Super-endurance load-bearing grabbing and clamping type logistics bird-shaped unmanned aerial vehicle and using method thereof

Abstract

The embodiment of the invention provides a super-endurance load-bearing grabbing and clamping type logistics bird-shaped unmanned aerial vehicle and a using method thereof, and relates to the field of aviation devices. The super-endurance load-bearing grabbing and clamping type logistics bird-shaped unmanned aerial vehicle comprises a vehicle body, a transmission assembly, a driving assembly, two hang gliders, a propelling mechanism, four supporting arms, four rotor wings and a grabbing assembly. The driving assembly is installed in the fuselage, the hang glider is rotationally connected with the fuselage, the driving assembly is connected with the hang glider, the four supporting arms are rotationally connected with the fuselage, the driving assembly is connected with the four supporting arms through the transmission assembly, the four rotors are connected with the four supporting arms correspondingly, and the four rotors are connected with the four supporting arms correspondingly. The propelling mechanism is connected with the machine body, and the grabbing assembly is arranged at the bottom of the machine body. The system is efficient in energy consumption control, and is especially suitable for medium and long distance logistics distribution scenes with high requirements for endurance time.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation devices, and in particular to an ultra-long-range, load-bearing, grabbing and clamping logistics bird-shaped drone and a method for using the same. Background Art

[0002] In recent years, with the rapid development of aviation and electronic control technologies, various types of aviation devices, particularly unmanned aerial vehicles (UAVs), have gained widespread application in both civil and industrial fields. Due to their high maneuverability, flexible deployment, and relatively low operating costs, UAVs are widely used in a variety of applications, including aerial photography, inspection, monitoring, surveying, agricultural spraying, and logistics distribution, becoming a vital component of modern intelligent equipment systems.

[0003] Especially in the logistics sector, the rapid delivery of small cargo using drones has become a cutting-edge technological exploration. However, in actual applications, when drones carry cargo to perform transportation missions, their energy consumption increases significantly, and flight distance and time are severely limited by battery capacity or fuel reserves. Currently, some drones extend their flight time by installing larger batteries or using fuel propulsion systems such as gasoline and diesel. However, such solutions not only suffer from energy efficiency losses but also increase structural complexity and carbon emissions, and still cannot meet the actual needs of long-distance, high-frequency delivery missions. Therefore, how to reduce energy consumption when carrying cargo and improve flight efficiency, especially achieving "super-long flight time" without significantly increasing energy consumption, has become a technical challenge that needs to be urgently addressed in the current drone delivery field. Summary of the Invention

[0004] According to an embodiment of the present invention, a bird-shaped, ultra-long-range, load-bearing, gripping logistics drone and a method of using the same are provided to address the problems raised by the above-mentioned background technology.

[0005] In a first aspect of the present invention, a bird-shaped drone with ultra-long endurance and load-bearing capacity for logistics with a gripping mechanism is provided.

[0006] The ultra-long-range, load-bearing, grabbing logistics bird-shaped drone includes: a fuselage, a transmission assembly, a drive assembly, two hang gliders, a propulsion mechanism, four arms, four rotors, and a grabbing assembly; the drive assembly is installed inside the fuselage, the hang gliders are rotatably connected to the fuselage, the drive assembly is connected to the hang gliders and is used to drive the hang gliders to unfold or fold, the four arms are rotatably connected to the fuselage, the drive assembly is connected to the four arms through the transmission assembly, the four rotors are respectively connected to the four arms, the propulsion mechanism is connected to the fuselage, and the grabbing assembly is arranged at the bottom of the fuselage.

[0007] Preferably, the hang glider includes a connecting arm, a connecting belt and a plurality of expansion pieces; the connecting arm is rotatably connected to the lower shell of the fuselage, the plurality of expansion pieces are rotatably connected to the connecting arm, the expansion pieces away from the connecting arm are fixedly connected to the fuselage, and a first notch is provided on the lower shell for the expansion pieces to extend out.

[0008] Preferably, the driving assembly includes an electric push rod, a moving seat and two support rods; the electric push rod is fixedly connected to the fuselage, the output end of the electric push rod extends into the interior of the fuselage and is fixedly connected to the moving seat, the moving seat is slidably installed inside the fuselage, the two support rods are both rotatably connected to the moving seat, and the ends of the two support rods away from the moving seat are respectively rotatably connected to the two connecting arms.

[0009] Preferably, the ends of the two connecting arms that are close to each other are provided with mutually meshing teeth.

[0010] Preferably, the transmission assembly includes a transmission rod, a mounting shaft, a transmission shaft, two racks, a gear and two transmission members; the mounting shaft is fixedly installed in the connecting shell of the fuselage, the mounting shaft passes through the transmission rod, the transmission rod is rotatably connected to the mounting shaft, the transmission shaft is fixedly connected to the rack located on the lower side, the transmission rod is provided with a first driving groove, the transmission shaft passes through the first driving groove and is movably connected to the first driving groove, the movable seat is provided with a second driving groove, the transmission rod is provided with a fixed shaft, the fixed shaft extends into the second driving groove, the gear is rotatably installed in the upper shell of the fuselage, the two racks are arranged opposite to each other and are respectively meshed with the gears, the side wall of the upper shell is provided with a second notch for the rack to extend, and the rack is slidably connected to the second notch; the two racks are respectively connected to the two transmission members, the support arm is provided with a guide groove, and the transmission member is provided with a limit rod passing through the guide groove, and the limit rod is movably connected to the guide groove.

[0011] Preferably, the propulsion mechanism includes a tube body, a motor and a fan; the tube body is fixedly connected to the fuselage, the motor is installed in the tube body, and the fan is installed at the output end of the motor.

[0012] Preferably, it further comprises a tail wing, which is mounted on the tube body.

[0013] Preferably, the grab assembly includes a connecting rope, a sleeve, a mounting tube, a push rod, a driving member, a clamping claw, a handle, a locking ring and a spring; the connecting rope is fixedly connected to the lower housing, the end of the connecting rope away from the lower housing is fixedly connected to the sleeve, the sleeve is fixedly connected to the mounting tube, the sleeve and the interior of the mounting tube are communicated, the push rod is installed in the sleeve and the mounting tube, the driving member is fixedly connected to the lower end of the push rod, the spring is sleeved on the push rod, and the lower end of the spring is connected to the push rod The upper end of the spring is connected to the sleeve, and the spring provides the elastic force for the push rod to push downward. The upper end of the push rod is fixedly connected to the handle, and the side wall of the sleeve is provided with a sliding groove for the handle to extend out. The sleeve is provided with a mounting portion, and the locking ring is in a hook shape. The locking ring is rotatably mounted on the mounting portion. The number of the clamping jaws is three, and the three clamping jaws are respectively rotatably connected to the lower end of the mounting tube. The clamping jaws are provided with teeth, and the driving member is provided with a protrusion that engages with the teeth of the clamping jaws.

[0014] Preferably, the lower end of the driving member is connected with a hook.

[0015] In a second aspect of the present invention, a method for using a long-range, load-bearing, grabbing and clamping logistics bird-shaped drone is provided, comprising the following steps:

[0016] One or more technical solutions provided in this application have at least the following technical effects or advantages:

[0017] This invention provides a long-range, load-bearing, gripping, and bird-shaped logistics drone. It can switch between rotor flight and gliding flight according to mission requirements. Combining a bionic bird-shaped nose design with deployable and retractable glider wings, it achieves low-energy, long-distance gliding flight, effectively extending flight time. Compared to existing single-powered drones, this invention offers a more flexible structural design and more efficient energy control, making it particularly suitable for medium- and long-distance logistics and delivery scenarios with demanding flight times.

[0018] It should be understood that the contents described in the summary of the invention are not intended to limit the key or important features of the embodiments of the present invention, nor are they intended to limit the scope of the present invention. Other features of the present invention will become readily understood through the following description. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The above and other features, advantages and aspects of the embodiments of the present invention will become more apparent with reference to the following detailed description in conjunction with the accompanying drawings. In the accompanying drawings, the same or similar reference numerals represent the same or similar elements, wherein:

[0020] Figure 1A schematic diagram of the three-dimensional structure of a bird-shaped, gripping logistics drone with extended endurance and load-bearing capability according to an embodiment of the present invention is shown;

[0021] Figure 2 An exploded view of a bird-shaped, gripping logistics drone with extended endurance and load-bearing capability according to an embodiment of the present invention is shown;

[0022] Figure 3 A schematic diagram of the three-dimensional structure of the transmission assembly of the ultra-long-range, load-bearing, gripping and clamping logistics bird-shaped drone according to an embodiment of the present invention is shown;

[0023] Figure 4 A schematic diagram of the connection structure of the fuselage, glider, and grabbing assembly of a bird-shaped, ultra-long-range, load-bearing, grabbing logistics drone according to an embodiment of the present invention is shown;

[0024] Figure 5 A schematic cross-sectional view of a bird-shaped, ultra-long-range, load-bearing, grabbing and clamping logistics drone according to an embodiment of the present invention is shown;

[0025] Figure 6 A schematic diagram of the three-dimensional structure of the propulsion mechanism of the ultra-long-range and load-bearing grabbing and clamping logistics bird-shaped drone according to an embodiment of the present invention is shown;

[0026] Figure 7 A schematic cross-sectional view of a grabbing assembly of a bird-shaped, ultra-long-range, load-bearing, grabbing logistics drone according to an embodiment of the present invention is shown;

[0027] Figure 8 A schematic diagram of the exploded structure of a grabbing assembly of a bird-shaped, ultra-long-range, load-bearing, grabbing logistics drone according to an embodiment of the present invention is shown;

[0028] Figure 9 A schematic diagram of the three-dimensional structure of the transmission assembly and the support arm of the ultra-long-range, load-bearing, gripping and clamping logistics bird-shaped drone according to an embodiment of the present invention is shown;

[0029] Figure 10 A schematic diagram of the three-dimensional structure of the fuselage of a bird-shaped, gripping logistics drone with extended endurance and load-bearing capability according to an embodiment of the present invention is shown;

[0030] Figure 11 A schematic diagram of the three-dimensional structure of a locking ring of a bird-shaped, gripping logistics drone with extended endurance and load-bearing capacity according to an embodiment of the present invention is shown;

[0031] Figure 12 A schematic diagram of the connection structure of the transmission assembly and the drive assembly of the ultra-long-range, load-bearing, gripping, and bird-shaped logistics drone according to an embodiment of the present invention is shown;

[0032] Figure 13A schematic diagram of the three-dimensional structure of the transmission parts of the ultra-long-range, load-bearing, gripping and clamping logistics bird-shaped drone according to an embodiment of the present invention is shown.

[0033] Tag Name

[0034] 1-body, 11-lower housing, 111-first notch, 12-connecting housing, 13-upper housing, 131-second notch, 2-transmission assembly, 21-transmission rod, 211-first drive slot, 212-fixed shaft, 22-installation shaft, 23-transmission shaft, 24-rack, 25-gear, 26-transmission member, 261-limiting rod, 3-drive assembly, 31-electric push rod, 32-moving seat, 321-second drive slot, 33-support rod, 4- Hang glider, 41-connecting arm, 42-connecting belt, 43-spreader, 5-propulsion mechanism, 51-tube, 52-motor, 53-fan, 6-support arm, 61-guide groove, 7-rotor, 8-grabbing assembly, 81-connecting rope, 82-casing, 821-slide, 822-mounting part, 83-mounting tube, 84-top rod, 85-driving part, 851-hook, 86-clamping claw, 87-handle, 88-locking ring, 89-spring, 9-tail. DETAILED DESCRIPTION

[0035] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0036] In this document, the term "and / or" simply describes a relationship between related objects, indicating that three possible relationships exist. For example, "A and / or B" can represent: A exists alone, A and B exist simultaneously, or B exists alone. Furthermore, the character " / " in this document generally indicates that the related objects are in an "or" relationship.

[0037] like Figures 1 to 13 As shown, it includes a fuselage 1, a transmission assembly 2, a drive assembly 3, two gliders 4, a propulsion mechanism 5, four arms 6, four rotors 7 and a grabbing assembly 8; wherein, the fuselage 1 is a hollow shell structure for carrying various functional components, and a bird-shaped nose is extended from the front thereof to improve the aerodynamic performance during flight and give the whole machine bionic characteristics, so as to facilitate adaptation to flight turbulence in natural environments.

[0038] The drive assembly 3 is mounted within the fuselage 1 and fixedly connected to the fuselage 1 to reduce vibration transmission and enhance overall structural stability. Two hang gliders 4 are rotatably connected to the left and right sides of the fuselage 1 via rotating connectors, each equipped with a pivot pin. Driven by the drive assembly 3, the hang gliders 4 can be deployed horizontally relative to the fuselage 1 to a flying attitude or retracted to a stowed position, tightly against the fuselage 1. The drive assembly 3 is connected to the rotational axis of the hang gliders 4 via an output shaft and incorporates a synchronization control mechanism to ensure synchronized deployment and retraction of the two hang gliders 4, preventing uneven force application during flight and potentially causing flight instability.

[0039] Transmission assembly 2 transmits the power output of drive assembly 3 to four arms 6, which are rotatably connected to the underside of fuselage 1 via rotating shafts. Specifically, transmission assembly 2 includes multiple sets of transmission rods 21 or gears 25, ensuring that the four arms 6 rotate, stow, and deploy synchronously or in a pre-set sequence when drive assembly 3 is in operation. A rotor 7 is fixedly attached to the distal end of each arm 6. These rotors are controlled by an independent electric drive system, enabling vertical takeoff and landing capabilities.

[0040] The propulsion mechanism 5 is mounted at the rear of the fuselage 1 and rigidly connected to it. It provides continuous propulsion and maintains stability during gliding flight. The gripping assembly 8 is located at the bottom of the fuselage 1 and mechanically connected to it, enabling the gripping, securing, and releasing of objects to be transported.

[0041] During use, the control system first controls the drive assembly 3 to deploy the arm 6 to a preset angle. At this point, the rotor 7 activates and rotates at high speed, generating vertical lift and launching the drone vertically from the ground to a predetermined altitude. Once the desired altitude is reached, the gripping assembly 8 is activated to grab and secure the cargo. Subsequently, the rotor 7 is controlled to maintain flight, allowing the drone to reach its glide starting point.

[0042] When the drone reaches a suitable altitude and position for gliding, the control drive assembly 3 deploys the glider 4 to its maximum wingspan. Simultaneously, the transmission assembly 2 rotates the arm 6 relative to the fuselage 1 and retracts it, bringing the rotor 7 into contact with the fuselage 1 and stopping its rotation, thus entering gliding mode. At this point, the propulsion mechanism 5 activates, providing propulsion for level flight, enabling the drone to glide long distances with the glider 4 deployed. Since the rotor 7 is no longer operational, power consumption is significantly reduced, thereby improving flight endurance.

[0043] After gliding to a set distance, the drive assembly 3 reverses its direction, retracting the glider 4. The glider 4 rotates around its pivoting connector and aligns closely with the sides of the fuselage 1. Simultaneously, the transmission assembly 2 simultaneously drives the arms 6 to redeploy to a flying attitude. At this point, the rotors 7 restart and enter a high-speed rotation state, providing vertical or oblique upward lift for the drone, allowing it to exit the gliding state and return to powered flight with the multi-rotor 7. Simultaneously, the propulsion mechanism 5 ceases operation to prevent unnecessary energy consumption or interference.

[0044] The drone in this embodiment can switch between rotor flight (7) and gliding flight according to mission requirements. Combining a bionic bird-shaped nose design with deployable / retractable gliders (4), it achieves low-energy, long-distance gliding flight, effectively extending flight time. Compared to existing single-powered drones, the present invention offers a more flexible structural design and more efficient energy control, making it particularly suitable for medium- and long-distance logistics and delivery scenarios where flight time is critical.

[0045] In this embodiment, the hang glider 4 includes a connecting arm 41, a connecting belt 42 and a plurality of expansion pieces 43; wherein, the inner end of the connecting arm 41 is rotatably connected to the lower housing 11 of the fuselage 1, and specifically, a rotating shaft structure is provided so that the connecting arm 41 can rotate around the axis under the drive of the driving assembly 3. The plurality of expansion pieces 43 are arranged in sequence along the length direction of the connecting arm 41, and are respectively rotatably connected to the connecting arm 41 through a hinge structure, so that they can be unfolded in the process of the rotation of the connecting arm 41. In order to enhance the coordination and stability of the overall unfolding structure, the connecting belt 42 is made of a flexible material, passes through the edges of each expansion piece 43 or is provided at the connection node between the expansion pieces 43, and is used to synchronously pull each expansion piece 43 when the connecting arm 41 rotates, ensuring that each expansion piece 43 maintains a relatively consistent positional relationship when rotating and unfolding, and avoiding local relaxation or deflection.

[0046] Furthermore, a flap 43 at one end, distal from the connecting arm 41, is fixedly connected to the fuselage 1, defining the deployment endpoint and providing rigid support for the deployed hang glider 4, thereby enhancing the structural strength of the hang glider 4 during flight. To allow the flap 43 to smoothly extend from the interior of the fuselage 1, a first notch 111 is defined in the lower housing 11. The size and position of this first notch 111 align with the deployment trajectory of the flap 43, ensuring that the flap 43 can pass through the notch unimpeded during deployment or retraction, and naturally emerge from both sides of the fuselage 1 in the fully deployed state.

[0047] When the hang glider 4 needs to be deployed for gliding mode, the control system activates the drive assembly 3, causing its output rotational force to drive the two connecting arms 41 to rotate synchronously about their axes. As the connecting arms 41 rotate, the multiple fins 43 connected to them unfold sequentially, driven by the coordinated action of their own rotating structures and the connecting straps 42, ultimately forming the hang glider 4 structure with a specific aspect ratio and curvature. The connecting straps 42 act as limiters, traction devices, and synchronized deployment during this process, allowing the fins 43 to unfold in an arc-shaped pattern while maintaining a certain tension, forming a complete and continuous wing surface.

[0048] When fully deployed, the glider 4, driven and positioned by the connecting arms 41, the stretch-limiting effect of the connecting straps 42, and the secure connection between the outermost flaps 43 and the fuselage 1, form a stable airfoil structure. This effectively provides lift during gliding, improving the drone's gliding efficiency, reducing energy consumption, and extending its flight time. Compared to existing drones with fixed wings or no wing structures, this embodiment achieves a balance between structural compactness and flight performance through the deployable, multi-stage glider 4. This ensures a compact structure and flexible flight, while effectively enhancing flight range and payload capacity.

[0049] In this embodiment, the drive assembly 3 includes an electric push rod 31, a movable base 32, and two support rods 33. The electric push rod 31 is fixedly connected to the internal frame of the body 1 via a bracket structure, maintaining axial stability during operation. The output end of the electric push rod 31 is longitudinally retractable and extends through the internal cavity of the body 1. Its distal end is fixedly connected to the movable base 32. Therefore, when the electric push rod 31 is in operation, it can drive the movable base 32 to slide linearly along the guide rail or slide groove 821 structure within the body 1.

[0050] Two struts 33 are hingedly mounted on the movable base 32. The first ends of the two struts 33 are rotatably connected to the movable base 32 via a rotational connection, allowing them to swing freely during the movement of the movable base 32. The second ends of the two struts 33 are located away from the movable base 32 and are rotatably connected to two connecting arms 41 provided on either side of the fuselage 1. Specifically, hinge points are provided at the proximal ends of the connecting arms 41, so that the struts 33 can drive the connecting arms 41 to rotate about their own rotation axes under the action of external forces.

[0051] During use, a control signal is applied to the electric push rod 31 through the control system to start the electric push rod 31 to extend. The output end of the electric push rod 31 is then pushed out axially, and drives the movable seat 32 connected to it to move forward. As the movable seat 32 moves, the middle rotation point of the two struts 33 is forced to approach the connecting arm 41, thereby pushing the two connecting arms 41 connected to their distal ends to rotate synchronously outward, so that the glider 4 is gradually unfolded. Since the struts 33 play a dual role of support and traction during the rotation of the connecting arms 41, the connecting arms 41 can maintain a stable and synchronous rotation state, effectively avoiding jamming or deformation caused by local uneven force. Finally, the connecting arm 41 rotates to a predetermined angle, so that it drives the expansion piece 43 to fully unfold, as shown in FIG. Figure 10 In the state shown, the unfolding action of the hang glider 4 is completed.

[0052] On the contrary, when the electric push rod 31 receives the retraction command, its output end will retract in the opposite direction, driving the moving seat 32 to move away from the connecting arm 41. The two struts 33 swing in the opposite direction under the pull of the moving seat 32, and then drive the connecting arm 41 to rotate toward the fuselage 1, so that it is gradually retracted to the initial storage state, and the expansion piece 43 is folded accordingly, completing the folding process of the glider 4.

[0053] This drive assembly 3, which converts linear motion into control through an electric push rod 31 and a linkage structure between a movable base 32 and a strut 33, not only achieves precise control of the hang glider 4 but also avoids the space requirements, control accuracy, and structural complexity inherent in conventional rotary motors 52 or complex gears 25. This mechanical drive allows the hang glider 4 to deploy and retract quickly and smoothly during flight, enhancing the drone's ability to quickly switch between different flight states and further improving flight stability and endurance.

[0054] In this embodiment, if Figure 10 As shown, the two connecting arms 41 are each provided with a latching tooth structure formed along the outer arc surface of the end portion at the end portion thereof, and the two latching tooth structures engage with each other. Specifically, the latching tooth is a tooth-shaped structure provided along the arc direction of the end portion of the connecting arm 41. During the process of extending or retracting the two connecting arms 41, the latching tooth always remains in a meshing state, establishing a mechanical synchronization constraint relationship between the two connecting arms 41.

[0055] By providing a mutually meshing latch structure, when one connecting arm 41 is driven to rotate by the force of the drive assembly 3, the latch teeth transmit this rotational force to the other connecting arm 41 through meshing, thereby causing the other connecting arm 41 to rotate synchronously in the opposite direction. This structure avoids the motion errors and asynchrony that may arise from independently driving the two connecting arms 41, ensuring that the two connecting arms 41 are always deployed or retracted in a relatively symmetrical posture during the driving process.

[0056] Furthermore, because the latching mechanism is a passive synchronous structure, it does not rely on complex control system coordination during transmission, thus offering significant advantages in structural simplicity, reliability, and anti-interference capabilities. Furthermore, when the connecting arm 41 reaches its maximum deployment or retraction position, the latching mechanism engages with each other to provide additional stopping force, preventing excessive rotation of the connecting arm 41 due to inertia or external interference, thereby improving the flight stability of the glider 4 when deployed.

[0057] In this embodiment, the transmission assembly 2 comprises a transmission rod 21, a mounting shaft 22, a transmission shaft 23, two racks 24, a gear 25, and two transmission members 26. The mounting shaft 22 is fixedly mounted within the connecting housing 12 of the body 1, with one end rigidly connected to the body 1 structure to provide a stable rotational fulcrum. The transmission rod 21 is sleeved onto the mounting shaft 22 through a central hole and forms a rotational connection with the mounting shaft 22, enabling the transmission rod 21 to rotate about the mounting shaft 22.

[0058] The transmission shaft 23 is disposed below the transmission rod 21 and is fixedly connected to the two lower racks 24. As a result, axial movement of the transmission shaft 23 drives the two lower racks 24 to move linearly. A first drive slot 211 is defined along the axial direction of the transmission rod 21. The transmission shaft 23 is inserted into this first drive slot 211 and is movably connected thereto. This allows the transmission rod 21 to exert restrictive guidance on the transmission shaft 23 through the walls of the drive slot during rotation, thereby achieving drive control of the transmission shaft 23.

[0059] In order to realize the rotation control of the transmission rod 21, a second driving groove 321 is provided on the movable seat 32, and a fixed shaft 212 is fixedly provided in the middle part of the transmission rod 21. One end of the fixed shaft 212 extends into the second driving groove 321 and movably cooperates with it. When the movable seat 32 slides longitudinally under the drive of the driving assembly 3, the second driving groove 321 drives the fixed shaft 212 to produce corresponding relative movement, thereby causing the transmission rod 21 to rotate at the mounting shaft 22.

[0060] The sidewall of the upper housing 13 defines a second notch 131 through which the rack 24 extends. The rack 24 is slidably connected to the second notch 131. During transmission, as the transmission rod 21 rotates about the mounting shaft 22, the first drive slot 211 thereon simultaneously guides the transmission shaft 23 for axial linear movement, thereby driving the synchronous translation of the lower rack 24 fixed thereto. Each rack 24 is meshed with a gear 25 positioned above it. The gear 25 is rotatably mounted within the upper housing 13 of the housing 1, with its axis of rotation supported by a support bearing. The two racks 24 are arranged opposite each other and located on either side of the gear 25. As the lower rack 24 moves linearly, the drive gear 25 rotates about its axis, further driving the upper rack 24 to synchronously move in the opposite direction through meshing.

[0061] To achieve interlocking control with the support arm 6, the two racks 24 are connected to the inner ends of two transmission members 26. These transmission members 26 are located within the fuselage 1 and arranged along the direction in which the support arm 6 is extended or retracted. A limit rod 261 is positioned on the outside of these transmission members. This limit rod 261 extends through and slidably engages with a guide slot 61 defined in the support arm 6. During movement of the transmission member 26, the limit rod 261 moves along its pre-set trajectory within the guide slot 61, thereby driving the support arm 6 to rotate about its mounting end.

[0062] In specific use, when the movable base 32 slides forward driven by the electric push rod 31, the second drive slot 321 drives the fixed shaft 212 to move, causing the transmission rod 21 to rotate about the mounting shaft 22. The transmission rod 21, through the first drive slot 211 therein, drives the transmission shaft 23 to move linearly, thereby driving the lower rack 24 to move, causing the gear 25 to rotate and synchronously drive the upper rack 24 to move in the opposite direction. Because the two racks 24 are respectively connected to the two transmission members 26, the opposing movement of the racks 24 will drive the two transmission members 26 closer to each other, thereby driving the support arm 6 outward through the limit rod 261, thereby achieving the deployment of the support arm 6.

[0063] On the contrary, when the movable seat 32 slides backward, the direction of the entire transmission process is reversed, the two transmission parts 26 move away from each other under the drive of the rack 24, and the limit rod 261 moves toward the center in the guide groove 61, thereby prompting the support arm 6 to fold and retract relative to the fuselage 1, completing the structural conversion from flight mode to gliding mode.

[0064] In this embodiment, the propulsion mechanism 5 comprises a tube 51, a motor 52, and a fan 53. The tube 51 is a hollow fluid channel structure with one end fixedly connected to the rear of the fuselage 1 and the other end forming an air outlet for generating a directional airflow to provide propulsion. The tube 51 can be made of a lightweight material with good strength and heat resistance to reduce the overall weight and improve structural reliability.

[0065] The motor 52 is mounted within the tube 51 and is securely fastened to the tube 51 via a bracket or motor 52 mounting assembly. The motor 52 is located at the end of the tube 51 near the fuselage 1. Its output shaft extends axially along the tube 51, driving the fan 53 to generate axial airflow. The fan 53 is mounted directly at the output end of the motor 52 and utilizes a high-efficiency blade structure. This rapidly compresses air and ejects it axially along the tube 51 as the motor 52 rotates, creating a backward reaction force that propels the drone forward.

[0066] In actual use, when the drone enters the gliding phase or long-distance cruising flight, the control system activates motor 52. The output shaft of motor 52 rotates, driving fan 53 at high speed. This rotation generates a powerful airflow, which is ejected from the rear end of tube 51, providing the drone with stable and continuous forward propulsion. During propulsion, the airflow generated by fan 53 exerts thrust along the longitudinal direction of fuselage 1, which synergizes with the lift provided by glider 4, significantly increasing flight speed and glide distance in the gliding state.

[0067] Specifically, in this embodiment, two fans 53 are provided, one on each side of the tube 51, or distributed vertically. This creates balanced thrust, improves propulsion stability, and prevents yaw or instability caused by unilateral thrust. Furthermore, four rotors 7 are located at the distal ends of the four arms 6, enabling vertical takeoff and landing (VTOL) and hovering.

[0068] To achieve optimal energy efficiency, when the drone enters the gliding mode, the control system automatically shuts down rotors 7, cutting off their power supply to stop rotation and eliminate inefficient power consumption. Simultaneously, fan 53 is activated, allowing propulsion mechanism 5 to take over the propulsion task, with only fan 53 providing propulsion and glider 4 providing flight power. This approach effectively reduces the energy consumption associated with the simultaneous operation of multiple rotors 7 and, leveraging the gliding principle, reduces reliance on battery capacity, thereby achieving longer flight time and greater range.

[0069] To sum up, the propulsion mechanism 5 in this embodiment provides continuous propulsion force in the gliding flight state of the UAV through the compact fan 53 propulsion device, and works in coordination with the glider 4, which not only improves the flight efficiency in the gliding stage, but also significantly reduces the overall energy consumption. Compared with traditional UAVs that only rely on multi-rotor 7 drive, it has better energy-saving performance and long-range operation capabilities, and is suitable for application scenarios with high endurance requirements such as medium and long-distance material transportation and aerial cruising.

[0070] The aircraft also includes a tail fin 9, which is mounted at the distal end of the tube 51. Specifically, it is arranged along the axial extension of the tube 51 and is securely connected to the tube 51 via structural connectors or an integrally formed structure, allowing it to stably move with the rear of the aircraft 1 during flight. The tail fin 9 can be a fixed structure or an adjustable structure according to flight conditions to control flight attitude.

[0071] The tail fin 9 is designed to facilitate aerodynamic stability control during gliding flight. Especially when the glider 4 is deployed and the drone is gliding, the tail fin 9 plays a crucial role in directional stability and pitch attitude adjustment. Through its shape and mounting angle, the tail fin 9 effectively directs the airflow behind the fuselage 1, suppressing yaw and pitch disturbances during flight, thereby enhancing the drone's flight stability and heading-keeping capabilities during gliding.

[0072] In this embodiment, the grab assembly 8 includes a connecting rope 81, a sleeve 82, a mounting tube 83, a push rod 84, a driving member 85, a clamping claw 86, a handle 87, a locking ring 88, and a spring 89. The upper end of the connecting rope 81 is fixedly connected to the lower housing 11, suspending or pulling the grab assembly 8 relative to the fuselage 1 to ensure its stability during takeoff, flight, and landing. The other end of the connecting rope 81 is fixedly connected to the sleeve 82, which is a hollow structure that accommodates and guides the upward and downward movement of the push rod 84.

[0073] The lower end of the sleeve 82 is connected to the mounting tube 83. The two are fixedly connected by a tight fit or threaded connection, maintaining a communication relationship between the internal channels, allowing the push rod 84 to move integrally within the two along its axial direction. The push rod 84 is a slender rod-shaped structure, mounted on the central axis of the sleeve 82 and mounting tube 83, and has excellent guiding and sliding properties. The lower end of the push rod 84 is fixedly connected to a driver 85, which is located inside the lower end of the mounting tube 83 and can move up and down with the push rod 84, driving the multiple clamping jaws 86 located at the lower end of the mounting tube 83 to open and close.

[0074] The spring 89 is a compression spring 89, one end of which is sleeved on the upper end of the push rod 84 and forms an elastic connection with the upper end surface inside the sleeve 82, and the other end rests on the push rod 84, and is used to provide a downward return elastic force during the upward movement of the push rod 84, so that the push rod 84 is always in the initial downward push state, which helps the clamping jaw 86 to automatically rebound to the open state when there is no operation.

[0075] The upper end of the push rod 84 is connected to a handle 87, which extends outwardly through a slot 821 provided in the side wall of the sleeve 82, allowing the operator to directly control the up and down movement of the push rod 84 through the handle 87. The sleeve 82 is also provided with a mounting portion 822, which is a fixed structure used to support the handle 87 during lifting and provide a rotational mounting position for the lock ring 88.

[0076] The locking ring 88 is a hook-shaped structure, one end of which is hinged to the mounting portion 822 and can be deflected about its axis by external force. As the handle 87 approaches the mounting portion 822, its surface contacts the hook portion of the locking ring 88, causing the locking ring 88 to temporarily deflect. Once the handle 87 enters the notch of the hook, the locking ring 88 quickly returns to its original position under the action of its own weight or the return spring, locking the handle 87 in place on the mounting portion 822 and achieving the self-retention function of the clamping jaws 86 when closed.

[0077] There are three symmetrically arranged clamping jaws 86, each mounted on the lower end of the mounting tube 83 via a rotating shaft. Each clamping jaw 86 is equipped with a tooth structure that engages with a protrusion on the driver 85. As the driver 85 moves upward under the influence of the push rod 84, the protrusions on its surface push the teeth of the clamping jaws 86, forcing each clamping jaw 86 to move inward about its rotating shaft. This brings the three clamping jaws 86 closer together, forming a closed gripping state and defining a limited space between the clamping jaws 86 for clamping an object.

[0078] Since the spring 89 is compressed during the clamping process, it provides a return force for the push rod 84. Therefore, when the clamping state needs to be released, it is only necessary to lift the handle 87 again to release the locking relationship between it and the locking ring 88, and then manually move the locking ring 88 to deflect it and disengage it from the mounting portion 822. At this time, under the action of the return force of the spring 89, the push rod 84 and the driving member 85 will be forced to move downward, and the driving member 85 will leave the meshing position with the clamping claw 86. The clamping claw 86 will return to the open state under its own gravity or the action of the reset elastic member, thereby completing the release of the object.

[0079] Furthermore, in this embodiment, the lower end of the driving member 85 is further connected to a hook 851, which is fixedly connected to the lower portion of the driving member 85 by means of threads, snaps, or welding. The hook 851 is used to hang items with handles, such as packaging bags, containers, or small devices, thereby expanding the scope of application of the grabbing assembly 8. When the gripping claws 86 are not suitable for grabbing, the hook can still be used to carry and transport items.

[0080] To sum up, the grasping component 8 in this embodiment realizes the organic combination of multiple functions such as grasping and releasing of the clamping claw 86, manual control and automatic locking, elastic reset and stable grasping through a mechanical linkage structure. It has a compact structure and reliable operation. It is particularly suitable for logistics drones to achieve stable and efficient grasping and releasing operations on various types of goods during the process of changing flight posture, gliding stage or target point grasping operations.

[0081] This technical solution introduces a switching mechanism between the foldable glider 4, the rotor 7 drive and the fan 53 propulsion, as well as a structured grasping component 8, to achieve the dynamic conversion of the UAV from the multi-rotor 7 vertical take-off and landing mode to the gliding flight mode during flight. It fully combines the design concept of "high gliding efficiency of fixed wings and strong maneuverability of rotors 7" in aviation engineering, and utilizes the coordinated regulation of aerodynamic lift and propulsion force to effectively extend the flight time and reduce energy consumption, reflecting the innovative application and system integration of aviation flight principles in small logistics UAVs.

[0082] In addition, another embodiment of the present invention further provides a method for using a long-range, load-bearing, grabbing, and clamping logistics bird-shaped drone, comprising the following steps:

[0083] Step 1: Takeoff preparation. The control system activates the drive assembly 3, causing the arms 6 to unfold, the rotors 7 to be in the takeoff state, the gliders 4 to be folded to the sides of the fuselage 1, the propulsion mechanism 5 to be turned off, and the grabbing assembly 8 to be in the initial standby state.

[0084] Step 2: Takeoff and hovering. Start the rotor 7 to make the drone take off vertically to the target height, and hover through the control system to position it above the object to be grasped.

[0085] Step 3: Grab the cargo. Control the grabbing assembly 8 to descend and contact the target object. Pull the handle 87 to drive the clamping claw 86 to close or the hook 851 to mount the target object, securing the target object under the drone and completing the grab.

[0086] Step 4: Entering gliding mode. Activate the drive assembly 3 to control the glider 4 to unfold, while driving the arm 6 to retract and close the rotor 7. Activate the propulsion mechanism 5 to generate thrust through the fan 53, causing the drone to enter gliding flight mode.

[0087] Step 5: Gliding flight. Under the synergistic effect of the continuous propulsion of the propulsion mechanism 5 and the lift provided by the glider 4, the UAV performs low-energy, long-distance gliding flight.

[0088] Step 6: Repeat the switch. According to the flight mission requirements and real-time environmental conditions, the control system cyclically switches between rotor 7 flight and gliding flight during the flight to achieve the purpose of reducing energy consumption and extending flight endurance.

[0089] Step 7: When approaching the target area, still select the optimal switching mode based on the flight status, so that the drone approaches the delivery area in a stable flight posture.

[0090] Step 8: Release the cargo. Control the gripping assembly 8 to unlock, and the clamping claw 86 or hook 851 releases the cargo, completing the delivery task.

[0091] Step 9: Return and Landing. Control the drone to return home according to the same flight mode switching strategy, gradually descend, and achieve vertical landing through rotor 7 control.

[0092] This method fully utilizes the maneuverability of the rotor 7 and the energy-saving characteristics of the glider 4 by switching back and forth between rotor 7 flight and gliding flight during the flight process. While ensuring that the UAV can stably carry cargo, it effectively reduces flight energy consumption and significantly improves endurance. Compared with the traditional continuous rotor 7-driven flight mode, this method can dynamically adapt to flight path and altitude changes, optimize energy distribution, extend battery life, and enhance the practicality and reliability of the UAV in medium and long-distance logistics missions.

[0093] The above specific embodiments do not limit the scope of protection of the present invention. Those skilled in the art will appreciate that various modifications, combinations, sub-combinations, and substitutions may be made based on design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention are intended to be included within the scope of protection of the present invention.

Claims

1. A bird-shaped drone with super-long endurance and load-bearing capacity for logistics, characterized by: include: A fuselage (1), a transmission assembly (2), a drive assembly (3), two hang gliders (4), a propulsion mechanism (5), four arms (6), four rotors (7) and a grabbing assembly (8); the drive assembly (3) is installed inside the fuselage (1); the hang glider (4) is rotatably connected to the fuselage (1); the drive assembly (3) is connected to the hang glider (4) and is used to drive the hang glider (4) to unfold or fold; the four arms (6) are rotatably connected to the fuselage (1); the drive assembly (3) is connected to the four arms (6) through the transmission assembly (2); the four rotors (7) are respectively connected to the four arms (6); the propulsion mechanism (5) is connected to the fuselage (1); and the grabbing assembly (8) is arranged at the bottom of the fuselage (1).

2. The ultra-long-range, load-bearing, grabbing and clamping logistics bird-shaped drone according to claim 1 is characterized in that: The hang glider (4) comprises a connecting arm (41), a connecting belt (42) and a plurality of spreading pieces (43); the connecting arm (41) is rotatably connected to the lower shell (11) of the fuselage (1); the plurality of spreading pieces (43) are rotatably connected to the connecting arm (41); the spreading pieces (43) away from the connecting arm (41) are fixedly connected to the fuselage (1); and a first notch (111) is provided on the lower shell (11) for the spreading pieces (43) to extend out.

3. The ultra-long-range, load-bearing, grabbing and clamping logistics bird-shaped drone according to claim 2 is characterized in that: The driving assembly (3) comprises an electric push rod (31), a movable seat (32) and two support rods (33); the electric push rod (31) is fixedly connected to the body (1); the output end of the electric push rod (31) extends into the interior of the body (1) and is fixedly connected to the movable seat (32); the movable seat (32) is slidably mounted inside the body (1); the two support rods (33) are both rotatably connected to the movable seat (32); and the ends of the two support rods (33) away from the movable seat (32) are rotatably connected to the two connecting arms (41) respectively.

4. The ultra-long-range, load-bearing, grabbing and clamping logistics bird-shaped drone according to claim 3 is characterized in that: The two connecting arms (41) are provided with mutually meshing teeth at their ends close to each other.

5. The ultra-long-range, load-bearing, grabbing and clamping logistics bird-shaped drone according to claim 3 is characterized in that: The transmission assembly (2) comprises a transmission rod (21), a mounting shaft (22), a transmission shaft (23), two racks (24), a gear (25) and two transmission members (26); the mounting shaft (22) is fixedly mounted in a connecting shell (12) of the fuselage (1); the mounting shaft (22) passes through the transmission rod (21); the transmission rod (21) is rotatably connected to the mounting shaft (22); the transmission shaft (23) is fixedly connected to the rack (24) located at the lower side; a first driving groove (211) is provided on the transmission rod (21); the transmission shaft (23) passes through the first driving groove (211) and is movably connected to the first driving groove (211); a second driving groove (321) is provided on the movable seat (32); and a second driving groove (321) is provided on the transmission rod (21). A fixed shaft (212) is provided, and the fixed shaft (212) extends into the second driving groove (321). The gear (25) is rotatably installed in the upper shell (13) of the body (1). The two racks (24) are arranged opposite to each other and are respectively engaged with the gears (25). The side wall of the upper shell (13) is provided with a second notch (131) for the racks (24) to extend out. The racks (24) are slidably connected to the second notch (131); the two racks (24) are respectively connected to the two transmission members (26). A guide groove (61) is provided on the support arm (6). A limiting rod (261) passing through the guide groove (61) is provided on the transmission member (26), and the limiting rod (261) is movably connected to the guide groove (61).

6. The ultra-long-range, load-bearing, grabbing and clamping logistics bird-shaped drone according to claim 1, characterized in that: The propulsion mechanism (5) comprises a tube body (51), a motor (52) and a fan (53); the tube body (51) is fixedly connected to the fuselage (1), the motor (52) is installed in the tube body (51), and the fan (53) is installed at the output end of the motor (52).

7. The ultra-long-range, load-bearing, grabbing and clamping logistics bird-shaped drone according to claim 6, characterized in that: It also includes a tail wing (9), which is mounted on the tube body (51).

8. The ultra-long-range, load-bearing, grabbing and clamping logistics bird-shaped drone according to claim 1, characterized in that: The grab assembly (8) comprises a connecting rope (81), a sleeve (82), a mounting tube (83), a push rod (84), a driving member (85), a clamping claw (86), a handle (87), a locking ring (88) and a spring (89); the connecting rope (81) is fixedly connected to the lower housing (11) of the machine body (1); the end of the connecting rope (81) away from the lower housing (11) is fixedly connected to the sleeve (82); the sleeve (82) is fixedly connected to the mounting tube (83); the sleeve (82) and the mounting tube (83) are internally communicated; the push rod (84) is installed in the sleeve (82) and the mounting tube (83); the driving member (85) is fixedly connected to the lower end of the push rod (84); the spring (89) is sleeved on the push rod (84); the spring (89) ) is connected to the push rod (84), the upper end of the spring (89) is connected to the sleeve (82), the spring (89) provides the push rod (84) with a downward ejecting elastic force, the upper end of the push rod (84) is fixedly connected to the handle (87), the side wall of the sleeve (82) is provided with a slide groove (821) for the handle (87) to extend, the sleeve (82) is provided with a mounting portion (822), the locking ring (88) is in a hook shape, the locking ring (88) is rotatably mounted on the mounting portion (822), the number of the clamping jaws (86) is three, the three clamping jaws (86) are respectively rotatably connected to the lower end of the mounting tube (83), the clamping jaws (86) are provided with latching teeth, and the driving member (85) is provided with a protrusion that engages with the latching teeth of the clamping jaws (86).

9. The ultra-long-range, load-bearing, grabbing and clamping logistics bird-shaped drone according to claim 8, characterized in that: The lower end of the driving member (85) is connected to a hook (851).

10. A method for using a bird-shaped, ultra-long-range, load-bearing, grabbing logistics drone, characterized in that: include: Step 1: Start the driving assembly (3), so that the arm (6) is unfolded, the rotor (7) is in the take-off state, the glider (4) is folded to both sides of the fuselage (1), the propulsion mechanism (5) is closed, and the grabbing assembly (8) is in the initial standby state; Step 2: Start the rotor (7) to make the drone take off vertically to the target height and hover above the object to be grasped; Step 3: Control the grabbing component (8) to grab the object; Step 4: The driving assembly (3) controls the glider (4) to unfold, and at the same time drives the arm (6) to retract and close the rotor (7), and starts the propulsion mechanism (5) to generate thrust through the fan (53), so that the UAV enters the gliding flight state; Step 5: After the gliding phase is completed, the propulsion mechanism (5) is turned off, the glider (4) is driven to fold up, the support arm (6) is driven to unfold, and the rotor (7) is restarted at the same time, entering the conventional multi-rotor (7) flight mode; Step 6: Based on the flight mission requirements and real-time environmental conditions, repeat steps 4 and 5 during the flight.

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