Vertical fixed-wing unmanned aerial vehicle

Abstract

The vertical fixed-wing unmanned aerial vehicle comprises a vehicle body, a mounting frame is arranged in the vehicle body, the mounting frame is arranged in a stacked structure, and a plurality of functional modules are arranged on the mounting frame in a stacked mode; the plurality of function modules comprise a flight control module configured to receive and process data from each sensor of the unmanned aerial vehicle so as to control the flight attitude, speed and height of the unmanned aerial vehicle; the sky end module is configured to be used for transmitting and transmitting an image acquired by a pod of the unmanned aerial vehicle in a wireless signal manner; and the power distribution board is configured to be used for performing power distribution on each electric device of the unmanned aerial vehicle. According to the vertical fixed-wing unmanned aerial vehicle, the multiple functional modules are arranged in a stacked structure, the structure is compact, the size of the fuselage of the unmanned aerial vehicle can be smaller, and therefore the flight resistance is reduced.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a vertical take-off and landing (VTOL) fixed-wing UAV. Background Technology

[0002] With the rapid development of science and technology, in recent years, drone equipment has become increasingly diverse, with products exhibiting various flight modes such as fixed-wing, multi-rotor, helicopter, and vertical take-off and landing fixed-wing.

[0003] Currently, existing fixed-wing drones typically carry antennas, pods, and equipment bays, with the equipment bay containing multiple functional modules. However, due to the disorganized and illogical layout of these accessories and functional modules, significant structural space is wasted, and the overall drag of the drone is relatively high, increasing the difficulty of takeoff and landing and causing considerable inconvenience to its use. Utility Model Content

[0004] To address the technical problem of high flight drag in existing fixed-wing UAVs, this application provides a vertical take-off fixed-wing UAV.

[0005] This application proposes a vertical take-off and landing fixed-wing unmanned aerial vehicle (UAV), including a fuselage, with a mounting frame inside the fuselage. The mounting frame adopts a stacked structure layout, and multiple functional modules are stacked on the mounting frame.

[0006] The aforementioned functional modules include:

[0007] The flight control module is configured to receive and process data from various sensors of the UAV in order to control the flight attitude, speed and altitude of the UAV;

[0008] The aerial module is configured to transmit images captured by the drone's pod wirelessly.

[0009] A power distribution board is configured to distribute power to the various electrical devices of the UAV.

[0010] Preferably, the mounting frame includes a main frame and a plurality of mounting plates, the plurality of mounting plates being fixed at intervals along the height direction of the main frame inside the main frame, and at least the flight control module and the sky-end module are respectively mounted on the mounting plates.

[0011] Preferably, it also includes a pod, and the lower front section of the fuselage has a mounting cavity, in which the pod is fixed.

[0012] Preferably, the pod includes a pod body and a fixing frame, the pod body is fixedly connected to the fixing frame, and the fixing frame is fixed in the mounting cavity by screws.

[0013] Preferably, it also includes landing gear, which is located on the lower side of the middle section of the fuselage, and the landing gear is offset from the pod.

[0014] Preferably, it also includes antennas, which are distributed on the lower sides of both sides of the fuselage and extend downward.

[0015] Preferably, it also includes a left wing and a right wing, and the fuselage includes connecting flanges on both sides, with the left wing and the right wing respectively connected to the connecting flanges on both sides;

[0016] One end of the antenna is fixed to the lower side of the connecting flange, and the other end extends downward.

[0017] Preferably, two antennas are respectively provided on both sides of the fuselage, and the two antennas on the same side are arranged in the same position along the length direction of the fuselage.

[0018] Preferably, the antenna includes a fixing component, a rotating component, and an antenna body. The fixing component is fixedly connected to the fuselage, the rotating component is rotatably connected to the fixing component, and the antenna body is hinged to the rotating component.

[0019] Compared with the prior art, the beneficial results of this application are as follows:

[0020] The vertical take-off and landing fixed-wing UAV of this application adopts a stacked structure for its flight control module, airborne module, and power distribution board, resulting in a compact structure that allows for a smaller UAV fuselage and reduced flight drag. Furthermore, the pod is positioned on the underside of the fuselage to minimize drag, and its offset design from the landing gear prevents interference during significant rotation. Two sets of antennas are arranged side-by-side on the connecting flange of the fuselage. This design allows for easy packing of the UAV; only the wings need to be removed, and the antennas can be folded and stored without disassembly. Additionally, the wings provide some protection against rain, and the antennas do not interfere with airflow beneath the wings, thus preventing interference with take-off and landing. Attached Figure Description

[0021] The accompanying drawings are included to provide a further understanding of the embodiments and are incorporated in and constitute a part of this specification. The drawings illustrate embodiments and, together with the description, serve to explain the principles of this application. Other embodiments and many anticipated advantages of these embodiments will be readily recognized as they become better understood through reference to the following detailed description. Elements in the drawings are not necessarily to scale. The same reference numerals refer to corresponding similar parts.

[0022] Figure 1 This is a schematic diagram of the structure of a vertical take-off fixed-wing unmanned aerial vehicle according to a specific embodiment of this application;

[0023] Figure 2 This is a schematic diagram of the structure of a vertical take-off fixed-wing UAV according to a specific embodiment of this application, highlighting the mounting frame;

[0024] Figure 3 This is a schematic diagram of the structure of a mounting bracket according to a specific embodiment of this application;

[0025] Figure 4 This is a schematic diagram of the mounting structure of multiple functional modules on a mounting rack according to a specific embodiment of this application;

[0026] Figure 5 This is a schematic diagram of the structure of a vertical take-off fixed-wing UAV according to a specific embodiment of this application, highlighting the lower side of the fuselage;

[0027] Figure 6 yes Figure 5 Enlarged view of point A in the middle;

[0028] Figure 7 This is a schematic diagram of the exploded wing structure of a vertical take-off fixed-wing UAV according to a specific embodiment of this application;

[0029] Figure 8 This is a schematic diagram of the structure of an antenna according to a specific embodiment of this application.

[0030] The meaning of each number in the diagram:

[0031] 100. Drones;

[0032] 10. Body; 11. Mounting cavity; 12. Connecting flange;

[0033] 20. Mounting bracket; 21. Main frame; 22. Mounting plate;

[0034] 30. Functional module; 31. Flight control module; 32. Sky-end module; 33. Power distribution board;

[0035] 40. Pod; 41. Pod body; 42. Mounting frame;

[0036] 50. Landing gear;

[0037] 60. Left wing;

[0038] 70. Right wing;

[0039] 80. Antenna; 81. Fixing component; 82. Rotating component; 83. Antenna body. Detailed Implementation

[0040] In the following detailed description, reference is made to the accompanying drawings, which form part of the detailed description and illustrate illustrative specific embodiments in which the present application may be practiced. In this regard, directional terms such as “top,” “bottom,” “left,” “right,” “up,” “down,” etc., are used with reference to the orientation of the described figures. Because components of the embodiments can be positioned in several different orientations, directional terms are used for illustrative purposes and are by no means limiting. It should be understood that other embodiments may be utilized or logical changes may be made without departing from the scope of the present application. Therefore, the following detailed description should not be taken in a limiting sense, and the scope of the present application is defined by the appended claims.

[0041] This application proposes a vertical take-off and landing (VTOL) fixed-wing unmanned aerial vehicle (UAV). The specific structure of the VTOL fixed-wing UAV according to an embodiment of this application will be described below with reference to the accompanying drawings.

[0042] Reference Figures 1-4 The vertical take-off and landing fixed-wing UAV 100 includes a fuselage 10. A mounting frame 20 is located inside the rear section of the fuselage 10. The mounting frame 20 adopts a stacked structure layout, and multiple functional modules 30 are stacked on the mounting frame 20. The stacked structure means that the multiple functional modules 30 are arranged sequentially from top to bottom on the mounting frame 20, and a certain gap can be set between adjacent functional modules 30 as needed. Therefore, the multiple functional modules 30 have a high degree of integration and a compact layout inside the fuselage 10, which can greatly reduce the size of the fuselage 10 and thus reduce the flight drag of the UAV 100.

[0043] Specifically, the mounting frame 20 includes a main frame 21 and several mounting plates 22. The main frame 21 is formed by the frame beams that constitute the fuselage 10. Several mounting plates 22 are fixed at intervals along the height direction of the main frame 21 on the inner side of the main frame 21, wherein the fixing method is to use screws for fixing.

[0044] The multiple functional modules 30 include a flight control module 31, a sky-end module 32, and a power distribution board 33. The flight control module 31 receives and processes data from various sensors of the UAV 100 to control the flight attitude, speed, and altitude of the UAV 100. The sky-end module 32 transmits images acquired by the UAV 100's pod 40 wirelessly. The power distribution board 33 distributes power to the various electrical devices of the UAV 100.

[0045] In this embodiment, there are two mounting plates 22. The flight control module 31 and the sky terminal module 32 are sequentially mounted on the two mounting plates 22. The power distribution board 33, due to its large size, is directly mounted on the main frame 21 at the bottom of the mounting bracket 20.

[0046] It is understood that in other implementations, other functional modules may also be included, such as a GPS module. The number of mounting plates may be set according to requirements, and the power distribution board may also be mounted on the mounting plate. There are no restrictions here.

[0047] Reference Figure 1 , Figure 5 and Figure 6 The vertical takeoff and landing fixed-wing UAV 100 also includes a pod 40 and landing gear 50. A mounting cavity 11 is provided on the lower front side of the fuselage 10, and the pod 40 is fixed in the mounting cavity 11. Due to the front-to-back mounting layout of the pod 40 and multiple functional modules 30, the center of gravity of the UAV 100 is located in the middle section of the fuselage 10. Therefore, the landing gear 50 is located on the lower middle section of the fuselage 10 (i.e., at the center of gravity), and the landing gear 50 and the pod 40 are offset from each other.

[0048] In one specific embodiment, the pod 40 includes a pod body 41 and a fixing frame 42, wherein the fixing frame 42 is fixed to the bottom of the mounting cavity 11 by locking screws, and the pod body 41 is fixedly connected to the fixing frame 42.

[0049] It should be noted that in traditional VTOL fixed-wing UAVs, the pod is usually mounted on the nose of the fuselage, resulting in significant wind resistance. Some VTOL fixed-wing UAVs, to avoid shifting the UAV's center of gravity when changing the pod, mount the pod directly in the middle of the fuselage (i.e., the UAV's center of gravity). In this case, the landing gear must also be mounted in the middle of the fuselage, which can interfere with the landing gear when the pod rotates significantly. This application addresses this by mounting the pod 40 on the lower front of the fuselage 10 to reduce wind resistance, and by integrating multiple functional modules 30 in the rear section of the fuselage 10 to reduce the overall size of the fuselage 10. This also ensures that the UAV 100's center of gravity is located in the middle of the fuselage 10. With the landing gear 50 mounted in the middle of the fuselage 10, the landing gear 50 is offset from the pod 40, preventing interference.

[0050] Reference Figure 7 and Figure 8 The vertical take-off fixed-wing UAV 100 also includes a left wing 60, a right wing 70, and an antenna 80. The left wing 60 and the right wing 70 are respectively located on both sides of the fuselage 10, and the antenna 80 is distributed on the lower sides of both sides of the fuselage 10 and extends downward.

[0051] Specifically, the fuselage 10 has connecting flanges 12 on both sides, and the left wing 60 and right wing 70 are respectively connected to the connecting flanges 12 on both sides. One end of the antenna 80 is fixed to the lower side of the connecting flange 12, and the other end extends vertically downward. In this way, the wings can protect the antenna 80 from rain to a certain extent, and the antenna 80 will not interfere with the airflow under the wings, thus not interfering with the take-off and landing of the UAV 100.

[0052] In one specific embodiment, two antennas 80 are respectively provided on the connecting flanges 12 on both sides of the fuselage 10, and the two antennas 80 on the same side are co-positioned along the length direction of the fuselage 10. Thus, when the UAV 100 is in flight, the two antennas 80 on the same side form only one drag surface, which reduces flight drag to a certain extent.

[0053] In one specific embodiment, the antenna 80 includes a fixing member 81, a rotating member 82, and an antenna body 83. The fixing member 81 is fixed to the lower side of the connecting flange 12 by a screw, the rotating member 82 is rotatably connected to the fixing member 81, and the antenna body 83 is hinged to the rotating member 82. Therefore, when the drone 100 needs to be packaged and transported, only the wings need to be removed, and the two antennas 80 can be rotated to a horizontal position for staggered storage without disassembly, greatly improving the convenience of packaging and transportation.

[0054] In summary, this application proposes a vertical takeoff and landing fixed-wing unmanned aerial vehicle (UAV) 100. The flight control module 31, the airborne terminal module 32, and the power distribution board 33, among other functional modules 30, are arranged in a stacked structure, resulting in a compact structure that allows for a smaller fuselage 10, thereby reducing flight drag. The pod 40 is positioned on the lower front section of the fuselage 10 to minimize flight drag. The landing gear 50 is located in the middle section of the fuselage 10 and offset from the pod 40, ensuring that the pod 40 is not interfered with by the landing gear 50 during significant rotation. Two sets of antennas 80 are arranged side-by-side on the connecting flange 12 of the fuselage 10. Firstly, during packaging, only the wings need to be removed; the antennas 80 can be folded and stored without disassembly. Secondly, the wings provide some protection against rain for the antennas 80, and the antennas 80 do not interfere with the airflow beneath the wings, thus not interfering with the takeoff and landing of the UAV 100.

[0055] It is obvious that those skilled in the art can make various modifications and alterations to the embodiments of this application without departing from the spirit and scope of this application. In this way, this application also aims to cover such modifications and alterations if they fall within the scope of the claims and their equivalents. The word "comprising" does not exclude the presence of other elements or steps not listed in the claims. The simple fact that certain measures are described in mutually different dependent claims does not indicate that a combination of these measures cannot be used for profit. Any reference numerals in the claims should not be considered limiting in scope.

Claims

1. A vertical take-off fixed wing drone comprising a fuselage, characterised in that, The machine body is equipped with a mounting frame, which adopts a stacked structure layout, and multiple functional modules are stacked on the mounting frame. The aforementioned functional modules include: The flight control module is configured to receive and process data from various sensors of the UAV in order to control the flight attitude, speed and altitude of the UAV; The aerial module is configured to transmit images captured by the drone's pod wirelessly. A power distribution board is configured to distribute power to the various electrical devices of the UAV.

2. The vertical take-off and fixed wing drone according to claim 1, wherein, The mounting frame includes a main frame and several mounting plates. The mounting plates are fixed at intervals along the height direction of the main frame inside the main frame, and at least the flight control module and the sky terminal module are respectively mounted on the mounting plates.

3. The vertical take-off and fixed wing drone of claim 1, wherein, It also includes a pod, and the lower front section of the fuselage has a mounting cavity, in which the pod is fixed.

4. The vertical take-off and fixed wing drone of claim 3, wherein, The pod includes a pod body and a mounting frame. The pod body is fixedly connected to the mounting frame, and the mounting frame is fixed in the mounting cavity by screws.

5. The vertical take-off fixed wing drone of claim 3, wherein, It also includes landing gear, which is located on the lower side of the middle section of the fuselage and is offset from the pod.

6. The vertical take-off fixed wing drone of claim 1, wherein, It also includes antennas, which are distributed on the lower sides of both sides of the fuselage and extend downward.

7. The vertical take-off fixed wing drone of claim 6, wherein, It also includes a left wing and a right wing, and the fuselage includes connecting flanges on both sides, with the left wing and the right wing respectively connected to the connecting flanges on both sides; One end of the antenna is fixed to the lower side of the connecting flange, and the other end extends downward.

8. The vertical take-off fixed wing drone of claim 6, wherein, Two antennas are respectively provided on both sides of the fuselage, and the two antennas on the same side are arranged in the same position along the length of the fuselage.

9. The vertical take-off fixed wing drone of claim 8, wherein, The antenna includes a fixed component, a rotating component, and an antenna body. The fixed component is fixedly connected to the fuselage, the rotating component is rotatably connected to the fixed component, and the antenna body is hinged to the rotating component.

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