Drones

Abstract

The application discloses an unmanned plane and relates to the technical field of aircrafts. The unmanned plane comprises an unmanned plane body, a floating assembly and a connecting piece. The floating assembly is arranged on one side of the unmanned plane body and is used for providing buoyancy for the unmanned plane body. The connecting piece is connected between the unmanned plane body and the floating assembly and can be switched between an extended state and a contracted state. When the unmanned plane is in a flying state, the connecting piece is in the extended state, the floating assembly and the unmanned plane body are spaced apart by a set distance, and the floating assembly is hung on the unmanned plane body. When the unmanned plane is in a floating state, the connecting piece is in the contracted state, and the floating assembly provides support for the unmanned plane body. The unmanned plane provided by the application can ensure the stability of the unmanned plane in the floating state and facilitate the control of the unmanned plane in the flying state.

Description

Technical Field

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

[0002] Currently, some seaplanes have floating components fixedly attached to their undersides. This allows the drone to maintain a portion of its fuselage above the water after landing, providing some resistance to wind and waves and ensuring equipment safety and stability during water operations. However, this design of undermount floating components significantly lowers the drone's overall center of gravity during flight, placing a considerable burden on and impacting flight control. Utility Model Content

[0003] The purpose of this application is to provide a drone that can be easily controlled while ensuring the stability of the drone's buoyancy.

[0004] To address the aforementioned technical problems, this application provides the following technical solutions: This application provides a drone, including: The main body of the drone; A floating component is located on one side of the drone body to provide buoyancy for the drone body; The connector connects the drone body and the floating components and can switch between extended and retracted states. When the drone is in flight, the connector is in an extended state, the floating component is spaced a set distance from the drone body, and the floating component is suspended on the drone body; when the drone is floating, the connector is in a retracted state, and the floating component provides support for the drone body.

[0005] In some modified embodiments of this application, the connector includes: A connecting rope connects the drone body to the floating components. The elastic element is connected to the connecting rope and can elastically deform to allow the connecting element to switch between a stretched state and a contracted state.

[0006] In some modified embodiments of this application, the connector further includes: The connecting sleeve has an elastic element inside it. One end of the elastic element is connected to the end of the connecting sleeve that is closer to the main body of the drone, and the other end of the elastic element is connected to the connecting rope. The connecting sleeve is connected to the floating component. When the drone is in flight, the floating component moves the connecting sleeve away from the drone body, the elastic element deforms elastically, the connecting sleeve and the drone body are spaced at a set distance, and the connecting rope provides tension to the floating component so that the floating component is suspended on the drone body; when the drone is floating, the elastic element moves the connecting sleeve closer to the drone body so that the connecting sleeve and the drone body are in contact and provide support for the drone body.

[0007] In some modified embodiments of this application, the connector further includes: A connecting sleeve is fixedly connected to the side of the drone body away from the floating component. An elastic element is set inside the connecting sleeve. One end of the elastic element is connected to the end of the connecting sleeve away from the drone. The other end of the elastic element is connected to one end of the connecting rope, and the other end of the connecting rope is detachably connected to the floating component. When the drone is in flight, the floating component moves the connecting rope closer to the drone body, the elastic element deforms elastically, the floating component and the drone body are spaced at a set distance, and the connecting rope provides tension to the floating component so that the floating component is suspended on the drone body; when the drone is floating, the elastic element moves the floating component and the drone body closer to each other so that the floating component and the drone body are in contact and provide support for the drone body.

[0008] In some modified embodiments of this application, a guide block is provided on the main body of the drone, and a guide hole is provided at one end of the connecting sleeve near the drone. The guide hole and the guide block cooperate, and the connecting rope passes through the guide block and connects to the elastic element.

[0009] In some modified embodiments of this application, the guide block includes: The mating part is fixedly connected to the main body of the UAV and is adapted to the guide hole; The extension is located on the side of the mating part away from the main body of the drone, and the cross-section of the extension gradually decreases towards the side away from the main body of the drone.

[0010] In some modified embodiments of this application, the side wall of the mating part is provided with a first snap-fit ​​part, and the wall of the guide hole is provided with a second snap-fit ​​part, and the first snap-fit ​​part and the second snap-fit ​​part are adapted to each other.

[0011] In some modified embodiments of this application, the guide hole is located at the center of the connecting sleeve, and a first insertion part is provided at the end of the connecting sleeve near the UAV, and a second insertion part is provided on the side of the UAV near the connecting sleeve, with the first insertion part and the second insertion part being compatible with each other.

[0012] In some modified embodiments of this application, it also includes: A locking device is installed between the connecting sleeve and the drone body to lock the position of the connecting sleeve.

[0013] In some modified embodiments of this application, it also includes: The first magnetic part is located on the side of the UAV body near the connecting sleeve; The second magnetic part is located on the side of the connecting sleeve near the main body of the drone; the first magnetic part and the second magnetic part can be magnetically connected.

[0014] In some modified embodiments of this application, the first magnetic part or the second magnetic part is an electromagnet. When the drone is in a floating state, the first magnetic part and the second magnetic part are magnetically connected. When the drone is in a flight state, the first magnetic part and the second magnetic part repel each other.

[0015] In some modified embodiments of this application, the first magnetic part and the second magnetic part are arranged along a first direction, which is perpendicular to the extension direction of the connecting sleeve.

[0016] In some modified embodiments of this application, it also includes: A drive unit is connected to a connector. The drive unit is used to pull the connector to switch the connector between an extended state and a retracted state. When the drone is in flight, the drive unit controls the connector to be in an extended state, and the floating component and the drone body are spaced at a set distance, with the floating component hanging on the drone body; when the drone is in a floating state, the drive unit pulls the connector to make the connector retract, and the floating component and the drone body approach and contact each other, with the floating component providing support for the drone body.

[0017] In some modified embodiments of this application, the floating component includes; Connecting rod, connecting rod and connector; The float, which is attached to the connecting rod, is used to provide buoyancy for the main body of the drone; The center of gravity adjustment component is located at the end of the connecting rod furthest from the main body of the drone.

[0018] In some modified embodiments of this application, the connector includes: Elastic rubber strip: The elastic rubber strip provides elasticity to the connector, allowing the connector to switch between a stretched and contracted state. The tubular structure is wrapped around the outside of the elastic rubber strip to protect the elastic rubber strip, constrain its radial deformation, and guide its axial expansion and contraction.

[0019] In some modified embodiments of this application, the elastic element is a spring or elastic plastic; The connecting rope can be made of metal wire, nylon rope, or power cord.

[0020] Compared to existing technologies, the present application provides a connector that can switch between extended and retracted states to connect the floating component and the drone body. When the drone is in flight, the connector is in the extended state, the floating component and the drone body are spaced at a set distance, and the floating component is suspended on the drone body. This allows operators to easily control the drone using mature suspension algorithms, reducing the burden and impact on drone flight control. When the drone is floating, the connector is in the retracted state, and the floating component provides support for the drone body, ensuring floating stability. Attached Figure Description

[0021] The above and other objects, features, and advantages of exemplary embodiments of this application will become readily understood by reading the following detailed description with reference to the accompanying drawings. In the drawings, several embodiments of this application are illustrated by way of example and not limitation, with the same or corresponding reference numerals denoteing the same or corresponding parts, wherein: Figure 1 A schematic diagram of a partial structure of a drone in a floating state is shown. Figure 2 A schematic diagram of a partial structure of a drone in flight is shown. Figure 3 schematically shown Figure 1 A partial structural diagram; Figure 4 A partial structural diagram of a second embodiment of a drone is schematically shown; Figure 5 A schematic diagram of the structure of a drone is shown. Figure 6 A schematic diagram of a third embodiment of a drone is shown. Figure 7 The diagram schematically illustrates the structure of a first connector and a second connector of a drone engaging. Figure 8 A partial structural diagram of a fourth embodiment of a drone is schematically shown.

[0022] Explanation of icon numbers: 1. UAV body; 11. Frame; 12. Rotor; 13. Guide block; 131. Mating part; 132. Extension part; 133. First snap-fit ​​part; 14. First magnetic part; 15. Second plug-in part; 2. Connector; 21. Connecting rope; 22. Elastic element; 23. Connecting sleeve; 24. Slider; 25. Guide hole; 26. Second snap-fit ​​part; 27. Second magnetic part; 28. First plug-in part; 3. Floating assembly; 31. Connecting rod; 32. Float; 33. Center of gravity adjustment part; 4. Locking device; 5. Drive device. Detailed Implementation

[0023] Exemplary embodiments of this application will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of this application are shown in the drawings, it should be understood that this application may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of this application and to fully convey the scope of this application to those skilled in the art.

[0024] It should be noted that, unless otherwise stated, the technical or scientific terms used in this application shall have the ordinary meaning as understood by one of ordinary skill in the art to which this disclosure pertains.

[0025] Currently, some unmanned aerial vehicles (UAVs) have floats positioned beneath them, allowing part of the fuselage to remain above water after landing, providing some resistance to wind and waves and ensuring equipment safety and stability during surface operations. However, this undermount float design significantly lowers the overall center of gravity of the UAV during flight, placing a considerable burden on and impacting flight control.

[0026] To address the aforementioned technical problems, this application provides a method for controlling a drone's flight while ensuring its stability during buoyancy.

[0027] Example 1

[0028] like Figure 1 , Figure 4 and Figure 6 As shown, a drone includes a drone body 1, a floating component 3, and a connector 2. The floating component 3 is disposed on one side of the drone body 1 to provide buoyancy for the drone body 1. The connector 2 is connected between the drone body 1 and the floating component 3 and can switch between an extended state and a retracted state. When the drone is in flight, the connector 2 is in an extended state, the floating component 3 is spaced a predetermined distance from the drone body 1, and the floating component 3 is suspended on the drone body 1. When the drone is floating, the connector 2 is in a retracted state, and the floating component 3 provides support for the drone body 1.

[0029] The UAV main body 1 refers to the core flight platform of the UAV. The UAV main body 1 can be an integrated structure including key components such as the frame 11, power system (motor, propeller, ESC), flight control system, communication module, energy system (battery or fuel system), and mission equipment (such as cameras and sensors). It is the foundation for the UAV to achieve aerial flight, navigation, and control, excluding auxiliary structures (such as floating components 3, deployable floats, etc.) added for specific environments (such as floating on water). The UAV main body 1 is essentially a fully capable UAV, with its design focus on flight performance (such as stability, endurance, and maneuverability). In water applications, its surface operation capabilities are expanded through external additional structures (such as side-mounted adjustable floats 32). The bottom, interfaces, and battery compartment of the UAV main body 1 can be sealed to prevent water ingress. The main structure is sufficiently rigid to prevent damage from water surface turbulence, and can also reduce weight and improve flight efficiency while ensuring strength.

[0030] The main body 1 of the drone can be a multi-rotor drone, with the frame 11 being cross-shaped, X-shaped, or H-shaped, and equipped with four or more rotors 12 (such as quadcopters 12, hexacopters 12, or octocopters 12). It can take off and land vertically without a runway, can hover, is suitable for precision operations, has a simple structure, and is easy to control; it can be applied in aerial photography, inspection, agricultural plant protection, logistics delivery, and other fields, and can serve as the main platform for a seaplane drone, using a side-mounted or deployable float 32 to achieve take-off and landing on the water surface. The main body 1 of the drone can also be a vertical take-off and landing fixed-wing drone, using a fixed-wing fuselage and a multi-rotor 12 lift system (such as tilt rotors 12 or separate lift motors), combining vertical take-off and landing capabilities with high-speed cruising performance, requiring no runway, and suitable for deployment in complex terrain or on ships; it is suitable for marine monitoring, long-distance inspection, and emergency communication, and is very suitable for maritime operations; the main body can integrate a waterproof design, and with the float 32, it can float on the water surface. The main body of the drone 1 can also be a single-rotor 12-rotor helicopter-type drone 1, which adopts a main rotor 12 plus tail rotor structure, similar to a traditional helicopter. It has a large payload and long endurance, and can be used for large-scale water rescue or material delivery.

[0031] The floating component 3 refers to an additional structure or device installed on the drone to provide buoyancy, enabling it to float on the water surface without sinking. It is a key component for enabling the drone to take off and land on water, hover on water, or perform water operations. The floating component 3 can provide sufficient buoyancy to support the entire or part of the drone's fuselage to float on the water surface; maintain the drone's attitude stability and prevent it from capsizing; ensure that critical components (such as motors, batteries, and flight controllers) are exposed above the water surface to avoid water damage; and improve its resistance to disturbances in windy and wave conditions.

[0032] The floating component 3 can be a fixed float, rigidly connected to the sides or bottom of the UAV and cannot be moved. It features a simple structure, low cost, and high reliability, making it suitable for small amphibious UAVs, training models, or missions with low flight efficiency requirements. The floating component 3 can also be a retractable float 32, deployed and retracted via mechanical mechanisms (such as hydraulic, electric actuators, or servo motors). It retracts during flight to reduce wind resistance and optimize the center of gravity, and deploys during surface operations to provide stable buoyancy, suitable for high-end industrial-grade amphibious UAVs and vertical take-off and landing fixed-wing UAV bodies 1. The floating component 3 can be installed on the left and right sides of the UAV body 1 (such as on the arm extensions or side beams), without affecting bottom equipment (such as gimbals and sensors), improving lateral stability, preventing rollover, and easily integrating with adjustable connectors 2 for attitude control. It avoids the problem of an excessively low center of gravity caused by a lowered float 32, balancing flight and floating performance. The floating component 3 can also be an inflatable float, which folds and stores when not in use, and inflates and unfolds to form a float 32 when needed. Its compact size does not affect flight performance, allows for rapid deployment, and provides strong emergency response capabilities. The inflatable float can be equipped with an air pump or high-pressure gas cylinder, making it suitable for emergency rescue drones and airdropped waterborne reconnaissance drones. The floating component 3 can also be a modular float 32 system. As a standardized module, the floating component 3 can be quickly replaced or added to according to mission requirements. It is flexibly configurable to adapt to different loads and aquatic environments, making it suitable for multi-functional operating platforms and scientific research and reconnaissance drones.

[0033] The connector 2 is a movable or adjustable structural device located between the UAV body 1 and the floating component 3. It can switch between extended and retracted states under control signals or external forces to adapt to the different performance requirements of the UAV in flight and floating states. The connector 2 ensures a secure connection between the floating component 3 and the UAV body 1, enabling the floating component 3 to expand or retract in space. It supports the UAV's transition between aerial flight and water surface floating, bearing the suspension force during flight and transmitting buoyancy support reaction force during floating. The connector 2 can be a connecting rope 21, with a drive device 5 such as an electric rope retractor used to switch between extended and retracted states. Alternatively, the connector 2 can be a combination of a connecting rope 21 and an elastic element 22, with the elastic element 22 used to switch between extended and retracted states.

[0034] Connector 2 can be hinged to the main body or float 32 via a pin, allowing for rotation at a certain angle. Connector 2 can also be fixed to the mounting base of the main body or float 32 using screws or bolts. Flexible connector 2 (such as rope or wire) can also be fixed to the main body or float 32 via anchor points. For example, a connection method using rope knots and compression loops (such as slings or rope clips), where the rope passes through a metal ring and is locked with a buckle, or the rope is directly wound around a built-in drum. Strong magnets (such as neodymium iron boron magnets) can also be embedded at the end of connector 2 or on the contact surface of float 32 for rapid adsorption. In the retracted state, float 32 automatically adsorbs and aligns when close to the main body; auxiliary mechanical locking improves the tightness of the fit, eliminating the need for precise alignment and providing automatic guidance. The magnetic force needs to be sufficiently strong to resist wave impact, and can also be combined with a mechanical lock to prevent accidental detachment, serving as an auxiliary connection method in the retracted state and improving the user experience. Connector 2 can also move along a preset slide rail to achieve linear extension and retraction, such as an aluminum alloy slide rail with a nylon slider 24. Waterproof rubber rings, gaskets, or potting compound can also be added to the connection points to prevent water from entering the internal circuitry. For example, O-rings can be used to seal threaded interfaces, and potting compound can be used to protect circuit board connectors.

[0035] The extended state refers to the state where the connector 2 is fully or partially stretched and extended, maintaining a set distance between the floating component 3 and the UAV body 1. This can be described as the floating component 3 being suspended at a fixed position below the UAV body 1. At this time, the length of the connector 2 can reach its maximum working length; the floating component 3 is away from the centerline of the UAV body 1; forming a stable "suspended mass" system. The floating component 3 is suspended as an external load; the UAV flight control system treats it as a suspended object and activates the corresponding anti-sway control algorithm. At this time, the UAV is in flight (cruising, take-off and landing), and the suspension control strategy simplifies the flight control logic.

[0036] The retracted state refers to the partially shortened or folded state of the connector 2, allowing the floating component 3 to move closer to the drone body 1 and form a tight fit or support relationship with it, thus constituting an integral floating unit. When the connector 2 is at its minimum length or retracted, the floating component 3 adheres to the bottom of the drone body 1 or is passively supported by other structures, forming a sealed cavity or an integrated float 32. The floating component 3 transforms from a suspended object into a supporting platform, providing direct buoyancy support for the drone body 1; improving the overall structural rigidity and anti-overturning capability. Suitable for drones in floating states (water surface mooring, data acquisition, charging), it can withstand wind and waves, prevent capsizing, and achieve a low-draft, highly stable static floating state.

[0037] In the field of UAVs, there has been extensive research and application of sling-mounted flight control (such as in relief material transportation and forestry operations). These algorithms can effectively suppress the swaying of the sling, predict disturbances, and dynamically compensate for attitude. If the floating component 3 is always considered as a "fixed-length sling mass," the existing sling-mounted control model can be directly called, without the need to redesign complex flight control logic for a "variable center of gravity + variable aerodynamic shape." The floating component 3 is always located at a fixed distance below the main body (even during flight), the center of gravity position is relatively stable, and the system dynamic characteristics are more consistent. The floating component 3 itself has sufficient buoyancy; after retraction, it forms a sealed combined floating body 32 structure with the UAV main body 1 (such as groove fitting, magnetic sealing), and the overall center of gravity is low and the center of buoyancy is high after combination, forming a stable structure similar to a "roly-poly toy."

[0038] In flight, the floating component 3 is suspended below the UAV body 1 via flexible or partially flexible connectors 2, forming a swing-type suspension system during flight. During flight, the floating component 3 will swing due to airflow disturbances, forming a typical suspension load dynamic phenomenon; the UAV flight control system uses a mature external suspension control algorithm to suppress swaying through attitude adjustment and maintain overall stability; it reuses existing control models, reducing the difficulty of flight control development; the flexible connection can absorb some impact energy, reducing direct vibration transmission to the airframe; the structure is simple, lightweight, and low-cost.

[0039] Compared to existing technologies, the present application provides a connection between the floating component 3 and the drone body 1 via a connector 2 that can switch between extended and retracted states. When the drone is in flight, the connector 2 is in the extended state, the floating component 3 and the drone body 1 are spaced at a set distance, and the floating component 3 is suspended on the drone body 1. This allows operators to easily control the drone using mature suspension algorithms, reducing the burden and impact on drone flight control. When the drone is floating, the connector 2 is in the retracted state, and the floating component 3 provides support for the drone body 1, ensuring the stability of the float.

[0040] like Figure 1 As shown, in some modified embodiments of this application, the connector 2 includes a connecting rope 21 and an elastic element 22. The connecting rope 21 is connected between the UAV body 1 and the floating component 3. The elastic element 22 is connected to the connecting rope 21 and can elastically deform to switch the connector 2 between a stretched state and a contracted state. Through the stretching and retraction of the elastic element 22, the connector 2 can automatically switch between the "stretched state" and the "contracted state".

[0041] The connecting rope 21 is a flexible connection structure connecting the main body 1 of the UAV and the floating component 3. It is used to transmit tension, maintain relative position, and optionally integrate other functions (such as conductivity, signal transmission, waterproofing, etc.). The elastic element 22 is a component with elastic deformation capability (such as a spring, elastic band, rubber block, etc.), integrated with the connecting rope 21, providing deformation and recovery capabilities. When the UAV is flying in the air, gravity causes the floating component 3 to sag, and the elastic element 22 is stretched, entering a stretched state; the connecting rope 21 remains taut, ensuring that the floating component 3 is stably suspended at a set distance; at this time, the system behaves as a damped suspended load, and the flight control uses a suspended control algorithm to suppress swaying; the elastic element 22 can absorb high-frequency vibrations and sudden disturbances (such as gusts) during flight, improving flight stability. When the UAV lands on the water surface, the buoyancy effect begins to appear; the floating component 3 is subjected to upward buoyancy and gradually floats.

[0042] The buoyancy and elastic force of the elastic element 22 work together to overcome gravity and push the floating component 3 upward; the elastic element 22 is compressed or retracted, and the connecting part 2 enters a contracted state as a whole; finally, the floating component 3 is close to the main body of the UAV 1, forming a compact integrated floating body 32 structure, providing stable support.

[0043] like Figure 1 As shown, in some modified embodiments of this application, the elastic element 22 is a spring or elastic plastic; the connecting rope 21 is a metal wire, nylon rope or power cord.

[0044] For example, the elastic element 22 can be a helical spring, a metal or plastic spring, which can be connected in series with the connecting rope 21 or in parallel with the connecting rope 21. It has strong rebound force, long service life, and can be preset with tension. The elastic element 22 can also be a rubber rope or elastic rope, with multiple strands of rubber filaments twisted together, which can be used directly as part of the connecting rope 21. It has high elasticity and is lightweight. The elastic element 22 can also be a torsion spring, which stores energy when the float 32 rotates around the rotating shaft. It is suitable for rotary deployment and retrieval structures. The elastic element 22 can also be an elastic diaphragm, a rubber or silicone sheet, which is connected between the main body and the float 32. It has good sealing performance and is suitable for small drones.

[0045] For example, the connecting rope 21 can be made of metal wire (such as stainless steel wire or steel wire rope), with multiple strands of metal twisted together. Its diameter can be 0.5–2 mm, offering high strength, corrosion resistance, and wear resistance. However, it is inelastic, prone to fatigue breakage, and conductive but not insulating, making it suitable for purely mechanical suspension with high reliability requirements. The connecting rope 21 can also be made of nylon or polyester rope, woven from high-molecular polymers. It is lightweight, flexible, water-resistant, insulating, prone to creep under long-term tension, non-conductive, suitable for general suspension, and low-cost design. The connecting rope 21 can also be an elastic rope (such as Dyneema + rubber core), composed of high-strength fibers and elastomers, combining strength and cushioning capabilities, suitable for flight scenarios requiring shock absorption. The connecting rope 21 can also be a power cord (conductive cable with an insulated layer), with a copper core and silicone insulation layer, capable of both power supply and load-bearing. For applications requiring enhanced tensile strength (such as adding Kevlar fibers), it is suitable for use when the floating component 3 carries electronic equipment. The connecting rope 21 can also be an integrated cable (power + signal composite cable), a multi-core cable, or a power cord plus a data cable, achieving "one rope for multiple uses," simplifying complex wiring designs. It requires waterproof connectors and is suitable for intelligent floats 32, which can be used for data acquisition tasks. The connecting rope 21 can also be a hybrid structure rope, with an outer nylon braid and an inner metal wire / electrical wire, combining strength, flexibility, and conductivity.

[0046] The connecting rope 21 and the elastic element 22 can be connected in series, that is, the connecting rope 21 and the elastic element 22 are connected end to end. During flight, the elastic element 22 is stretched, and the whole thing extends; when floating, the buoyancy pushes the float 32 upward, the spring retracts, and the whole thing shortens. The connecting rope 21 and the elastic element 22 can also be connected in parallel for elastic support, with the main rope bearing the static load and the elastic band absorbing the dynamic impact.

[0047] like Figure 1 and Figure 2 As shown, in some modified embodiments of this application, the connector 2 further includes a connecting sleeve 23, an elastic element 22 is disposed inside the connecting sleeve 23, one end of the elastic element 22 is connected to the end of the connecting sleeve 23 near the drone body 1, the other end of the elastic element 22 is connected to the connecting rope 21, and the connecting sleeve 23 is connected to the floating component 3.

[0048] When the drone is in flight, the floating component 3 drives the connecting sleeve 23 to move away from the drone body 1, the elastic element 22 deforms elastically, the connecting sleeve 23 and the drone body 1 are spaced at a set distance, and the connecting rope 21 provides tension to the floating component 3 so that the floating component 3 is suspended on the drone body 1; when the drone is in a floating state, the elastic element 22 drives the connecting sleeve 23 to move closer to the drone body 1 so that the connecting sleeve 23 contacts the drone body 1 and provides support for the drone body 1.

[0049] The connecting sleeve 23 is a hollow tubular structure that serves as a rigid outer shell to house the slider 24 and provide sliding guidance, while also acting as part of the connection between the floating assembly 3 and the drone body 1. It not only bears the force transmission path but also provides protection and constraint for the internal elastic element 22 and sliding components. One end of the connecting sleeve 23 is fixedly connected to the floating assembly 3, and it has an internal sliding channel for the slider 24 to move axially. Its end near the drone body 1 has a fixed point for connecting the elastic element 22. In the floating state, its top end can contact the drone body 1, providing direct support. The connecting sleeve 23 restricts the slider 24 to linear axial movement, preventing off-center loading or jamming, and serves as the main load-bearing structure of the floating assembly 3, directly supporting the drone body 1 in the retracted state. It also protects internal components, encasing the elastic element 22 (such as a spring) to prevent damage from water, dust, and external forces, and transmits the buoyancy / gravity of the float 32 to the drone body 1. Cables, sensors, dampers, etc., can also be integrated into the inner cavity or outer wall of the connecting sleeve 23.

[0050] The connecting sleeve 23 can be a straight cylindrical sleeve, a cylindrical tube with a uniform inner diameter and open at both ends. It can be made of aluminum alloy, stainless steel, or engineering plastic and serves as a basic guide. Alternatively, the connecting sleeve 23 can be a stepped sleeve with segmented changes in inner diameter and limiting steps. It can be made of metal or composite materials and can prevent the slider 24 from dislodging, serving as a limit control for the slider 24. One end of the connecting sleeve 23 can have an outwardly protruding flange for easy installation and fixation, enhancing connection strength. The connecting sleeve 23 can be a double-layer sleeve, consisting of an outer tube and an inner tube forming a sealed cavity. It can be made of stainless steel with O-rings, providing a high waterproof rating suitable for marine environments. Finally, the connecting sleeve 23 can be a carbon fiber reinforced resin tube, lightweight and high-strength, non-magnetic, suitable for high-performance UAVs and applications requiring significant weight reduction.

[0051] The connecting rope 21 can be directly connected to the elastic element 22, or it can be connected to the elastic element 22 through the slider 24. For example, the slider 24 can be slidably connected inside the connecting sleeve 23 and is located on the side of the connecting sleeve 23 away from the drone body 1. The slider 24 is connected to the other end of the connecting rope 21 and the elastic element 22 respectively.

[0052] The slider 24 is a mechanical component that can slide axially within the connecting sleeve 23. It connects the connecting rope 21 and the elastic element 22, and enables force transmission and displacement adjustment under different operating conditions of the UAV. It is the key motion element for the connector 2 to switch between "stretching" and "contraction" states. The slider 24 is located inside the connecting sleeve 23, close to the UAV body 1. One end of it is connected to the connecting rope 21 (leading to the UAV body 1), and the other end is connected to the elastic element 22 (such as a spring). It moves up and down with the float 32 and slides relative to the connecting sleeve 23, causing the elastic element 22 to deform. The slider 24 can couple and transmit the tension of the connecting rope 21 and the restoring force of the elastic element 22, realizing relative displacement during the stretching and contraction process, and converting external mechanical energy (gravity / buoyancy) into elastic potential energy. The slider 24 can also serve as the basis for position feedback. For example, a sensor can be added to detect the position of the slider 24 to determine the operating state.

[0053] The slider 24 can be a plunger-type structure, a solid cylindrical body with a threaded connection hole, suitable for high-precision sliding and highly versatile. The slider 24 can also be a piston-type slider 24 with a sealing groove, which can be fitted with a sealing ring, making it waterproof and dustproof, suitable for humid environments. The outer ring of the slider 24 can be equipped with ball grooves, working with linear bearings for low friction and long service life. The slider 24 can also be a T-shaped slider 24 with a T-shaped cross-section, featuring an anti-rotation design, strong torsional resistance, and preventing rotation. The slider 24 and the connecting sleeve 23 can have a clearance sliding fit, maintaining a small gap (0.05mm–0.2mm) between the slider 24 and the inner wall of the sleeve, simplifying machining and ensuring smooth movement.

[0054] When the drone is flying, gravity dominates. The floating component 3 falls due to its own weight, causing the connecting sleeve 23 to move downwards. The sleeve pulls the slider 24 (if any) to slide away from the main body relative to its interior. The elastic element 22 (such as a compression spring or tension spring) is stretched / compressed, undergoes elastic deformation, and stores potential energy. The connecting rope 21 remains taut, providing the main tensile force support for the floating component 3. At this time, the connecting sleeve 23 maintains a set distance from the main body of the drone 1. The floating component 3 is stably suspended below, forming an "external load" system. The flight control uses the suspension control algorithm to suppress swaying. The slider 24 decouples the tension of the connecting rope 21 from the restoring force of the elastic element 22, realizing independent force transmission.

[0055] As the drone lands on the water, its buoyancy gradually increases. The floating component 3 is subjected to an upward buoyancy force and begins to rise. The buoyancy and the restoring force of the elastic element 22 overcome gravity, pushing the connecting sleeve 23 upward. The slider 24 (if present) slides relative to the sleeve, and the elastic element 22 gradually retracts. When the float 32 approaches the drone body 1, the top of the connecting sleeve 23 contacts the body. The elastic element 22 fully recovers, and the system enters a contracted state. At this time, the connecting sleeve 23 directly supports the drone body 1, forming a "float 32 load-bearing platform," which can improve floating stability. It can also be locked in place with buckles or magnetic attraction.

[0056] This modified implementation represents a highly integrated and engineered design of the structure of the unmanned aerial vehicle (UAV) connector 2. By introducing a composite mechanism consisting of a connecting sleeve 23, an elastic element 22, and a connecting rope 21, it achieves controllable, stable, and directional automatic switching between the "extended" and "contracted" states of the connector 2. This solution not only retains the flight control advantages of flexible suspension but also enhances structural rigidity and motion reliability, utilizing gravity and buoyancy conversion to drive state changes without requiring an additional power source.

[0057] like Figure 4 As shown, in some modified embodiments of this application, the connector 2 further includes a connecting sleeve 23, which is fixedly connected to the side of the drone body 1 away from the floating component 3. An elastic element 22 is disposed inside the connecting sleeve 23, and one end of the elastic element 22 is connected to the end of the connecting sleeve 23 away from the drone. One end of the connecting rope 21 is detachably connected to the floating component 3. When the drone is in flight, the floating component 3 drives the connecting rope 21 to move closer to the drone body 1, and the elastic element 22 elastically deforms. The floating component 3 and the drone body 1 are spaced at a set distance, and the connecting rope 21 provides tension to the floating component 3 so that the floating component 3 is suspended on the drone body 1. When the drone is in a floating state, the elastic element 22 drives the floating component 3 and the drone body 1 to move closer to each other so that the floating component 3 and the drone body 1 come into contact and provide support for the drone body 1.

[0058] The connecting sleeve 23 can be fixed to the top of the drone body 1 (away from the float 32) by means of screws or welding, or it can be integrally formed with the drone body 1. The specific structure of the connecting sleeve 23 and the slider 24 can be the same as described above, only the installation position is different, which will not be described again here.

[0059] Similarly, the connecting rope 21 can be directly connected to the elastic element 22, or it can be connected to the elastic element 22 through the slider 24. The slider 24 can be slidably connected inside the connecting sleeve 23 and is located on the side of the connecting sleeve 23 away from the drone body 1. The slider 24 is connected to the other end of the connecting rope 21 and the elastic element 22 respectively.

[0060] After the drone takes off, gravity causes the floating component 3 to droop. The floating component 3 pulls the slider 24 (if any) downward through the connecting rope 21. The slider 24 slides (i.e. moves inward) towards the main body inside the connecting sleeve 23. The elastic element 22 (such as a tension spring or compression spring) is stretched or compressed, undergoes elastic deformation, and stores potential energy. At this time, the connecting rope 21 remains taut, providing the main pulling force for the floating component 3. The floating component 3 is stably suspended at a set distance below the main body 1 of the drone. The system is in a stretched state. The flight control uses the suspension load control algorithm to suppress swaying. The slider 24 is "pulled downward" while the sleeve remains fixed, forming a relative displacement.

[0061] When the drone lands on the water, the floating component 3 floats upward due to buoyancy. The buoyancy overcomes gravity and the tension of the elastic element 22, pushing the floating component 3 upward. The connecting rope 21 slackens, and the slider 24 (if present) rebounds outward under the restoring force of the elastic element 22. The elastic element 22 releases its stored energy, causing the slider 24 to return to its initial position. The floating component 3 continues to move upward and eventually contacts and adheres to the main body of the drone 1. At this time, the connecting piece 2 enters a retracted state. The floating component 3 directly supports the main body of the drone 1, forming an integrated floating body 32 structure, which improves floating stability. If a locking mechanism (such as a latch or magnetic attraction) is provided, it can be automatically locked.

[0062] The floating assembly 3 is connected via a detachable connecting rope 21, allowing for quick replacement of different functional floats 32 (such as sensor floats, life rings, and lighting modules). The connector 2 is largely integrated into one end of the drone body, facilitating wiring, power supply, and signal integration, as well as modular installation. The slider 24 and elastic element 22 are located on the side of the main body, providing better dust and water resistance. For example, the connecting rope 21 and the floating assembly 3 can be connected via a quick-connect fitting, allowing for one-handed operation and reliable connection. The connecting rope 21 can also be threaded onto the floating assembly 3; the internal and external threads provide strong load-bearing capacity and prevent loosening.

[0063] like Figure 3 As shown, in some modified embodiments of this application, a guide block 13 is provided on the main body 1 of the drone, and a guide hole 25 is provided at one end of the connecting sleeve 23 near the drone. The guide hole 25 and the guide block 13 cooperate, and the connecting rope 21 passes through the guide block 13 and is connected to the elastic element 22, or the connecting rope 21 passes through the guide block 13 and is connected to the elastic element 22.

[0064] The guide block 13 is a protruding structure fixedly mounted on the drone body 1. It may have a through hole or a groove-shaped channel to guide the direction of the connecting rope 21 and cooperate with the guide hole 25 on the connecting sleeve 23 to achieve spatial positioning. The guide block 13 may be located at the center of the bottom of the drone body 1. It can guide the connecting rope 21 to pass through in a preset direction and cooperate with the guide hole 25 to limit the lateral displacement of the connecting sleeve 23, thereby improving the centering and torsional resistance of the overall structure.

[0065] The guide hole 25 is a hole-like or groove-like structure located at one end of the connecting sleeve 23 near the drone body 1. It is used to engage with the guide block 13 on the drone body 1 to form a mechanical limit and guide. It can be a circular hole, a square hole, a T-slot, etc., to match the shape of the guide block 13; it enables quick alignment and installation between the connecting sleeve 23 and the drone body 1, prevents the sleeve from rotating or swaying laterally, enhances connection rigidity, and improves stability during state switching.

[0066] For example, guide block 13 can be a circular boss, and guide hole 25 can be a circular through hole, resulting in a simple structure and easy fit. Guide block 13 can also be a square boss, and guide hole 25 can be a square hole, providing good anti-rotation effect. Guide block 13 can also be a T-shaped protrusion, and guide hole 25 can be a T-shaped groove, providing strong load-bearing capacity.

[0067] During drone flight, the connecting rope 21 always passes through the through hole of the guide block 13, ensuring that its force direction is perpendicular to the main body plane. The guide block 13 separates from the guide hole 25 and maintains a set distance to avoid affecting the connection rope 21's suspension of the floating component 3. When the drone is floating, the guide block 13 continues to engage with the guide hole 25, guiding the entire sleeve to rise smoothly along the axis. The floating component 3 continues to move upward, eventually fitting against the drone body 1, and the system enters a retracted state, forming an integrated float structure 32. The guiding structure ensures accurate alignment with each retraction, avoiding misalignment failure.

[0068] like Figure 3 As shown, in some modified embodiments of this application, the guide block 13 includes a mating part 131 and an extension part 132. The mating part 131 is fixedly connected to the drone body 1 and is adapted to the guide hole 25. The extension part 132 is disposed on the side of the mating part 131 away from the drone body 1, and the cross-section of the extension part 132 gradually decreases towards the side away from the drone body 1.

[0069] The mating part 131 is the portion of the guide block 13 that is fixedly connected to the UAV body 1, and its shape is adapted to the guide hole 25 on the connecting sleeve 23; it achieves rigid fixation between the guide block 13 and the body, and forms a sliding or plug-in engagement with the guide hole 25. For example, the mating part 131 can be fixed to the UAV body 1 by means of screws, welding, snap-fit, or embedding; the mating part 131 can be cylindrical, square, polygonal, or T-shaped, matching the shape of the guide hole 25 on the connecting sleeve 23. The mating part 131 can provide structural support, restrict the rotation and lateral displacement of the connecting sleeve 23, and ensure axial alignment during movement.

[0070] The extension 132 is a tapered or tapered structure located on the side of the mating part 131 away from the main body 1 of the UAV. Its cross-section gradually decreases in size to guide alignment, facilitating automatic insertion of the guide hole 25. The cross-section (such as diameter or width) of the extension 132 gradually decreases in the direction away from the main body, forming a tapered, frustum-shaped, or wedge-shaped structure. The extension 132 can consist of a conical tip (similar to a "guide head") and a trapezoidal structure with a beveled transition. The extension 132 can guide the entry point during the retraction or installation of the connecting sleeve 23; when the guide hole 25 is not fully aligned, the beveled surface converts the lateral deviation into axial sliding, achieving automatic correction.

[0071] If there is a slight misalignment during the process of the guide hole 25 approaching the guide block 13, the tapered surface of the extension 132 will contact the edge of the guide hole 25, and the inclined surface will generate a lateral force, which will push the connecting sleeve 23 to automatically correct its position. Finally, the guide hole 25 will be smoothly fitted into the mating part 131, completing the precise alignment.

[0072] like Figure 3 As shown, in some modified embodiments of this application, the side wall of the mating part 131 is provided with a first snap-fit ​​part 133, and the hole wall of the guide hole 25 is provided with a second snap-fit ​​part 26, and the first snap-fit ​​part 133 and the second snap-fit ​​part 26 are adapted to each other.

[0073] The first engaging portion 133 is a protrusion or recess on the side wall of the mating portion 131 of the guide block 13, used to achieve mechanical interlocking with the second engaging portion 26 in the guide hole 25. It can be a protrusion, a groove, a barb, an annular protrusion, a polygonal boss, etc.; as one of the engaging parts, it participates in the locking action. The second engaging portion 26 is a corresponding structure on the hole wall of the guide hole 25 of the connecting sleeve 23, adapted to the first engaging portion 133 to form a lock. If the first engaging portion 133 is a protrusion, the second engaging portion 26 can be a groove; and vice versa, cooperating with the first engaging portion 133 to achieve quick locking with "insertion and locking".

[0074] By introducing the aforementioned mechanical snap-fit ​​structure, reliable fixation between the connecting sleeve 23 and the UAV body 1 is achieved, preventing accidental separation due to vibration, impact, or water flow disturbance, and significantly improving the safety and reliability of the UAV in a floating state.

[0075] like Figure 7 As shown, in some modified embodiments of this application, the guide hole 25 is located at the center of the connecting sleeve 23, and the end of the connecting sleeve 23 near the UAV is also provided with a first plug-in part, and the side of the UAV near the connecting sleeve 23 is provided with a second plug-in part, and the first plug-in part and the second plug-in part are adapted to each other.

[0076] A guide hole 25 is positioned at the center of the connecting sleeve 23 to provide axial guidance, ensuring smooth sliding. A first insertion part is located at one end of the connecting sleeve 23 near the drone body 1 (usually the outer periphery or end face periphery) as the insertion interface, used to mate with the body. A second insertion part is located on the side of the drone body 1 near the connecting sleeve 23, matching the first insertion part to achieve circumferential or end face insertion. The central guide hole 25 is responsible for axial movement guidance, while the peripheral insertion parts are responsible for structural fixation, alignment assistance, or functional integration. For example, multiple first and second insertion parts can be provided, evenly distributed circumferentially along the guide hole 25 to enhance the button capability during connection, allowing the floating component 3 to rotate synchronously with the drone body 1, facilitating control of the floating component 3 by the drone body 1. For example, the first and second insertion parts can be direct-insertion boss-groove types, directly inserted axially, with a simple structure and easy processing.

[0077] When the drone lands on the water, the floating component 3 floats up, causing the connecting sleeve 23 to move upward. The guide hole 25 first engages with the guide block 13 (as described in the previous case, the tapered extension 132) on the drone body 1 to achieve center alignment and axial guidance. As the sleeve continues to move upward, the first insertion part and the second insertion part gradually approach each other. When they reach the preset position, they automatically insert or engage to complete the circumferential or end face connection. The connecting sleeve 23 is guided by the center and fixed around the periphery, forming a rigid connection, which significantly improves the overall structural stability.

[0078] like Figure 5 As shown, in some modified embodiments of this application, a locking device 4 is also included. The locking device 4 is disposed between the connecting sleeve 23 and the UAV body 1 and is used to lock the position of the connecting sleeve 23.

[0079] A locking device 4 is disposed between the connecting sleeve 23 and the UAV body 1 to fix the position of the connecting sleeve 23 in a specific state. For example, when the connecting sleeve 23 is fixedly connected to the floating component 3, the locking device 4 may include a clamp and a solenoid valve. When the UAV and the sleeve structure are connected together, the solenoid valve activates the clamp device. When the UAV takes off, the clamp device opens, and the suspension rope is pulled out. The clamp is an openable and closable ring or clamp-type structure that can be clamped at the connection between the connecting sleeve 23 and the UAV to lock the position of the connecting sleeve 23. When the connecting sleeve 23 reaches the preset retracted position (which can be detected by a limit switch or Hall sensor), the flight control system confirms that it is "in position" and sends a signal to activate the solenoid valve. The solenoid valve drives the clamp to close, clamping the connection between the connecting sleeve 23 and the UAV body 1. When the user issues a takeoff command, the flight control system performs a self-check and sends an unlock signal to the solenoid valve. The solenoid valve activates, driving the clamp to open. Under the influence of gravity, the floating component 3 causes the connecting sleeve 23 to fall, pulling the connecting rope 21. The connecting sleeve 23 begins to slide downward along the guide structure, and the elastic element 22 is stretched. The system enters the stretched state and is ready to fly.

[0080] The locking device 4 can also be an electromagnetic pin lock, consisting of a spring pin and an electromagnetic push rod. When energized, the pin pops out and inserts into the positioning hole for precise positioning and high reliability. For example, the positioning hole can be horizontally set on the guide block 13, and the electromagnetic push rod can be set on the inner wall of the guide hole 25. The two work together to actively lock the position of the connecting sleeve 23. By setting the locking device 4 to actively control the position of the connecting sleeve 23, the state of the connector 2 can be controlled, allowing the drone to be used in different scenarios as needed.

[0081] like Figure 3 As shown, in some modified embodiments of this application, a first magnetic part 14 and a second magnetic part 27 are also included. The first magnetic part 14 is disposed on the side of the drone body 1 near the connecting sleeve 23; the second magnetic part 27 is disposed on the side of the connecting sleeve 23 near the drone body 1; the first magnetic part 14 and the second magnetic part 27 can be magnetically connected.

[0082] The first magnetic part 14 can be located on the side of the drone body 1 near the connecting sleeve 23 (such as the bottom mounting surface), providing one pole for magnetic adsorption; the second magnetic part 27 can be located on the side of the connecting sleeve 23 near the drone body 1 (such as the end face or side wall), corresponding to the first magnetic part 14, forming a magnetic circuit. The first magnetic part 14 and the second magnetic part 27 can be permanent magnets (such as neodymium iron boron N35-N52), electromagnets, or ferromagnetic materials (attracted end); when approaching the drone body 1, the first magnetic part 14 and the second magnetic part 27 enter the effective working distance, the magnetic force begins to act, generating automatic traction and centering effect, and the two quickly adsorb and stick together, completing the connection. When the drone is ready to take off, the flight control issues an unlocking command; if it is an electromagnet design: the magnetic force disappears after power is cut off, and the connection naturally separates; if it is a permanent magnet design, it can be detached by mechanical push rods, rotating mechanisms, or elastic elements 22, or passively released by relying on gravity to overcome the magnetic attraction.

[0083] In some modified embodiments of this application, the first magnetic part 14 or the second magnetic part 27 is an electromagnet. When the drone is in a floating state, the first magnetic part 14 and the second magnetic part 27 are magnetically connected. When the drone is in a flight state, the first magnetic part 14 and the second magnetic part 27 repel each other.

[0084] One of the first magnetic part 14 and the second magnetic part 27 is an electromagnet, and at least one is an electromagnet (coil + iron core). The direction and strength of the magnetic field can be controlled by current. The other magnetic part can be a permanent magnet (such as neodymium iron boron) or another electromagnet. When the UAV lands on the water, the floating component 3 floats upward due to buoyancy. The connecting sleeve 23 slides upward along the guide structure (such as guide block 13). When it approaches the main body 1 of the UAV, it enters the range of the electromagnet. The flight control system detects that it is "in position" (which can be triggered by a position sensor or water sensor). It controls the electromagnet to pass a positive current, generating a magnetic field opposite to the opposite pole of the magnetic part. The two are magnetically connected, completing a rigid fit. When the user issues a takeoff command, the flight control system initiates the unlocking process. It controls the electromagnet to switch the current direction (reverse power supply). The magnetic field polarity is reversed, forming the same pole opposite to the opposite magnetic part. A repulsive force is generated, actively pushing the connecting sleeve 23 downward to avoid the risk of jamming. The repulsive force overcomes the initial static friction and residual adsorption force. The connecting rope 21 is pulled out, and the elastic element 22 begins to deform. The system smoothly enters the extension state and is ready for flight.

[0085] like Figure 8 As shown, in some modified embodiments of this application, the first magnetic part 14 and the second magnetic part 27 are arranged along a first direction, which is perpendicular to the extension direction of the connecting sleeve 23.

[0086] The connecting sleeve extends along its axial direction, i.e., the direction in which it slides along the guide block or slider (e.g., vertical). The first direction is specified as perpendicular to the extending direction of the connecting sleeve, such as the horizontal direction. The first and second magnetic parts are aligned in the horizontal plane, and the magnetic attraction occurs horizontally. For example, the first magnetic part can be located on the bottom side of the drone body (e.g., a side wall); the second magnetic part is located on the corresponding side wall at the top of the connecting sleeve, with the two facing each other radially or laterally, and the magnetic force acting horizontally. In some embodiments, the first magnetic part can be located on the guide block near the connecting sleeve, and the second magnetic part can be located on the inner wall of the connecting sleeve, so that during sliding, the connecting sleeve slides up and down along its extending direction (Z-axis). At this time, the first and second magnetic parts gradually approach each other, but since the magnetic force is horizontal (X / Y-axis), it does not directly oppose or assist the axial sliding; thus avoiding sliding jamming, unstable movement, and excessive impact upon arrival caused by axial magnetic attraction. During the docking process (lateral magnetic attraction), when the connecting sleeve slides to the preset position, the first magnetic part and the second magnetic part are aligned in the horizontal direction; the magnetic attraction force acts along the first direction (horizontal), pulling the connecting sleeve towards the side of the drone body; achieving radial centering, structural fit and preventing loosening, which can prevent the drone and the connecting sleeve from rotating relative to each other to a certain extent.

[0087] This solution decouples the direction of magnetic attraction from the direction of movement of the connector by adjusting the spatial orientation of the magnetic part, thus avoiding interference of magnetic force on the sliding process and ensuring stable adsorption at the final docking position.

[0088] like Figure 6 As shown, in some modified embodiments of this application, a drive device 5 is also included. The drive device 5 is connected to the connector 2. The drive device 5 is used to pull the connector 2 to switch between an extended state and a retracted state. When the drone is in flight, the drive device 5 controls the connector 2 to be in the extended state, and the floating component 3 and the drone body 1 are spaced at a set distance. The floating component 3 is suspended on the drone body 1. When the drone is in a floating state, the drive device 5 pulls the connector 2 to be in the retracted state, and the floating component 3 and the drone body 1 approach and contact each other. The floating component 3 provides support for the drone body 1.

[0089] The drive unit 5 is a device that converts energy (electrical, hydraulic, pneumatic, etc.) into mechanical motion. It is directly or indirectly connected to the connector 2 and is used to actively pull or push the connector 2, switching it between an extended state (flight mode) and a retracted state (floating mode). The drive unit 5 can be an electric actuator, consisting of a motor and a lead screw / nut, outputting linear motion with high precision, accurate control, and fast response. However, it is relatively large and expensive, making it suitable for industrial-grade drones. Alternatively, the drive unit 5 can consist of a servo motor and a cable reel, with the motor driving the drum to wind and unwind the connecting rope 21. This design is compact, has a long stroke, is speed-adjustable, and requires protection against rope tangling, making it suitable for most applications. Finally, the drive unit 5 can also consist of a stepper motor and a rack and pinion system, with the motor driving the gear along the rack for precise positioning and reversible control.

[0090] The drive unit 5 can be set independently or simultaneously with the elastic element 22, connecting sleeve 23, and slider 24. When the drone is in flight, the drive unit 5 receives a "takeoff" command, activates and releases the connecting rope 21 or pushes the connecting sleeve 23 outward; the floating component 3 droops under gravity, the connecting piece 2 enters the extended state, confirms the state is in place, and allows takeoff; the drive unit 5 can maintain slight tension to suppress swaying. When the drone is floating, the connecting piece 2 is pulled into the retracted state, the drone lands on the water surface, and buoyancy acts on the floating component 3; the flight controller detects "water contact" (via air pressure, attitude, and water sensor); sends a command to the drive unit 5; the drive unit 5 reverses its operation, starting to retract the rope or pull back the slider 24; it actively pulls the connecting piece 2 towards the drone body 1; the elastic element 22 (if present) is compressed / stretched, storing energy; the floating component 3 contacts and adheres to the drone body 1, and can be locked in place with magnetic attraction or buckles, and the system enters a stable floating mode.

[0091] like Figure 5As shown, in some modified embodiments of this application, the floating component 3 includes a connecting rod 31, a float 32, and a center of gravity adjuster 33. The connecting rod 31 and the connecting component 2 are connected. The float 32 is connected to the connecting rod 31 and is used to provide buoyancy for the UAV body 1. The center of gravity adjuster 33 is located at the end of the connecting rod 31 away from the UAV body 1. Setting the center of gravity adjuster 33 can significantly lower the overall center of gravity of the UAV and improve its stability when floating. However, an excessively low center of gravity also brings a greater burden and impact to flight control. This solution is particularly suitable for UAVs with such a low center of gravity, which can further ensure floating stability while facilitating control of the UAV. The point of application of the buoyancy force on the float 32 is usually located at the geometric center of the float 32, and the center of gravity is the center of mass of the entire system (UAV + floating component 3). When the center of gravity is lower than the center of buoyancy, the system has self-restoring capability. After tilting, the buoyancy generates a restoring torque to make it upright. By setting the center of gravity adjuster 33 at the farthest end, the center of gravity is significantly lowered, which can be lower than the center of buoyancy, forming an "inverted pendulum" structure, which greatly improves the ability to resist capsizing in wind and waves.

[0092] One end of the connecting rod 31 is connected to the connecting piece 2 (such as the connecting sleeve 23 / slider 24), and the other end is connected to the float 32 and the center of gravity adjustment piece 33, serving as a force transmission and structural support component. The float 32 is connected to the connecting rod 31 (it can be located in the middle or near the UAV), providing the main buoyancy, and its material can be foam, hollow shell, etc. The center of gravity adjustment piece 33 is located at the end of the connecting rod 31 furthest from the UAV body 1 (i.e., at the bottom), and is used to actively lower the overall center of gravity of the system.

[0093] In some modified embodiments of this application, the connector 2 includes an elastic rubber strip and a tubular structure. The elastic rubber strip provides elasticity to the connector 2 so that the connector 2 switches between an extended state and a contracted state. The tubular structure is wrapped around the outside of the elastic rubber strip to protect the elastic rubber strip and constrain its radial deformation, and guide its axial extension and contraction.

[0094] The core elastic element of the elastic rubber strip provides restoring force for connector 2, enabling automatic switching between extended and contracted states. The tubular structure, woven from high-strength fibers, covers the outer side of the elastic rubber strip, protecting it from external damage, constraining its radial expansion, and guiding it to extend and contract only axially. Together, the elastic rubber strip and the tubular structure form a structure similar to an elastic band, ensuring a flexible connection during suspension while allowing switching between extended and contracted states.

[0095] The above are merely specific embodiments of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A drone, characterized in that, include: The main body of the drone (1); A floating component (3) is disposed on one side of the UAV body (1) to provide buoyancy to the UAV body (1); Connector (2), which connects the UAV body (1) and the floating component (3) and can switch between an extended state and a retracted state; When the drone is in flight, the connector (2) is in an extended state, the floating component (3) and the drone body (1) are spaced at a set distance, and the floating component (3) is suspended on the drone body (1); when the drone is in a floating state, the connector (2) is in a retracted state, and the floating component (3) provides support for the drone body (1).

2. The UAV according to claim 1, characterized in that, The connector (2) includes: A connecting rope (21) is used to connect the main body of the UAV (1) and the floating component (3); An elastic element (22) is connected to the connecting rope (21), and the elastic element (22) is capable of elastic deformation to allow the connecting member (2) to switch between an extended state and a contracted state.

3. The UAV according to claim 2, characterized in that, The connector (2) further includes: A connecting sleeve (23) is provided, the elastic element (22) is disposed inside the connecting sleeve (23), one end of the elastic element (22) is connected to the end of the connecting sleeve (23) near the drone body (1), the other end of the elastic element (22) is connected to the connecting rope (21), and the connecting sleeve (23) is connected to the floating component (3). When the drone is in flight, the floating component (3) drives the connecting sleeve (23) to move away from the drone body (1), the elastic element (22) deforms elastically, the connecting sleeve (23) and the drone body (1) are spaced at a set distance, and the connecting rope (21) provides tension to the floating component (3) so that the floating component (3) is suspended on the drone body (1); when the drone is floating, the elastic element (22) drives the connecting sleeve (23) to move closer to the drone body (1) so that the connecting sleeve (23) contacts the drone body (1) and provides support for the drone body (1).

4. The UAV according to claim 2, characterized in that, The connector (2) further includes: A connecting sleeve (23) is fixedly connected to the side of the UAV body (1) away from the floating component (3). An elastic element (22) is disposed inside the connecting sleeve (23). One end of the elastic element (22) is connected to the end of the connecting sleeve (23) away from the UAV. The other end of the elastic element (22) is connected to one end of the connecting rope (21). The other end of the connecting rope (21) is detachably connected to the floating component (3). When the drone is in flight, the floating component (3) drives the connecting rope (21) to move closer to the drone body (1), the elastic element (22) deforms elastically, the floating component (3) and the drone body (1) are spaced at a set distance, and the connecting rope (21) provides tension to the floating component (3) so that the floating component (3) is suspended on the drone body (1); when the drone is floating, the elastic element (22) drives the floating component (3) and the drone body (1) to move closer to each other so that the floating component (3) and the drone body (1) come into contact and provide support for the drone body (1).

5. The UAV according to claim 3, characterized in that, The main body (1) of the drone is provided with a guide block (13), and the end of the connecting sleeve (23) near the drone is provided with a guide hole (25). The guide hole (25) and the guide block (13) cooperate, and the connecting rope (21) passes through the guide block (13) and connects to the elastic element (22).

6. The UAV according to claim 5, characterized in that, The guide block (13) includes: The mating part (131) is fixedly connected to the main body (1) of the UAV and is adapted to the guide hole (25); An extension (132) is provided on the side of the mating part (131) away from the main body of the drone (1), and the cross-section of the extension (132) gradually decreases towards the side away from the main body of the drone (1).

7. The UAV according to claim 6, characterized in that, The side wall of the mating part (131) is provided with a first snap-fit ​​part (133), and the wall of the guide hole (25) is provided with a second snap-fit ​​part (26). The first snap-fit ​​part (133) and the second snap-fit ​​part (26) are adapted to each other.

8. The UAV according to claim 5, characterized in that, The guide hole (25) is located at the center of the connecting sleeve (23). The connecting sleeve (23) is also provided with a first plug-in part (28) at one end near the UAV. The UAV is provided with a second plug-in part (15) on the side near the connecting sleeve (23). The first plug-in part (28) and the second plug-in part (15) are compatible.

9. The UAV according to claim 3, characterized in that, Also includes: Locking device (4), which is disposed between the connecting sleeve (23) and the UAV body (1), is used to lock the position of the connecting sleeve (23).

10. The UAV according to claim 3, characterized in that, Also includes: The first magnetic part (14) is disposed on the side of the UAV body (1) near the connecting sleeve (23); The second magnetic part (27) is disposed on the side of the connecting sleeve (23) near the main body of the UAV (1); the first magnetic part (14) and the second magnetic part (27) can be magnetically connected.

11. The UAV according to claim 10, characterized in that, The first magnetic part (14) or the second magnetic part (27) is an electromagnet. When the drone is in a floating state, the first magnetic part (14) and the second magnetic part (27) are magnetically connected. When the drone is in a flight state, the first magnetic part (14) and the second magnetic part (27) repel each other.

12. The UAV according to claim 10, characterized in that, The first magnetic part (14) and the second magnetic part (27) are arranged along a first direction, which is perpendicular to the extension direction of the connecting sleeve (23).

13. The UAV according to claim 1, characterized in that, Also includes: A drive device (5) is connected to the connector (2), and the drive device (5) is used to pull the connector (2) to switch the connector (2) between an extended state and a contracted state; When the UAV is in flight, the drive device (5) controls the connector (2) to be in an extended state, the floating component (3) and the UAV body (1) are spaced at a set distance, and the floating component (3) is suspended on the UAV body (1); when the UAV is in a floating state, the drive device (5) pulls the connector (2) to make the connector (2) be in a retracted state, the floating component (3) and the UAV body (1) approach each other and contact each other, and the floating component (3) provides support for the UAV body (1).

14. The UAV according to any one of claims 1-13, characterized in that, The floating component (3) includes: A connecting rod (31) is connected to the connecting piece (2); A float (32) is connected to the connecting rod (31) and is used to provide buoyancy for the main body of the UAV (1); A center of gravity adjustment component (33) is disposed at the end of the connecting rod (31) away from the main body of the UAV (1).

15. The UAV according to claim 1, characterized in that, The connector (2) includes: An elastic rubber strip provides elasticity to the connector (2) so that the connector (2) switches between an extended state and a contracted state; The tube structure wraps around the outside of the elastic rubber strip to protect the elastic rubber strip, constrain its radial deformation, and guide its axial expansion and contraction.

16. The UAV according to claim 2, characterized in that, The elastic element (22) is a spring or elastic plastic; The connecting rope (21) is a metal wire, nylon rope, or power cord.

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