An unmanned aerial vehicle with wing protection structure and a protection method

Abstract

This invention relates to the field of unmanned aerial vehicle (UAV) technology, specifically disclosing a UAV with a wing protection structure and its protection method. The UAV includes a UAV body, a first protection structure, a buffer structure, a second protection structure, and a linkage structure. The UAV body includes a fuselage and arms. The arms consist of a first arm, a second arm, and a wing assembly. The first arm is fixed to the side wall of the fuselage, and the second arm is connected to the first arm via a hinge axis and can swing horizontally. The wing assembly is located at the end of the second arm. The first protection structure is located around the wing assembly and detachably connected to the second arm. The buffer structure is located at the hinge point of the two arms. The second protection structure is located at both ends of the fuselage. The linkage structure connects the first and second protection structures. The protection method includes lateral impact protection steps and front-to-rear impact protection steps. This invention achieves the transmission and conversion of impact force through the linkage structure, enabling the buffer structure to effectively buffer impacts from multiple directions.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a UAV with a wing protection structure and a protection method thereof. Background Technology

[0002] With the rapid development of drone technology, its application in fields such as agricultural and forestry plant protection, power line inspection, and logistics transportation is becoming increasingly widespread. In complex operating environments, drones inevitably collide with obstacles. Among these, the wings, as a key component, directly affect flight safety and mission execution capabilities. Therefore, how to effectively improve the protective performance of the wings has become an important issue in drone design.

[0003] Currently, drone wing protection mainly adopts a ring-shaped protective frame structure. This type of structure achieves basic protection through a rigid or semi-rigid frame surrounding the wing, which can form physical isolation in all directions. To further improve the protective effect, existing technologies have set up buffer elements at the connection between the protective frame and the wing, which absorb part of the impact energy through elastic deformation. In addition, adjustable height protective ring designs have been developed to adapt to different operating environment requirements. These technical solutions constitute the mainstream technical path in the current field of wing protection.

[0004] However, existing ring-shaped protective frame structures have significant shortcomings in protective effectiveness. Although they can achieve all-round coverage, they can only passively resist impact through the deformation of the material itself when subjected to an impact, lacking an effective energy buffering mechanism. This protection method causes the impact energy to be directly transferred to the wing connection, which can easily cause damage to the wing or the connection mechanism. In particular, when subjected to impacts of different angles and intensities, traditional protective structures are unable to achieve stable and efficient energy absorption, affecting the actual effect of wing protection. Summary of the Invention

[0005] To address the technical problems in the prior art, this invention provides a drone with a wing protection structure and a protection method thereon. The aim is to solve the problem that the wing protection structure of drones in the prior art can only passively resist impact through material deformation, lacking an efficient and controllable energy buffering and dissipation mechanism, resulting in insufficient protection effectiveness.

[0006] The technical solution of the present invention is as follows: A drone with a wing protection structure includes a drone body, a first protection structure, a buffer structure, a second protection structure, and a linkage structure, wherein... The drone body includes a body and arms; the arms include a first arm, a second arm and a wing assembly. The first arm is fixed to the side wall of the body, the second arm is hinged to the first arm via a hinge axis, and the second arm can swing around the hinge axis in the horizontal plane. The wing assembly is located at the end of the second arm away from the first arm. The first protective structure is located on the periphery of the wing assembly and is detachably connected to the second arm. The buffer structure is located at the hinge of the first arm and the second arm, and is used to stabilize the second arm during normal flight and to buffer when the second arm swings. The second protective structure is located at both ends of the fuselage; The linkage structure is connected between the first protective structure and the second protective structure. When the second protective structure is impacted, the impact force is transmitted through the linkage structure and the second arm is driven to swing horizontally, which is then buffered by the buffer structure.

[0007] Optionally, the robotic arms include two sets, which are symmetrically arranged at the front and rear ends of the machine body. Each set of robotic arms includes two arms, which are symmetrically arranged on both sides of the machine body.

[0008] Optionally, the first protective structure includes a first protective arc plate, a connecting rod, a sleeve, and a locking nut, wherein, The first protective arc plate is disposed around the periphery of the wing assembly; The connecting rods include multiple rods, the top of which are arranged in a ring array at the bottom of the first protective arc plate and are fixedly connected to it; The second arm extends to the bottom with a support leg, and the sleeve is located outside the support leg and is fixedly connected to the bottom of the plurality of connecting rods; The locking nut can be threaded onto the support leg to lock and fix the sleeve onto the support leg.

[0009] Optionally, a first keyway is formed on the inner wall of the sleeve along its axial direction, and a first flat key is provided on the outer peripheral surface of the support corresponding to the first keyway. The first keyway and the first flat key cooperate to restrict the relative rotation between the sleeve and the support.

[0010] Optionally, the buffer structure includes a mounting bracket and a damper, wherein, The mounting bracket is detachably connected to the first support arm; One end of the damper is hinged to the mounting bracket, and the other end is hinged to the second arm.

[0011] Optionally, the arm further includes a first limiting block and a second limiting block, wherein, The first limiting block is located at the hinge of the first arm; The second limiting block is located at the hinge of the second arm; When the drone is flying normally, the restoring force provided by the damper drives the second arm to rotate, so that the second limiting block keeps in contact with the first limiting block; When the second arm swings due to an impact, it overcomes the restoring force of the damper, rotates about the hinge axis away from the first limiting block, and compresses the damper.

[0012] Optionally, the second protective structure includes a connecting frame, a sliding rod, and a second protective arc plate, wherein, The connecting frame spans between the two mounting frames of the same set of arms; The slide bar is arranged along the front and rear direction of the machine body and is slidably inserted into the connecting frame; The second protective arc plate is located on the end of the slide bar away from the connecting frame.

[0013] Optionally, the second protective structure further includes a second flat key and an anti-disengagement block, wherein, The second flat key is located at the insertion point between the slide rod and the connecting frame, and the connecting frame has a second keyway corresponding to the second flat key. The anti-disengagement block is located at the end of the slide rod away from the second protective arc plate and is threadedly connected to the slide rod to prevent the slide rod from disengaging from the connecting frame.

[0014] Optionally, the linkage structure includes a sleeve block and a linkage plate, wherein, The sleeve block is slidably sleeved on the slide rod, and a limiting ring block is fixedly provided on the slide rod. The limiting ring block is located on the side of the sleeve block facing the second protective arc plate. Two linkage plates are provided, symmetrically arranged on both sides of the sleeve block. One end of each linkage plate is hinged to the sleeve block, and the other end is hinged to the edge of the corresponding first protective arc plate. When the second protective arc plate is impacted, the sliding block is driven to slide through the sliding rod and the limiting ring block, and the impact force is converted into a lateral pulling force on the first protective arc plate through the linkage plates on both sides, thereby driving the second arm to swing the compression damper.

[0015] The present invention also provides a protection method for a UAV with a wing protection structure as described above, the protection method comprising: S1: Lateral Impact Protection When the drone is impacted from the side, the impact force acts on the first protective arc plate and is transmitted to the hinge through the connecting rod and the second arm. This drives the second arm to swing around the hinge axis in the horizontal plane and compress the damper. The damping effect of the damper consumes the impact energy and achieves buffering. S2: Impact protection in both front and rear directions When the drone's head or tail is impacted, the impact force acts on the second protective arc plate, pushing the slide bar to move axially. Through the limit ring block, the sleeve block slides, causing the linkage plate to convert the axial impact force into a lateral tensile force. At the same time, it pulls the first protective arc plates on both sides towards the center, driving the second arm to swing around the hinge axis and compress the damper. The damping effect of the damper consumes the impact energy to achieve buffering.

[0016] Compared with the prior art, the UAV with wing protection structure and protection method provided by the present invention have the following beneficial effects: (1) An intelligent impact response mechanism was established through the coordinated cooperation of the horizontal swing buffer mechanism and the linkage force transmission system. When the side is impacted, the impact force directly drives the second arm swing compression damper. When the front and rear are impacted, the impact force is converted into a lateral tension on the wing protection arc plate through the linkage structure, which also drives the second arm swing compression damper. This allows the impacts from different directions to be efficiently guided to the dedicated buffer element for energy dissipation, realizing a fundamental transformation from traditional passive resistance to active guidance buffer.

[0017] (2) The design of the buffer structure maintains the arm extension attitude through the damper restoring force during normal flight, ensuring flight stability; when subjected to impact, the damper compresses and smoothly absorbs the impact energy, achieving efficient buffering. This effectively solves the inherent contradiction between rigid and flexible structures in traditional solutions, enabling the protection system to both ensure flight quality and cope with sudden impacts.

[0018] (3) Impact in the front and rear directions: Through the coordinated action of components such as sliding rod, limiting ring block, sleeve block, and linkage plate, the axial impact force is reliably converted into lateral tension, forming a complete force flow transmission path, ensuring that the impact energy can be concentrated and guided to the damper for consumption, avoiding the problems of energy dispersion and rigid bearing of the fuselage structure, and significantly improving the energy absorption efficiency.

[0019] (4) Adopting a modular design concept, the first protective structure can be quickly disassembled and assembled through sleeves and locking nuts, and the buffer structure is connected through a detachable mounting bracket, making local maintenance and replacement more convenient; at the same time, the keyway prevents relative rotation and the anti-loosening block prevents the components from loosening, ensuring that the system can maintain structural integrity and functional reliability after multiple impacts, significantly reducing maintenance costs. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of a drone with a wing protection structure according to the present invention; Figure 2 This is a top view schematic diagram of a UAV with a wing protection structure according to the present invention; Figure 3This is a schematic diagram of the first protective structure of a UAV with a wing protective structure according to the present invention, in a disassembled state. Figure 4 This is a schematic diagram showing the connection between the arm and the buffer structure of a drone with a wing protection structure according to the present invention; Figure 5 This is a schematic diagram showing the connection between the first protective structure and the second protective structure of a UAV with a wing protection structure according to the present invention; Figure 6 This is a schematic diagram of the second protective structure of a UAV with a wing protective structure according to the present invention, in a disassembled state. Figure 7 This is a schematic diagram of the linkage structure of a drone with a wing protection structure according to the present invention.

[0021] In the diagram: 1. UAV body; 11. Airframe; 12. Arm; 121. First arm; 122. Second arm; 123. Wing assembly; 124. Support leg; 125. First flat key; 126. First limiting block; 127. Second limiting block; 2. First protective structure; 21. First protective arc plate; 22. Connecting rod; 23. Sleeve; 201. First keyway; 24. Locking nut; 3. Buffer structure; 31. Mounting bracket; 32. Damper; 4. Second protective structure; 41. Connecting bracket; 42. Slide rod; 43. Second protective arc plate; 44. Second flat key; 401. Second keyway; 45. Anti-locking block; 46. Limiting ring block; 5. Linkage structure; 51. Sleeve block; 52. Linkage plate. Detailed Implementation

[0022] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0023] In the description of the embodiments of the present invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of the present invention based on the specific circumstances.

[0024] In the description of the embodiments of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", and "outer" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the embodiments of the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the embodiments of the present invention.

[0025] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0026] Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0027] The following disclosure provides numerous different embodiments or examples for implementing various structures of the invention. To simplify the disclosure, specific examples of components and arrangements are described below. These are merely examples and are not intended to limit the invention. Furthermore, reference numerals and / or letters may be repeated in different examples. Such repetition is for simplification and clarity and does not in itself indicate a relationship between the various embodiments and / or arrangements discussed. Additionally, examples of various specific processes and materials are provided in this invention; however, those skilled in the art will recognize the applicability of other processes and / or the use of other materials.

[0028] Please see Figure 1-7 The present invention provides a drone with a wing protection structure, characterized in that it includes a drone body 1, a first protection structure 2, a buffer structure 3, a second protection structure 4, and a linkage structure 5.

[0029] like Figure 1-2As shown, the UAV body 1 includes a body 11 and an arm 12; the arm 12 includes a first arm 121, a second arm 122, and a wing assembly 123. The first arm 121 is fixedly mounted on the side wall of the body 11, and the second arm 122 is hinged to the first arm 121 via a hinge axis. The second arm 122 can swing horizontally around the hinge axis. The wing assembly 123 is located at the end of the second arm 122 away from the first arm 121. A first protective structure 2 is located around the wing assembly 123 and is connected to the second arm. 122 is detachable; the buffer structure 3 is located at the hinge of the first arm 121 and the second arm 122, used to stabilize the second arm 122 during normal flight and to buffer when the second arm 122 swings; the second protective structure 4 is located at both ends of the fuselage 11; the linkage structure 5 is connected between the first protective structure 2 and the second protective structure 4, used to transmit the impact force through the linkage structure 5 and drive the second arm 122 to swing horizontally when the second protective structure 4 is impacted, and the buffer structure 3 provides buffering.

[0030] Specifically, by designing the first arm 121 and the second arm 122 as hinged, and setting up a dedicated buffer structure 3 and linkage structure 5, a complete protection system is constructed. Its innovation lies in establishing a force flow conversion mechanism: when the second protective structure 4 is impacted, the linkage structure 5 can transmit the impact force and drive the second arm 122 to swing horizontally, so that the buffer structure 3 can play its role. This achieves a fundamental transformation from traditional passive resistance to active guided buffering, solving the technical problem that traditional ring-shaped protective frames can only passively resist impacts through material deformation. In particular, the design of the second arm 122 swinging in the horizontal plane around the hinge axis, together with the buffer structure 3, not only ensures the stability during normal flight, but also provides a unified buffer path for multi-directional impacts.

[0031] In some embodiments, such as Figure 1-2 As shown, the robotic arms 12 include two sets, which are symmetrically arranged at the head and tail ends of the body 11. Each set of robotic arms 12 includes two arms, which are symmetrically arranged on both sides of the body 11.

[0032] Specifically, this embodiment forms the basis for achieving all-around protection. By symmetrically arranging two sets of arms 12 at both ends of the body 11, and using two symmetrical arm units in each set, a complete protective frame is formed. This layout allows the UAV to effectively cope with impacts from any direction through the corresponding arm units and protective structures. More importantly, this symmetrical layout provides the structural basis for the subsequent linkage structure 5, ensuring that impacts from the front and rear directions can be evenly transmitted to the protective units on both sides, avoiding the imbalance problem caused by unilateral force.

[0033] In some embodiments, such as Figure 2-3As shown, the first protective structure 2 includes a first protective arc plate 21, a connecting rod 22, a sleeve 23, and a locking nut 24. The first protective arc plate 21 is arranged around the periphery of the wing assembly 123. The connecting rod 22 includes multiple rods, the top of which is arranged in a ring array at the bottom of the first protective arc plate 21 and fixedly connected to it. The second support arm 122 extends to the bottom with a support leg 124. The sleeve 23 is located outside the support leg 124 and is fixedly connected to the bottom of the multiple connecting rods 22. The locking nut 24 can be threadedly connected to the support leg 124 to lock the sleeve 23 onto the support leg 124.

[0034] Specifically, this embodiment solves the problem of inconvenient maintenance of the protective structure through modular design; the first protective arc plate 21 is connected to the sleeve 23 through multiple connecting rods 22, forming a stable protective frame that can effectively disperse impact force; the sleeve 23 and the support leg 124 are fitted together, and the locking nut 24 is used to fasten the first protective structure 2 and the arm 12, which not only facilitates installation and maintenance, but more importantly, when the protective structure is damaged, the damaged parts can be quickly replaced, greatly reducing maintenance costs and time; the arrangement of multiple connecting rods 22 in a ring array further enhances the overall rigidity and impact resistance of the protective structure.

[0035] In some embodiments, such as Figure 3 As shown, a first keyway 201 is formed on the inner wall of the sleeve 23 along its axial direction. A first flat key 125 is provided on the outer peripheral surface of the support leg 124 corresponding to the first keyway 201. The first keyway 201 and the first flat key 125 cooperate to restrict the relative rotation between the sleeve 23 and the support leg 124.

[0036] Specifically, the anti-rotation mechanism design in this embodiment effectively solves the problem of loosening that may occur in the protective structure during long-term use; the cooperation between the first keyway 201 and the first flat key 125 ensures that there will be no relative rotation between the sleeve 23 and the support leg 124, thereby ensuring that the first protective structure 2 always remains in the correct protective position; this design is particularly important because during the flight of the UAV, the protective structure needs to withstand aerodynamic loads and vibrations from different directions. Without a reliable anti-rotation mechanism, the connection parts may gradually loosen, affecting the protective effect and even flight safety; the cooperation design of the keyway and the flat key provides a simple and effective solution.

[0037] In some embodiments, such as Figure 4 As shown, the buffer structure 3 includes a mounting frame 31 and a damper 32. The mounting frame 31 is detachably connected to the first support arm 121. One end of the damper 32 is hinged to the mounting frame 31, and the other end is hinged to the second support arm 122.

[0038] Specifically, the design of the buffer structure in this embodiment is one of the core innovations of this invention. The damper 32, with its hinged connection at both ends, can provide a stable restoring force during normal flight, maintaining the extended posture of the arm 12 and ensuring flight stability. It can also absorb impact energy through compression deformation when subjected to impact, achieving efficient buffering. More importantly, the damper 32 can provide a slow and controlled recovery process after compression deformation, avoiding secondary impact damage that may be caused by the instantaneous recovery of traditional components such as springs. The detachable design of the mounting bracket 31 facilitates the maintenance and replacement of the damper 32, while the hinged connection ensures that the damper 32 can work smoothly under various working conditions without jamming. It perfectly solves the contradiction between rigid and flexible structures in traditional solutions, achieving a unity of stability and buffering.

[0039] In some embodiments, such as Figure 4 As shown, the arm 12 also includes a first limiting block 126 and a second limiting block 127. The first limiting block 126 is located at the hinge of the first arm 121; the second limiting block 127 is located at the hinge of the second arm 122. When the UAV is flying normally, the restoring force provided by the damper 32 drives the second arm 122 to rotate, so that the second limiting block 127 and the first limiting block 126 remain in contact. When the second arm 122 is driven by an impact and swings, it overcomes the restoring force of the damper 32, rotates around the hinge axis away from the first limiting block 126, and compresses the damper 32.

[0040] Specifically, the coordinated design of the limiting mechanism and the buffer structure in this embodiment ensures reliable operation of the system under different working conditions. Under normal flight conditions, the contact between the two limiting blocks provides a clear positioning reference for the arm 12. Combined with the restoring force of the damper 32, a stable force-sealed system is formed, effectively preventing vibration and swaying during flight. Under impact conditions, the second arm 122 rotates away from the limiting blocks, ensuring that the impact energy is effectively absorbed by the damper 32 and is not directly transmitted to the fuselage through the limiting blocks. This design ensures flight accuracy while optimizing the buffering effect.

[0041] In some embodiments, such as Figure 5-7 As shown, the second protective structure 4 includes a connecting frame 41, a sliding rod 42, and a second protective arc plate 43. The connecting frame 41 is connected across the two mounting frames 31 of the same set of machine arms 12. The sliding rod 42 is arranged along the head and tail direction of the machine body 11 and is slidably inserted into the connecting frame 41. The second protective arc plate 43 is located on the end of the sliding rod 42 away from the connecting frame 41.

[0042] Specifically, this embodiment constructs a platform for receiving and transmitting impacts from the front and rear directions; the design of the connecting frame 41 spanning and connecting the two mounting frames 31 ensures that the impact force can be evenly distributed to the buffer systems on both sides; the sliding rod 42 is slidably set along the front and rear directions of the body 11, enabling it to effectively receive impacts from the front or rear of the UAV and transmit the impact force backward; the second protective arc plate 43, as the component directly subjected to impact, has an arc-shaped design that helps to disperse the impact pressure and reduce local stress concentration; the entire second protective structure 4 forms a complete force transmission path, providing a structural basis for the effective handling of impacts from the front and rear directions.

[0043] In some embodiments, such as Figure 6 As shown, the second protective structure 4 also includes a second flat key 44 and an anti-disengagement block 45. The second flat key 44 is located at the insertion point of the slide rod 42 and the connecting frame 41. The connecting frame 41 has a second keyway 401 corresponding to the second flat key 44. The anti-disengagement block 45 is located at the end of the slide rod 42 away from the second protective arc plate 43 and is threadedly connected to the slide rod 42 to restrict the slide rod 42 from disengaging from the connecting frame 41.

[0044] Specifically, this embodiment ensures the reliability of the second protective structure 4 through a double insurance mechanism; the cooperation between the second flat key 44 and the second keyway 401 prevents relative rotation between the slide rod 42 and the connecting frame 41, ensuring the accuracy of the force transmission direction; the anti-disengagement block 45 is fixed to the end of the slide rod 42 by a threaded connection, effectively preventing the slide rod 42 from coming out of the connecting frame 41 under repeated impacts; the synergistic effect of these two components ensures the stability and reliability of the second protective structure 4 in long-term use, especially in maintaining its complete function after withstanding multiple impacts.

[0045] In some embodiments, such as Figure 7 As shown, the linkage structure 5 includes a sleeve block 51 and a linkage plate 52. The sleeve block 51 is slidably sleeved on the slide rod 42, and a limiting ring block 46 is fixedly provided on the slide rod 42. The limiting ring block 46 is located on the side of the sleeve block 51 facing the second protective arc plate 43. There are two linkage plates 52, symmetrically arranged on both sides of the sleeve block 51. One end of each linkage plate 52 is hinged to the sleeve block 51, and the other end is hinged to the edge of the corresponding first protective arc plate 21. When the second protective arc plate 43 is impacted, the sleeve block 51 is driven to slide through the slide rod 42 and the limiting ring block 46, and the impact force is converted into a lateral tension force on the first protective arc plate 21 through the linkage plates 52 on both sides, thereby driving the second support arm 122 to swing the compression damper 32.

[0046] Specifically, the linkage structure in this embodiment is the key link to realize the force flow conversion. When the second protective arc plate 43 is impacted, the slide rod 42 pushes the limiting ring block 46 to move, thereby driving the sleeve block 51 to slide. The sleeve block 51 converts the axial impact force into a lateral tension force on the first protective arc plate 21 through the linkage plates 52 on both sides, and finally drives the second support arm 122 to swing the compression damper 32. This ingenious mechanism design realizes the conversion of the impact direction, so that impacts in different directions can be handled through a unified buffer path. The symmetrical arrangement of the two linkage plates 52 ensures the balance of force transmission and avoids the problem of eccentric load caused by unilateral force.

[0047] The present invention also provides a protection method for a UAV with a wing protection structure as described above, the protection method comprising: S1: Lateral impact protection. When the drone is impacted from the side, the impact force acts on the first protective arc plate and is transmitted to the hinge through the connecting rod and the second arm. This drives the second arm to swing around the hinge axis in the horizontal plane and compress the damper. The damping effect of the damper consumes the impact energy and achieves buffering.

[0048] In this step, the impact force first acts on the first protective arc plate 21, and is transmitted to the sleeve 23 through multiple connecting rods 22 arranged in a ring array. Since the sleeve 23 is fixedly connected to the support leg 124 through the cooperation of the first keyway 201 and the first flat key 125, the impact force is further transmitted to the second support arm 122. The second support arm 122 swings around the hinge axis in the horizontal plane, overcoming the restoring force of the damper 32, causing the second limiting block 127 to separate from the first limiting block 126, while compressing the damper 32. The damper 32 converts the impact kinetic energy into heat energy through the throttling effect of its internal damping medium, achieving smooth buffering. After the impact ends, the damper 32 provides a slow restoring force, causing the second support arm 122 to gradually return to its original position, avoiding secondary damage caused by instantaneous rebound.

[0049] S2: Impact protection in the front and rear directions. When the front or rear of the drone is impacted, the impact force acts on the second protective arc plate, pushing the slide bar to move axially. Through the limit ring block, the sleeve block slides, driving the linkage plate to convert the axial impact force into lateral tension. At the same time, it pulls the first protective arc plates on both sides towards the middle, driving the second arm to swing around the hinge axis and compress the damper. The damping effect of the damper consumes the impact energy to achieve buffering.

[0050] In this step, the impact force first acts on the second protective arc plate 43, pushing the slide rod 42 to move along the head-to-tail direction of the body 11; the slide rod 42 slides in the connecting frame 41 through the guidance of the second flat key 44 and the second keyway 401, ensuring the accuracy of the movement direction; the limiting ring block 46 on the slide rod 42 pushes the sleeve block 51 to slide along the slide rod 42, and the sleeve block 51 drives the linkage plates 52 on both sides to move; each linkage plate 52 converts the linear movement of the sleeve block 51 into a lateral pulling force on the edge of the first protective arc plate 21 through the hinge points at both ends, while pulling the first protective arc plates 21 on both sides towards the middle of the body 11; this action is transmitted to the second support arm 122 through the connecting rod 22 and the sleeve 23, driving the second support arm 122 to swing around the hinge axis in the horizontal plane, and the compression damper 32 achieves buffering; throughout the process, the anti-disengagement block 45 prevents the slide rod 42 from disengaging from the connecting frame 41, ensuring the reliability of the system.

[0051] It should be noted that the two protection steps above can be executed independently or in combination. When the drone is subjected to impact from multiple directions, the two protection mechanisms will be activated simultaneously, acting together on the buffer structure 3 through their respective independent force transmission paths to achieve all-round impact protection.

[0052] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A drone with a wing protection structure, characterized in that, It includes the UAV body (1), the first protective structure (2), the buffer structure (3), the second protective structure (4), and the linkage structure (5), among which, The UAV body (1) includes a body (11) and an arm (12); the arm (12) includes a first arm (121), a second arm (122) and a wing assembly (123). The first arm (121) is fixedly mounted on the side wall of the body (11). The second arm (122) is hinged to the first arm (121) via a hinge axis. The second arm (122) can swing around the hinge axis in the horizontal plane. The wing assembly (123) is located at the end of the second arm (122) away from the first arm (121). The first protective structure (2) is located on the periphery of the wing assembly (123) and is detachably connected to the second arm (122); The buffer structure (3) is located at the hinge of the first arm (121) and the second arm (122) to stabilize the second arm (122) during normal flight and to buffer when the second arm (122) swings. The second protective structure (4) is located at both ends of the body (11); The linkage structure (5) is connected between the first protective structure (2) and the second protective structure (4). When the second protective structure (4) is impacted, the linkage structure (5) transmits the impact force and drives the second arm (122) to swing horizontally, which is then buffered by the buffer structure (3).

2. The UAV with wing protection structure according to claim 1, characterized in that, The robotic arms (12) include two sets, which are symmetrically arranged at the head and tail ends of the body (11). Each set of robotic arms (12) includes two arms, which are symmetrically arranged on both sides of the body (11).

3. The UAV with wing protection structure according to claim 2, characterized in that, The first protective structure (2) includes a first protective arc plate (21), a connecting rod (22), a sleeve (23), and a locking nut (24), wherein, The first protective arc plate (21) is arranged around the periphery of the wing assembly (123); The connecting rod (22) includes multiple rods, the top of which is arranged in a ring array at the bottom of the first protective arc plate (21) and fixedly connected thereto; The second arm (122) extends to the bottom with a foot (124), and the sleeve (23) is located outside the foot (124) and is fixedly connected to the bottom of the plurality of connecting rods (22); The locking nut (24) can be threaded to the support leg (124) to lock the sleeve (23) onto the support leg (124).

4. The UAV with wing protection structure according to claim 3, characterized in that, The inner wall of the sleeve (23) is provided with a first keyway (201) along its axial direction. The outer peripheral surface of the support (124) is provided with a first flat key (125) corresponding to the first keyway (201). The first keyway (201) and the first flat key (125) cooperate to restrict the relative rotation between the sleeve (23) and the support (124).

5. A UAV with a wing protection structure according to claim 3, characterized in that, The buffer structure (3) includes a mounting bracket (31) and a damper (32), wherein, The mounting bracket (31) is detachably connected to the first support arm (121); One end of the damper (32) is hinged to the mounting bracket (31), and the other end is hinged to the second arm (122).

6. A UAV with a wing protection structure according to claim 5, characterized in that, The arm (12) further includes a first limiting block (126) and a second limiting block (127), wherein, The first limiting block (126) is located at the hinge of the first arm (121); The second limiting block (127) is located at the hinge of the second arm (122); When the drone is flying normally, the restoring force provided by the damper (32) drives the second arm (122) to rotate, so that the second limiting block (127) and the first limiting block (126) remain in contact; When the second arm (122) swings due to impact, it overcomes the restoring force of the damper (32), rotates about the hinge axis away from the first limit block (126), and compresses the damper (32).

7. A UAV with a wing protection structure according to claim 5, characterized in that, The second protective structure (4) includes a connecting frame (41), a sliding rod (42), and a second protective arc plate (43), wherein, The connecting frame (41) spans between the two mounting frames (31) of the same set of arms (12); The slide bar (42) is arranged along the head and tail direction of the machine body (11) and is slidably inserted into the connecting frame (41); The second protective arc plate (43) is located on the end of the slide rod (42) away from the connecting frame (41).

8. A UAV with a wing protection structure according to claim 7, characterized in that, The second protective structure (4) further includes a second flat key (44) and an anti-disengagement block (45), wherein, The second flat key (44) is located at the insertion point of the slide rod (42) and the connecting frame (41), and the connecting frame (41) has a second keyway (401) corresponding to the second flat key (44). The anti-disengagement block (45) is located at the end of the slide rod (42) away from the second protective arc plate (43) and is threadedly connected to the slide rod (42) to prevent the slide rod (42) from disengaging from the connecting frame (41).

9. A UAV with a wing protection structure according to claim 7, characterized in that, The linkage structure (5) includes a sleeve block (51) and a linkage plate (52), wherein, The sleeve (51) is slidably sleeved on the slide rod (42), and a limiting ring (46) is fixedly provided on the slide rod (42). The limiting ring (46) is located on the side of the sleeve (51) facing the second protective arc plate (43). Two linkage plates (52) are provided, symmetrically arranged on both sides of the sleeve block (51). One end of each linkage plate (52) is hinged to the sleeve block (51), and the other end is hinged to the edge of the corresponding first protective arc plate (21). When the second protective arc plate (43) is impacted, the sliding block (51) is driven to slide through the sliding rod (42) and the limiting ring block (46), and the impact force is converted into a lateral pulling force on the first protective arc plate (21) through the linkage plates (52) on both sides, thereby driving the second arm (122) to swing the compression damper (32).

10. A protection method for a UAV with a wing protection structure as described in any one of claims 1-9, characterized in that, The protection method includes: S1: Lateral Impact Protection When the drone is impacted from the side, the impact force acts on the first protective arc plate and is transmitted to the hinge through the connecting rod and the second arm. This drives the second arm to swing around the hinge axis in the horizontal plane and compress the damper. The damping effect of the damper consumes the impact energy and achieves buffering. S2: Impact protection in both front and rear directions When the drone's head or tail is impacted, the impact force acts on the second protective arc plate, pushing the slide bar to move axially. Through the limit ring block, the sleeve block slides, causing the linkage plate to convert the axial impact force into a lateral tensile force. At the same time, it pulls the first protective arc plates on both sides towards the center, driving the second arm to swing around the hinge axis and compress the damper. The damping effect of the damper consumes the impact energy to achieve buffering.

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