Fuselage structure and unmanned aerial vehicle

Abstract

The utility model discloses a fuselage structure and an unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles. The fuselage structure comprises a first structural part and a second structural part, and the second structural part and the first structural part can move relatively, so that the fuselage structure can be converted between a first form and a second form; wherein at least one of the first structural part and the second structural part forms an avoiding space, and in the first form, at least part of the other one of the first structural part and the second structural part is contained in the avoiding space. By applying the fuselage structure, the size of the unmanned aerial vehicle can be reduced, and the damage risk of the unmanned aerial vehicle is reduced.

Description

TECHNICAL FIELD

[0001] The present application relates to, but is not limited to, the technical field of unmanned aerial vehicles, and particularly relates to a fuselage structure and an unmanned aerial vehicle. BACKGROUND

[0002] An unmanned aerial vehicle is an unmanned aerial vehicle that is controlled by radio remote control equipment and self-provided program control device. In the related art, the overall size of the unmanned aerial vehicle is large, and a lot of space is occupied during storage or transportation of the unmanned aerial vehicle. CONTENT

[0003] The fuselage structure and the unmanned aerial vehicle provided by the present application can reduce the size of the unmanned aerial vehicle and reduce the damage risk of the unmanned aerial vehicle.

[0004] In one aspect, the present application provides a fuselage structure, which includes a first structural member and a second structural member. The second structural member is movable relative to the first structural member, so that the fuselage structure can be transformed between a first mode and a second mode. At least one of the first structural member and the second structural member is formed with an avoiding space. In the first mode, at least part of the other of the first structural member and the second structural member is accommodated in the avoiding space.

[0005] The fuselage structure provided by the present application can be transformed between the first mode and the second mode by the relative movement of the first structural member and the second structural member. When the unmanned aerial vehicle is not in flight or needs to be compactly stored (in the first mode), the first structural member and the second structural member can be accommodated in the avoiding space of the other by relative movement, so as to reduce the overall size of the first structural member and the second structural member, thereby reducing the space occupation of the unmanned aerial vehicle and facilitating the miniaturization and thinning of the unmanned aerial vehicle. Meanwhile, since the avoiding space can accommodate at least part of the first structural member or the second structural member, the part accommodated in the avoiding space (such as a wing, a propeller, a functional device, etc.) can be protected by the structure of the avoiding space, so as to reduce the collision or abrasion of the accommodated part, thereby reducing the damage risk of the unmanned aerial vehicle. In one possible implementation manner of the present application, the first structural member includes a first avoiding space and a first protruding portion, and the second structural member includes a second avoiding space and a second protruding portion. In the first mode, at least part of the first protruding portion is located in the second avoiding space, and at least part of the second protruding portion is located in the first avoiding space.

[0006] In one possible implementation manner of the present application, at least one end of the avoiding space penetrates the corresponding first structural member or second structural member.

[0007] In a possible implementation of the present application, the first structural member and the second structural member each include a first structural surface and a second structural surface, the avoiding space forms an opening on the first structural surface and penetrates through the second structural surface; the second structural surface is arranged opposite to the first structural surface; or, the second structural surface is arranged adjacent to the first structural surface.

[0008] In a possible implementation of the present application, the first structural member and the second structural member are arranged in relative rotation through a shaft body; the penetration direction of the avoiding space is parallel to the central axis of the shaft body, and / or the penetration direction of the avoiding space is arranged at an angle with the central axis of the shaft body.

[0009] In a possible implementation of the present application, the first structural member and the second structural member each include a first structural surface, the avoiding space forms an opening on the first structural surface; the first structural surface is provided with at least two openings, the length directions of the at least two openings are parallel to each other; or, the length directions of the at least two openings are arranged at an angle.

[0010] In a possible implementation of the present application, the first structural member or the second structural member includes a protruding part accommodated in the avoiding space; in the first mode, the outer surface of the protruding part is fitted with the inner surface of the avoiding space; or, the outer surface of the protruding part is arranged in a spaced manner with the inner surface of the avoiding space.

[0011] On the other hand, the present application provides a UAV, which includes the fuselage structure, the central body and the power assembly of any one of the above, the central body is provided with the first structural member and the second structural member; the power assembly is arranged corresponding to the first structural member and the second structural member respectively.

[0012] In a possible implementation of the present application, one of the first structural member and the second structural member is arranged in relative fixation with the central body, and the other is arranged in relative movement with the central body.

[0013] In a possible implementation of the present application, the UAV further includes a locking structure, a first part of the locking structure is connected to the second structural member, a second part of the locking structure is connected to the first structural member or the central body; the locking structure is used for locking or unlocking the relative movement of the first structural member and the second structural member.

[0014] In a possible implementation of the present application, the first structural member and the second structural member are respectively provided with a mounting position, the mounting position is used for mounting the power assembly, and the power assembly is used for driving the movement of the fuselage structure.

[0015] In a possible implementation of the present application, the UAV further includes an electronic device, the electronic device includes an active state and a disabled state; in response to the UAV switching from the first mode to the second mode, the electronic device is switched to the active state; in response to the UAV switching from the second mode to the first mode, the electronic device is switched to the disabled state.

[0016] The unmanned aerial vehicle provided by the present application has the same technical effects as the fuselage structure, i.e., the volume of the unmanned aerial vehicle is reduced, and the damage risk of the unmanned aerial vehicle is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 A structural schematic view of a first mode of the fuselage structure provided by the embodiment of the present application is shown in the figure.

[0018] Figure 2 A structural schematic view of a second mode of the fuselage structure provided by the embodiment of the present application is shown in the figure.

[0019] Figure 3 A front view of the second mode of the fuselage structure provided by the embodiment of the present application is shown in the figure.

[0020] Figure 4 A front view of the first mode of the fuselage structure provided by the embodiment of the present application is shown in the figure.

[0021] Figure 5 One of the bottom views of the second mode of the fuselage structure provided by the embodiment of the present application is shown in the figure.

[0022] Figure 6 A bottom view of the first mode of the fuselage structure provided by the embodiment of the present application is shown in the figure.

[0023] Figure 7 The second mode of the fuselage structure provided by the embodiment of the present application is shown in the figure.

[0024] Figure 8 The bottom view of the second mode of the fuselage structure provided by the embodiment of the present application is shown in the figure.

[0025] Figure 9 The second mode of the fuselage structure provided by the embodiment of the present application is shown in the figure.

[0026] REFERENCE SIGNS:

[0027] 1-first structural member; 11-first protrusion; 12-first structural surface; 13-second structural surface; 14-mounting position; 2-second structural member; 21-second protrusion; 3-avoidance space; 31-first avoidance space; 32-second avoidance space; 4-shaft body; 5-central body; 6-locking structure; 61-first part; 62-second part; 7-electronic device; Z-thickness direction of the fuselage structure; Y-length direction of the fuselage structure; X-width direction of the fuselage structure. DETAILED DESCRIPTION

[0028] In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the following will further describe the specific technical solutions of the present application with reference to the drawings in the embodiments of the present application. The following embodiments are used to explain the present application, but not to limit the scope of the present application.

[0029] In the embodiments of the present application, the terms "first", "second" are only used for descriptive purpose, and should not be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features defined with "first", "second" can explicitly or implicitly include one or more of the features. In the description of the embodiments of the present application, unless otherwise specified, the meaning of "a plurality of" is two or more.

[0030] In addition, in the embodiments of the present application, the orientation terms such as "upper", "lower", "left" and "right" are defined with respect to the orientation of the components shown in the drawings, and it should be understood that these directional terms are relative concepts, which are used for relative description and clarification, and can be changed accordingly according to the change of the orientation of the components placed in the drawings.

[0031] In the embodiments of the present application, unless otherwise specified and limited, the term "connection" should be understood in a broad sense, for example, "connection" can be fixed connection, or detachable connection, or integral; can be directly connected, or indirectly connected through intermediate medium.

[0032] In the embodiments of the present application, the term "include", "contain" or any other variant thereof is intended to cover non-exclusive inclusion, so that the process, method, article or device including a series of elements not only includes those elements, but also includes other elements not explicitly listed, or includes elements inherent to such process, method, article or device. Without more limitation, the element defined by the sentence "including a…" does not exclude the existence of other same elements in the process, method, article or device including the element.

[0033] In the embodiments of the present application, the words such as "exemplary" or "for example" are used to mean an example, illustration or description. Any embodiment or design scheme described as "exemplary" or "for example" in the embodiments of the present application should not be interpreted as more preferred or more advantageous than other embodiments or design schemes. Rather, the words such as "exemplary" or "for example" are intended to present the relevant concept in a specific manner.

[0034] Referring to Figure 1 , Figure 2 , Figure 3 and Figure 4This application provides a fuselage structure, which includes a first structural member 1 and a second structural member 2. The second structural member 2 and the first structural member 1 are movable relative to each other so that the fuselage structure can be transformed between a first form and a second form. In the first form, at least one of the first structural member 1 and the second structural member 2 forms a clearance space 3. In the first form, at least a portion of the other one of the first structural member 1 and the second structural member 2 is accommodated in the clearance space 3.

[0035] In this embodiment, the second structural member 2 and the first structural member 1 can move relative to each other. Since the first structural member 1 and the central body 5 are relatively fixedly connected, it can be understood that the second structural member 2 can move relative to the central body 5. The second structural member 2 can be connected to the central body 5 or to the first structural member 1; the specific connection relationship can be a sliding connection, a rotational connection, a swing connection, etc.

[0036] Reference Figure 1 and Figure 2 In this embodiment of the application, the first structural member 1 and the second structural member 2 can move relative to each other, so that the drone has different first and second forms. The first form may include the form in which the drone is in storage and transportation, and the second form may include the form in which the drone is in flight or working.

[0037] In this embodiment, the first structural component 1 and the second structural component 2 can be understood as the wings of the UAV, and the relative movement between the wings allows the UAV to switch between different states such as folded or unfolded. It should be added that the first structural component 1 and the second structural component 2 can also be understood as other structures, such as rotors, propellers, tail fins, stabilizing fins, payload mounting structures, or other innovative structures, etc., and this application does not limit them in this regard.

[0038] In this embodiment of the application, when the second structural member 2 rotates relative to the central body 5 or the first structural member 1, it can be understood that the first form includes the case where the first structural member 1 and the second structural member 2 are folded together by rotation. The folded form is usually the non-flight stage of the UAV, such as transportation, storage or operation in a confined space; the second form includes the first structural member 1 and the second structural member 2 being rotated and unfolded to the position where the UAV works, thereby meeting different flight mission requirements.

[0039] In this embodiment of the application, the clearance space 3 may be a groove or recessed structure provided inside or on the surface of the first structural member 1 or the second structural member 2, or a hollow structure with an opening. The size and shape of the clearance space 3 are capable of accommodating at least a portion of the second structural member 2 or the first structural member 1.

[0040] In this embodiment, the clearance space 3 may be provided on the first structural member 1, on the second structural member 2, or on both the first structural member 1 and the second structural member 2. The clearance space 3 may contain a portion of the first structural member 1 or the second structural member 2, a functional device provided on the first structural member 1 or the second structural member 2, or a part of a protective cover on the first structural member 1 or the second structural member 2. This application does not limit the scope of the application.

[0041] The technical solution provided in this application embodiment, in a first configuration, at least a portion of the other of the first structural member 1 and the second structural member 2 is accommodated in the clearance space 3. This not only helps reduce the size of the drone in the first configuration (not working or stored) and improves space utilization, but also protects the structure accommodated in the clearance space 3 and reduces damage to the drone. Simultaneously, when the drone needs to transition from the first configuration to the second configuration to perform a specific task, the second structural member 2 can be removed from the clearance space 3 and deployed so that the drone can perform the task.

[0042] The fuselage structure provided in this application embodiment allows the first structural member 1 and the second structural member 2 to move relative to each other, enabling the fuselage structure to transform between a first form and a second form. Since at least one of the first structural member 1 and the second structural member 2 forms a clearance space 3, when the drone is not flying or needs to be compactly stored (first form), the first structural member 1 and the second structural member 2 can move relative to each other, allowing at least a portion of one of the first structural member 1 and the second structural member 2 to be accommodated within the clearance space 3 of the other. This reduces the overall volume of the first structural member 1 and the second structural member 2, thereby reducing the space occupied by the drone and contributing to its miniaturization and thinning. Simultaneously, since the clearance space 3 can accommodate at least a portion of the first structural member 1 or the second structural member 2, the portion accommodated within the clearance space 3 (such as wings, propellers, functional components, etc.) can be protected by the clearance space 3 structure, reducing the risk of collision or wear on the accommodated portion and thus reducing the risk of damage to the drone.

[0043] Reference Figure 1 , Figure 2 , Figure 3 and Figure 4 In some possible embodiments of this application, the first structural member 1 includes a first clearance space 313 and a first protrusion 11, and the second structural member 2 includes a second clearance space 323 and a second protrusion 21; in a first configuration, at least a portion of the first protrusion 11 is located in the second clearance space 323, and at least a portion of the second protrusion 21 is located in the first clearance space 313.

[0044] In this embodiment, the first clearance space 313 can be a groove or cavity on the first structural member 1. The first clearance space 313 provides a receiving space for the second protrusion 21 of the second structural member 2, so that when the first structural member 1 and the second structural member 2 are in the first configuration, the second protrusion 21 can be accommodated within the first clearance space 313. The first clearance space 313 can be adjusted in shape and size according to the actual needs of the second protrusion 21. For example, the first clearance space 313 can be rectangular, circular, elliptical, or other irregular shapes.

[0045] In this embodiment, the second clearance space 323 can also be adjusted according to the structure of the first protrusion 11 so that when the first structural member 1 and the second structural member 2 are in the first form, the first protrusion 11 can be accommodated in the second clearance space 323.

[0046] It should be added that the first protrusion 11 and the second protrusion 21 can each be provided as one, or multiple, or one can be provided as one and the other as multiple. This application does not limit this.

[0047] In this embodiment, the shapes of the first protrusion 11 and the second protrusion 21 can be designed according to actual needs, such as cylindrical, conical, polygonal, etc., to adapt to different working requirements. The first protrusion 11 and the second protrusion 21 can also integrate other functional components, such as sensors, actuators, lighting equipment, etc., to achieve multi-functional integration and intelligent control.

[0048] For example, when the first structural member 1 and the second structural member 2 are wings, the power assembly of the UAV's wings may include a propeller, and protective shields for protecting the propeller are provided on the first structural member 1 and the second structural member 2, as shown in the reference. Figure 3 and Figure 4 From the perspective of the main view of the fuselage structure, the thickness Z dimension of the fuselage structure includes two protective shields. However, with a first clearance space 313 provided on the first structural member 1 and a second clearance space 323 provided on the second structural member 2, the first protrusion 11 of the first structural member 1 can be accommodated in the second accommodating space, and the second protrusion 21 of the second structural member 2 can be accommodated in the first clearance space 313. In this way, in the thickness direction (thickness Z direction of the fuselage structure) of the first structural member 1 and the second structural member 2, the dimensions of the two protective shields can be reduced to the dimensions of one protective member, thereby reducing the volume of the fuselage structure and reducing space occupation.

[0049] The fuselage structure of this application embodiment has a first clearance space 313 and a second clearance space 323 respectively provided on the first structural member 1 and the second structural member 2, which can further reduce the space occupied by the fuselage structure in the first form (in the folded form).

[0050] In some possible embodiments of this application, at least one end of the clearance space 3 passes through the corresponding first structural member 1 or second structural member 2.

[0051] In this embodiment of the application, at least one end of the clearance space 3 refers to the passage through the corresponding first structural member 1 or second structural member 2. It can be understood that the clearance space 3 is not completely closed. The clearance space 3 is open at one or some ends, that is, these open ends allow the first protrusion 11 or the second protrusion 21 (such as functional devices, circuits, etc.) or structure to pass through.

[0052] In this embodiment, at least one end of the clearance space 3 passes through the corresponding first structural member 1 or second structural member 2, which can also reduce the weight of the first structural member 1 and the second structural member 2, saving materials and costs.

[0053] In this embodiment, the direction and size of at least one end of the clearance space 3 passing through the corresponding first structural member 1 or second structural member 2 can be adjusted according to the structure of the first protrusion 11 or the second protrusion 21.

[0054] For example, refer to Figure 5 The first protrusion 11 and the second protrusion 21 both extend along the length direction Y of the fuselage structure and have a cuboid-like structure. In order to accommodate the structure of the first protrusion 11 and the second protrusion 21, the first clearance space 313 and the second clearance space 323 both penetrate along the length direction Y of the fuselage structure to accommodate the first protrusion 11 and the second protrusion 21.

[0055] Reference Figure 2 , Figure 3 , Figure 4 and Figure 5 In some possible embodiments of this application, the first structural member 1 and the second structural member 2 both include a first structural surface 12 and a second structural surface 13, and the clearance space 3 forms an opening in the first structural surface 12 and penetrates through the second structural surface 13; wherein the second structural surface 13 is disposed opposite to the first structural surface 12; or, the second structural surface 13 is disposed adjacent to the first structural surface 12.

[0056] In this embodiment, the first structural member 1 includes a first structural surface 12 and a second structural surface 13, and the second structural member 2 also includes a first structural surface 12 and a second structural surface 13. The first structural surface 12 and the second structural surface 13 on the first structural member 1 and the second structural member 2 can be the same corresponding surface or different surfaces. For example, the first structural surface 12 and the second structural surface 13 of the first structural member 1 can be arranged opposite to each other, and the first structural surface 12 and the second structural surface 13 of the second structural member 2 can be arranged adjacent to each other. Alternatively, the first structural surface 12 and the second structural surface 13 of the first structural member 1 can be arranged adjacent to each other, and the first structural surface 12 and the second structural surface 13 of the second structural member 2 can be arranged opposite to each other, etc.

[0057] In this embodiment, the clearance space 3 forms an opening on the first structural surface 12 and penetrates through the second structural surface 13. This can be understood as a space or channel extending outward from the first structural surface 12 and penetrating through the second structural surface 13 on the first structural member 1 and the second structural member 2, i.e., the clearance space 3. By changing the position, size, shape, etc. of the first structural surface 12 and the second structural surface 13, clearance spaces 3 of different shapes and sizes can be formed.

[0058] It should be added that the number of openings formed by the first structural surface 12 can be one or more, and the shape of the clearance opening can be rectangular, circular, etc., and the size is not limited, so that the clearance space 3 can adapt to the first protrusion 11 or the second protrusion 21 of different shapes and sizes.

[0059] For example, refer to Figure 3 and Figure 5 When the first structural surface 12 and the second structural surface 13 are arranged opposite to each other, the first structural surface 12 can be the surface of the first structural member 1 that is close to the second structural member 2 in the first form, and the second structural surface 13 is the surface that is far away from the second structural member 2. Multiple rectangular openings are formed on the first structural surface 12. The rectangular openings extend along the thickness direction Z of the fuselage structure and penetrate the second structural surface 13, thereby forming multiple clearance spaces 3 in the thickness direction.

[0060] In another embodiment, when the second structural surface 13 is arranged adjacent to the first structural surface 12, that is, the second structural surface 13 and the first structural surface 12 are close to or in contact with each other in space, they may form a right angle, parallel or other angular relationship. The clearance space 3 extends from the first structural surface 12 to the second structural surface 13, but it is not necessarily a straight line through; it may involve turning or changing direction. The first structural surface 12 is the surface of the first structural member 1 that is close to the second structural member 2 in the first configuration, and the second structural surface 13 is the surface that is adjacent to the first structural surface 12 and is far away from the second structural member 2 in the second configuration.

[0061] Reference Figure 1 ,Figure 2 and Figure 5 In some possible embodiments of this application, the first structural member 1 and the second structural member 2 are arranged to rotate relative to each other via the shaft 4; the through direction of the clearance space 3 is parallel to the central axis of the shaft 4, and / or the through direction of the clearance space 3 is set at an angle to the central axis of the shaft 4.

[0062] In this embodiment, the shaft 4 can be disposed on the first structural member 1, the second structural member 2, or other structures, and is connected to the first structural member 1 and the second structural member 2.

[0063] For example, a shaft 4 can be provided for the first structural component 1, and a bushing can be provided for the second structural component 2. The bushing is fitted on the outer periphery of the shaft 4. When the second structural component 2 rotates relative to the first structural component 1, the shaft 4 rotates inside the bushing.

[0064] In this embodiment of the application, when the penetrating direction of the clearance space 3 is parallel to the central axis of the shaft 4, referring to... Figure 5 and Figure 6 The central axis of shaft 4 extends along the length Y of the fuselage structure, and the penetrating direction of clearance space 3 also extends along the length Y of the fuselage structure.

[0065] In another embodiment, in reference Figure 7 When the central axis of the shaft 4 extends along the length Y of the fuselage structure, the penetrating direction of the clearance space 3 can be perpendicular to the length Y of the fuselage structure, that is, the clearance space 3 is set to extend along the width X of the fuselage structure.

[0066] With the central axis of shaft 4 extending along the length Y of the fuselage structure, the penetration direction of clearance space 3 can form an acute or obtuse angle with the length Y of the fuselage structure. The penetration direction can be a straight line or a curve, etc.

[0067] Reference Figure 3 , Figure 5 and Figure 8 In some possible embodiments of this application, both the first structural member 1 and the second structural member 2 include a first structural surface 12, and the clearance space 3 forms an opening in the first structural surface 12; the first structural surface 12 is provided with at least two openings, and the length directions of the at least two openings are parallel to each other; or, the length directions of the at least two openings are set at an angle.

[0068] In this embodiment, the length direction of the opening can be understood as the extension direction of the side with the relatively longer opening size. For example, see... Figure 8The first structural component 1 has multiple rectangular openings on its first structural surface 12, and multiple first protrusions 11 are formed between the openings on the first structural surface 12. The second structural component 2 also has multiple rectangular openings on its first structural surface 12, and these rectangular openings are aligned with the first protrusions 11. Multiple second protrusions 21 are formed between the multiple rectangular openings on the second structural component 2 on the first structural surface 12, and these second protrusions 21 are aligned with the rectangular openings on the first structural component 1. With this structure, when the fuselage structure is in the first configuration, the first protrusions 11 on the first structural component 1 can extend into the second clearance space 323 from the openings of the second structural component 2, and the second protrusions 21 on the second structural component 2 can extend into the first clearance space 313 from the openings of the first structural component 1.

[0069] In another embodiment of this application, at least two openings are arranged at an angle in their length directions. That is, the length directions of the first protrusion 11 and the second protrusion 21 are not the same. With this structure, when the fuselage structure is in the first form, the openings with different extension directions cooperate with the first protrusion 11 and the second protrusion 21 to limit the first protrusion 11 and the second protrusion 21, thereby reducing the relative displacement between the first structural member 1 and the second structural member 2 in the first form.

[0070] Reference Figure 8 and Figure 9 In some possible embodiments of this application, the first structural member 1 or the second structural member 2 includes a protrusion accommodated in the clearance space 3; in a first configuration, the outer surface of the protrusion is in contact with the inner surface of the clearance space 3; or, the outer surface of the protrusion is spaced apart from the inner surface of the clearance space 3.

[0071] In this embodiment, the outer surface of the protrusion fits into the inner surface of the clearance space 3. This can be understood as the shape and size of the clearance space 3 being adapted to the shape and size of the protrusion. This allows the fuselage structure in the first form to have a tighter fit between the protrusion and the clearance space 3, further reducing the size of the fuselage structure.

[0072] In this embodiment, the outer surface of the protrusion and the inner surface of the clearance space 3 are spaced apart. This can be understood as the clearance space 3 having a larger volume than the protrusion. The relatively larger volume space can be used to accommodate other structures, or to allow clearance between the protrusion and the inner wall of the clearance space 3, thereby reducing friction and collision between the protrusion and the inner wall of the clearance space 3.

[0073] In the fuselage structure of this application embodiment, the outer surface of the protrusion and the inner surface of the clearance space 3 are fitted together, which can further reduce the space occupied by the wing after folding; the outer surface of the protrusion and the inner surface of the clearance space 3 have a gap, which allows the components in the protrusion and the clearance space 3 to avoid each other in the first state of the fuselage structure.

[0074] This application provides an unmanned aerial vehicle (UAV) including a central body 5 and a power assembly. The central body 5 is provided with a first structural component 1 and a second structural component 2. The power assembly is respectively provided with the first structural component 1 and the second structural component 2.

[0075] In this embodiment, the central body 5 provides an installation foundation and structural support for the first structural component 1 and the second structural component 2, enabling the UAV to maintain structural integrity and stability in complex environments. The central body 5 typically includes a shell, inside which functional devices are housed. The shell can be made of lightweight and high-strength materials, such as carbon fiber composites, to reduce the weight of the central body 5 while increasing structural strength. The central body 5 may also house other load-bearing structures.

[0076] In this embodiment, the first structural member 1 and the second structural member 2 are respectively provided with power components. The power components provide flight propulsion for the UAV and may include a motor, transmission device, propeller, etc. For example, a turboshaft engine can be used in the power component, transmitting power from the engine to the propeller via a gearbox and drive shaft. The propeller can be a large-diameter, high-pitch propeller to provide sufficient lift and thrust. It should be noted that the power components can be adjusted according to different operational requirements; this application does not limit this adjustment.

[0077] Reference Figure 1 , Figure 2 , Figure 8 and Figure 9 In some possible embodiments of this application, one of the first structural member 1 and the second structural member 2 is fixed relative to the central body 5, and the other is movable relative to the central body 5.

[0078] In this embodiment, the first structural member 1 and the central body 5 may be fixedly arranged relative to each other, while the corresponding second structural member 2 and the central body 5 may be movable relative to each other; alternatively, the second structural member 2 and the central body 5 may be fixedly arranged relative to each other, while the corresponding first structural member 1 and the central body 5 may be movable relative to each other.

[0079] For example, in this application, for ease of description, the first structural member 1 is fixed relative to the central body 5, and the second structural member 2 is movable relative to the central body 5.

[0080] In this embodiment, it can be understood that the relative position between the first structural component 1 and the central body 5 remains essentially unchanged regardless of the different states of the UAV. The fixed relative arrangement of the first structural component 1 and the central body 5 can include direct connection, rigid connection, connection through a fixed mounting bracket, etc. For example, the first structural component 1 can be directly connected to the central body 5 by bolts, welding, riveting or other fastening methods; the first structural component 1 and the central body 5 can also be connected to the central body 5 through rigid connecting parts (such as connecting rods, brackets, etc.).

[0081] In this embodiment, the second structural member 2 is relatively movable relative to the central body 5. This can be understood as the connection between the second structural member 2 and the central body 5 allowing for a certain relative movement or activity. Since the first structural member 1 and the central body 5 are relatively fixed, it can be understood that the second structural member 2 is relatively movable relative to the first structural member 1.

[0082] In some embodiments of this application, one of the first structural member 1 and the second structural member 2 is movably configured relative to the central body 5, and the specific connection relationship can be a sliding connection, a rotational connection, a swing connection, etc.

[0083] Based on this, one of the first structural component 1 and the second structural component 2 can rotate, fold, or otherwise move relative to the central body 5. This structure allows the drone to switch between different configurations, enabling it to be compactly folded for easy carrying and storage when needed, or to adjust its configuration during flight to adapt to different mission requirements.

[0084] Reference Figure 9 In some possible embodiments of this application, the drone also includes a locking structure 6, a first part 61 of which is connected to the second structural member 2, and a second part 62 of which is connected to the first structural member 1 or the central body 5; the locking structure 6 is used to lock or unlock the relative movement of the first structural member 1 and the second structural member 2.

[0085] In this embodiment, the locking structure 6 is configured to lock or unlock the relative movement of the first structural member 1 and the second structural member 2. When the drone switches between different configurations, if the second structural member 2 moves to a predetermined position relative to the first structural member 1, or if the drone needs to be transported or stored, the locking mechanism triggers a locking state, locking the second structural member 2 and the first structural member 1. If the drone needs to switch between configurations again, or if the drone needs to be transported or stored, the locking mechanism triggers an unlocking state, allowing the first structural member 1 and the second structural member 2 to be interchanged.

[0086] In this embodiment, the locking structure 6 can be locked using mechanical components (such as springs, pins, etc.), providing a high-strength and highly reliable locking effect. For example, the first part 61 of the locking structure 6 can be a pin connected to the second structural member 2, and the second part 62 can be a lock seat with a socket connected to the first structural member 1 or the central body 5. The pin and lock seat can be connected to the second structural member 2, the first structural member 1, or the central body 5 via threaded connection, welding, or snap-fit. When the relative positions of the second structural member 2 and the first structural member 1 or the central body 5 are determined, the pin is pushed into the socket by a spring or other driving force to achieve locking. For unlocking, the pin can be pulled out of the socket manually or electrically. The structures of the first part 61 and the second part 62 can also be interchanged.

[0087] In some embodiments of this application, the locking structure 6 can also employ electromagnetic locking, based on the principle of electromagnetic attraction, to achieve locking by controlling electromagnetic force. For example, the first part 61 of the locking structure 6 can be an electromagnet connected to the second structural member 2, and the second part 62 can be a lock seat with an iron core connected to the first structural member 1 or the central body 5. When the electromagnet is energized, it generates a magnetic force to attract the iron core, so that the second structural member 2 and the first structural member 1 or the central body 5 are tightly fitted together, achieving locking. When unlocking, the power supply to the electromagnet is cut off, the magnetic force disappears, and the second structural member 2 can move. The structures of the first part 61 and the second part 62 can also be interchanged.

[0088] The technical solution provided in this application embodiment is that the locking structure 6 can lock or unlock the relative movement of the first structural member 1 and the second structural member 2, which can improve the overall stability of the drone in the locked state. Especially when the drone is stationary or parked, by locking key components such as wings and propellers, damage to the drone in the non-working state can be reduced, which helps to extend the service life of the drone and reduce maintenance costs.

[0089] Reference Figure 1 and Figure 2 In some possible embodiments of this application, the first structural member 1 and the second structural member 2 are respectively provided with mounting positions 14, which are used to install power components and drive the movement of the fuselage structure.

[0090] In this embodiment of the application, for example, when the power assembly includes a propeller, a first mounting position 14 is provided on the first structural member 1, and a second mounting position 14 is provided on the second structural member 2. The first mounting position 14 and the second mounting position are used to mount the propeller. The first structural member 1 is also provided with a first duct at the position corresponding to the first mounting position 14, and the second structural member 2 is also provided with a second duct at the position corresponding to the second mounting position 14. The first duct and the second duct are aerodynamic structures that can improve the propeller efficiency.

[0091] Reference Figure 9 In some possible embodiments of this application, the drone further includes an electronic device 7, which includes an active state and a disabled state; in response to the drone switching from the first mode to the second mode, the electronic device 7 switches to the active state; in response to the drone switching from the second mode to the first mode, the electronic device 7 switches to the disabled state.

[0092] In this embodiment, the active state of electronic device 7 can be understood as the power-on state of electronic device 7. In the active state, electronic device 7 can perform its predetermined functions, such as the activation of components like flight control systems, navigation systems, communication modules, and sensors. The disabled state of electronic device 7 can be understood as the power-off state of electronic device 7. In the disabled state, electronic device 7 is turned off or in a low-power standby mode and does not perform any functions.

[0093] In this embodiment, when the drone switches from one form (such as a compact, easily transportable and storable first form) to another form (such as an unfolded, flight-suitable second form), the electronic device 7 needs to be activated to support the drone's flight operations. The state switching of the electronic device 7 may be triggered by a mechanical trigger, sensor signal, or user command.

[0094] Conversely, when the drone completes its flight mission and is ready to return to its compact form, the electronics 7 need to be turned off or placed in a low-power mode so that the drone does not accidentally start up or consume unnecessary energy during storage or transportation.

[0095] The sequence numbers of the embodiments in this application are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments. The above are merely preferred embodiments of this application and do not limit the patent scope of this application. Any equivalent structural or procedural transformations made based on the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this application.

Claims

1. A fuselage structure, characterized in that, include: First structural component; The second structural component is movable relative to the first structural component, so that the fuselage structure can be transformed between the first and second forms. In this configuration, at least one of the first structural member and the second structural member forms a clearance space, and in the first configuration, at least a portion of the other of the first structural member and the second structural member is accommodated within the clearance space.

2. The fuselage structure according to claim 1, characterized in that, The first structural member includes a first clearance space and a first protrusion, and the second structural member includes a second clearance space and a second protrusion. In the first configuration, at least a portion of the first protrusion is located in the second clearance space, and at least a portion of the second protrusion is located in the first clearance space.

3. The fuselage structure according to claim 1 or 2, characterized in that, At least one end of the clearance space passes through the corresponding first structural member or second structural member.

4. The fuselage structure according to claim 3, characterized in that, Both the first structural member and the second structural member include a first structural surface and a second structural surface, and the clearance space forms an opening in the first structural surface and penetrates through the second structural surface; Wherein, the second structural surface is disposed opposite to the first structural surface; or, the second structural surface is disposed adjacent to the first structural surface.

5. The fuselage structure according to claim 4, characterized in that, The first structural component and the second structural component are rotatably mounted relative to each other via a shaft. The penetrating direction of the clearance space is parallel to the central axis of the shaft, and / or the penetrating direction of the clearance space is set at an angle to the central axis of the shaft.

6. The fuselage structure according to claim 1 or 2, characterized in that, Both the first structural member and the second structural member include a first structural surface, and the clearance space forms an opening in the first structural surface; The first structural surface is provided with at least two openings, the length directions of the at least two openings are parallel to each other; or, the length directions of the at least two openings are arranged at an angle.

7. The fuselage structure according to claim 1 or 2, characterized in that, The first structural member or the second structural member includes a protrusion accommodated in the clearance space; In the first configuration, the outer surface of the protrusion is in contact with the inner surface of the clearance space; or, the outer surface of the protrusion is spaced apart from the inner surface of the clearance space.

8. A drone, characterized in that, include: The fuselage structure as described in any one of claims 1 to 7; The central body is provided with the first structural component and the second structural component; The power components are respectively provided for the first structural component and the second structural component.

9. The UAV according to claim 8, characterized in that, One of the first structural component and the second structural component is fixed relative to the central body, and the other is movable relative to the central body.

10. The UAV according to claim 9, characterized in that, It also includes a locking structure, a first part of which is connected to the second structural member, and a second part of which is connected to the first structural member or the central body; the locking structure is used to lock or unlock the relative movement of the first structural member and the second structural member.

11. The UAV according to claim 8, characterized in that, The first structural component and the second structural component are respectively provided with mounting positions, the mounting positions are used to install power components, and the power components are used to drive the movement of the fuselage structure.

12. The UAV according to claim 8, characterized in that, The drone also includes electronic devices, which have active and disabled states. In response to the drone switching from the first mode to the second mode, the electronic device switches to an active state; In response to the drone switching from the second mode to the first mode, the electronic devices switch to a disabled state.

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