Sea-land-air multipurpose multi-rotor unmanned aerial vehicle

Abstract

The invention discloses a sea-land-air multipurpose multi-rotor unmanned aerial vehicle. The unmanned aerial vehicle comprises a fuselage; the multiple arm mechanisms are arranged on the fuselage in a spaced mode in pairs and comprise arms, deformation joints, rotating joints, blades, rollers and driving mechanisms, the arms are connected to the fuselage, the blades, the rollers and the driving mechanisms are all installed on the rotating joints, the rotating joints are rotationally arranged relative to the deformation joints, and the deformation joints are rotationally arranged relative to the arms; the driving mechanism is used for driving the rollers and the blades to rotate. The sea-land-air multipurpose multi-rotor unmanned aerial vehicle can be used in the air, on the land and in water, and has high practicability.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle (UAV) technology, specifically relating to a multi-rotor UAV that can be used for sea, land, and air operations. Background Technology

[0002] With the rapid development of drone technology, drones are increasingly being used in daily life. Currently, drones typically include multi-rotor drones and fixed-wing drones. However, existing drone technologies are simple to use and are generally only suitable for aerial flight, limiting their application. Summary of the Invention

[0003] The purpose of this invention is to disclose a multi-purpose multi-rotor unmanned aerial vehicle (UAV) for use on land, sea, and air, in order to solve the technical problem of the limited usage of UAVs in the prior art.

[0004] To achieve the above objectives, this invention discloses a multi-purpose multi-rotor unmanned aerial vehicle (UAV) for sea, land, and air use, comprising:

[0005] body;

[0006] Multiple robotic arm mechanisms are arranged in pairs on the fuselage, including robotic arms, deformable joints, rotary joints, blades, rollers, and drive mechanisms. The robotic arms are connected to the fuselage. The blades, rollers, and drive mechanisms are all mounted on the rotary joints. The rotary joints are rotatably arranged relative to the deformable joints, and the deformable joints are rotatably arranged relative to the robotic arms. The drive mechanism is used to drive the rollers and blades to rotate.

[0007] As an optional implementation, the deformable joint includes a first drive member and a first joint connected together, the first output shaft of the first drive member being connected to the arm, and the first joint mounting the rotary joint.

[0008] As an optional implementation, the rotary joint includes a second drive member and a second joint connected to each other, the output shaft of the second drive member being connected to the deformable joint, and the second joint mounting the blade, the roller, and the drive mechanism.

[0009] As an optional implementation, the roller is arranged parallel to the propeller blade, and when the UAV is in flight, the roller is located below the propeller blade.

[0010] As an optional implementation, the drive mechanism is connected between the blade and the roller, the rotation axis of the blade coincides with the rotation axis of the roller, and the blade is foldable relative to the rotary joint.

[0011] As an optional implementation, the blade includes a main body section and folding sections at both ends of the main body section. The main body section is connected to the output shaft of the drive mechanism, and the folding sections are rotatably arranged relative to the main body section so as to be in a folded or unfolded state relative to the main body section.

[0012] As an optional implementation, the multi-rotor UAV for land, sea and air use also includes a first locking mechanism, which is used to lock the folding section relative to the main body section when the folding section is in a folded state.

[0013] As an optional implementation, the multi-rotor UAV for land, sea and air use also includes a second locking mechanism, which is used to lock the folding section relative to the main body section when the folding section is in the unfolded state.

[0014] As an optional implementation, the arm is telescopic relative to the body.

[0015] As an optional implementation, the fuselage, the deformable joint, the rotating joint, and the propeller blades are all made of carbon fiber material.

[0016] Compared with the prior art, the beneficial effects of the multi-purpose multi-rotor UAV for sea, land and air use of the present invention are as follows:

[0017] The multi-rotor UAV of this invention, capable of operating in the air, land, and sea, mounts propellers, rollers, and a drive mechanism on a rotating joint. The drive mechanism drives the propellers and rollers to rotate, and the rotating joint is rotatably positioned relative to the deformable joint. This allows the propellers to rotate until their rotation axis b is parallel to the fuselage's central axis a, enabling flight. Alternatively, the rollers can rotate until their rotation axis c is perpendicular to the fuselage's central axis a, placing them vertically and allowing them to contact a support surface for movement on land. Furthermore, when both the roller's rotation axis c and the propeller's rotation axis b are perpendicular to the fuselage's central axis a, the propellers can move in water. The rotation of the deformable joint relative to the arm allows for control of the direction of movement in water. Therefore, this multi-rotor UAV of the present embodiment is highly practical and can be used in the air, on land, and at sea. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the usage state of a multi-purpose multi-rotor UAV for land, sea and air according to an embodiment of the present invention;

[0020] Figure 2 yes Figure 1 A schematic diagram illustrating another usage state of the multi-rotor UAV used for land, sea, and air operations;

[0021] Figure 3 yes Figure 1 A schematic diagram illustrating another usage state of the multi-rotor UAV used for land, sea, and air operations;

[0022] Figure 4 yes Figure 3 A schematic diagram of the arm mechanism in the diagram;

[0023] Figure 5 yes Figure 4 An exploded view of the arm mechanism in the diagram;

[0024] Figure 6 yes Figure 5 A schematic diagram of the propeller blades in a semi-folded state;

[0025] Figure 7 yes Figure 5 A schematic diagram of the propeller blades in a folded state.

[0026] Explanation of key figure labels:

[0027] 100-Multi-purpose multi-rotor UAV for land, sea, and air use; 10-Fuselage; 11-Transparent window; 12-LiDAR; 13-Camera; 20-Arm mechanism; 21-Arm; 22-Deformable joint; 221-First drive component; 222-First joint; 23-Rotating joint; 231-Second drive component; 232-Second joint; 24-Propeller blade; 241-Main body section; 242-Folding section; 243-First groove; 244-Second groove; 25-Roller; 26-Drive mechanism; 30-First locking mechanism; 31-First magnetic component; 32-Second magnetic component; 40-Second locking mechanism; 41-Third magnetic component; 42-Fourth magnetic component. Detailed Implementation

[0028] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0029] In this invention, the terms "upper," "lower," "left," "right," "front," "rear," "top," "bottom," "inner," "outer," "middle," "vertical," "horizontal," "lateral," and "longitudinal" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. These terms are primarily for the purpose of better describing the invention and its embodiments, and are not intended to limit the indicated devices, elements, or components to having a specific orientation, or to be constructed and operated in a specific orientation.

[0030] Furthermore, in addition to indicating direction or positional relationship, some of the aforementioned terms may also have other meanings. For example, the term "above" may also be used in certain situations to indicate a dependency or connection. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances.

[0031] Furthermore, the terms "installation," "setup," "equipped with," "connection," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral structure; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium, or an internal connection between two devices, components, or parts. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances.

[0032] Furthermore, the terms "first," "second," etc., are primarily used to distinguish different devices, components, or parts (which may be the same or different in specific type and construction), and are not intended to indicate or imply the relative importance or quantity of the indicated devices, components, or parts. Unless otherwise stated, "a plurality of" means two or more.

[0033] The technical solution of the present invention will be further described below with reference to the embodiments and accompanying drawings.

[0034] Please see Figures 1 to 7 This application provides a multi-purpose multi-rotor unmanned aerial vehicle (UAV) 100 for use on land, sea, and air, including a fuselage 10 and multiple arm mechanisms 20.

[0035] The fuselage 10 serves as the mounting base; multiple arm mechanisms 20 are arranged in pairs on the fuselage 10, including arms 21, deformable joints 22, rotary joints 23, blades 24, rollers 25, and drive mechanisms 26. Arms 21 are connected to the fuselage 10, and blades 24, rollers 25, and drive mechanisms 26 are all mounted on rotary joints 23. Rotary joints 23 are rotatably arranged relative to deformable joints 22, and deformable joints 22 are rotatably arranged relative to arms 21. Drive mechanisms 26 are used to drive rollers 25 and blades 24 to rotate.

[0036] The aforementioned multi-rotor UAV 100, capable of operating on land, sea, and air, mounts the rotor blades 24, rollers 25, and drive mechanism 26 onto a rotating joint 23. The drive mechanism 26 drives the rotor blades 24 and rollers 25 to rotate, and the rotating joint 23 is rotatably positioned relative to the deformable joint 22. This allows the rotor blades 24 to rotate until their rotation axis b is parallel to the central axis a of the fuselage 10, enabling flight and aerial use. Alternatively, the rollers 25 can rotate until their rotation axis c is perpendicular to the central axis a of the fuselage 10, meaning the rollers 25 are vertically positioned. In this configuration, the rotor 24 can contact the support surface for walking, and can be used on land. Alternatively, when the rotation axis c of the roller 25 is perpendicular to the central axis a of the fuselage 10 and the rotation axis b of the propeller 24 is also perpendicular to the central axis a of the fuselage 10, the rotation of the propeller 24 can be used for walking in water, such as gliding in the complex environment of seawater. Furthermore, the direction of travel in water can be controlled by the rotation of the deformable joint 22 relative to the arm 21. Thus, the multi-purpose multi-rotor UAV 100 of this embodiment has strong practicality and can be used in the air, on land, and at sea.

[0037] For ease of explanation, the 100 multi-rotor UAV for land, sea and air use will be referred to as UAV for short.

[0038] It should be noted that the various attitudes of the drone in this embodiment are illustrated using the drone parked on a horizontal parking platform as an example: Please refer to [link to relevant documentation]. Figure 1 When the drone is in flight, the propeller 24 has a rotation axis b, which is perpendicular to the platform on which the landing platform is located. The cross-section of the roller 25 is also parallel to the plane of the landing platform; that is, the central axis c of the roller 25 is perpendicular to the plane of the landing platform. The roller 15 is set parallel to the plane of the landing platform. (Refer to point 2) When the drone is used on land, the rotation axis c of the roller 25 is parallel to the plane of the landing platform; that is, the cross-section of the roller 25 is perpendicular to the plane of the landing platform, thus enabling it to contact the ground for movement. (Refer to point 3) Figure 3 When the drone is used in water, the axis b of the rotor blade 24 is in a plane parallel to the landing platform, and the central axis c of the roller 25 is also parallel to the landing platform. When the rotor blade 24 rotates in the water, it can glide in the water, and the rotation speed of the rotor blade 24 can be controlled to control the speed of gliding in the water.

[0039] Please see Figure 4 and Figure 5In one embodiment of the present invention, when the deformable joint 22 rotates relative to the arm 21, a first rotating shaft can be provided on the deformable joint 22. The first rotating shaft is rotatably configured relative to the arm 21 and has damping relative to the arm 21. The deformable joint 22 can be manually driven to rotate, thereby adjusting the orientation of the rotary joint 23, the blade 24, the roller 25, and the drive mechanism 26 relative to the arm 21. Alternatively, in another embodiment, the rotation of the deformable joint 22 relative to the arm 21 can be achieved by electric drive, so as to adjust the angle between the deformable joint 22 and the arm 21 in real time as needed.

[0040] Specifically, the deformable joint 22 in this embodiment includes a first drive member 221 and a first joint 222 connected to each other. The first output shaft of the first drive member 221 is connected to the arm 21, and the first joint 222 is equipped with a rotary joint 23. Thus, by setting the first drive member 221, the first output shaft rotates relative to the arm 21 under the drive of the first drive member 221, which can drive the rotary joint 23 to rotate. This enables the adjustment of the orientation of the propeller 24, roller 25 and drive mechanism 26 relative to the arm 21. Furthermore, by setting the first drive member 221, the angle between the rotary joint 23 and the arm 21 can be adjusted in real time when a command is received. For example, when used in water, the direction of the flight can be controlled in real time, improving the convenience of operating the drone.

[0041] In this embodiment, the first driving component 221 can be configured as a drive motor or a servo motor.

[0042] For the same principle, please refer to Figure 4 and Figure 5 In one embodiment of the present invention, when the rotary joint 23 is rotated relative to the deformable joint 22 (i.e., rotated relative to the first joint 222), a second rotating shaft can be provided on the rotary joint 23. This second rotating shaft is rotated relative to the first joint 222 and has damping relative to the first joint 222. The rotation of the rotary joint 23 can be manually driven to adjust the orientation of the paddle 24, roller 25, and drive mechanism 26 relative to the arm 21. Alternatively, in another embodiment, the rotation of the rotary joint 2322 relative to the first joint 222 can be electrically driven to facilitate real-time adjustment of the orientation of the rotary joint 23 relative to the arm 21 as needed.

[0043] Specifically, the rotary joint 23 in this embodiment includes a second drive member 231 and a second joint 232 connected together. The second output shaft of the second drive member 231 is connected to the first joint 222. The second joint 232 is equipped with a roller 25, a drive mechanism 26, and a propeller 24. Thus, through the setting of the second drive member 231, the second output shaft rotates relative to the first joint 222 under the drive of the second drive member 231, which can drive the roller 25, the drive mechanism 26, and the propeller 24 to rotate. This enables the adjustment of the orientation of the propeller 24, the roller 25, and the drive mechanism 26 relative to the arm 21. Furthermore, through the setting of the second drive member 231, the angle between the second joint 232 and the arm 21 can be adjusted in real time when a command is received. For example, it is possible to control whether the drone is in flight or ground posture in real time, improving the convenience of drone operation.

[0044] In this embodiment, the second driving component 231 can be configured as a drive motor or a servo motor.

[0045] Please see Figures 1 to 4 In one embodiment of the present invention, when the propeller 24 and roller 25 are configured, the roller 25 is arranged parallel to the propeller 24, and when the UAV is in flight mode, the roller 25 is positioned below the propeller 24. Thus, when the UAV is in flight mode, the upper propeller 24 rotates under the drive of the drive mechanism 26, providing the driving force for the UAV's flight. Simultaneously, arranging the roller 25 parallel to the propeller 24 facilitates adjustment of the placement of the roller 25 and propeller 24 when walking on land or gliding in water. In other embodiments, the posture of the propeller 24 and roller 25 when mounted on the deformable joint 22 can be configured as needed.

[0046] Specifically, in this embodiment, when driving the roller 25 and the blade 24 to rotate, the drive mechanism 26 is connected between the blade 24 and the roller 25, and the rotation axis b of the blade 24 and the rotation axis c of the roller 25 coincide. The blade 24 is foldable relative to the deformable joint 22. For example, the drive mechanism 26 can be set as a dual-axis drive motor, with one output shaft connected to the blade 24 and the other output shaft connected to the roller 25, so that the blade 24 and the roller 25 share the same power, thereby achieving the compactness of the entire UAV model and miniaturization. Furthermore, the blade 24 is foldable relative to the deformable joint 22, which allows the blade 24 to be folded, preventing the simultaneous rotation of the blade 24 and the roller 25 from affecting the normal contact between the roller 25 and the support surface under the drive of the drive mechanism 26.

[0047] Understandably, when the blade 24 is in a folded state, the edge of the blade 24 is within the range of the outer edge of the roller 25, that is, the length of the folded blade 24 is less than the diameter of the roller 25, so as to avoid the rotation of the blade 24 interfering with the rotation of the roller 25.

[0048] Specifically, please refer to Figure 6 and Figure 7 The blade 24 includes a main body section 241 and folding sections 242 located at both ends of the main body section 241. The main body section 241 is connected to the output shaft of the drive mechanism 26. The folding sections 242 are rotatably arranged relative to the main body section 241 so that they can be in a folded or unfolded state relative to the main body section 241. In this way, the two folding sections 242 are folded to one side of the main body section 241, shortening the length of the entire blade 24, so that the length of the folded blade 24 is less than the diameter of the roller 25, thus avoiding interference with the rotation of the roller 25.

[0049] Please see Figure 6 and Figure 7 To ensure the stability of the orientation of the folded section 242 relative to the main body section 241 when the propeller 24 is in the folded state, the multi-rotor UAV 100 for land, sea and air use also includes a first locking mechanism 30. The first locking mechanism 30 is used to lock the folded section 242 relative to the main body section 241 when the UAV is in the folded state. Thus, by setting the first locking mechanism 30, when the folded section 242 is in the folded state, it is ensured that the folded section 242 can always be in a fixed position relative to the main body section 241, so as to avoid the folded section 242 opening relative to the main body section 241 when the UAV is used on land, which would affect the normal movement of the roller 25.

[0050] Specifically, the first locking mechanism 30 in this embodiment includes a first magnetic element 31 and a second magnetic element 32 that can attract each other. The first magnetic element 31 is mounted on the surface of the main body segment 241, and the second magnetic element 32 is disposed on the folding segment 242. The first magnetic element 31 and the second magnetic element 32 are used to attract each other when the folding segment 242 is in a folded state relative to the main body segment 241. Thus, by setting the first magnetic element 31 and the second magnetic element 32 to attract each other, the folding segment 242 relative to the main body segment 241 can be quickly folded. In other embodiments, a latch and a locking groove can be respectively provided on the folding segment 242 and the main body segment 241. The folding segment 242 relative to the main body segment 241 is achieved by the latch locking into the locking groove.

[0051] Furthermore, in order to ensure that the folded section 242 fits as closely as possible to the surface of the main body section 241 when the blade 24 is in the folded state, one of the main body section 241 or the folded section 242 has a first groove 243 in the area where the magnetic element is located. When the first magnetic element 31 and the second magnetic element 32 are attracted to each other, one of the magnetic elements can be inserted into the first groove 243. Specifically, in this embodiment, the first magnetic element 31 protrudes from the main body section 241, and the first groove 243 is provided in the area where the second magnetic element 32 is located. The insertion of the first magnetic element 31 into the first groove 243 not only ensures that the first magnetic element 31 and the second magnetic element 32 can fit and attract as closely as possible, but also ensures that the main body section 241 and the folded section 242 fit as closely as possible.

[0052] Please see Figure 6 and Figure 7 To ensure the stability of the orientation of the folding section 242 relative to the main body section 241 when the propeller 24 is in the unfolded state, the multi-rotor UAV 100 for land, sea and air use also includes a second locking mechanism 40. The second locking mechanism 40 is used to lock the folding section 242 relative to the main body section 241 when the UAV is in the unfolded state. In this way, by setting the second locking mechanism 40, when the folding section 242 is in the unfolded state, it is ensured that the folding section 242 can always be fixed relative to the main body section 241, so as to avoid the folding section 242 rotating relative to the main body section 241 when the UAV is in flight or in water, which would affect the normal use of the UAV.

[0053] Specifically, the second locking mechanism 40 in this embodiment includes a third magnetic element 41 and a fourth magnetic element 42 that can attract each other. The third magnetic element 41 is disposed on the end face of the main body segment 241 facing the folded segment 242, and the fourth magnetic element 42 is disposed on the end face of the folded segment 242 facing the main body segment 241. The third magnetic element 41 and the fourth magnetic element 42 are used to attract each other when the folded segment 242 is in an unfolded state relative to the main body segment 241. Through the arrangement of the third magnetic element 41 and the fourth magnetic element 42 attracting each other, when the folded segment 242 needs to be in an unfolded state relative to the main body segment 241, the unfolding of the folded segment 242 relative to the main body segment 241 can be quickly realized. In other embodiments, the main body segment 241 and the folding segment 242 can be connected by an invisible hinge to ensure the continuity of the blade shape and meet aerodynamic requirements; alternatively, a locking pin can be provided on one of the main body segment 241 and the folding segment 242, and a locking hole can be provided on the other. The locking pin can slide along a direction parallel to the surface of the main body segment 241 to be inserted into the locking hole, which can also achieve locking of the folding segment 242 relative to the main body segment 241 when it is in the unfolded state.

[0054] Furthermore, in order to ensure that the end face of the folding section 242 can fit as close as possible to the end face of the main body section 241 when the blade 24 is in the unfolded state, a second groove 244 is provided in the area where the magnetic element is located in either the main body section 241 or the folding section 242. When the third magnetic element 41 and the fourth magnetic element 42 are attracted to each other, the magnetic element can be inserted into the second groove 244.

[0055] Specifically, in this embodiment, the end face of the main body segment 241 is provided with a second groove 244, the third magnetic element 41 is provided corresponding to the second groove 244, and the fourth magnetic element 42 protrudes from the end face of the folded segment 242.

[0056] In order to adapt to different usage scenarios, the arm 21 of this embodiment is telescopic relative to the body 10. For example, depending on the environment, the arm 21 can be telescopic relative to the body 10 manually, or a transmission mechanism such as a motor, gear and rack can be installed on the body 10 to telescopically achieve the telescopic movement of the arm 21 relative to the body 10. In this way, when the arm 21 is in the shortened state, the entire drone becomes smaller, which can be used in more complex environments and confined spaces.

[0057] In addition, in order to ensure that the entire fuselage 10 has a relatively light weight, the fuselage 10, deformable joint 22, rotating joint 23, and propeller 24 in this embodiment can be made of lightweight and high-strength materials, such as carbon fiber. In this way, by using carbon fiber, not only is the structural strength of the whole machine guaranteed, but the whole machine also has the characteristics of being lightweight, which can guarantee the flight range; at the same time, using lightweight materials makes it easy for the entire UAV to be carried when going out.

[0058] Understandably, the drone also includes structures such as a power system and a flight control system installed on the fuselage 10. For example, the power system includes structures such as a battery and a battery control module, and the flight control system includes structures such as a barometer, an inertial navigation unit, GPS, and control circuits. It may also include structures such as a camera 13 and a lidar 12.

[0059] Specifically, in this embodiment, the top of the fuselage 10 is provided with a transparent window 11, and the lidar 12 is located inside the transparent window 11.

[0060] The aforementioned multi-rotor UAV 100, which is used for air, land, and sea operations, can be used in the air, on land, and in water through the rotation of the rotating joint 23 and the deformable joint 22, as well as through the rotation of the roller 25 and the propeller 24. It has multiple uses, meets the operational needs of different complex environments, and improves the practicality of the UAV.

[0061] The technical means disclosed in this invention are not limited to those disclosed in the above embodiments, but also include technical solutions composed of any combination of the above technical features. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of this invention, and these improvements and modifications are also considered within the scope of protection of this invention.

Claims

1. A multi-purpose multi-rotor unmanned aerial vehicle (UAV) for sea, land, and air use, characterized in that: include: Fuselage (10); Multiple arm mechanisms (20) are arranged in pairs on the fuselage (10), including an arm (21), a deformable joint (22), a rotary joint (23), a blade (24), a roller (25), and a drive mechanism (26). The arm (21) is connected to the fuselage (10). The blade (24), the roller (25), and the drive mechanism (26) are all mounted on the rotary joint (23). The rotary joint (23) is rotatably arranged relative to the deformable joint (22). The deformable joint (22) is rotatably arranged relative to the arm (21). The drive mechanism (26) is used to drive the roller (25) and the blade (24) to rotate.

2. The multi-purpose multi-rotor UAV (100) for sea, land, and air use according to claim 1, characterized in that, The deformable joint (22) includes a first drive member (221) and a first joint (222) connected to each other. The first output shaft of the first drive member (221) is connected to the arm (21), and the first joint (222) is mounted on the rotary joint (23).

3. The multi-purpose multi-rotor UAV (100) for sea, land, and air use according to claim 1 or 2, characterized in that, The rotary joint (23) includes a second drive member (231) and a second joint (232) connected to each other. The output shaft of the second drive member (231) is connected to the deformable joint (22). The second joint (232) is equipped with the blade (24), the roller (25) and the drive mechanism (26).

4. The multi-purpose multi-rotor UAV (100) for sea, land, and air use according to claim 1 or 2, characterized in that, The roller (25) is arranged parallel to the propeller (24), and when the UAV is in flight attitude, the roller (25) is located below the propeller (24).

5. The multi-purpose multi-rotor UAV (100) for sea, land, and air use according to claim 1 or 2, characterized in that, The drive mechanism (26) is connected between the blade (24) and the roller (25). The rotation axis of the blade (24) coincides with the rotation axis of the roller (25), and the blade (24) is foldable relative to the rotating joint (23).

6. The multi-purpose multi-rotor UAV (100) for sea, land, and air use according to claim 5, characterized in that, The blade (24) includes a main body section (241) and folding sections (242) located at both ends of the main body section (241). The main body section (241) is connected to the output shaft of the drive mechanism (26). The folding sections (242) are rotatably arranged relative to the main body section (241) so that they can be in a folded or unfolded state relative to the main body section (241).

7. The multi-purpose multi-rotor UAV (100) for sea, land, and air use according to claim 6, characterized in that, The multi-rotor UAV (100) for use in land, sea and air also includes a first locking mechanism (30), which is used to lock the folding section (242) relative to the main body section (241) when the folding section (242) is in a folded state.

8. The multi-purpose multi-rotor UAV (100) for sea, land, and air use according to claim 6, characterized in that, The multi-rotor UAV (100) for use in land, sea and air also includes a second locking mechanism (40), which is used to lock the folding section (242) relative to the main body section (241) when it is in the unfolded state.

9. The multi-purpose multi-rotor UAV (100) for sea, land, and air use according to claim 1 or 2, characterized in that, The arm (21) is telescopically oriented relative to the body (10).

10. The multi-purpose multi-rotor UAV (100) for sea, land, and air use according to claim 1 or 2, characterized in that, The fuselage (10), the deformable joint (22), the rotating joint (23), and the propeller (24) are all made of carbon fiber material.

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