An unmanned aerial vehicle

Abstract

The application discloses a kind of unmanned plane, unmanned plane includes wing and rotor, wherein, wing includes framework structure and skin structure, skin structure includes upper skin and lower skin, and framework structure is formed with lower skin between rotor accommodating portion.Rotor has working position and storage position, in storage position, rotor is stored in rotor accommodating portion, in working position, rotor extends out rotor accommodating portion.Such, by adopting hidden rotor telescopic vertical take-off and landing mode, the free switching between vertical motion and horizontal motion of unmanned plane is realized, the lift-drag ratio and aerodynamic efficiency of unmanned plane are improved, the area requirement to take-off and landing site is reduced, suitable for complex and changeable geographical environment, to complete air, ground, water surface and underwater shooting, surveying and mapping and covert etc. Designated task;And overall structure is simple, easy to install and maintain.In addition, rotor is hidden in lower skin, can play a protective role to rotor, to prolong the service life of unmanned plane.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a UAV. Background Art

[0002] Vertical take-off and landing fixed-wing drones combine the advantages of multi-rotor and fixed-wing aircraft, with the advantages of large payload, long flight time, high speed and vertical take-off and landing. Vertical take-off and landing drones are currently widely used in the drone field. Traditional vertical take-off and landing fixed-wing drones have the following problems:

[0003] 1. It uses an open rotor, which has low lift-drag ratio and lower aerodynamic efficiency than fixed-wing UAVs;

[0004] 2. Vertical take-off and landing rotor systems usually adopt a four-rotor layout, which has poor resistance to strong wind interference and low controllability. Summary of the Invention

[0005] In order to solve the above technical problems, the present invention provides a drone.

[0006] The present invention provides a drone, comprising:

[0007] A wing, the wing comprising a skeleton structure and a skin structure, the skin structure comprising an upper skin and a lower skin, a rotor accommodating portion being formed between the skeleton structure and the lower skin;

[0008] The rotor has a working position and a storage position. In the storage position, the rotor is stored in the rotor storage portion. In the working position, the rotor extends out of the rotor storage portion.

[0009] In some embodiments of the present invention, the lower skin includes a skin body and a linked skin movably connected to the skin body, the skin body is provided with an opening corresponding to the position of the rotor, and the linked skin is capable of opening and closing the opening, and the rotor accommodating portion is formed between the linked skin in a closed state and the skeleton structure;

[0010] When the linked skin is in an open state, the rotor can extend out of the rotor accommodating portion;

[0011] When the linked skin is in a closed state, the rotor is accommodated in the rotor accommodating portion.

[0012] In some embodiments of the present invention, the wing further includes a spar joint, which is arranged on the skeleton structure, and the spar joint is used to install a first drive motor, and the first drive motor is used to drive the rotor to rotate.

[0013] In some embodiments of the present invention, the skeleton structure comprises:

[0014] a spar structure, the spar structure comprising a first spar, a second spar, and a third spar spaced apart along a first direction;

[0015] a wing rib structure, the wing rib structure passing through the wing spar structure and connected to the wing spar structure, the wing rib structure comprising a wing root rib, a first wing rib, a second wing rib, and a wing tip rib spaced apart along a second direction, wherein the first direction is arranged at an angle to the second direction;

[0016] The spar joint is provided on the second spar and connected to the first spar and the third spar, and the spar joint is located between the wing root rib and the first rib.

[0017] In some embodiments of the present invention, the spar joint includes at least one guide groove structure and a first connecting structure, the first connecting structure is annular, the spar joint is connected to the second spar, the first spar, and the third spar via the first connecting structure, and the first drive motor is accommodated in the first connecting structure and can move axially along the first connecting structure;

[0018] The guide groove structure is formed by a portion of the first connection structure extending radially outward, and the guide groove structure is used to guide the axial movement of the first drive motor.

[0019] In some embodiments of the present invention, the first drive motor includes a motor sleeve and a motor body built into the motor sleeve, and a lifting block is provided at the end of the motor sleeve away from the rotor. The lifting blocks correspond one-to-one to the guide groove structures and can move along the guide groove structure.

[0020] In some embodiments of the present invention, the drone also includes a lifting mechanism connected to the first drive motor, the lifting mechanism is connected to the first drive motor through a second connecting structure, the lifting mechanism is accommodated in the space between the first wing beam and the second wing beam or in the space between the second wing beam and the third wing beam, and the second connecting structure is connected to the first drive motor through the first connecting structure.

[0021] In some embodiments of the present invention, the lifting mechanism includes a second drive motor, a gear connected to the drive shaft of the second drive motor, and a rack meshing with the gear, the extension direction of the rack is parallel to the axial direction of the first drive motor, and the second connecting structure is fixedly connected to the rack.

[0022] In some embodiments of the present invention, the lifting mechanism further includes a guide structure for guiding the movement of the rack, and the guide structure is fixed to the web of the second spar.

[0023] In some embodiments of the present invention, the lifting mechanism further includes a rack fixing structure, the guide structure guides the movement of the rack fixing structure, and the second connecting structure is fixedly connected to the rack via the rack fixing structure.

[0024] Beneficial Effects: The drone provided by the present invention includes wings and rotors, wherein the wings include a skeleton structure and a skin structure, the skin structure including an upper skin and a lower skin, and a rotor accommodating portion formed between the skeleton structure and the lower skin. The rotor has a working position and a storage position. In the storage position, the rotor is accommodated in the rotor accommodating portion, and in the working position, the rotor extends out of the rotor accommodating portion. Thus, by adopting a concealed rotor retractable vertical take-off and landing method, the drone can freely switch between vertical and horizontal movement, improve the drone's lift-to-drag ratio and aerodynamic efficiency, reduce the area required for take-off and landing sites, and be suitable for complex and changing geographical environments, thereby completing designated tasks such as aerial, ground, surface, and underwater photography, mapping, and concealment. Furthermore, by varying the lift generated by the two rotors, the drone has strong resistance to strong wind interference, high maneuverability, and a simple overall structure, making it easy to install and maintain. Furthermore, hiding the rotors in the lower skin can protect the rotors, thereby extending the drone's service life. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative work.

[0026] Figure 1 A schematic structural diagram of a lower skin provided according to an exemplary embodiment of the present invention;

[0027] Figure 2 A schematic structural diagram of a wing without a skin structure according to an exemplary embodiment of the present invention;

[0028] Figure 3 for Figure 2 A partial enlarged view of the middle part;

[0029] Figure 4 This is a schematic structural diagram of the cooperation between the first drive motor, the second drive motor and the rotor according to an exemplary embodiment of the present invention;

[0030] Figure 5A schematic diagram of the structure of the motor body and the rotor provided according to an exemplary embodiment of the present invention;

[0031] Figure 6 A schematic structural diagram of a wing without a skin structure provided according to another exemplary embodiment of the present invention;

[0032] Figure 7 for Figure 6 Enlarged view of point B in the middle.

[0033] The following are marked in the accompanying drawings:

[0034] 100, skeleton structure; 110, spar structure; 111, first spar; 112, second spar; 1121, through hole; 113, third spar; 120, rib structure; 121, root rib; 122, first rib; 123, second rib; 124, tip rib; 200, lower skin; 210, skin body; 220, linked skin; 230, opening; 300, rotor; 310, positioning plate; 5 00, wing beam joint; 510, guide groove structure; 520, first connecting structure; 600, first drive motor; 610, motor sleeve; 611, lifting block; 620, motor body; 710, second drive motor; 711, drive shaft; 720, gear; 730, rack; 740, guide structure; 750, rack fixing structure; 800, second connecting structure; X1, first direction; X2, second direction. DETAILED DESCRIPTION

[0035] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0036] References herein to "embodiments" mean that a particular feature, structure, or characteristic described in connection with the embodiments may be included in at least one embodiment of the present invention. The appearance of this phrase in various places in the specification does not necessarily refer to the same embodiment, nor does it constitute a separate or alternative embodiment that is mutually exclusive of other embodiments. It is understood, both explicitly and implicitly, by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0037] Related technologies employ open rotors, which have low lift-to-drag ratios during flight and lower aerodynamic efficiency than fixed-wing drones. This forces the wings to increase structural strength, which in turn increases aircraft weight and ultimately reduces performance. Furthermore, vertical take-off and landing (VTOL) rotor systems typically employ a quadrotor layout, a mechanical structure with four rotors. This requires four motors as the direct power source for flight and is controlled by varying the lift generated by the four rotors. This results in poor resistance to strong wind interference and low maneuverability.

[0038] Based on this, the present invention provides a drone that utilizes a concealed, retractable rotor for vertical takeoff and landing (VTOL) to achieve free switching between vertical and horizontal motion. This improves the drone's lift-to-drag ratio and aerodynamic efficiency, reduces the required takeoff and landing area, and is suitable for complex and changing geographical environments, enabling the completion of designated tasks such as aerial, ground, surface, and underwater photography, mapping, and concealment. Furthermore, the drone is controlled by varying the lift generated by its two rotors, resulting in strong resistance to strong wind interference, high maneuverability, and a simple overall structure for easy installation and maintenance. Furthermore, the rotors are concealed within the lower skin, protecting them and extending the drone's service life.

[0039] An exemplary embodiment of the present invention provides a drone, such as Figures 1 to 7 As shown, the UAV includes wings and rotors 300. The wings include a skeleton structure 100 and a skin structure. The skin structure includes an upper skin and a lower skin 200. A rotor accommodating portion is formed between the skeleton structure 100 and the lower skin 200. The rotors 300 have a working position and a storage position. In the storage position, the rotors 300 are accommodated in the rotor accommodating portion. In the working position, the rotors 300 extend out of the rotor accommodating portion.

[0040] In this embodiment, combined with Figure 1 、 Figure 2 and Figure 6The drone's wing consists of an upper and lower skin 200, and a skeleton structure 100. The skin structure is capable of withstanding local aerodynamic forces and forming the wing's shape. The upper skin of the skin structure abuts against the lower skin 200, enclosing the skeleton structure 100. A space, or rotor accommodating portion, is defined between the lower skin 200 and the skeleton structure 100. This space accommodates the rotors 300. When the drone is performing vertical takeoff and landing (VTOL), or when the rotors 300 are in operation, the rotors 300 extend out of the accommodating portion and rotate. When the drone is in horizontal flight, the rotors 300 retract into the accommodating portion. In this way, by adopting a concealed, retractable vertical takeoff and landing (VTOL) system with rotors 300, the drone can freely switch between vertical and horizontal motion, improving its lift-to-drag ratio and aerodynamic efficiency while reducing the required takeoff and landing area. This makes it suitable for complex and changing geographical environments, enabling the drone to complete designated tasks such as aerial, ground, surface, and underwater photography, mapping, and concealment. Furthermore, by varying the lift generated by the two rotors, the drone is highly resistant to strong wind interference, offers high maneuverability, and features a simple overall structure, making it easy to install and maintain. Furthermore, by concealing the rotors 300 within the lower skin 200, the rotors 300 are protected, thereby extending the drone's service life.

[0041] For example, the upper skin and the lower skin 200 and the skeleton structure 100 can be connected by rivet connection, adhesive connection, or a combination of rivet connection and adhesive connection. Of course, the upper skin and the lower skin 200 can also be formed as one piece.

[0042] For example, the material of the skin structure may be an aluminum-magnesium alloy plate, a titanium alloy plate, or a nylon and titanium alloy composite plate, etc., and this embodiment does not impose any limitation thereto.

[0043] In one embodiment, referring to Figure 1 The lower skin 200 includes a skin body 210 and a linkage skin 220 movably connected to the skin body 210. The skin body 210 is provided with an opening 230 corresponding to the position of the rotor 300. The linkage skin 220 can open and close the opening 230. When the linkage skin 220 is closed, a rotor accommodating portion is formed between the linkage skin 220 and the skeleton structure 100. When the linkage skin 220 is open, the rotor 300 can extend from the rotor accommodating portion. When the linkage skin 220 is closed, the rotor 300 is accommodated in the rotor accommodating portion.

[0044] In this embodiment, an opening 230 is provided on the lower skin 200 at a position corresponding to the rotor 300. A movable linkage skin 220 is provided at the opening 230 to open and close the opening 230. The linkage skin 220 and the rest of the lower skin 200, namely the skin body 210, together constitute the lower skin 200. The linkage skin 220 is movable relative to the skin body 210, having an open state and a closed state. In the closed state, the linkage skin 220 forms a rotor accommodating portion between the linkage skin 220 and the wing skeleton structure 100. When the drive motor is activated, the linkage skin 220 slowly moves until the opening 230 is fully opened. The rotor 300 then slowly extends out of the rotor accommodating portion and rotates, thereby generating lift for the drone. When the rotor 300 automatically folds and retracts into the rotor accommodating portion under the action of wind, the linkage skin 220 slowly moves in the opposite direction until the opening 230 is fully closed. In this way, it is possible to quickly switch from a vertical take-off and landing state to a fixed-wing flight state, realizing free switching between vertical and horizontal movements of the UAV, improving the lift-to-drag ratio and aerodynamic efficiency of the UAV. In addition, hiding the rotor 300 in the lower skin 200 can protect the rotor 300, thereby extending the service life of the UAV.

[0045] Exemplarily, the shape of the linkage skin 220 may be square or circular, etc., and of course, it may also be an irregular shape, as long as the rotor 300 can extend out of the lower skin 200. This embodiment does not impose any limitation here.

[0046] For example, the shape and size of the opening 230 may be set according to the shape and size of the linkage skin 220 .

[0047] In one embodiment, combining Figures 2 to 4 The wing further includes a spar joint 500 , which is disposed on the skeleton structure 100 . The spar joint 500 is used to install a first drive motor 600 , which is used to drive the rotor 300 to rotate.

[0048] In this embodiment, a spar joint 500 is further provided on the wing skeleton structure 100 , and a first drive motor 600 for driving the rotor 300 to rotate is installed in the spar joint 500 .

[0049] For example, the wing beam joint 500 can be integrally formed with the skeleton structure 100, so as to ensure the consistency of the force transmission path and reduce the weight of the wing. Of course, it can also be connected to the skeleton structure 100 by rivets, welding, etc., as long as the overall structural strength of the wing is guaranteed.

[0050] In one embodiment, the skeleton structure 100 includes a spar structure 110 and a rib structure 120. The spar structure 110 includes a first spar 111, a second spar 112, and a third spar 113 spaced apart along a first direction X1. The rib structure 120 passes through and is connected to the spar structure 110. The rib structure 120 includes a root rib 121, a first rib 122, a second rib 123, and a tip rib 124 spaced apart along a second direction X2. The first direction X1 and the second direction X2 form an angle. A spar joint 500 is provided on the second spar 112 and connected to the first spar 111 and the third spar 113. The spar joint 500 is located between the root rib 121 and the first rib 122.

[0051] In this embodiment, the wing adopts a three-beam structure, and the first wing beam 111, the second wing beam 112 and the third wing beam 113 are arranged at intervals along the first direction X1, wherein the first wing beam 111, the second wing beam 112 and the third wing beam 113 are close to one end of the fuselage (for example Figure 2 The distance between the ends (shown on the left side) is the same as the distance between the ends away from the fuselage (such as Figure 2 The distances between them are different, for example Figure 2 As shown in , the distance between the first spar 111 and the second spar 112 at the end close to the fuselage is greater than the distance between the ends away from the fuselage. The spar includes upper and lower flanges and a middle web, which bears most of the bending moment and shear force on the wing. Different structures are developed according to the specific force conditions, such as Figure 2 As shown, the first wing spar 111 and the third wing spar 113 are C-shaped structures, and the second wing spar 112 is an I-shaped structure, so that the strength and stability of the overall wing structure can be guaranteed.

[0052] The wing's rib structure 120 is arranged at an angle to the spar structure 110, supporting the spar web and improving its stability. It also transfers local aerodynamic forces transferred from the skin structure to the rib structure 120. The rib structure 120 includes a root rib 121, a first rib 122, a second rib 123, and a tip rib 124, arranged along a second direction X2 (from the wing root to the wing tail). Rib structure 120 passes through the web of spar structure 110 and connects to it. This ensures the strength, rigidity, and stability of the overall wing structure, thereby enhancing the performance of the drone.

[0053] The spar joint 500 is positioned on the second spar 112 and integrally formed with the second spar 112. It is also connected to the first spar 111 and the third spar 113, ensuring consistency in the force transmission path and preventing interruptions, thereby improving the stability of the overall wing structure. The spar joint 500 is located between the root rib 121 and the first rib 122. When the rotor 300 located below the spar joint 500 rotates, the drone can obtain sufficient lift, which helps improve the drone's performance.

[0054] Exemplarily, the structural shapes of the first spar 111, the second spar 112 and the third spar 113 can be set according to specific stress conditions. For example, the first spar 111 and the third spar 113 can also be I-shaped structures, and this embodiment does not impose any limitations here.

[0055] For example, the distances between the first wing beam 111, the second wing beam 112 and the third wing beam 113 can be set as needed, and the distances between the root rib 121, the first wing rib 122, the second wing rib 123 and the wing tip rib 124 can be set as needed, and this embodiment does not impose any limitations thereon.

[0056] For example, the spar structure 110 and the rib structure 120 may be connected by rivet connection, screw connection, or the like.

[0057] For example, the material of the flange of the spar may be a forged aluminum alloy or a high-strength aluminum alloy, and the material of the web may be a hard aluminum alloy, a titanium alloy, or the like.

[0058] In one embodiment, combining Figures 2 to 4 The spar joint 500 includes at least one guide groove structure 510 and a first connecting structure 520. The first connecting structure 520 is annular. The spar joint 500 is connected to the second spar 112, the first spar 111, and the third spar 113 via the first connecting structure 520. The first drive motor 600 is accommodated in the first connecting structure 520 and can move axially along the first connecting structure 520. The guide groove structure 510 is formed by a portion of the first connecting structure 520 extending radially outward. The guide groove structure 510 is used to guide the axial movement of the first drive motor 600.

[0059] In this embodiment, combined with Figures 2 to 4The wing beam joint 500 includes a first annular connecting structure 520 connected to the second wing beam 112, the first wing beam 111 and the third wing beam 113. The first connecting structure 520 has an accommodating space inside, and the first drive motor 600 is accommodated in it and can move upward or downward along the side wall of the first connecting structure 520, thereby driving the rotor 300 connected to the bottom of the first drive motor 600 to move downward to extend out of the rotor accommodating portion and move upward to be accommodated in the rotor accommodating portion.

[0060] The portion of the first connection structure 520 not connected to the spar structure 110 extends radially outward to form a guide groove structure 510. This guide groove structure 510 can cooperate with the first drive motor 600, allowing the first drive motor 600 to move upward or downward along the guide groove structure 510. In this way, the lifting and lowering movement of the rotor 300 is achieved, thereby hiding the rotor 300 in the lower skin 200, and being able to quickly switch from vertical take-off and landing mode to fixed-wing flight mode, realizing free switching between vertical and horizontal movement of the UAV, improving the lift-to-drag ratio and aerodynamic efficiency of the UAV, and also protecting the rotor 300, thereby extending the service life of the UAV.

[0061] For example, the number of the guide groove structures 510 can be set as needed, for example Figure 3 As shown in the figure, three guide groove structures 510 can be formed between the first wing spar 111 and the second wing spar 112, and between the second wing spar 112 and the third wing spar 113, respectively. In this way, the stability of the wing can be improved, thereby improving the performance of the UAV.

[0062] For example, refer to Figure 3 The upper end surface and the lower end surface of the guide groove structure 510 are both closed structures, which prevent the first drive motor 600 from over-travel, thereby ensuring the stability of the UAV operation.

[0063] For example, the first connecting structure 520 may also be in other shapes, such as an elliptical shape, a square shape, etc. The shape of the first driving motor 600 may be set according to the shape of the first connecting structure 520 , and this embodiment does not impose any limitation thereto.

[0064] In one embodiment, referring to Figures 3 to 7 The first drive motor 600 includes a motor cover 610 and a motor body 620 built into the motor cover 610. A lifting block 611 is provided at the end of the motor cover 610 away from the rotor 300. The lifting blocks 611 correspond one-to-one to the guide groove structures 510 and can move along the guide groove structure 510.

[0065] In this embodiment, first refer to Figure 3 and Figure 4A lifting block 611 is provided on the motor housing 610 of the first drive motor 600. The lifting block 611 is located at the end of the motor housing 610 away from the rotor 300, i.e., the upper side of the motor housing 610. The lifting block 611 can cooperate with the guide groove structure 510 of the spar joint 500, so that the first drive motor 600 can move upward or downward along the guide groove structure 510. Figure 5 As shown, the rotor 300 is also equipped with a positioning plate 310, which presses the rotor 300 and hinges it together. When the rotor 300 is deployed or retracted, it rotates relative to the positioning plate 310. The output shaft of the motor body 620 is fixedly connected to the positioning plate 310. Figure 6 and Figure 7 When the first drive motor 600 is activated, its output shaft drives the rotor 300 to unfold, generating lift. When the first drive motor 600 is deactivated, the rotor 300 automatically folds under the influence of the wind, retracting into its storage space. This allows the rotor 300 to ascend and descend, concealing it within the lower skin 200. This allows for rapid transition from vertical takeoff and landing to fixed-wing flight, enabling the drone to freely switch between vertical and horizontal motion. This improves the drone's lift-to-drag ratio and aerodynamic efficiency, while also protecting the rotor 300 and extending its service life.

[0066] Illustratively, the number of the lifting blocks 611 is the same as the number of the guide groove structures 510 . The size of the lifting blocks 611 can be set as needed, and this embodiment does not impose any limitation thereto.

[0067] For example, the motor cover 610 and the motor body 620 may be connected by bolt connection, thread connection, or the like.

[0068] In one embodiment, referring to Figures 2 to 4 The drone also includes a lifting mechanism (not shown in the figure) connected to the first drive motor 600. The lifting mechanism is connected to the first drive motor 600 through a second connecting structure 800. The lifting mechanism is accommodated in the space between the first wing beam 111 and the second wing beam 112 or in the space between the second wing beam 112 and the third wing beam 113. The second connecting structure 800 is connected to the first drive motor 600 through the first connecting structure 520.

[0069] In this embodiment, the drone also includes a lifting mechanism capable of driving the first drive motor 600 to move axially along the guide groove structure 510. The lifting mechanism is connected to the first drive motor 600 via a second connecting structure 800. A through hole 1121 is also defined on the sidewall of the first connecting structure 520 near the second spar 112, through which the second connecting structure 800 passes to connect with the first drive motor 600. The lifting mechanism can be accommodated in the space between the second spar 112 and the third spar 113, or alternatively, in the space between the first spar 111 and the second spar 112. The position of the through hole 1121 can be adjusted based on the desired location of the lifting mechanism. This allows for the lifting and lowering movement of the first drive motor 600, and thus the rotor 300, to be concealed within the lower skin 200. This allows for rapid transition from vertical takeoff and landing to fixed-wing flight, enabling the drone to freely switch between vertical and horizontal motion, improving the drone's lift-to-drag ratio and aerodynamic efficiency. Furthermore, the rotor 300 is protected, thereby extending the drone's service life.

[0070] For example, the material of the second connecting structure 800 can be high-strength aluminum alloy, titanium alloy, etc. The shape and size of the second connecting structure 800 can be set as needed, as long as the connection stability of the first drive motor 600 and the lifting mechanism is guaranteed. This embodiment does not make any restrictions here.

[0071] Exemplarily, the shape and size of the through hole 1121 may be set according to the shape and size of the second connection structure 800 .

[0072] In one embodiment, referring to Figure 4 The lifting mechanism includes a second drive motor 710, a gear 720 connected to the drive shaft 711 of the second drive motor 710, and a rack 730 meshing with the gear 720. The extension direction of the rack 730 is parallel to the axial direction of the first drive motor 600, and the second connecting structure 800 is fixedly connected to the rack 730.

[0073] In this embodiment, the second connecting structure 800 is fixedly connected to the rack 730 of the lifting mechanism, and the extension direction of the rack 730 is the same as the movement direction of the first drive motor 600. The lifting mechanism also includes a second drive motor 710 and a gear 720 meshing with the rack 730, wherein the gear 720 is connected to the drive shaft 711 of the second drive motor 710. The second drive motor 710 rotates by driving the gear 720, thereby driving the rack 730 to move upward or downward, and in turn driving the first drive motor 600 connected to the second connecting structure 800 to move upward or downward. In this way, the lifting and lowering movement of the rotor 300 can be achieved, and the rotor 300 is hidden in the lower skin 200, which can quickly switch from a vertical take-off and landing state to a fixed-wing flight state, realizing free switching between vertical and horizontal movement of the UAV, improving the lift-to-drag ratio and aerodynamic efficiency of the UAV, and protecting the rotor 300, thereby extending the service life of the UAV.

[0074] For example, the second drive motor 710 may be fixed to the web of the second spar 112 by bolt connection, thread connection, or the like.

[0075] For example, the second connection structure 800 and the rack 730 may be fixedly connected by welding, threaded connection, etc., and of course, they may also be integrally formed.

[0076] In one embodiment, continue to refer to Figure 4 The lifting mechanism further includes a guide structure 740 for guiding the movement of the rack 730 , and the guide structure 740 is fixed to the web of the second spar 112 .

[0077] In this embodiment, reference Figure 3 and Figure 4 The lifting mechanism also includes a guide structure 740, which includes a groove. The rack 730 is effectively assembled with the groove, so that the rack 730 can move upward or downward in the groove, thereby driving the first drive motor 600 to move upward or downward along the guide groove structure 510. In this way, the lifting movement of the rotor 300 can be realized, and the rotor 300 is hidden in the lower skin 200, and can be quickly switched from a vertical take-off and landing state to a fixed-wing flight state, realizing free switching between vertical and horizontal movements of the UAV, improving the lift-to-drag ratio and aerodynamic efficiency of the UAV, and also protecting the rotor 300, thereby extending the service life of the UAV.

[0078] For example, the guide structure 740 may be fixed to the web of the second spar 112 by bolt connection, thread connection, or the like.

[0079] In one embodiment, referring to Figure 4The lifting mechanism also includes a rack fixing structure 750 , the guide structure 740 guides the movement of the rack fixing structure 750 , and the second connecting structure 800 is fixedly connected to the rack 730 through the rack fixing structure 750 .

[0080] In this embodiment, Figure 4 As shown, the second connecting structure 800 is fixedly connected to the rack fixing structure 750. The rack fixing structure 750 includes a partial structure that matches the groove formed by the guide structure 740 and a partial structure for fixing the rack 730. When the second drive motor drives the gear 720 to rotate, thereby driving the rack 730 to move upward or downward, the rack fixing structure 750 can move upward or downward under the guidance of the guide structure 740, thereby driving the second connecting structure 800 and the first drive motor 600 to move upward or downward.

[0081] For example, the second connection structure 800 may be fixedly connected to the rack fixing structure 750 by means of threaded connection, welding, etc. Of course, it may also be integrally formed, and this embodiment does not impose any limitation thereto.

[0082] The contents described in the embodiments of this specification are merely an enumeration of the implementation forms of the inventive concept. The scope of protection of the present invention should not be regarded as limited to the specific forms described in the embodiments. The scope of protection of the present invention also includes equivalent technical means that can be thought of by those skilled in the art based on the inventive concept.

Claims

1. A drone, characterized in that: The drone includes: A wing, the wing comprising a skeleton structure and a skin structure, the skin structure comprising an upper skin and a lower skin, a rotor accommodating portion being formed between the skeleton structure and the lower skin; a rotor, the rotor having a working position and a storage position, wherein the rotor is stored in the rotor storage portion in the storage position and extends out of the rotor storage portion in the working position; The wing further includes a spar joint portion, the spar joint portion being arranged on the skeleton structure, the spar joint portion being used to mount a first drive motor, the first drive motor being used to drive the rotor to rotate; The wing beam joint includes at least one guide groove structure and a first connecting structure. The first drive motor is accommodated in the first connecting structure and can move axially along the first connecting structure. The guide groove structure is formed by a portion of the first connecting structure extending radially outward. The guide groove structure is used to guide the axial movement of the first drive motor.

2. The drone according to claim 1, characterized in that The lower skin includes a skin body and a linkage skin movably connected to the skin body, the skin body is provided with an opening corresponding to the position of the rotor, and the linkage skin can open and close the opening, and the rotor accommodating portion is formed between the linkage skin and the skeleton structure in a closed state; When the linked skin is in an open state, the rotor can extend out of the rotor accommodating portion; When the linked skin is in a closed state, the rotor is accommodated in the rotor accommodating portion.

3. The drone according to claim 1, wherein: The skeleton structure comprises: a spar structure, the spar structure comprising a first spar, a second spar, and a third spar spaced apart along a first direction; a wing rib structure, the wing rib structure passing through the wing spar structure and connected to the wing spar structure, the wing rib structure comprising a wing root rib, a first wing rib, a second wing rib, and a wing tip rib spaced apart along a second direction, wherein the first direction is arranged at an angle to the second direction; The spar joint is provided on the second spar and connected to the first spar and the third spar, and the spar joint is located between the wing root rib and the first rib.

4. The drone according to claim 3, characterized in that The first connecting structure is ring-shaped, and the spar joint is connected to the second spar, the first spar and the third spar through the first connecting structure.

5. The drone according to claim 4, characterized in that: The first drive motor includes a motor sleeve and a motor body built into the motor sleeve. A lifting block is provided at one end of the motor sleeve away from the rotor. The lifting blocks correspond one-to-one to the guide groove structures and can move along the guide groove structure.

6. The drone according to claim 4, characterized in that: The drone also includes a lifting mechanism connected to the first drive motor, the lifting mechanism being connected to the first drive motor via a second connecting structure, the lifting mechanism being accommodated in the space between the first wing spar and the second wing spar or in the space between the second wing spar and the third wing spar, and the second connecting structure being connected to the first drive motor through the first connecting structure.

7. The drone according to claim 6, characterized in that: The lifting mechanism includes a second drive motor, a gear connected to the drive shaft of the second drive motor, and a rack meshing with the gear. The extension direction of the rack is parallel to the axial direction of the first drive motor, and the second connecting structure is fixedly connected to the rack.

8. The drone according to claim 7, characterized in that: The lifting mechanism further includes a guide structure for guiding the movement of the rack, wherein the guide structure is fixed to the web of the second spar.

9. The drone according to claim 8, characterized in that The lifting mechanism further includes a rack fixing structure, the guide structure guides the movement of the rack fixing structure, and the second connecting structure is fixedly connected to the rack through the rack fixing structure.

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