the second frame are arranged in a staggered mode in the direction perpendicular to the axis of the fuselage. According to the structure, the first frame and the second frame are triangular, due to the stability of the triangles, the fuselage of the unmanned aerial vehicle has stability, the first frame and the second frame are arranged in a staggered mode, and six small triangular structures are formed at the six corners, so that the fuselage is more stable and firmer; moreover, parts are convenient to replace, the fuselage is simple in structure, easy to process and mount and light in weight, and the flight time of the unmanned aerial vehicle is prolonged.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, and specifically relates to a UAV fuselage. Background Technology

[0002] With societal development, drones, as an efficient and safe tool, have experienced rapid growth, capable of replacing manual high-altitude operations, exploring dangerous areas, and performing missions in places inaccessible to humans. Currently, there are many types of drones in China, but some problems still exist. For example, the polygonal fuselage frame is not stable and is prone to deformation when encountering large impacts (such as gusts of wind) during flight, leading to errors in flight control logic and serious consequences. Furthermore, because drones need to adjust their flight attitude, the fuselage is constantly subjected to torque and tension from each motor adjustment; a stable drone fuselage structure is crucial. In addition, the weight distribution of the drone fuselage is also closely related to its flight performance.

[0003] The applicant has discovered the following problems with the existing drone fuselage: The existing drone fuselage structure results in uneven weight distribution. This unreasonable weight distribution causes individual motors to bear excessive weight, reducing motor efficiency and consequently decreasing the overall energy utilization of the drone. Secondly, the complex fuselage structure makes manufacturing and installation difficult, and the drone is also relatively heavy, which is detrimental to increasing its flight time.

[0004] Therefore, in order to address the problems of unstable and complex drone fuselage structures in existing technologies, there is a need to provide a new drone fuselage. Utility Model Content

[0005] This utility model provides a drone fuselage to solve the problems of unstable and complex drone fuselage structures in the prior art.

[0006] This utility model is achieved through the following technical solution: it includes a fuselage, wherein the fuselage includes a first frame and a second frame, wherein:

[0007] Both the first frame and the second frame are triangular frames. The first frame and the second frame are fixedly connected and arranged along the axial direction of the fuselage. The end corners of the first frame and the end corners of the second frame are staggered in a direction perpendicular to the fuselage axis.

[0008] To better realize this utility model, further optimizations are made to the above structure. Both the first frame and the second frame are equilateral triangular frames, and the first frame and the second frame have the same structure.

[0009] To better realize this utility model, the above structure is further optimized. The center point of the first frame and the center point of the second frame are set to coincide, and the outer contours of the first frame and the outer contours of the second frame are centrally rotationally symmetrical about their centers.

[0010] To better realize this utility model, further optimizations are made to the above structure. The first frame includes a fuselage main beam and main beam connectors. There are three fuselage main beams, and the fuselage main beams are connected in pairs through the main beam connectors to form a triangular frame.

[0011] To better realize this utility model, further optimization is made to the above structure. The main beam of the fuselage is provided with multiple frame connectors. The frame connectors are a first frame connector provided in the first frame and a second frame connector provided in the second frame. The first frame connector and the second frame connector are connected.

[0012] To better realize this utility model, the above structure is further optimized by uniformly providing a machine arm module on each of the main beam connectors.

[0013] To better realize this utility model, further optimizations are made to the above structure. The arm module includes an L-shaped connecting rod and a fan blade. One end of the L-shaped connecting rod is fixedly connected to the main beam connector, and the other end of the L-shaped connecting rod is hinged to the fan blade.

[0014] To better realize this utility model, further optimizations are made to the above structure, and the main beam connector is a triangular iron.

[0015] To better realize this utility model, the above structure is further optimized by making the frame connector an embedded inner bushing.

[0016] To better realize this utility model, further optimizations are made to the above structure, and a drone is also provided, which includes the above drone fuselage.

[0017] Compared with the prior art, this utility model has the following advantages:

[0018] This utility model provides a drone fuselage, including a fuselage comprising a first frame and a second frame, wherein both the first and second frames are triangular frames, fixedly connected and arranged along the axial direction of the fuselage, with the end corners of the first and second frames staggered in a direction perpendicular to the fuselage axis. This structure, by setting the first and second frames as triangles, leverages the inherent stability of triangles to enhance the stability of the drone fuselage. Furthermore, the staggered arrangement of the first and second frames forms six smaller triangular structures at the six corners, making the fuselage even more stable and robust. Additionally, the components are easy to replace, the fuselage structure is simple, easy to manufacture and install, and the fuselage is lightweight, thus increasing the drone's flight time. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a front view of the fuselage of the drone in this utility model;

[0021] Figure 2 This is a side view of the fuselage of the drone in this utility model.

[0022] In the picture:

[0023] 1-First frame; 2-Second frame; 3-Fuselage main beam; 4-Main beam connector; 5-Frame connector; 6-L-shaped connecting rod; 7-Fan blade. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions of this utility model will be described in detail below. Obviously, the described embodiments are only a part of the embodiments of this utility model, and not all of them. Based on the embodiments of this utility model, all other implementation methods obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0025] In the description of this utility model, it should be noted that, unless otherwise stated, "a plurality of" means two or more; the terms "upper," "lower," "left," "right," "inner," "outer," "front end," "rear end," "head," "tail," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and 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, and therefore should not be construed as a limitation of this utility model. Furthermore, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0026] In the description of this utility model, it should also be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" 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. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0027] Example 1:

[0028] A drone fuselage includes a fuselage, wherein the fuselage includes a first frame 1 and a second frame 2, wherein:

[0029] Both the first frame 1 and the second frame 2 are triangular frames. The first frame and the second frame are fixedly connected and arranged along the axial direction of the fuselage. The end corners of the first frame and the end corners of the second frame are staggered in a direction perpendicular to the fuselage axis.

[0030] The above structure sets the first frame 1 and the second frame 2 as triangles. Due to the inherent stability of triangles, the drone's fuselage is stable. Furthermore, the first and second frames are arranged in an alternating manner, forming six small triangular structures at the six corners, which makes the fuselage more stable and robust. In addition, the parts are easy to replace, the fuselage structure is simple, easy to process and install, and the fuselage is lightweight, which increases the drone's flight time.

[0031] Both the first frame 1 and the second frame 2 described above are equilateral triangular frames, and their structures are identical. This use of equilateral triangular frames simplifies the fabrication of the fuselage and ensures structural stability.

[0032] The center points of the first frame 1 and the second frame 2 are coincidentally located, and the outer contours of the first frame 1 and the second frame 2 are rotationally symmetrical about their centers. That is, the first and second frames form an equilateral hexagonal star with internal sides.

[0033] The aforementioned first frame 1 includes a fuselage main beam 3 and main beam connecting members 4. There are three fuselage main beams 3, which are connected in pairs by the main beam connecting members 4 to form a triangular frame. Optionally, the ends of every two fuselage main beams 3 are welded, threaded, or snapped to the main beam connecting members 4 to form a triangular frame.

[0034] The aforementioned main beam 3 of the fuselage is provided with multiple frame connectors 5. The frame connectors 5 are a first frame connector provided in the first frame 1 and a second frame connector provided in the second frame 2. The first frame connector and the second frame connector are connected. The frame connectors 5 are embedded in the main beam 3 of the fuselage, and the first frame 1 and the second frame 2 are detachably connected through the threaded connection between the frame connectors 5.

[0035] Arm modules are evenly distributed on each of the aforementioned main beam connectors 4. By evenly installing arm modules on the main beam connectors 4, the weight of the arm modules on each main beam connector 4 is the same, which helps to improve the stability of the UAV. Furthermore, since the efficiency of the UAV motor decreases exponentially with the increase of the motor current, evenly distributing the weight of each arm module can make more efficient use of the energy carried by the UAV, which can greatly increase the flight time of the UAV.

[0036] The aforementioned arm module includes an L-shaped connecting rod 6 and a fan blade 7. One end of the L-shaped connecting rod 6 is fixedly connected to the main beam connector 4, and the other end of the L-shaped connecting rod 6 is hinged to the fan blade 7. By hinged to the fan blade 7 via the L-shaped connecting rod 6, and by installing wires on the L-shaped connecting rod 6 to connect to the battery, the drone can fly.

[0037] The aforementioned main beam connector 4 is a triangular iron.

[0038] The aforementioned frame connector 5 is an embedded inner bushing.

[0039] Specifically, by setting the first frame 1 and the second frame 2 as triangles, and intersecting the first frame 1 and the second frame 2 to form an equilateral hexagonal star structure, the drone body has extremely strong stability, and the body structure is simple, easy to install and process. Due to the simple structure, the body is lightweight, which improves the drone's endurance.

[0040] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the protection scope of the claims.

Claims

1. A drone fuselage, characterized in that: The fuselage includes a first frame (1) and a second frame (2), wherein: The first frame (1) and the second frame (2) are both triangular frames. The first frame (1) and the second frame (2) are fixedly connected and arranged along the axial direction of the fuselage. The end corners of the first frame (1) and the end corners of the second frame (2) are staggered in a direction perpendicular to the fuselage axis.

2. The unmanned aerial vehicle (UAV) fuselage according to claim 1, characterized in that: Both the first frame (1) and the second frame (2) are equilateral triangle frames, and the first frame (1) and the second frame (2) have the same structure.

3. The unmanned aerial vehicle fuselage according to claim 2, characterized in that: The center point of the first frame (1) and the center point of the second frame (2) are set to coincide, and the outer contours of the first frame (1) and the outer contours of the second frame are centrally rotate symmetrical about their centers.

4. The unmanned aerial vehicle fuselage according to claim 3, characterized in that: The first frame (1) includes a fuselage main beam (3) and a main beam connector (4). There are three fuselage main beams (3), and the fuselage main beams (3) are connected in pairs through the main beam connectors (4) to form a triangular frame.

5. The unmanned aerial vehicle fuselage according to claim 4, characterized in that: The main beam (3) of the fuselage is provided with multiple frame connectors (5), the frame connectors (5) are a first frame connector provided in the first frame (1) and a second frame connector provided in the second frame (2), and the first frame connector and the second frame connector are connected.

6. The unmanned aerial vehicle fuselage according to claim 5, characterized in that: Each of the main beam connectors (4) is uniformly provided with a machine arm module.

7. The unmanned aerial vehicle fuselage according to claim 6, characterized in that: The arm module includes an L-shaped connecting rod (6) and a fan blade (7). One end of the L-shaped connecting rod (6) is fixedly connected to the main beam connector (4), and the other end of the L-shaped connecting rod (6) is hinged to the fan blade (7).

8. The unmanned aerial vehicle fuselage according to claim 4, characterized in that: The main beam connector (4) is a triangular iron.

9. The unmanned aerial vehicle fuselage according to claim 5, characterized in that: The frame connector (5) is an embedded inner bushing.

10. A drone, characterized in that, Includes the unmanned aerial vehicle fuselage as described in any one of claims 1-9.

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