Unmanned aerial vehicle with wing protection structure

Abstract

The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle with a wing protection structure, the unmanned aerial vehicle comprises an unmanned aerial vehicle frame and a connecting frame, the top of the unmanned aerial vehicle frame is connected with a rotating wing, the bottom of the rotating wing is provided with a storage mechanism, and the storage mechanism comprises a rotating rod, a buffer rod, a groove, a fixing groove and a fixing block. According to the unmanned aerial vehicle with the wing protection structure, the buffer rods at the bottoms of the rotating wings can be controlled to be unfolded and folded through micro motors, the buffer rods are unfolded to 90 degrees during take-off and landing, the protection range is expanded, the buffer rods are folded to 30 degrees during flight, wind resistance is reduced, fixing blocks on the surfaces of the buffer rods are matched with fixing grooves, the structure stability during storage is ensured, and the situation that the attitude of the unmanned aerial vehicle is affected by shaking during flight is avoided; the spring damper in the elastic rubber layer is filled with magnetorheological fluid, the magnitude of current is controlled through an electromagnetic coil, the damping characteristic is adjusted in real time, the magnetorheological fluid is subjected to low-viscosity flexible buffering during small impact, the viscosity is suddenly increased during large impact, rigid supporting is formed, and secondary damage is avoided.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles (UAVs), in particular to a UAV with a wing protection structure. Background Art

[0002] Drones are increasingly used in today's society, encompassing numerous fields such as aerial photography, surveying and mapping, logistics and distribution, and agricultural plant protection. However, during drone operation, wings, as critical components, are susceptible to damage from various factors. For example, during takeoff and landing, drone wings may collide with external objects due to operator errors or ground obstacles. During flight, strong winds, inclement weather, or collisions with objects such as birds can also cause wing damage. Wing damage not only affects the drone's flight performance, leading to unstable flight attitude and reduced flight efficiency, but in severe cases, can even cause the drone to crash, resulting in economic losses and safety hazards. While some drones currently on the market have some wing protection measures, they generally suffer from ineffective protection, complex structures, and excessive weight that limits the drone's flight range. Therefore, developing an efficient, reliable, and lightweight wing protection structure is crucial for improving the safety and stability of drones. Summary of the Invention

[0003] The object of the present invention is to provide a UAV with a wing protection structure to solve the problems raised in the above background technology.

[0004] To achieve the above objectives, the present invention provides the following technical solution: a drone with a wing protection structure, comprising a drone frame and a connecting frame fixedly connected to the top of the drone frame, a baffle fixedly mounted on the top of the connecting frame, and a power box mounted inside the baffle;

[0005] The top of the drone frame is connected to a rotating wing, and a storage mechanism is provided at the bottom of the rotating wing. The storage mechanism includes a rotating rod, a buffer rod, a groove, a fixing groove and a fixing block. The groove is opened on the lower surface of the rotating wing, and the fixing groove is opened on the inner wall of the groove. The rotating rod is rotatably connected to the inner wall of the groove, the buffer rod is fixedly connected to the outer surface of the rotating rod, and the fixing block is fixedly connected to the outer surface of the buffer rod.

[0006] Preferably, a micro motor is fixedly mounted on the side of the rotary wing, one end of the rotary wing is rotatably connected to the drone frame via a hinged joint, the other end of the rotary wing is fixedly connected to a mounting plate, a motor is fixedly mounted on the top of the mounting plate, the output end of the motor is connected to a blade, and a limit frame is fixedly mounted on the top of the motor.

[0007] Preferably, the output shaft of the micro motor is fixedly connected to the rotating rod, the other end of the rotating rod is connected to the inner wall of the groove through a bearing seat, the output shaft of the motor passes through the limit frame, and the length of the buffer rod is less than the length of the groove.

[0008] Preferably, the top of the drone frame is fixedly connected to a support rod, the outer surface of the support rod is fixedly connected to an elastic rubber layer, and the outer surface of the elastic rubber layer is connected to bionic scales.

[0009] Preferably, the elastic rubber layer is provided with honeycomb energy-absorbing foam inside, and microcapsules are provided inside the honeycomb energy-absorbing foam.

[0010] Preferably, a spring damper is provided inside the elastic rubber layer, an electromagnetic coil is connected to a side of the spring damper close to the power box, and magnetorheological fluid is filled inside the spring damper.

[0011] Preferably, the elastic rubber layer is made of shape memory polymer material, and a microcapsule repair agent is embedded inside. The microcapsule shell is made of heat-sensitive polymer, which breaks under the action of heat generated by the damage of the elastic rubber layer to release the repair agent.

[0012] Preferably, the power box is electrically connected to the electromagnetic coil, the micro motor and the control switch of the motor respectively, and the control panel of the power box is electrically connected to the electromagnetic coil, the micro motor and the control switch of the motor through a PLC program.

[0013] Compared with the prior art, the present invention has the following beneficial effects:

[0014] 1. This drone features a wing protection structure. The buffer bar at the bottom of the rotor wing can be unfolded and folded by a micro-motor. During takeoff and landing, it unfolds to 90 degrees to expand the protection range and resist ground collisions. During flight, it folds to 30 degrees to reduce wind resistance, balancing protection and energy consumption. The fixing blocks on the surface of the buffer bar cooperate with the fixing grooves to ensure structural stability when stored, preventing shaking during flight that may affect the drone's posture.

[0015] 2. This drone with a wing protection structure has an elastic rubber layer on the outside of the support rod made of shape-memory polymer material, and is embedded with honeycomb energy-absorbing foam and microcapsule repair agents. In the event of a collision, the bionic scales first open to disperse the impact force, and the elastic rubber layer absorbs energy through deformation. The honeycomb structure further dissipates residual impact through plastic deformation. The bionic scales adhere to the surface during flight to reduce wind resistance, and open in the event of a collision to increase the contact area, avoid local stress concentration, and improve protection efficiency.

[0016] 3. This drone with a wing protection structure has a spring damper within the elastic rubber layer filled with magnetorheological fluid. The current is controlled by an electromagnetic coil, and the damping characteristics are adjusted in real time: during small impacts, the magnetorheological fluid has a low viscosity and provides a flexible buffer. During large impacts, the viscosity increases sharply to form a rigid support, preventing secondary damage. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0018] Figure 1 This is a schematic diagram of the overall structure of the UAV of the present invention;

[0019] Figure 2 Schematic diagram of the elastic rubber layer structure of the present invention;

[0020] Figure 3 This is a schematic diagram of the disassembled structure of the UAV of the present invention;

[0021] Figure 4 This is a schematic diagram of the rotary wing structure of the present invention;

[0022] Figure 5 This is a schematic diagram of the structure of the drone of the present invention after it is folded;

[0023] Figure 6 is a cross-sectional view of the elastic rubber layer of the present invention;

[0024] Figure 7 for Figure 6 A magnified schematic diagram of the structure in the middle.

[0025] In the figure: 1. UAV frame; 2. connecting frame; 3. rotary wing; 301. hinge joint; 302. mounting plate; 303. motor; 304. limit frame; 305. blade; 306. micro motor; 307. rotating rod; 308. buffer rod; 309. groove; 310. fixing groove; 311. fixing block; 4. baffle; 5. power box; 6. support rod; 601. elastic rubber layer; 602. bionic scale; 603. honeycomb energy-absorbing foam; 604. microcapsule; 605. spring damper; 606. magnetorheological fluid; 607. electromagnetic coil. DETAILED DESCRIPTION

[0026] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. 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.

[0027] In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," "connect," "fixed," etc. should be understood broadly. For example, they may refer to fixed connection, detachable connection, or integration; mechanical connection or electrical connection; direct connection or indirect connection through an intermediate medium; internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0028] Example 1: To solve the problem that although UAVs in the prior art have certain wing protection measures, they generally have poor protection effects and complex structures. Figure 1-Figure 7 The present invention provides a technical solution: a UAV with a wing protection structure, comprising a UAV frame 1 and a connecting frame 2 fixedly connected to the top of the UAV frame 1, a baffle 4 fixedly installed on the top of the connecting frame 2, and a power box 5 installed inside the baffle 4;

[0029] The top of the drone frame 1 is connected to the rotor 3, and a storage mechanism is provided at the bottom of the rotor 3. The storage mechanism includes a rotating rod 307, a buffer rod 308, a groove 309, a fixing groove 310 and a fixing block 311. The groove 309 is opened on the lower surface of the rotor 3, and the fixing groove 310 is opened on the inner wall of the groove 309. The rotating rod 307 is rotatably connected to the inner wall of the groove 309, the buffer rod 308 is fixedly connected to the outer surface of the rotating rod 307, and the fixing block 311 is fixedly connected to the outer surface of the buffer rod 308.

[0030] A micro motor 306 is fixedly installed on the side of the rotor 3. One end of the rotor 3 is rotatably connected to the drone frame 1 through a hinge joint 301. The other end of the rotor 3 is fixedly connected to a mounting plate 302. A motor 303 is fixedly installed on the top of the mounting plate 302. The output end of the motor 303 is connected to a blade 305. A limit frame 304 is fixedly installed on the top of the motor 303. The output shaft of the micro motor 306 is fixedly connected to a rotating rod 307. The other end of the rotating rod 307 is connected to the inner wall of the groove 309 through a bearing seat. The output shaft of the motor 303 passes through the limit frame 304. The length of the buffer rod 308 is less than the length of the groove 309. The power box 5 is electrically connected to the control switches of the micro motor 306 and the motor 303 respectively. The model of the motor 303 is N5045 / 07, the model of the micro motor 306 is DS-S002M, the voltage range is 3.7-5V; the maximum torque is ≥1.1kgf·cm, and the control panel of the power box 5 is electrically connected to the control switches of the micro motor 306 and the motor 303 through the PLC program and control system.

[0031] When the UAV takes off, the motor 303 is started through the control system, and the output shaft of the motor 303 drives the blade 305 to rotate, thereby making the UAV take off. When the buffer rod 308 is retracted, the rotating rod 307 can be driven to rotate by starting the micro motor 306, and the rotating rod 307 drives the buffer rod 308 to rotate so that it is retracted into the inside of the groove 309. The fixing block 311 on the surface of the buffer rod 308 will enter the inside of the fixing groove 310, thereby further fixing the buffer rod 308.

[0032] During takeoff and landing, the control system allows the bumper bar 308 to be extended to 90°, providing maximum protection for the wings and protecting them from potential ground collisions. During flight, to reduce wind resistance and lower energy consumption, the bumper bar 308 can be folded to 30°, providing some protection for the wings while minimizing any impact on flight performance.

[0033] The top of the drone frame 1 is fixedly connected to a support rod 6, the outer surface of the support rod 6 is fixedly connected to an elastic rubber layer 601, the outer surface of the elastic rubber layer 601 is connected to a bionic scale 302, the interior of the elastic rubber layer 601 is provided with a honeycomb energy-absorbing foam 603, the interior of the honeycomb energy-absorbing foam 603 is provided with microcapsules 604, the elastic rubber layer 601 is made of shape memory polymer material, and the microcapsules 604 repair agent are embedded inside. The shell of the microcapsules 604 is made of heat-sensitive polymer, and it ruptures under the action of the heat generated by the damage of the elastic rubber layer 601, releasing the repair agent.

[0034] When the drone's wing encounters a collision, the bionic scales 602 of the elastic rubber layer 601 are the first to contact the obstacle. These scales expand at the moment of impact, increasing the contact area and initially dispersing the impact force, preventing localized excessive force. Furthermore, the elastic rubber layer 601 itself possesses a certain degree of elasticity, allowing it to absorb some of the energy through deformation, buying time for subsequent cushioning.

[0035] During the flight of the drone, the airflow acts on the bionic scales 602 on the surface of the elastic rubber layer 601, causing the scales to adhere to the surface of the elastic rubber layer 601, presenting a closed state. This closed state can effectively reduce air resistance, lower energy loss during flight, and improve the drone's endurance and flight efficiency. When the drone encounters a collision, the bionic scales 602 are impacted by external forces and will quickly open. The opened bionic scales 602 increase the contact area between the elastic rubber layer 601 and the colliding object, and can more evenly disperse the impact force, thus preventing local stress concentration from damaging the elastic rubber layer 601 and the wings, further enhancing the cushioning effect.

[0036] The bionic scales are designed in a fan-shaped structure with a radius of 10mm and a thickness of 0.5mm. This fan-shaped structure maximizes impact dispersion when open and effectively reduces wind resistance by conforming to the elastic rubber layer during flight. The scales have serrated edges with a 1mm spacing and a depth of 0.2mm. These serrations further disrupt airflow during impact, enhancing energy absorption. They also increase friction between adjacent scales when the scales are in contact, improving overall stability. The scales are connected to the elastic rubber layer via hinges, with hinge points located every 20mm on the surface. These hinges utilize titanium alloy hinges, which are both strong and lightweight. These hinges ensure flexible opening and closing under impact, while also ensuring a secure connection. The scales are staggered on the elastic rubber layer, with adjacent scales overlapping by 2mm. This ensures that they synergistically disperse impact forces during impact and form a tightly fitting surface during flight, reducing wind resistance.

[0037] Material properties: The bionic scales are made of thermoplastic polyurethane elastomer (TPU) material. TPU has excellent elasticity, wear resistance and weather resistance, and can adapt to the complex flight environment of drones. Its Shore hardness is 85A and its elastic modulus is 5-10MPa. While ensuring that the scales have good flexibility, it can provide a certain degree of rigid support during impact. The elongation at break of TPU material can reach 400%-500%. It is not easy to break when the scales are subjected to large deformation and can effectively absorb impact energy. In addition, TPU material has good self-lubricating properties, which can reduce friction loss and increase service life during the opening and closing process of the scales. By surface treating the TPU material, its bonding strength with the elastic rubber layer is increased, ensuring that the scales are always tightly combined with the elastic rubber layer during the flight and impact of the drone, and play their due functions.

[0038] As the impact force continues to transmit, spring damper 605 begins to function. When subjected to force, the spring undergoes elastic deformation, converting some of its kinetic energy into stored elastic potential energy, slowing the transmission of the impact force. Spring damper 605, in turn, generates a damping force through the flow of internal fluid, slowing the spring's rebound speed and converting the kinetic energy into heat, dissipating it and preventing secondary impacts caused by the spring's rebound. During this process, spring damper 605 provides a stable buffering force, initially attenuating the impact force.

[0039] After being weakened by spring dampers 605, the remaining impact force is transmitted to the honeycomb energy-absorbing foam 603 at the corners of the buffer bracket. When subjected to force, the honeycomb structure's walls gradually collapse and deform, absorbing a large amount of energy through plastic deformation, converting the residual impact force into the foam's internal energy. This further reduces the impact force on the wing, ensuring that the wing maintains structural integrity and normal function after a collision.

[0040] The microcapsule 604 is made of a high molecular polymer material, specifically polyurea formaldehyde. The shell material has a specific glass transition temperature (Tg) or melting point. When the temperature exceeds the threshold, the shell will soften and expand until it ruptures. The Tg of the polyurea formaldehyde microcapsule 604 is about 60-80°C, and frictional heat can easily cause it to reach the rupture condition. The shell can maintain structural integrity during normal use and can also rupture precisely under the action of frictional heat or impact force. When the elastic rubber layer 601 rubs against an external object, mechanical energy is converted into thermal energy, and the local temperature rises rapidly. The thermal sensitive temperature of the shell of the microcapsule 604 is set in this range (60°C). The shell will soften due to heat absorption, and the internal repair agent will squeeze the shell under the action of thermal expansion, causing rupture. When the elastic rubber layer 601 is damaged, the heat generated by friction or deformation will be concentrated in the damaged area, accurately triggering the rupture of the microcapsule 604 in that area, avoiding global waste of repair agent.

[0041] When elastic rubber layer 601 is scratched or slightly damaged, the heat generated during the damage process triggers the rupture of embedded microcapsules 604. The repair agent stored in microcapsules 604 is then released, filling the cracks and performing a preliminary repair. Simultaneously, ambient temperature or artificial heating causes the shape memory polymer to reach its transition temperature, causing the polymer molecular segments to begin to move, gradually returning to their pre-set initial shape. This restores the shape and structure of elastic rubber layer 601, maintaining the integrity and protective performance of the protective layer.

[0042] By adjusting the material ratio and thickness of the microcapsule 604 shell, the temperature threshold of its rupture can be precisely controlled. In the drone protection scenario, the instantaneous high temperature generated by frictional heat is sufficient to trigger the rupture of the microcapsule 604. However, the air flow friction in daily flight is usually below 40°C and will not cause it to be falsely triggered.

[0043] The core material of the microcapsule 604 repair agent is mainly composed of epoxy resin and amine curing agent. The epoxy resin is bisphenol A epoxy resin, which has good adhesion, mechanical properties and chemical corrosion resistance, and is widely used in the field of aerospace material repair. Specifically, it is E-51 type bisphenol A epoxy resin, with an epoxy value of 0.48-0.54eq / 100g and an average molecular weight of approximately 380-450, which can meet the repair needs of the elastic rubber layer of drones. The amine curing agent uses diethylenetriamine, which has high reaction activity with epoxy resin and can be quickly cured at room temperature. The active hydrogen equivalent of diethylenetriamine is 20.6. When mixed with epoxy resin in a certain proportion, it can ensure that the repair agent quickly cures after the microcapsule 604 ruptures and repairs the damage to the elastic rubber layer 601.

[0044] When the elastic rubber layer of the drone is impacted and microcracks are generated, the crack expansion will cause the local temperature to rise, triggering the thermal sensitivity of the microcapsule 604 shell. The polyurea formaldehyde shell breaks when the temperature reaches a certain threshold (such as 60-80°C), and the epoxy resin and amine curing agent inside quickly flow to the cracks under capillary action. Due to the high reactivity of diethylenetriamine and epoxy resin, the two quickly undergo polymerization reaction at room temperature. During the reaction, the active hydrogen in the amine curing agent undergoes a ring-opening addition reaction with the epoxy group of the epoxy resin to form a three-dimensional cross-linked network structure, which firmly bonds the elastic rubber layers on both sides of the crack together, thereby repairing the microcracks and restoring the mechanical properties and protective functions of the elastic rubber layer 601.

[0045] Example 2: On the basis of Example 1, in order to further enhance the protective effect of the drone, a spring damper 605 is arranged inside the elastic rubber layer 601. The model of the spring damper 605 is SHM-9-4500. The spring damper 605 is connected to an electromagnetic coil 607 on the side close to the power box 5. The interior of the spring damper 605 is filled with magnetorheological fluid 606. The power box 5 is electrically connected to the control switch of the electromagnetic coil 607, and the control panel of the power box 5 is electrically connected to the control switch of the electromagnetic coil 607 through the PLC program. A pressure sensor is installed on the spring damper 605.

[0046] The pressure sensor monitors the impact force in real time and transmits the signal to the control system. When the impact force is low, the control system applies a low current to electromagnetic coil 607. The magnetorheological fluid 606 maintains a low viscosity and can flexibly deform, providing flexible support for the cushioning and gently absorbing energy. When the impact force is high, the control system increases the current in electromagnetic coil 607. The viscosity of the magnetorheological fluid 606 increases rapidly under the influence of the magnetic field, becoming almost solid and forming a rigid support to effectively resist the strong impact force. The magnetorheological fluid 606 adjusts its damping characteristics in real time based on the actual impact force, achieving dynamic optimization of cushioning performance.

[0047] The magnetorheological fluid 606 uses the model MRF-132DG. Its main parameters are as follows: the magnetic permeability is 1.002-1.005 (relative magnetic permeability) under zero magnetic field, and can reach 1.2-1.3 under saturated magnetic field, ensuring that the rheological properties can be effectively changed under different magnetic field intensities; the density is 3.0-3.2g / cm 3 , which can meet the requirements of drones for lightweight components; the zero magnetic field viscosity is 0.1-0.3Pa·s, showing Newtonian fluid characteristics, providing less damping under low impact conditions and achieving flexible buffering; under a magnetic field strength of 1000Oe (Oersted), the shear yield stress can reach 30-40kPa, which makes the magnetorheological fluid harden rapidly under high impact and provide rigid support. The response time of MRF-132DG magnetorheological fluid is short, less than 5ms, and it can respond quickly to changes in the magnetic field to meet the frequently changing impact conditions during the flight of drones.

[0048] Electromagnetic coil 607 is wound with 500 enameled copper wire with a wire diameter of 0.5 mm. The enameled copper wire has excellent electrical conductivity and insulation properties, ensuring stable operation of electromagnetic coil 607 during operation. The coil is wound into a cylindrical shape with an inner diameter of 20 mm and an outer diameter of 30 mm and tightly wound around the piston of the magnetorheological buffer device. The magnetic field strength, and thus the rheological properties of magnetorheological fluid 606, are adjusted by controlling the current input to electromagnetic coil 607. According to Ampere's circuit theorem, the magnetic field strength H generated by the coil is related to the current I and the number of turns N by the formula H = NI / L (where L is the coil length). When the input current varies within the range of 0-2 A, a magnetic field strength of 0-2000 A / m can be generated, meeting the magnetic field requirements of magnetorheological fluid 606 as it changes from low viscosity to high viscosity.

[0049] During flight, the PLC program controls the electromagnetic coil to input a low current (0.2-0.5A), generating a weak magnetic field. This keeps the viscosity of the magnetorheological fluid low, providing flexible cushioning and reducing impact on the drone's delicate internal components. If the impact acceleration exceeds a set threshold, it is considered a significant impact. The PLC program quickly controls the electromagnetic coil to input a higher current (1.5-2A), generating a strong magnetic field that rapidly hardens the magnetorheological fluid, providing rigid support and preventing serious damage to the drone's structure.

[0050] It should be noted that, in this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or elements inherent to such process, method, article, or device. In the absence of further limitations, an element defined by the phrase "comprising a..." does not exclude the presence of additional identical elements in the process, method, article, or device comprising the element.

[0051] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. A UAV with a wing protection structure, comprising an UAV frame (1) and a connecting frame (2) fixedly connected to the top of the UAV frame (1), characterized in that: A baffle (4) is fixedly mounted on the top of the connecting frame (2), and a power supply box (5) is mounted inside the baffle (4); The top of the unmanned aerial vehicle frame (1) is connected to a rotary wing (3), and a storage mechanism is provided at the bottom of the rotary wing (3). The storage mechanism comprises a rotating rod (307), a buffer rod (308), a groove (309), a fixing groove (310), and a fixing block (311). The groove (309) is provided on the lower surface of the rotary wing (3), the fixing groove (310) is provided on the inner wall of the groove (309), the rotating rod (307) is rotatably connected to the inner wall of the groove (309), the buffer rod (308) is fixedly connected to the outer surface of the rotating rod (307), and the fixing block (311) is fixedly connected to the outer surface of the buffer rod (308).

2. The UAV with a wing protection structure according to claim 1, characterized in that: A micro motor (306) is fixedly mounted on the side of the rotary wing (3); one end of the rotary wing (3) is rotatably connected to the drone frame (1) via a hinged joint (301); the other end of the rotary wing (3) is fixedly connected to a mounting plate (302); a motor (303) is fixedly mounted on the top of the mounting plate (302); an output end of the motor (303) is connected to a blade (305); and a limiting frame (304) is fixedly mounted on the top of the motor (303).

3. The UAV with a wing protection structure according to claim 2, characterized in that: The output shaft of the micro motor (306) is fixedly connected to the rotating rod (307), the other end of the rotating rod (307) is connected to the inner wall of the groove (309) through a bearing seat, the output shaft of the motor (303) passes through the limiting frame (304), and the length of the buffer rod (308) is less than the length of the groove (309).

4. The UAV with a wing protection structure according to claim 1, characterized in that: The top of the drone frame (1) is fixedly connected to a support rod (6), the outer surface of the support rod (6) is fixedly connected to an elastic rubber layer (601), and the outer surface of the elastic rubber layer (601) is connected to a bionic scale (302).

5. The UAV with a wing protection structure according to claim 4, characterized in that: The elastic rubber layer (601) is provided with a honeycomb energy-absorbing foam (603) inside, and the honeycomb energy-absorbing foam (603) is provided with microcapsules (604) inside.

6. The UAV with a wing protection structure according to claim 4, characterized in that: A spring damper (605) is provided inside the elastic rubber layer (601), and an electromagnetic coil (607) is connected to the side of the spring damper (605) close to the power box (5). The interior of the spring damper (605) is filled with magnetorheological fluid (606).

7. The UAV with a wing protection structure according to claim 4, characterized in that: The elastic rubber layer (601) is made of a shape memory polymer material, and a microcapsule (604) repair agent is embedded therein. The shell of the microcapsule (604) is made of a heat-sensitive polymer and ruptures under the action of heat generated by damage to the elastic rubber layer (601), thereby releasing the repair agent.

8. The UAV with a wing protection structure according to claim 1, characterized in that: The power box (5) is electrically connected to the electromagnetic coil (607), the micro motor (306) and the control switch of the motor (303), respectively, and the control panel of the power box (5) is electrically connected to the control switch of the electromagnetic coil (607), the micro motor (306) and the motor (303) through a PLC program.

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