Unmanned aerial vehicle

Abstract

An unmanned aerial vehicle, comprising a central body (1) and a vehicle body assembly (2), wherein the central body (1) is provided with a functional device; the vehicle body assembly (2) is connected to the central body (1); the vehicle body assembly (2) comprises a first structural member (21) and a second structural member (22), the first structural member (21) and the second structural member (22) are separately provided with a power assembly (3), and the first structural member (21) and the second structural member (22) are capable of moving relative to each other, so that the unmanned aerial vehicle has a first configuration and a second configuration that are different; the first structural member (21) is fixedly arranged relative to the central body (1), and the second structural member (22) is movably arranged relative to the central body (1).

Description

A type of drone Technical Field

[0001] This disclosure relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to a UAV. Background Technology

[0002] A drone is an unmanned aircraft that is controlled by radio remote control equipment and its own program control device. Summary of the Invention

[0003] To address the aforementioned technical problems, this disclosure provides an unmanned aerial vehicle (UAV) comprising a central body and a fuselage assembly. The central body is equipped with functional devices. The fuselage assembly is connected to the central body and includes a first structural member and a second structural member. The first and second structural members are respectively equipped with power components, and the first and second structural members can move relative to each other, allowing the UAV to have different first and second forms. The first structural member is fixed relative to the central body, while the second structural member is movable relative to the central body.

[0004] The drone provided in this embodiment features a fuselage assembly connected to a central body. This fuselage assembly includes a first structural member and a second structural member, which are movable relative to each other. This allows the drone to have different first and second forms, enabling it to adapt to various operational needs. When the drone needs to be carried, stored, or transported, its overall size can be reduced by changing its form. This smaller form makes the drone's structure more compact, reducing its overall space occupation. When the drone needs to work or adjust its form during flight, it can adapt its form to the current operational requirements. Furthermore, since the second structural member is movable relative to the central body (i.e., movable relative to the first structural member), the drone's structure is simplified, facilitating disassembly, assembly, and maintenance. The first structural member is fixed to the central body, serving as a positioning reference for the second structural member's movement relative to the central body. When the drone switches to a smaller form, the first structural member increases the stability of the second structural member, reducing the likelihood of swaying or deflection. Attached Figure Description

[0005] To more clearly illustrate the technical solutions in the specific embodiments of this disclosure, the accompanying drawings used in the description of the specific embodiments or the prior art will be described below. These drawings are incorporated in the specification and constitute a part of this specification. They illustrate embodiments consistent with this disclosure and are used together with the specification to illustrate the technical solutions of this disclosure.

[0006] Figure 1 is a schematic diagram of the first configuration of the unmanned aerial vehicle provided in an embodiment of this disclosure;

[0007] Figure 2 is a schematic diagram of the second form of the drone provided in the embodiments of this disclosure;

[0008] Figure 3 is a front view of the drone in its first configuration according to an embodiment of this disclosure;

[0009] Figure 4 is a front view of the UAV in a second configuration according to an embodiment of this disclosure;

[0010] Figure 5 is a schematic diagram of the first and second structural components of the UAV provided in this embodiment having a preset gap;

[0011] Figure 6 is a schematic diagram of the structure in which the first and second structural components of the UAV are partially attached according to an embodiment of this disclosure.

[0012] Figure 7 is a schematic diagram of the structure of the UAV provided in this embodiment, showing a third included angle between the extended surface of the second surface and the first surface.

[0013] Figure 8 is a schematic diagram of the structure of an unmanned aerial vehicle provided in an embodiment of the present disclosure, in which at least one of the third and fourth surfaces satisfies the condition of being flush with the outer surface of the central body;

[0014] Figure 9 is a schematic diagram of a UAV provided in an embodiment of this disclosure, showing that at least one of the third and fourth surfaces is flush with the structural surface.

[0015] Figure 10 is a top view of the UAV in the first configuration provided in the embodiments of this disclosure;

[0016] Figure 11 is a schematic diagram of the structure of the bushing and shaft of the UAV provided in the embodiment of this disclosure;

[0017] Figure 12 is a top view of the structure of the bushing and shaft of the UAV provided in the embodiment of this disclosure;

[0018] Figure 13 is a schematic diagram of the locking structure of the UAV provided in an embodiment of this disclosure;

[0019] Figure 14 is a schematic diagram of a first and second structural component of an unmanned aerial vehicle provided in an embodiment of the present disclosure, which has at least two components.

[0020] Figure 15 is one of the structural schematic diagrams of a drone with a protective cover provided in an embodiment of this disclosure;

[0021] Figure 16 is a second schematic diagram of the structure of the drone with a protective cover provided in an embodiment of this disclosure;

[0022] Figure 17 is a front view of the drone with a protective cover in a second configuration according to an embodiment of the present disclosure;

[0023] Figure 18 is a front view of the drone with a protective cover provided in the first configuration according to an embodiment of the present disclosure.

[0024] Explanation of reference numerals in the attached drawings: 1-Central body; 2-Body assembly; 21-First structural component; 211-First surface; 212-Third surface; 213-First connecting part; 2131-Shaft; 2132-Connector; 214-First mounting part; 215-First duct; 22-Second structural component; 221-Second surface; 222-Fourth surface; 223-Second connecting part; 2231-Busset; 2232-Groove; 224-Second mounting part; 225-Second duct; 226-Protective cover; 3-Power assembly; 4-Structural part; 41-Structural surface; 5-Locking structure; 51-First part; 52-Second part; 6-Electronic components; A-First included angle; B-Second included angle; C-Third included angle; D-Rotation axis; E-Preset plane; F-Allowing space; G-Extension surface; H-Placement surface. Detailed Implementation

[0025] The technical solutions of the embodiments of this disclosure will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this disclosure. Based on the embodiments of this disclosure, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this disclosure.

[0026] In the embodiments of this disclosure, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the embodiments of this disclosure, unless otherwise stated, "a plurality of" means two or more.

[0027] Furthermore, in the embodiments of this disclosure, directional terms such as "up," "down," "left," and "right" are defined relative to the orientation in which the components are schematically placed in the accompanying drawings. It should be understood that these directional terms are relative concepts, used for relative description and clarification, and can change accordingly depending on the orientation in which the components are placed in the accompanying drawings.

[0028] In the embodiments disclosed herein, unless otherwise expressly specified and limited, the term "connection" should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral part; it can be a direct connection or an indirect connection through an intermediate medium.

[0029] In embodiments of this disclosure, the terms "comprising," "including," or any other variations thereof are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element.

[0030] In this disclosure, the terms "exemplary" or "for example" are used to indicate that something is an example, illustration, or illustration. Any embodiment or design described as "exemplary" or "for example" in this disclosure should not be construed as being more preferred or advantageous than other embodiments or designs. Rather, the use of terms such as "exemplary" or "for example" is intended to present the relevant concepts in a specific manner.

[0031] Furthermore, the technical features involved in the different embodiments of this disclosure described below can be combined with each other as long as they do not conflict with each other.

[0032] A drone is an unmanned aerial vehicle, an unmanned aircraft controlled by radio remote control equipment and its own program control device. Drones can be used in aerial photography, entertainment, agricultural assistance, environmental monitoring, disaster relief, inspection and surveying, public safety, and logistics distribution, among other fields.

[0033] Drones include fixed-wing drones, rotary-wing drones, vertical take-off and landing fixed-wing drones, and tilt-rotor drones, among which drones with foldable wings have advantages such as portability, space saving, and efficient deployment. However, the complex structure of drones in related technologies makes them inconvenient to disassemble and maintain, and when drones are converted to a smaller form factor, their wings are prone to wobbling and deflection.

[0034] Referring to Figures 1 and 2, this disclosure provides an unmanned aerial vehicle (UAV). The UAV provided in this disclosure includes a central body 1 and a fuselage assembly 2. The central body 1 is provided with functional devices. The fuselage assembly 2 is connected to the central body 1 and includes a first structural member 21 and a second structural member 22. The first structural member 21 and the second structural member 22 are respectively provided with a power assembly 3, and the first structural member 21 and the second structural member 22 can move relative to each other, so that the UAV has different first and second forms. The first structural member 21 is fixed relative to the central body 1, and the second structural member 22 is movable relative to the central body 1.

[0035] In this embodiment, the central body 1 provides an installation foundation and structural support for the fuselage assembly 2, enabling the UAV to maintain structural integrity and stability in complex environments. The central body 1 typically includes a shell, within which functional components 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 1 while increasing structural strength. The central body 1 may also house other load-bearing structures.

[0036] In this embodiment, the fuselage assembly 2 includes a first structural member 21 and a second structural member 22. The first structural member 21 and the second structural member 22 can switch between different forms through relative movement. The first structural member 21 and the second structural member 22 can be understood as the wings of the drone, and the drone can switch between different states such as folded or unfolded through relative movement between the wings.

[0037] It should be added that fuselage component 2 can also be understood as other structures, such as rotor, propeller, tail, stabilizer, load-bearing structure or other innovative structures, etc., which are not limited in this disclosure.

[0038] In this embodiment, the central body 1 is equipped with functional components, which may include a camera, flight controller, power system, sensors (such as GPS, navigation unit, etc.), communication module, etc. These functional components work together to enable the drone to fly stably, locate accurately, and transmit data in real time.

[0039] For example, a battery compartment may be installed inside or near the central body 1 to store the battery pack that powers the drone. The central body 1 may be equipped with standardized interfaces and connection points for connection to external devices such as the fuselage components 2 and payloads (e.g., cameras, sensor pods).

[0040] In this embodiment, the first structural member 21 and the second structural member 22 are respectively provided with a power assembly 3. The power assembly 3 can provide flight power for the UAV and may include a motor, a transmission device, a propeller, etc. For example, a turboshaft engine can be used in the power assembly 3, and the power of the engine is transmitted to the propeller through a gearbox and a drive shaft. The propeller can be a large-diameter, high-pitch propeller to provide sufficient lift and thrust. It should be added that the power assembly 3 can be adjusted according to different operational requirements, and this disclosure does not limit it.

[0041] For example, when the power assembly 3 includes a propeller, a first mounting portion 214 is provided on the first structural member 21, and a second mounting portion 224 is provided on the second structural member. The first mounting portion 214 and the second mounting portion 224 are used to mount the propeller. The first structural member 21 is also provided with a first duct 215 at the position corresponding to the first mounting portion 214, and the second structural member 22 is also provided with a second duct 225 at the position corresponding to the second mounting portion 224. The first duct 215 and the second duct 225 are aerodynamic structures that can improve the propeller efficiency.

[0042] In this embodiment, the first structural component 21 is fixedly disposed relative to the central body 1, which can be understood as the relative position between the first structural component 21 and the central body 1 remaining essentially unchanged under different states of the UAV. The fixed disposal of the first structural component 21 and the central body 1 can include direct connection, rigid connection, or connection via a fixed mounting bracket. For example, the first structural component 21 can be directly connected to the central body 1 by bolts, welding, riveting, or other fastening methods; the first structural component 21 and the central body 1 can also be connected to the central body 1 via rigid connecting components (such as connecting rods, brackets, etc.).

[0043] In some embodiments of this disclosure, a fixed mounting base may also be provided on the central body 1, which is configured to install and fix the first structural member 21. This structure not only facilitates the installation and disassembly of the first structural member 21, but also improves the stability and reliability between the first structural member 21 and the central body 1.

[0044] In this embodiment of the disclosure, the second structural member 22 is relatively movable relative to the central body 1. This can be understood as the connection between the second structural member 22 and the central body 1 allowing for a certain relative movement or activity. Since the first structural member 21 and the central body 1 are relatively fixed, it can be understood that the second structural member 22 is relatively movable relative to the first structural member 21.

[0045] In some embodiments of this disclosure, the second structural member 22 can rotate, fold, or otherwise move relative to the central body 1 or the first structural member 21. Such a structure allows the UAV to switch between different configurations, enabling it to be compactly folded for easy carrying and storage when needed, or to adjust its shape during flight to adapt to different mission requirements.

[0046] In some embodiments of this disclosure, the connection between the second structural member 22 and the central body 1 or the first structural member 21 can be a sliding connection, a rotational connection, a swing connection, etc.

[0047] In this embodiment of the disclosure, the first structural member 21 and the second structural member 22 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.

[0048] The technical solution provided in this disclosure, since the fuselage assembly 2 is connected to the central body 1, and the fuselage assembly 2 includes a first structural member 21 and a second structural member 22, and the first structural member 21 and the second structural member 22 can move relative to each other, the drone has different first and second forms. Thus, the drone can adapt to more operational needs by switching between the first and second forms. When the drone needs to be carried, stored, and transported, the drone can reduce its overall size by switching forms. The reduced size makes the drone's structure more compact and reduces the overall space occupied by the drone. When the drone needs to work or adjust its form during flight, it can adapt its form to the current operational needs by switching forms. This structure can improve the flexibility of the drone in switching between different forms. Meanwhile, since the second structural component 22 is movably positioned relative to the central body 1, that is, the second structural component 22 can be movably positioned relative to the first structural component 21, the structure of the drone is simplified, making it easier to disassemble, assemble, and maintain the drone. Furthermore, the first structural component 21 and the central body 1 are fixed to each other, and the first structural component 21 can serve as a positioning reference for the movement of the second structural component 22 relative to the central body 1. When the drone switches to a smaller form, the first structural component 21 can increase the stability of the second structural component 22, making it less prone to shaking and deflection.

[0049] Referring to Figures 3, 4, and 6, in some possible embodiments of this disclosure, in a first configuration, the first structural member 21 and the second structural member 22 are relatively close to each other and have a first included angle A; in a second configuration, the first structural member 21 and the second structural member 22 are relatively far apart and have a second included angle B; the first included angle A is smaller than the second included angle B.

[0050] In this embodiment of the present disclosure, in a first configuration, the first structural member 21 and the second structural member 22 are relatively close to each other, and the included angle between the first structural member 21 and the second structural member 22 is defined as a first included angle A. In a second configuration, the first structural member 21 and the second structural member 22 are relatively far apart, and the included angle between the first structural member 21 and the second structural member 22 is defined as a second included angle B.

[0051] In this embodiment of the disclosure, the first included angle A is smaller than the second included angle B. This can be understood as the angle between the first structural member 21 and the second structural member 22 increasing during the switching process from the first form to the second form. That is, the second structural member 22 and the first structural member 21 move from being close to each other to being far apart, which facilitates the UAV switching from a relatively compact form to a relatively extended form.

[0052] It should be added that a smaller included angle (first included angle A) makes the drone easier to carry and store. A larger included angle (second included angle B) provides the drone with a greater wingspan and more stable flight performance. The specific values ​​of the first included angle A and the second included angle B may be adjusted according to the drone's specifications and application requirements.

[0053] In some embodiments of this disclosure, when the second structural member 22 rotates relative to the central body 1 or the first structural member 21, it can be understood that the first form includes the case where the first structural member 21 and the second structural member 22 are folded together by rotation. The folded form is usually for the non-flight phase of the UAV, such as transportation, storage or operation in a confined space. The second form includes the first structural member 21 and the second structural member 22 being unfolded to the position where the UAV is working by rotation, thereby meeting different flight mission requirements.

[0054] Referring to Figures 3, 5, and 6, in some possible embodiments of this disclosure, the first structural member 21 includes a first surface 211, and the second structural member 22 includes a second surface 221; the first surface 211 and the second surface 221 have a first included angle A; in a first configuration, the first surface 211 and the second surface 221 are disposed opposite to each other, and the first included angle A is less than or equal to 30 degrees.

[0055] In this embodiment of the disclosure, the first surface 211 refers to a specific surface or region on the first structural member 21. Depending on the shape and size of the first structural member 21, the first surface 211 can be planar, curved, or any other shape. Similarly, the second surface 221 refers to a specific surface or region on the second structural member 22. Depending on the shape and size of the second structural member 22, the second surface 221 can be planar, curved, or any other shape.

[0056] In some embodiments of this disclosure, in a first configuration, namely a configuration in which the first structural member 21 and the second structural member 22 are close to each other, the surface of the first structural member 21 relative to the second structural member 22 is defined as the first surface 211, the surface of the second structural member 22 relative to the first structural member 21 is defined as the second surface 221, and the included angle formed between the first surface 211 and the second surface 221 is defined as the first included angle A.

[0057] In some embodiments of this disclosure, the first included angle A can be less than or equal to 30 degrees. In this case, a relatively small angle is formed between the first surface 211 and the second surface 221 so that the first structural member 21 and the second structural member 22 are close to each other or nearly overlap, which helps to reduce the overall size of the UAV in the first form and makes it easier to carry and store.

[0058] Referring to Figures 3, 5 and 8, in some possible embodiments of this disclosure, in a first configuration, the first surface 211 and the second surface 221 satisfy a parallel condition.

[0059] In this embodiment, the first surface 211 and the second surface 221 satisfy the parallel condition in the first configuration, which can be understood as the first surface 211 and the second surface 221 being in a non-intersecting state, or as the first included angle A formed between the first surface 211 and the second surface 221 being 0 degrees. This can further reduce the space occupied by the drone in the first configuration, while improving the visual effect and aesthetics of the drone.

[0060] In some embodiments of this disclosure, the first surface 211 and the second surface 221 can be completely fitted together, which can further compress the gap between the first structural member 21 and the second structural member 22, thereby further reducing the volume of the drone and reducing the space occupied by the drone.

[0061] Referring to Figures 3 and 6, in some possible embodiments of this disclosure, the first surface 211 is at least partially attached to the second surface 221.

[0062] In this embodiment of the disclosure, in order to reduce the space occupied by the drone in the first configuration, even if there is an angle between the first surface 211 and the second surface 221, the first surface 211 and the second surface 221 can at least partially fit together. For example, referring to FIG6, there is an angle between the first surface 211 and the second surface 221, but the sides of the first surface 211 and the second surface 221 closer to the central body 1 can fit together.

[0063] In some embodiments of this disclosure, the first surface 211 and the second surface 221 may be planar or curved, etc. For example, when the first surface 211 and the second surface 221 are curved, the curved surfaces that are close to each other on the first surface 211 and the second surface 221 can fit together, which can reduce the gap between the first surface 211 and the second surface 221.

[0064] Referring to FIG5, in some possible embodiments of this disclosure, in a first configuration, the first surface 211 and the second surface 221 are at least partially spaced apart by a predetermined distance.

[0065] In this embodiment, the preset distance refers to the distance at which the first surface 211 and the second surface 221 will not contact each other in the first configuration. The preset distance can be adjusted according to factors such as the movement mode of the second structural member 22 relative to the central body 1 and the shapes of the first structural member 21 and the second structural member 22. The preset distance can reduce collisions and interference between the first structural member 21 and the second structural member 22 when the UAV switches configurations, thereby improving the safety of the UAV during configuration changes.

[0066] In this embodiment, not all areas of the first surface 211 and the second surface 221 need to be spaced apart. A preset spacing can be set only for the areas where some structures are located, which can reduce collisions or interference in these areas when the UAV changes form.

[0067] Referring to FIG4, in some possible embodiments of this disclosure, in a second configuration, the first surface 211 and the second surface 221 satisfy the coplanar condition.

[0068] In this embodiment of the disclosure, in the second form, that is, the form in which the second structural member 22 is relatively far away from the first structural member 21, the first surface 211 and the second surface 221 satisfy the coplanar condition, which can be understood as the second included angle B formed between the first surface 211 and the second surface 221 being 180 degrees, and the first structural member 21 and the second structural member 22 being in an unfolded state.

[0069] For example, when the second structural member 22 and the central body 1 are rotatably connected, the first surface 211 and the second surface 221 satisfy the coplanar condition, and the second structural member 22 is rotated 180 degrees relative to the central body 1 or the first structural member 21.

[0070] Referring to FIG7, in some possible embodiments of this disclosure, the extension surface G of the second surface 221 and the first surface 211 have a third included angle C; in a second embodiment, the third included angle C is less than or equal to 30 degrees.

[0071] In this embodiment of the disclosure, in order to facilitate the UAV to adapt to different working requirements, the second included angle B between the first structural member 21 and the second structural member 22 can be adjusted as needed. This can be understood as follows: when the second surface 221 and the first surface 211 are coplanar, the third included angle C is 0.

[0072] In some embodiments of this disclosure, when the third included angle C is not 0 degrees, the second included angle B between the first surface 211 and the second surface 221 can be the value of the third included angle C added to 180 degrees, or the value of the third included angle C subtracted from 180 degrees. That is, the range of the second included angle B is greater than or equal to 150 degrees and less than or equal to 210 degrees.

[0073] Referring to Figures 3 and 5, in some possible embodiments of this disclosure, the first structural member 21 includes a third surface 212, and the second structural member 22 includes a fourth surface 222; in a first configuration, the third surface 212 and the fourth surface 222 are disposed opposite to each other, and the third surface 212 and the fourth surface 222 satisfy a parallel condition.

[0074] In this embodiment of the disclosure, the third surface 212 and the fourth surface 222 are arranged opposite to each other. It can be understood that in the first configuration, the third surface 212 and the fourth surface 222 face opposite directions, and the third surface 212 and the fourth surface 222 can form the outer contour of the UAV.

[0075] In this embodiment, when the drone is stowed, the parallel and oppositely positioned third surface 212 and fourth surface 222 allow multiple drones to fit together tightly, reducing unnecessary space waste during stowage and storage. Simultaneously, the parallelism of the third surface 212 and fourth surface 222 in the first configuration helps maintain the overall structural stability and compactness of the drone. When the drone switches from the first configuration (folded state) to the second configuration (flight state), the parallelism of the third surface 212 and fourth surface 222 improves the drone's stability during flight.

[0076] Referring to FIG8, in some possible embodiments of this disclosure, in a first configuration, at least one of the third surface 212 and the fourth surface 222 satisfies the condition of being flush with the outer surface of the central body 1.

[0077] In this embodiment, the central body 1 can be a cylinder, cube, cuboid, triangular prism, or square pyramid, etc. The outer surface of the central body 1 refers to the surface that directly contacts the placement surface H (such as a tabletop, ground, or the inner surface of a storage box) when the drone is placed. For example, for shapes such as cubes, cuboids, or cylinders, the outer surface is usually the side of the central body 1.

[0078] In this embodiment of the present disclosure, when at least one of the third surface 212 and the fourth surface 222 is flush with the outer surface of the central body 1, at least one of the third surface 212 and the fourth surface 222 will be on the same surface as the outer surface of the central body 1. This can increase the contact area between the drone and the placement surface H when the drone is placed, thereby improving the stability of the drone when it is placed and reducing the phenomenon that the central body 1 is easily damaged when squeezed because it is relatively protruding.

[0079] Referring to FIG9, in some possible embodiments of this disclosure, the UAV further includes a structural portion 4 disposed on the outer surface of the central body 1, the structural portion 4 including a structural surface 41 away from the central body 1; in a first configuration, at least one of the third surface 212 and the fourth surface 222 satisfies the condition of being flush with the structural surface 41.

[0080] In this embodiment, the structural part 4 may include structures of various shapes and sizes disposed on the outer surface of the central body 1, such as brackets, wing plates, protective covers, etc. The structural part 4 can work in conjunction with other parts of the UAV by being connected or fixed to the outer surface of the central body 1. The structural surface 41 is one of the structural parts 4 that is away from the central body 1.

[0081] In this embodiment, since the structural part 4 is a component disposed on the central body 1, there may be a height difference between the surface of the structural part 4 away from the central body 1 and the outer surface of the central body 1. When the drone in the first form is placed on the placement surface H, the structural surface 41 will directly contact the placement surface H. At this time, at least one of the third surface 212 and the fourth surface 222 satisfies the condition of being flush with the structural surface 41, so that at least one of the third surface 212 and the fourth surface 222 and the structural surface 41 combine to form a larger contact surface, which can contact the placement surface H, thereby improving the stability of the drone when placed and reducing the phenomenon that the structural part 4 is easily damaged when squeezed because it is relatively protruding.

[0082] Referring to Figures 1, 2, 3 and 5, in some possible embodiments of this disclosure, the first structural member 21 and the second structural member 22 are arranged to rotate relative to each other about the rotation axis D; in a first configuration, the first structural member 21 and the second structural member 22 are arranged relative to each other about a preset plane E, and the preset plane E passes through the rotation axis D.

[0083] In this embodiment, the rotation axis D is the axis on which the second structural member 22 can rotate. The rotation axis D can be the central axis of the central body 1, the axis of the rotational connection structure between the second structural member 22 and the central body 1, or the axis of the rotational connection structure between the second structural member 22 and the first structural member 21. When the second structural member 22 rotates from the first form to the second form around the rotation axis D, the relative angle between the first structural member 21 and the second structural member 22 will change, but the rotation axis D will serve as the reference axis for the relative rotation of the first structural member 21 and the second structural member 22.

[0084] In this embodiment, the preset plane E is a virtual plane. As the axis of rotation D changes, the position of the preset plane E will also change. The preset plane E can describe or refer to the relative positional relationship between the first structural member 21 and the second structural member 22.

[0085] In this embodiment of the disclosure, since the first structural member 21 and the second structural member 22 are arranged relative to each other about the preset plane E, it can be understood that the first structural member 21 and the second structural member 22 are arranged symmetrically on both sides of the preset plane E, which helps to maintain the overall balance and stability of the UAV when switching forms, and may also improve the visual integrity of the UAV.

[0086] Referring to Figures 1, 2 and 10, in some possible embodiments of this disclosure, the first structural member 21 includes a first connecting portion 213, and the second structural member 22 includes a second connecting portion 223; the first connecting portion 213 and the second connecting portion 223 are respectively connected to the central body 1; or, the first connecting portion 213 is connected to the central body 1, and the second connecting portion 223 is connected to the first connecting portion 213.

[0087] In this embodiment, the first structural member 21 and the central body 1 are fixedly arranged relative to each other. Thus, the first connecting part 213 can be a connecting seat or a fixed bracket, and is connected to the central body 1 by bolts, welding or other fastening methods. In this way, the first structural member 21 can remain stable relative to the central body 1 during the drone mode switching process.

[0088] In some embodiments of this disclosure, the second structural member 22 is rotatably connected to the first connecting portion 213 of the first structural member 21. In this case, the first connecting portion 213 can be a rotary joint or a rotary shaft, thereby realizing the rotation of the second structural member 22 relative to the first structural member 21. Correspondingly, auxiliary components such as bearings and slip rings can be provided on the first structural member 21 to reduce friction and wear during rotation.

[0089] For example, in the case where the second structural member 22 is rotatably connected to the first connecting part 213 of the first structural member 21, the first connecting part 213 may be a cylinder or sphere with an inner hole in which a bearing is installed so that the second connecting part 223 (which may be a shaft or pin, etc.) can rotate smoothly in the inner hole.

[0090] In some embodiments of this disclosure, the second structural member 22 is rotatably connected to the central body 1. In this case, the second connecting part 223 can be a rotary joint or a rotary bracket, thereby enabling the second structural member 22 to rotate relative to the central body 1. The central body 1 can be provided with a corresponding support structure and a rotation shaft to support the second structural member 22 and enable the second structural member 22 to rotate relative to the central body 1.

[0091] For example, when the second structural member 22 is rotatably connected to the central body 1, the second connecting part 223 can be a cylinder with external threads or a flange, and the central body 1 can be provided with a corresponding internal thread hole or another flange, so that the second structural member 22 can be connected to the central body 1. At the same time, the central body 1 can also be provided with a bearing seat and a bearing to reduce friction and wear during rotation.

[0092] Referring to Figures 2, 10, 11 and 12, in some possible embodiments of this disclosure, one of the first connecting portion 213 and the second connecting portion 223 includes a shaft body 2131, and the other of the first connecting portion 213 and the second connecting portion 223 includes a bushing 2231; the bushing 2231 is sleeved on the outer peripheral side of the shaft body 2131, and the first structural member 21 and the second structural member 22 are rotatably connected relative to each other.

[0093] In this embodiment of the disclosure, the first connecting part 213 may include a shaft 2131, and the second connecting part 223 may include a bushing 2231. The bushing 2231 is sleeved on the outer periphery of the shaft 2131. When the second structural member 22 rotates relative to the first structural member 21, the bushing 2231 rotates relative to the shaft 2131 about the central axis of the shaft 2131.

[0094] In some embodiments of this disclosure, the first connecting part 213 may include a bushing 2231, and the second connecting part 223 may include a shaft body 2131. The bushing 2231 is sleeved on the outer periphery of the shaft body 2131. When the second structural member 22 rotates relative to the first structural member 21, the shaft body 2131 rotates within the bushing 2231.

[0095] In this embodiment, the shaft 2131 can be a cylindrical or cuboid component, and its outer periphery can be a smooth surface or have threads, grooves, or other structures to mate with the bushing 2231. The bushing 2231 is typically a hollow tubular component, and its inner diameter matches the outer diameter of the shaft 2131 so that the bushing 2231 can be tightly fitted onto the outer periphery of the shaft 2131. The inner wall of the bushing 2231 can be designed with a lubricating layer, a wear-resistant layer, or a specific mating structure to reduce friction and wear during rotation and improve the smoothness and durability of rotation.

[0096] In this embodiment, the materials of the shaft 2131 and the bushing 2231 can be selected according to the usage environment and requirements of the UAV. For example, for situations requiring the bearing of large torque and radial force, high-strength and high-hardness metallic materials, such as steel and aluminum alloys, can be selected; for situations requiring weight reduction and improved corrosion resistance, non-metallic materials, such as plastics and carbon fiber materials, can be selected.

[0097] The technical solution provided in this disclosure allows for relative rotational connection between the first structural member 21 and the second structural member 22 when the bushing 2231 is fitted onto the outer periphery of the shaft body 2131. This connection method is not only simple in structure and easy to implement, but also capable of withstanding large torque and radial force, making it suitable for various complex UAV morphology transformation requirements.

[0098] Referring to Figures 11 and 12, in some possible embodiments of this disclosure, the first connecting portion 213 includes a bushing 2231, and the bushing 2231 has a groove 2232, which forms the movement space of the second connecting portion 223; or, the second connecting portion 223 includes a bushing 2231, and the bushing 2231 has a groove 2232, which forms the movement space of the first connecting portion 213.

[0099] In this embodiment of the present disclosure, when the first connecting part 213 includes a bushing 2231, the second connecting part 223 includes a shaft 2131, which is disposed inside the bushing 2231. The second connecting part 223 also includes a connector 2132, which can extend out of the bushing 2231 from the groove 2232 and connect with other structures of the second connecting part 223. When the second structural member 22 rotates relative to the first structural member 21, the connector 2132 can move along the space formed by the groove 2232, thereby driving the shaft 2131 to move relative to the bushing 2231.

[0100] In some embodiments of this disclosure, when the second connecting portion 223 includes a bushing 2231, the first connecting portion 213 includes a shaft 2131 disposed within the bushing 2231. The first connecting portion 213 also includes a connector 2132, which extends out of the bushing 2231 from the groove 2232 and connects to other structures of the first connecting portion 213. When the second structural member 22 rotates relative to the first structural member 21, the second structural member 22 drives the bushing 2231 to move relative to the shaft 2131, and the connector 2132 can move along the space formed by the groove 2232.

[0101] In this embodiment of the disclosure, in order to achieve relative rotation between the first structural member 21 and the second structural member 22, the groove 2232 can be opened along the circumference of the bushing 2231. The groove 2232 can be a straight groove or a curved groove. According to the extension route of the groove 2232, the mode and trajectory of relative movement between the second structural member 22 and the first structural member 21 can be changed.

[0102] In the technical solution provided by the embodiments of this disclosure, the second structural member 22 rotates relative to the first structural member 21, and there is mutual movement between the first connecting part 213 and the second connecting part 223. The groove 2232 opened on the bushing 2231 can not only avoid the first connecting part 213 and the second connecting part 223 during relative movement, but also limit the movement between the first structural member 21 and the second structural member and guide the movement trajectory.

[0103] In some possible embodiments of this disclosure, the shaft body 2131 and the bushing 2231 correspond one-to-one; or, the shaft body 2131 is connected to at least two bushings 2231, and the at least two bushings 2231 are arranged sequentially along the rotation axis D; or, the bushing 2231 is connected to at least two shaft bodies 2131, and the at least two shaft bodies 2131 are arranged sequentially along the rotation axis D.

[0104] In this embodiment of the disclosure, when the second structural member 22 and the first structural member 21 are rotatably connected by a bushing 2231 and a shaft body 2131, the rotation axis D can be the central axis of the shaft body 2131. The one-to-one correspondence between the shaft body 2131 and the bushing 2231 can be understood as each shaft body 2131 corresponding to one bushing 2231. Thus, the connection between each bushing 2231 and the shaft body 2131 can provide an independent rotation function.

[0105] In some embodiments of this disclosure, at least two bushings 2231 may be connected to a shaft 2131. The at least two bushings 2231 may be arranged sequentially along the rotation axis D. The bushings 2231 may be evenly or unevenly arranged. For example, when two bushings 2231 are provided on a shaft 2131, the two bushings 2231 may be respectively provided at the two ends of the shaft 2131. When three bushings 2231 are provided on a shaft 2131, the three bushings 2231 may be evenly arranged on the outer periphery of the shaft 2131.

[0106] In some embodiments of this disclosure, the bushing 2231 can connect at least two shafts 2131. It can be understood that at least two shafts 2131 can be provided within the two bushings 2231. For example, when the second connecting part 223 includes a shaft 2131, multiple second connecting parts 223 can be provided, and correspondingly multiple second structural members 22 can be provided, so that multiple second structural members 22 can achieve different rotations relative to the second structural member 22.

[0107] The technical solution provided in this disclosure can be composed of multiple independently rotatable parts through the cooperation of different numbers of shafts 2131 and bushings 2231. In this way, the rotation mode of the first structural member 21 and the second structural member 22 can be flexibly set.

[0108] Referring to Figures 11 and 12, in some possible embodiments of this disclosure, the first connecting portion 213 and the second connecting portion 223 are disposed at the ends of the central body 1; or, the first connecting portion 213 forms a receiving space, and at least a portion of the central body 1 is disposed within the receiving space.

[0109] In this embodiment, the first connecting portion 213 and the second connecting portion 223 are disposed at the ends of the central body 1. This can be understood as the first structural member 21 being connected to the central body 1 via the first connecting portion 213, and the second structural member 22 being connected to the central body 1 via the second connecting portion 223. Since the first structural member 21 and the central body 1 are relatively fixed, while the second structural member 22 and the central body 1 are relatively movable, the first connecting portion 213 and the central body 1 can be fixedly connected, and the second connecting portion 223 and the central body 1 can be connected according to the mode of movement.

[0110] In some embodiments of this disclosure, the first connecting portion 213 and the second connecting portion 223 are disposed at the ends of the central body 1, so that other functional devices, such as cameras and sensors, can be disposed in the middle part of the central body 1, and the first connecting portion 213 and the second connecting portion 223 will not obstruct these functional devices.

[0111] In some embodiments of this disclosure, the first connecting part 213 and the central body 1 are fixedly disposed relative to each other. The first connecting part 213 can be a cylindrical structure or a structure with a space reserved in the middle to form a receiving space, and the central body 1 is fixed in the receiving space. The receiving space can be provided with an opening in a certain area of ​​the first connecting part 213. For example, an opening can be provided at the end of the first connecting part 213, and the camera provided on the central body 1 can be exposed from the opening to perform shooting work. The second connecting part 223 can be connected to the first connecting part 213.

[0112] Referring to FIG13, in some possible embodiments of this disclosure, the drone further includes a locking structure 5, a first portion 51 of which is connected to a second structural member 22, and a second portion 52 of which is connected to a first structural member 21 or a central body 1; the locking structure 5 is configured to lock or unlock the relative movement of the first structural member 21 and the second structural member 22.

[0113] In this embodiment, the locking structure 5 is configured to lock or unlock the relative movement of the first structural member 21 and the second structural member 22. When the drone switches between different modes, if the second structural member 22 moves to a predetermined position relative to the first structural member 21, or if the drone needs to be transported or stored, the locking mechanism triggers a locking state, locking the second structural member 22 and the first structural member 21. If the drone needs to switch between modes again, or if the drone needs to be transported or stored, the locking mechanism triggers an unlocking state, allowing the first structural member 21 and the second structural member 22 to move relative to each other.

[0114] In this embodiment, the locking structure 5 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 51 of the locking structure 5 can be a pin connected to the second structural member 22, and the second part 52 can be a lock seat with a socket connected to the first structural member 21 or the central body 1. The pin and lock seat can be connected to the second structural member 22, the first structural member 21, or the central body 1 via threaded connection, welding, or snap-fit. When the relative positions of the second structural member 22 and the first structural member 21 or the central body 1 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 51 and the second part 52 can also be interchanged.

[0115] In some embodiments of this disclosure, the locking structure 5 can also employ electromagnetic locking, based on the principle of electromagnetic attraction, to achieve locking by controlling electromagnetic force. For example, the first part 51 of the locking structure 5 can be an electromagnet connected to the second structural member 22, and the second part 52 can be a lock seat with an iron core connected to the first structural member 21 or the central body 1. When the electromagnet is energized, it generates magnetic force to attract the iron core, so that the second structural member 22 is tightly fitted with the first structural member 21 or the central body 1, achieving locking. When unlocking, the power supply to the electromagnet is cut off, the magnetic force disappears, and the second structural member 22 can move. The structures of the first part 51 and the second part 52 can also be interchanged.

[0116] The technical solution provided in this disclosure is that the locking structure 5 can lock or unlock the relative movement of the first structural member 21 and the second structural member 22, 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.

[0117] Referring to FIG14, in some possible embodiments of this disclosure, there are at least two first structural members 21, and at least two first structural members 21 are arranged along the extension direction of the central body 1; or, there are at least two second structural members 22, and at least two second structural members 22 are arranged along the extension direction of the central body 1; or, there are at least two first structural members 21 and at least two second structural members 22, and at least two first structural members 21 are arranged along the extension direction of the central body 1, and at least two second structural members 22 are arranged along the extension direction of the central body 1.

[0118] In this embodiment of the present disclosure, when the first structural member 21 and the second structural member 22 are wings, the wings are usually installed on both sides of the fuselage (central body 1). It can be understood that a second structural member 22 is provided on one side of the central body 1, and at least two first structural members 21 are provided on the other side. The at least two first structural members 21 are arranged along the extension direction of the central body 1.

[0119] In some embodiments of this disclosure, a first structural member 21 is provided on the central body 1, and at least two second structural members 22 are also provided. The at least two second structural members 22 are arranged along the extending direction of the central body 1, and the at least two second structural members 22 can be movably set relative to the central body 1. In this way, the drone can have more morphological changes, thereby adapting to more usage environments.

[0120] In some embodiments of this disclosure, two first structural members 21 and at least two second structural members 22 may be provided on the central body 1. It should be noted that the number, size, and layout of the first structural members 21 and the second structural members 22 can be adjusted according to the flight performance and mission requirements of the UAV.

[0121] Referring to FIG13, in some possible embodiments of this disclosure, the drone further includes an electronic device 6, which includes an active state and a disabled state; in response to the drone switching from a first state to a second state, the electronic device 6 switches to an active state; in response to the drone switching from a second state to a first state, the electronic device 6 switches to a disabled state.

[0122] In this embodiment, the active state of electronic device 6 can be understood as the power-on state of electronic device 6. In the active state, electronic device 6 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 6 can be understood as the power-off state of electronic device 6. In the disabled state, electronic device 6 is turned off or in a low-power standby mode and does not perform any functions.

[0123] In this embodiment of the disclosure, 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 6 needs to be activated to support the drone's flight operations. The state switching of the electronic device 6 may be triggered by a mechanical trigger, sensor signal, or user command.

[0124] Conversely, when the drone completes its flight mission and is ready to return to its compact form, the electronics 6 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.

[0125] Referring to Figures 15, 16, 17 and 18, in some possible embodiments of this disclosure, the first structural member 21 and the second structural member 22 further include a protective cover 226, which is disposed corresponding to the power assembly 3 and extends to the side of the power assembly 3 away from the central body 1.

[0126] In this embodiment of the disclosure, the power device provided on the first structural member 21 and the second structural member 22 may include structures such as propellers and motors. The first structural member 21 and the second structural member 22 may also be provided with structures such as lines, sensors, and ducts. Therefore, the protective cover 226 can protect the power component 3 or other structures on the first structural member 21 and the second structural member 22.

[0127] In this embodiment, the protective cover 226 extends to the side of the power assembly 3 away from the central body 1, so that the protective cover 226 can protect as many components on the first structural member 21 and the second structural member 22 as possible, so that the power assembly 3 is still protected even during the flight or operation of the UAV.

[0128] In this embodiment, to reduce the weight of the drone while maintaining the strength of the protective shield 226, the protective shield 226 can be made of lightweight materials such as carbon fiber, glass fiber, or high-strength plastic. The shape of the protective shield 226 can be streamlined, rectangular, etc., and ventilation holes can be provided on the protective shield 226 to help dissipate heat from the power component 3 and prevent overheating. The ventilation holes can be designed as mesh, honeycomb, or other shapes.

[0129] Referring to Figures 17 and 18, in some possible embodiments of this disclosure, at least one of the first structural member 21 and the second structural member 22 is formed with a clearance space F. In a first configuration, at least a portion of the other of the first structural member 21 and the second structural member 22 is accommodated in the clearance space F.

[0130] In this embodiment of the disclosure, the clearance space F may be a groove, recess, or hollow structure with an opening provided inside or on the surface of the first structural member 21 or the second structural member 22. The size and shape of the clearance space F are capable of accommodating at least a portion of the second structural member 22 or the first structural member 21.

[0131] In this embodiment, the clearance space F may be provided on the first structural member 21, the second structural member 22, or both the first and second structural members 21 may have clearance spaces F. The clearance space F may contain a portion of the first structural member 21 or the second structural member 22, a functional device disposed on the first structural member 21 or the second structural member 22, or a portion of the protective cover 226 on the first structural member 21 or the second structural member 22. This disclosure does not limit the scope of the invention.

[0132] For example, referring to Figures 17 and 18, both the first structural member 21 and the second structural member 22 are provided with protective covers 226. The protective covers 226 are hollow structures, and the protective covers 226 have clearance openings along the extension direction of the central body 1. The clearance openings and the space inside the protective covers 226 together form a clearance space F. The clearance openings on the first structural member 21 and the second structural member 22 are spaced apart. Thus, when the drone is in the first form, part of the protective cover 226 structure of the first structural member 21 can be accommodated in the clearance space F of the second structural member 22, and part of the protective cover 226 structure of the second structural member 22 can be accommodated in the clearance space F of the first structural member 21. This reduces the common size of the first structural member 21 and the second structural member 22 in the first form, thereby reducing the volume of the drone.

[0133] The technical solution provided in this disclosure, in a first configuration, at least a portion of the other of the first structural member 21 and the second structural member 22 is housed in a clearance space F. This not only helps reduce the size of the drone in the first configuration (not in operation or in storage) and improves space utilization, but also protects the structure housed in the clearance space F 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 22 can be removed from the clearance space F and deployed so that the drone can switch to the operational state.

[0134] Obviously, the above embodiments are illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this disclosure.

Claims

1. An unmanned aerial vehicle (UAV), comprising: The central unit is equipped with functional components; The fuselage assembly is connected to the central body. The fuselage assembly includes a first structural component and a second structural component. The first structural component and the second structural component are respectively provided with a power component. The first structural component and the second structural component can move relative to each other, so that the drone has different first and second forms. The first structural component is fixedly disposed relative to the central body, and the second structural component is movable relative to the central body.

2. The UAV according to claim 1, wherein, In the first configuration, the first structural member and the second structural member are relatively close to each other and have a first included angle; in the second configuration, the first structural member and the second structural member are relatively far apart and have a second included angle; the first included angle is smaller than the second included angle.

3. The UAV according to claim 2, wherein, The first structural member includes a first surface, and the second structural member includes a second surface; the first surface and the second surface have the first included angle; in the first configuration, the first surface and the second surface are disposed opposite to each other, and the first included angle is less than or equal to 30 degrees.

4. The UAV according to claim 3, wherein, In the first configuration, the first surface and the second surface satisfy the parallel condition.

5. The UAV according to claim 3, wherein, In the first configuration, the first surface and the second surface are at least partially attached.

6. The UAV according to claim 3, wherein, In the first configuration, the first surface and the second surface are at least partially spaced apart by a predetermined distance.

7. The UAV according to claim 3, wherein, In the second configuration, the first surface and the second surface satisfy the coplanar condition.

8. The UAV according to claim 3, wherein, The extension surface of the second surface and the first surface have a third included angle; in the second configuration, the third included angle is less than or equal to 30 degrees.

9. The UAV according to any one of claims 1 to 8, wherein, The first structural member includes a third surface, and the second structural member includes a fourth surface; In the first configuration, the third surface and the fourth surface are disposed opposite to each other, and the third surface and the fourth surface satisfy the condition of parallelism.

10. The UAV according to claim 9, wherein, In the first configuration, at least one of the third and fourth surfaces satisfies the condition of being flush with the outer surface of the central body.

11. The UAV according to claim 9, wherein, It also includes a structural portion disposed on the outer surface of the central body, the structural portion including a structural surface away from the central body; In the first configuration, at least one of the third and fourth surfaces satisfies the condition of being flush with the structural surface.

12. The UAV according to any one of claims 1 to 11, wherein, The first structural component and the second structural component are arranged to rotate relative to each other about a rotation axis; In the first configuration, the first structural member and the second structural member are arranged opposite each other about a preset plane, and the preset plane passes through the axis of rotation.

13. The UAV according to claim 12, wherein, The first structural component includes a first connecting portion, and the second structural component includes a second connecting portion; The first connecting part and the second connecting part are respectively connected to the central body; or, the first connecting part is connected to the central body, and the second connecting part is connected to the first connecting part.

14. The UAV according to claim 13, wherein, One of the first connecting portion and the second connecting portion includes a shaft, and the other of the first connecting portion and the second connecting portion includes a bushing; The bushing is fitted onto the outer periphery of the shaft, and the first structural component and the second structural component are rotatably connected relative to each other.

15. The UAV according to claim 14, wherein, The first connecting part includes the bushing, and the bushing has a groove, the groove forming a movement space for the second connecting part; or, the second connecting part includes the bushing, and the bushing has a groove, the groove forming a movement space for the first connecting part.

16. The drone according to claim 14, wherein, The shaft and the bushing are in one-to-one correspondence; or, the shaft is connected to at least two bushings, and the at least two bushings are arranged sequentially along the axis of rotation; or, the bushing is connected to at least two shafts, and the at least two shafts are arranged sequentially along the axis of rotation.

17. The UAV according to claim 13, wherein, The first connecting portion and the second connecting portion are disposed at the ends of the central body; or, The first connecting portion forms a receiving space, and at least a portion of the central body is disposed within the receiving space.

18. The UAV according to any one of claims 1 to 17, wherein, 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 configured to lock or unlock the relative movement of the first structural member and the second structural member.

19. The UAV according to any one of claims 1 to 18, wherein, There are at least two first structural members, and at least two first structural members are arranged along the extension direction of the central body; or, there are at least two second structural members, and at least two second structural members are arranged along the extension direction of the central body; or, there are at least two first structural members and at least two second structural members, and at least two first structural members are arranged along the extension direction of the central body, and at least two second structural members are arranged along the extension direction of the central body.

20. The UAV according to any one of claims 1 to 19, wherein, 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 device switches to a disabled state.

21. The UAV according to any one of claims 1 to 20, wherein, The first structural component and the second structural component also include a protective cover, which is disposed corresponding to the power assembly and extends to the side of the power assembly away from the central body.

22. The UAV according to any one of claims 2 to 21, wherein, At least one of the first structural member and the second structural member has 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 in the clearance space.

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