Vertical fixed-wing unmanned aerial vehicle

Abstract

The utility model provides a vertical fixed-wing unmanned aerial vehicle which comprises a vehicle body, a fixed-wing unmanned aerial vehicle body, a fixed-wing unmanned aerial vehicle body and a fixed-wing unmanned aerial vehicle body, the multi-rotor wing assembly comprises a plurality of vertical rotor wings connected with the wings; wherein the wings are detachably connected to the fuselage through a first quick release assembly; the vertical rotor wing comprises a rotor wing body and a rotor wing arm, the rotor wing body is installed at one end of the rotor wing arm, and the other end of the rotor wing arm is rotatably connected to the wing through a folding assembly. According to the vertical fixed-wing unmanned aerial vehicle, the wings and the empennage on the two sides can achieve quick disassembly of the whole vehicle through the quick disassembly assemblies and the quick disassembly line connectors, the multi-rotor assemblies can be quickly unfolded and stored through the folding assemblies, and the main control plane and the tail control plane are designed to be of a hidden control plane steering engine, so that the size of the whole vehicle is reduced, and packaging and transportation are convenient.

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, the wings of existing vertical take-off and landing fixed-wing UAVs are usually fixedly connected to the UAV body, and the rotor arms are usually integrally formed with the wings. This makes the overall size of the aircraft relatively large, which is inconvenient during transportation and requires a large space for relocation and transport. Utility Model Content

[0004] To address the technical problems of existing vertical take-off and landing fixed-wing UAVs being large in size and inconvenient to package and transport, this application provides a vertical take-off and landing fixed-wing UAV.

[0005] This application proposes a vertical take-off and landing fixed-wing unmanned aerial vehicle, comprising:

[0006] The fuselage has two wings that serve as lifting surfaces;

[0007] A multi-rotor assembly, comprising a plurality of vertical take-off and landing rotors connected to the wing; wherein...

[0008] The wing is detachably connected to the fuselage via a first quick-release assembly;

[0009] The vertical take-off rotor includes a rotor body and a rotor arm. The rotor body is mounted on one end of the rotor arm, and the other end of the rotor arm is rotatably connected to the wing via a folding assembly.

[0010] Preferably, the vertical take-off rotor can be switched between an unfolded state and a retracted state via the folding assembly;

[0011] When the vertical take-off rotor is in the deployed state, the rotor arm is perpendicular to the wing;

[0012] When the vertical rotor is in the retracted state, the rotor arm is parallel to the wing.

[0013] Preferably, the first quick-release mechanism includes an elastic buckle, a ring hook, and a hanging lug;

[0014] The elastic buckle is rotatably mounted on the wing, the annular hook is rotatably connected to the elastic buckle, and the hanging ear is mounted on the fuselage and engages with the annular hook.

[0015] Preferably, the folding assembly includes a connecting seat, a rotating member, and a folding portion;

[0016] One end of the connecting seat is detachably connected to the fuselage, one end of the folding part is rotatably connected to the other end of the connecting seat via the rotating member, and the other end of the folding part is detachably connected to the rotor arm.

[0017] Preferably, the folding assembly further includes a locking sleeve, which is slidably fitted onto the folding portion and the connecting seat;

[0018] When the locking sleeve slides at least to cover the rotating member, the folded portion cannot rotate relative to the connecting seat;

[0019] When the locking sleeve disengages from the rotating member, the folded portion can rotate relative to the connecting seat.

[0020] Preferably, a limiting rod is provided at one end of the wing that connects to the fuselage, and a limiting hole is provided on the fuselage to engage with the limiting rod.

[0021] Preferably, the end of the wing that connects to the fuselage is provided with a signal line connector and a power line connector, wherein the power line connector is an aviation quick-release connector.

[0022] Preferably, the wing further includes a main control surface rotatably disposed on the wing, and a first drive assembly for driving the main control surface to rotate;

[0023] The first drive assembly includes a main servo motor, a servo arm, and an arm insert. The main servo motor is disposed inside the wing. The servo arm is connected to the output end of the main servo motor. One end of the arm insert engages with the servo arm, and the other end is connected to the main control surface.

[0024] Preferably, it also includes a tail fin, which is detachably connected to the fuselage via a second quick-release assembly;

[0025] The second quick-release component has the same structure as the first quick-release component.

[0026] Preferably, the tail fin further includes a tail control surface rotatably mounted on the tail fin, and a second drive assembly for driving the tail control surface to rotate.

[0027] The second driving component has the same structure as the first driving component.

[0028] Compared with the prior art, the beneficial results of this application are as follows:

[0029] (1) The wings and tail can be quickly disassembled by quick-release components and quick-release connectors, reducing the size of the packaging box and facilitating relocation and transportation.

[0030] (2) The multi-rotor assembly can be quickly unfolded and stored through the folding assembly, reducing the overall volume of the wings on both sides without disassembly, which further facilitates packaging and transportation.

[0031] (3) The main control surface and tail control surface adopt a hidden control surface servo design, which can not only reduce the space occupied by the UAV to a certain extent, but also effectively reduce the drag during flight. Attached Figure Description

[0032] 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.

[0033] Figure 1 This is a schematic diagram of the overall structure of a vertical take-off and landing fixed-wing UAV in the deployed state according to an embodiment of this application.

[0034] Figure 2 yes Figure 1 Enlarged view of point A in the middle;

[0035] Figure 3 This is a structural schematic diagram illustrating the wing end face according to an embodiment of this application;

[0036] Figure 4 This is a schematic diagram of the wing structure when the vertical take-off rotor is in the retracted state according to an embodiment of this application;

[0037] Figure 5 This is a schematic diagram of the airfoil structure when the vertical take-off rotor is in the deployed state according to an embodiment of this application;

[0038] Figure 6 This is a schematic diagram of the installation structure of the folding assembly when the vertical rotor is in the retracted state, according to an embodiment of this application.

[0039] Figure 7 This is a schematic diagram of the installation structure of the folding assembly when the vertical take-off rotor is in the deployed state, according to an embodiment of this application.

[0040] Figure 8 This is an exploded view of the folding assembly according to an embodiment of this application;

[0041] Figure 9 This is a structural schematic diagram of a vertical take-off and landing fixed-wing UAV according to an embodiment of this application, highlighting the main servo motor;

[0042] Figure 10 yes Figure 9 Enlarged view of point B in the middle.

[0043] The meanings of the numbers in the diagram are as follows: 100, UAV; 10, fuselage; 20, wing; 21, limit rod; 22, signal line connector; 23, power line connector; 24, main control surface; 30, tail fin; 31, tail control surface; 40, multi-rotor assembly; 41, vertical rotor; 411, rotor body; 412, rotor arm; 50, tail thrust rotor; 60, first quick-release assembly; 61, elastic buckle; 62, ring hook; 63, lug; 70, folding assembly; 71, connecting seat; 711, external thread; 72, rotating part; 73, folding part; 74, locking sleeve; 741, internal thread; 80, first drive assembly; 81, main servo; 82, servo rocker arm; 83, rocker arm insert. Detailed Implementation

[0044] 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.

[0045] This application proposes a vertical take-off and landing fixed-wing unmanned aerial vehicle (UAV). The specific structure of the UAV according to the embodiments of this application will be described below with reference to the accompanying drawings.

[0046] Please see Figures 1-10 The unmanned aerial vehicle (UAV) 100 includes a fuselage 10, wings 20 on both sides of the fuselage 10, a tail 30 at the rear of the fuselage 10, a multi-rotor assembly 40, and a tail thruster 50. The multi-rotor assembly 40 includes four vertical take-off rotors 41 connected to the wings 20 on both sides in pairs, and the tail thruster 50 is located at the end of the fuselage 10.

[0047] Understandably, the two wings 20 are symmetrically arranged on both sides of the fuselage 10, serving as fixed wings to provide lift for the UAV 100; the tail fin 30 can be used to adjust the flight attitude of the UAV 100; the multi-rotor assembly 40 generates lift through four vertical take-off and landing rotors 41, enabling the UAV 400 to rise vertically to a designated height in rotor mode. When the UAV 100 reaches the designated height, the tail thrust rotor 50 starts to work and generate thrust. When the airspeed of the UAV 100 reaches a certain level, the lift generated by the wings 20 balances with gravity, at which point the vertical take-off and landing rotors 41 stop working, and the UAV 100 performs its flight mission in fixed-wing mode. After the UAV 100 completes its mission, it flies back to the take-off and landing point. At this point, the tail thrust rotor 50 stops working, and multiple vertical take-off and landing rotors 41 start working, allowing the UAV 100 to land at the take-off and landing point in rotor mode.

[0048] It should be noted that in this embodiment, four vertical rotors 41 are provided. In other embodiments, there may be three, five, or more vertical rotors.

[0049] Further, please refer to Figure 1 and Figure 2 The wings 20 on both sides are detachably connected to the sides of the fuselage 10 via the first quick-release assembly 60; the tail 30 is a "V-shaped tail", and the tail 30 on both sides is detachably connected to the rear of the fuselage 10 via the second quick-release assembly (not shown in the figure).

[0050] In this embodiment, the first quick-release component 60 and the second quick-release component have the same structure. The first quick-release component 60 will be described in detail below as an example.

[0051] Specifically, the first quick-release assembly 60 includes an elastic buckle 61, an annular hook 62, and a lug 63. The elastic buckle 61 is rotatably mounted on the wing 20, the annular hook 62 is rotatably connected to the elastic buckle 61, and the lug 63 is fixedly mounted on the fuselage 10 and forms a snap-fit ​​relationship with the annular hook 62, thereby achieving a fixed connection between the wing 20 and the fuselage 10.

[0052] In this embodiment, each wing 20 is provided with two sets of first quick-release components 60.

[0053] Further, please refer to Figure 3 A limiting rod 21 is provided on one end face of the wing 20 that connects to the fuselage 10, and a limiting hole (not shown in the figure) is provided on the corresponding position of the fuselage 10 to engage with the limiting rod 21. The connection strength between the wing 20 and the fuselage 10 can be improved by engaging the limiting rod 21 and the limiting hole.

[0054] In this embodiment, two limiting rods 21 are symmetrically arranged on the wing 20 to further improve the connection strength between the wing 20 and the fuselage 10.

[0055] Further reading Figure 3 The end face of the wing 20 connecting to the fuselage 10 is also equipped with a signal line connector 22 and a power line connector 23, wherein the power line connector 23 adopts an aviation quick-release connector. By adopting an aviation quick-release connector, the wing 20 can be quickly connected and stored.

[0056] In this embodiment, the signal line connector 22 and the power line connector 23 are disposed between the two limit rods 21.

[0057] In this way, the two wings 20 can be quickly disassembled through the first quick-release assembly 60 and the quick-release cable connector, and the tail fin 30 can be quickly disassembled through the second quick-release assembly, thereby realizing the quick disassembly of the whole aircraft, reducing the size of the packaging box, and facilitating relocation and transportation.

[0058] Further, please refer to Figure 4 and Figure 5 The vertical take-off rotor 41 has an deployed state and a retracted state, and can switch between the two states via a folding assembly 70. The vertical take-off rotor 41 includes a rotor body 411 and a rotor arm 412. The rotor body 411 is mounted on one end of the rotor arm 412, and the other end of the rotor arm 412 is rotatably connected to the wing 20 via the folding assembly 70. When the vertical take-off rotor 41 is in the deployed state, the rotor arm 412 is perpendicular to the wing 20; when the vertical take-off rotor 41 is in the retracted state, the rotor arm 412 is parallel to the wing 20.

[0059] For details, please refer to Figures 6-8 The folding assembly 70 includes a connecting base 71, a rotating member 72, a folding portion 73, and a locking sleeve 74. One end of the connecting base 71 is detachably connected to the fuselage 10. One end of the folding portion 73 is rotatably connected to the other end of the connecting base 71 via the rotating member 72. The other end of the folding portion 73 is detachably connected to the rotor arm 412. The locking sleeve 74 is slidably fitted onto the folding portion 73 and the connecting base 71. When the locking sleeve 74 slides at least to cover the rotating member 72, the folding portion 73 cannot rotate relative to the connecting base 71. When the locking sleeve 74 disengages from the rotating member 72, the folding portion 73 can rotate relative to the connecting base 71, thereby achieving the locking function.

[0060] In this embodiment, one end of the connector 71 is detachably connected to the body 10 by a clamping method. In other embodiments, the connector 71 can also be detachably connected to the body by means of screwing, plugging, snapping, etc., which is not limited here.

[0061] In this embodiment, the rotating member 72 is a pin, and one end of the folding part 73 is rotatably connected to the other end of the connecting seat 71 via the pin. In other embodiments, the folding part can also be rotatably connected to the connecting seat by means of hinge or other methods, which is not limited here.

[0062] In this embodiment, the other end of the folding part 73 is detachably connected to the rotor arm 412 by riveting. In other embodiments, the folding part can also be detachably connected to the rotor arm by means of clamping, screwing, plugging, snapping, etc., which is not limited here.

[0063] Further, please refer to Figure 7 In this embodiment, in the unfolded state, the locking sleeve 74 slides to the position of the connecting seat 71 and is fixedly connected to the connecting seat 71, so that the folded part 73 cannot rotate relative to the connecting seat 71. In other embodiments, the locking sleeve may simply slide to cover the rotating member and be fixedly connected to the rotating member, so that the folded part cannot rotate relative to the connecting seat.

[0064] Further, please refer to Figure 8 In this embodiment, the outer circumferential surface of the connecting seat 71 is provided with an external thread 711, and the inner circumferential surface of the locking sleeve 74 is provided with an internal thread 741. The locking sleeve 74 and the connecting seat 71 are connected by the mating of the internal thread 741 and the external thread 711. In other embodiments, the locking sleeve and the connecting seat can also be detachably connected by other connection methods such as snap-fit, which is not limited here.

[0065] Further, please refer to Figure 6 In this embodiment, in the retracted state, the locking sleeve 74 disengages from the rotating member 72 and slides onto the rotor arm 412, allowing the folded portion 73 to rotate relative to the connecting seat 71. In other embodiments, the locking sleeve may simply disengage from the rotating member and slide onto the folded portion, allowing the folded portion to rotate relative to the connecting seat; this is not a limitation.

[0066] In this way, the multi-rotor assembly 40 can be quickly unfolded and stored through the folding assembly 70, reducing the overall volume of the two wings 20 without disassembly, further facilitating packaging and transportation.

[0067] Further, please refer to Figure 1 , Figure 9 and Figure 10 The wing 20 also includes a main control surface 24 rotatably disposed on one side of the wing 20, and a first drive assembly 80 for driving the main control surface 24 to rotate; the tail 30 also includes a tail control surface 31 rotatably disposed on one side of the tail 30, and a second drive assembly (not shown in the figure) for driving the tail control surface 31 to rotate.

[0068] In this embodiment, the first driving component 80 and the second driving component have the same structure. The first driving component 80 will be described in detail below.

[0069] For details, please refer to Figure 9 and Figure 10 The first drive assembly 80 includes a main servo motor 81, a servo rocker arm 82, and a rocker arm insert 83. The main servo motor 81 is hidden inside the wing 20. The servo rocker arm 82 is connected to the output end of the main servo motor 81. One end of the rocker arm insert 83 cooperates with the servo rocker arm 82, and the other end is fixedly connected to the main control surface 24.

[0070] Thus, the main control surface 24 and the tail control surface 31 adopt a hidden control surface and servo design, which can not only reduce the space occupied by the UAV 100 to a certain extent, but also effectively reduce the drag during flight.

[0071] In summary, this application proposes a vertical take-off and landing fixed-wing unmanned aerial vehicle (UAV) 100. Its two wings 20 and tail 30 can be quickly disassembled using quick-release components and quick-release connectors. The multi-rotor assembly 40 can be quickly unfolded and stored using a folding assembly 70, reducing the overall volume of the two wings 20 without disassembly, thereby reducing the size of the packaging box and facilitating relocation and transportation. The main control surface 24 and tail control surface 31 adopt a concealed control surface and servo design, which not only further reduces the overall space occupied by the UAV 100 to a certain extent, but also effectively reduces drag during flight.

[0072] 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, characterized in that, The utility model relates to a kind of multi-rotor aircraft, including: Machine body, the machine body has two wings as lifting surface; Multi-rotor assembly, the multi-rotor assembly includes multiple vertical rotors connected with the wing; Wherein, the wing is detachably connected to the machine body by first quick-release assembly; The vertical rotor includes rotor body and rotor arm, the rotor body is installed at one end of the rotor arm, and the other end of the rotor arm is rotatably connected to the wing by folding assembly.

2. The vertical take-off and fixed wing drone according to claim 1, wherein, The vertical rotor can be switched between the unfolded state and the storage state by the folding assembly; When the vertical rotor is in the unfolded state, the rotor arm is perpendicular to the wing; When the vertical rotor is in the storage state, the rotor arm is parallel to the wing.

3. The vertical take-off and fixed wing drone of claim 1, wherein, The first quick-release assembly includes elastic buckle, ring-shaped hook and ear hook; The elastic buckle is rotatably arranged on the wing, the ring-shaped hook is rotatably connected to the elastic buckle, and the ear hook is arranged on the machine body and buckled with the ring-shaped hook.

4. The vertical take-off fixed wing drone of claim 1, wherein, The folding assembly includes connecting seat, rotating part and folding part; One end of the connecting seat is detachably connected to the machine body, one end of the folding part is rotatably connected to the other end of the connecting seat by the rotating part, and the other end of the folding part is detachably connected to the rotor arm.

5. A vertical take-off fixed wing drone according to claim 4, wherein, The folding assembly further includes locking sleeve, which is slidably sleeved on the folding part and the connecting seat; When the locking sleeve at least slides to cover the rotating part, the folding part cannot rotate relative to the connecting seat; When the locking sleeve is separated from the rotating part, the folding part can rotate relative to the connecting seat.

6. The vertical take-off fixed wing drone of claim 1, wherein, The end of the wing connected to the machine body is extended to provide a limiting rod, and the machine body is provided with a limiting hole for plug-in cooperation with the limiting rod.

7. The vertical take-off fixed wing drone of claim 1, wherein, The end of the wing connected to the machine body is provided with signal line connector and power line connector, wherein the power line connector is an aviation quick-release connector.

8. The vertical take-off fixed wing drone of claim 1, wherein, The wing further includes a main control surface rotatably arranged on the wing, and a first drive assembly for driving the main control surface to rotate; The first drive assembly includes a main rudder, a rudder rocker arm and a rocker arm insert, the main rudder is arranged inside the wing, the output end of the main rudder is connected to the rudder rocker arm, one end of the rocker arm insert is matched with the rudder rocker arm, and the other end is connected to the main control surface.

9. The vertical take-off fixed wing drone of claim 8, wherein, It further includes a tail wing, which is detachably connected to the machine body by a second quick-release assembly; Wherein, the second quick-release assembly is consistent with the first quick-release assembly in structure.

10. The vertical take-off fixed wing drone of claim 9, wherein, The tail wing further includes a tail control surface rotatably arranged on the tail wing, and a second drive assembly for driving the tail control surface to rotate; Wherein, the second drive assembly is consistent with the first drive assembly in structure.

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