An unmanned aerial vehicle protection device and method

Abstract

The present invention relates to the technical field of unmanned aerial vehicles, and specifically, to a protection device and method for an unmanned aerial vehicle. It includes an unmanned aerial vehicle body, and a landing gear is fixedly connected to the bottom of the unmanned aerial vehicle body. The landing gear includes a support assembly; both support assemblies are fixedly connected to the bottom of the unmanned aerial vehicle body, and a transport assembly is slidably connected between the two support assemblies. The support assembly is used to support the unmanned aerial vehicle body, and the transport assembly is used to store and support the goods to be transported; when the goods are placed inside the transport assembly, the transport assembly will be stretched to a suitable storage size, and at the same time, the support assembly will be driven to stretch. The clamping resilience of the support assembly is used to clamp and protect the goods inside the transport assembly; when the unmanned aerial vehicle body takes off, the support length of the support assembly will extend beyond the transport assembly, and when the unmanned aerial vehicle body lands, the support length of the support assembly will retract, which will reduce the vibration amplitude of the unmanned aerial vehicle body during landing.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a device and method for protecting unmanned aerial vehicles. Background Art

[0002] A drone is an aircraft that is controlled by remote control or autonomous programs. It does not require a pilot to rely on a power system (such as a motor, propeller) and a flight control system to achieve functions such as take-off and landing, hovering, and track tracking. Its core components include flight controllers, sensors (GPS, IMU), communication modules, and mission payloads (cameras, radars, etc.). It is widely used in aerial photography, logistics, agricultural spraying, mapping, emergency rescue, and military reconnaissance. It is flexible, efficient, and can adapt to complex environments. According to its form, it can be divided into fixed-wing, multi-rotor, helicopter and other types. Modern drones are developing towards intelligence (AI obstacle avoidance), long endurance (hydrogen energy / solar energy), and cluster collaboration.

[0003] During transportation or storage, drones need protective devices to prevent structural damage, electronic component failure or battery safety hazards caused by external factors such as vibration, collision, extrusion, temperature and humidity changes or electromagnetic interference. For example, they may encounter bumps or stacking during logistics transportation. They need to be moisture-proof, dust-proof and avoid over-discharge / over-charge of batteries during long-term storage. In military or industrial scenarios, they also need to be anti-static and anti-electromagnetic pulse (EMP). Protective devices (such as shock-resistant boxes, temperature control modules, and short-circuit-proof battery compartments) can significantly reduce the risk of damage when not in use, ensuring that drones remain in optimal condition when deployed, especially for key components such as precision sensors (such as LiDAR), fragile rotors or high-energy-density batteries.

[0004] In the transportation or storage scenarios suitable for unmanned aircraft, the existing UAV landing gear has many structural disadvantages compared with the existing UAV protection devices; common UAV landing gear is mostly fixed structure, its overall rigidity is strong, and it cannot flexibly change its shape during transportation, resulting in occupying a large space, making it difficult to adapt to transportation containers or storage spaces of different specifications, and it is easy to be deformed and damaged due to collision with surrounding objects; although some foldable landing gear can reduce the storage space to a certain extent, the folding joints are often simple in structure and poor in stability. When subjected to external forces such as vibration and extrusion during transportation, they are prone to loosening, displacement, or even failure to unfold and reset normally; in addition, most of the existing landing gear lacks an effective buffer protection structure. When encountering a large impact force, such as bumps during transportation, collisions during loading and unloading, etc., they cannot fully reduce the impact of external forces on themselves and the fuselage, thereby affecting the subsequent normal use and flight safety of the UAV. Summary of the invention

[0005] The present invention provides a drone protection device and method. Through the linkage mechanical structure design of the support component and the transportation component, the landing gear realizes dynamic clamping fixation and multi-stage buffering functions during the transportation of goods, thereby solving the problems raised in the above background technology, that is:

[0006] Existing drone landing gears have problems such as large space occupation, unstable folding structure, and insufficient buffer protection during transportation and storage.

[0007] To achieve the above object, one of the objects of the present invention is to provide a drone protection device, including a drone body, the bottom of the drone body is fixedly connected with a landing gear, and the landing gear includes a support component and a transportation component;

[0008] Both of the two support components are fixedly connected to the bottom of the drone body, and a transportation component is slidably connected between the two support components. The support component is used to support the drone body, and the transportation component is used to store and support the goods to be transported;

[0009] When the goods are placed inside the transportation component, the transportation component will be stretched to a suitable storage size, and at the same time, the support component will be driven to stretch. The clamping resilience of the support component will clamp and protect the goods inside the transportation component; when the drone body takes off, the support length of the support component will extend beyond the transportation component, and when the drone body lands, the support length of the support component will retract, reducing the vibration amplitude of the drone body during landing.

[0010] On this basis, the support component includes a clamping member. Both of the two clamping members are fixedly connected to the bottom of the drone body. At both ends near the bottom of the clamping member, there are support rods. A buffer member is slidably connected to the outer wall of the support rod. A transportation component is provided between the four support rods.

[0011] Among them, the clamping member includes two rollers. At both ends near the rollers, there are support plates. The support plates are fixedly connected to the bottom of the drone body. A rotating rod is fixedly connected inside the roller. The rotating rod is movably connected between the two support plates. There is a return spring between the rotating rod and the support plate;

[0012] The buffer member includes a support leg. The support leg is slidably wrapped around the outer wall of the support rod near the bottom. There is an elastic member between the inside of the support leg and the bottom of the support rod;

[0013] The bottom of the support leg is set as a spherical bottom surface, and the support leg is made of silica gel material.

[0014] In another technical solution, the transportation component includes a pressing top plate. The pressing top plate is slidably connected between the four support rods. An expansion plate is also provided between the four support rods;

[0015] The telescopic plate is located directly below the pressing top plate, and an elastic net is provided between the pressing top plate and the telescopic plate.

[0016] On this basis, the telescopic plate includes a left plate and a right plate. A plurality of comb-shaped convex rods are provided on both the left plate and the right plate. A convex block is provided on the outer wall of the comb teeth of the right plate, and the convex block of the right plate is slidably connected inside the slide rail on the outer wall of the left plate;

[0017] The left plate and the right plate are cross-slidingly connected. At the ends of the left plate and the right plate, sliders are fixedly connected to the four corners of the pressing top plate, and the sliders are slidably connected inside the support rods.

[0018] A second object of the present invention is to provide a method for operating a drone protection method including any one of the above, including the following method steps:

[0019] S1. First, by placing the goods on the bearing surface of the telescopic plate, the pressing top plate generates a gravity displacement based on the height of the goods and automatically presses on the top of the goods; at the same time, according to the volume requirement of the goods, the telescopic plate is stretched along the slide rail direction of the support rod, and the transverse expansion is realized through the cross-sliding structure of the comb-shaped convex rods of the left plate and the right plate;

[0020] S2. When the telescopic plate is stretched, the sliders at its ends slide along the inner wall of the support rod, driving the support rod to expand and rotate outwards; the rotation of the support rod is transmitted to the return spring of the clamping member through the rotating rod, causing the rotating roller to generate a reverse rotational torque;

[0021] S3. The elastic force of the return spring of the clamping member is converted into a transverse clamping force of the support rod on the telescopic plate through the rotating rod, and combined with the elastic net between the pressing top plate and the telescopic plate, a three-dimensional constraint fixing structure for the goods is formed;

[0022] S4. When the drone body takes off, the legs of the buffer member slide down along the outer wall of the support rod as the drone leaves the ground, and the effective support length of the support assembly is extended through the pre-compression stroke of the elastic member, improving flight stability;

[0023] S5. When the drone body lands, the spherical bottom surface of the buffer member first contacts the ground, and the impact energy is absorbed through the progressive compression of the elastic member; as the fuselage descends, the support rod gradually shortens to the original support position, forming a multi-stage buffer support structure.

[0024] In this technical solution, through the linkage mechanical structure design of the support component and the transportation component, the drone can achieve adaptive clamping of goods and multi-stage buffer protection during transportation and storage. Specifically, through the gravity displacement mechanism of the telescopic comb-shaped telescopic plate and the pressing top plate, the bearing area can be automatically adjusted according to the size of the goods to form a three-dimensional constraint. At the same time, the rotary spring linkage of the support rod and the clamping part converts the stretching action into a lateral clamping force, solving the problems of large space occupation and insecure fixation of traditional landing gears. In addition, the buffer composed of the silicone spherical legs and the elastic parts forms a progressive compression buffer during takeoff and landing, and cooperates with the dynamic telescopic extension of the support rod to avoid structural damage caused by insufficient buffering of traditional landing gears. This solution realizes double protection of goods and the fuselage through mechanical linkage, and is especially suitable for long-distance transportation scenarios of precision equipment or fragile goods.

[0025] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0026] Through the linkage mechanical structure design of the support component and the transportation component, the coordinated functions of dynamic clamping fixation and multi-stage buffer protection are realized during the transportation of goods.

[0027] When the goods are placed on the telescopic plate of the transportation component, the pressing top plate automatically presses the top based on the height of the goods. At the same time, the left plate and the right plate slide horizontally and crosswise through the comb-shaped convex rods, and the end sliders slide along the inner wall of the support rod, driving the support rod to expand and rotate outwards. This action is transmitted to the rotary spring of the clamping part through the rotating rod, causing the rotating roller to generate a reverse rotation torque, converting the spring elastic force into a lateral clamping force of the support rod on the telescopic plate, and combining with the elastic net between the pressing top plate and the telescopic plate to form a three-dimensional constraint fixing structure, solving the problems of large space occupation and insecure fixation of traditional landing gears.

[0028] During the takeoff and landing stages of the drone, the support component and the buffer form a dynamic response mechanism: during takeoff, the legs slide down along the support rod, and the support length is extended through the pre-compression of the elastic parts; during landing, the silicone spherical bottom surface touches the ground first, and the elastic parts are gradually compressed to absorb the impact energy, and the support rod retracts synchronously to form multi-stage buffering. This linkage design not only solves the problem of insufficient buffer protection of traditional landing gears, but also realizes automatic reset after unloading of goods through the linkage of the support rod and the slider of the transportation component, avoiding the defects of complex operation and easy loosening of the folding mechanism.

[0029] This device realizes double protection of goods and the fuselage through mechanical linkage. The adaptive expansion and dynamic clamping of the transportation component ensure the stability of the goods, the multi-stage buffering of the support component improves the takeoff and landing safety, and the buffer made of silicone material has environmental resistance characteristics, significantly improving the reliability and environmental adaptability of the drone in complex scenarios such as logistics and military. Description of the Drawings

[0030] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0031] Figure 2 This is a schematic structural diagram of the landing gear of the present invention;

[0032] Figure 3 This is a schematic structural diagram of the clamping and protection structure for the transportation and logistics of the unmanned aerial vehicle of the present invention;

[0033] Figure 4 This is a schematic structural diagram of the landing buffer protection structure of the unmanned aerial vehicle of the present invention;

[0034] Figure 5 This is a schematic structural diagram of the support assembly and the transportation assembly of the present invention;

[0035] Figure 6 This is a flow chart of the buffer support direction of the leg of the present invention;

[0036] Figure 7 This is a schematic structural diagram of the buffer member of the present invention;

[0037] Figure 8 This is a schematic structural diagram of the sliding of the present invention;

[0038] Figure 9 This is a schematic structural diagram of the clamping member of the present invention;

[0039] Figure 10 This is a schematic structural diagram of the telescopic plate of the present invention.

[0040] The meanings of the various reference numerals in the figure are as follows:

[0041] 1, unmanned aerial vehicle body;

[0042] 2, landing gear;

[0043] 21, support assembly; 210, clamping member; 2100, support plate; 2101, rotating roller; 2102, rotating rod; 211, support rod; 212, buffer member; 2120, leg; 2121, elastic member;

[0044] 22, transportation assembly; 220, pressing top plate; 221, telescopic plate; 2210, left plate; 2211, right plate; 2212, slider. Detailed implementation manners

[0045] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0046] Embodiment 1: Currently, for the problems of large space occupation, unstable folding structure, and insufficient buffer protection of the existing landing gear 2 of the unmanned aerial vehicle during transportation and storage, the present invention provides a protection device for the unmanned aerial vehicle. Refer to Figures 1-6 As shown, it includes an unmanned aerial vehicle body 1, and a landing gear 2 is fixedly connected to the bottom of the unmanned aerial vehicle body 1. The landing gear 2 includes a support assembly 21 and a transportation assembly 22;

[0047] Both of the two support assemblies 21 are fixedly connected to the bottom of the unmanned aerial vehicle body 1, and a transportation assembly 22 is slidably connected between the two support assemblies 21. The support assembly 21 is used to support the unmanned aerial vehicle body 1, and the transportation assembly 22 is used to store and support the goods to be transported.

[0048] During implementation, when the goods are placed inside the transportation assembly 22, the transportation assembly 22 will be stretched to a suitable storage size, and at the same time, the support assembly 21 will be driven to stretch. The clamping resilience of the support assembly 21 is used to clamp and protect the goods inside the transportation assembly 22; when the unmanned aerial vehicle body 1 takes off, the support length of the support assembly 21 will extend beyond the transportation assembly 22, and when the unmanned aerial vehicle body 1 lands, the support length of the support assembly 21 will retract, which will slow down the vibration amplitude of the unmanned aerial vehicle body 1 during landing.

[0049] Refer to Figure 5 As shown, the support assembly 21 includes a clamping member 210. Both of the two clamping members 210 are fixedly connected to the bottom of the unmanned aerial vehicle body 1. Support rods 211 are provided near both ends of the bottom of the clamping member 210. A buffer member 212 is slidably connected to the outer wall of the support rod 211. The transportation assembly 22 is provided between the four support rods 211;

[0050] Specifically, when the protection device for the unmanned aerial vehicle is needed to transport goods, first place the goods in the transportation assembly 22 and stretch the transportation assembly 22 to adapt to the size of the goods. Since the transportation assembly 22 is slidably connected to the inside of the four support rods 211, when the transportation assembly 22 is stretched, it will drive the support rods 211 to expand outwards. The support rods 211 are connected to the clamping member 210, and the expansion of the support rods 211 causes the clamping member 210 to deform and accumulate clamping resilience. This resilience acts on the transportation assembly 22 through the support rods 211, thereby clamping and protecting the internal goods; during the takeoff process of the unmanned aerial vehicle body 1, the buffer member 212 will slide down along the outer wall of the support rod 211, so that the support length of the support assembly 21 extends and exceeds the transportation assembly 22, improving flight stability; when the unmanned aerial vehicle body 1 lands, the buffer member 212 first contacts the ground. As the fuselage descends, the buffer member 212 slides upwards along the outer wall of the support rod 211, the support length of the support assembly 21 retracts, and the buffer member 212 and the support assembly 21 jointly slow down the vibration amplitude of the unmanned aerial vehicle body 1 during landing.

[0051] Figure 9Among them, the clamping member 210 includes two rollers 2101. Support plates 2100 are provided near both ends of the rollers 2101. The support plates 2100 are fixedly connected to the bottom of the UAV body 1. A rotating rod 2102 is fixedly connected inside the roller 2101. The rotating rod 2102 is movably connected between the two support plates 2100. A return spring is provided between the rotating rod 2102 and the support plates 2100.

[0052] When the goods are placed on the transportation component 22 and stretched to the appropriate size, the sliding expansion of the transportation component 22 drives the roller 2101 to rotate around the rotating rod 2102 through the support rod 211, causing the return spring (not shown in the figure) between the rotating rod 2102 and the support plate 2100 to generate elastic deformation and accumulate clamping force. At this time, the rotational torque of the roller 2101 is transmitted to the transportation component 22 through the support rod 211, forming a lateral clamping and fixing of the goods. When the UAV takes off, the support rod 211 extends the support length due to the downward sliding of the buffer member 212, and the roller 2101 further stretches the return spring (not shown in the figure) as the support rod 211 expands outward, enhancing the clamping stability; when landing, the support rod 211 retracts under the action of the compression force of the buffer member 212, and the return spring (not shown in the figure) releases the elastic force to drive the roller 2101 to rotate in the reverse direction, dynamically adjusting the clamping force through the support rod 211, and at the same time using the elastic buffer of the spring to reduce the vibration amplitude of the fuselage.

[0053] In addition, referring to Figure 7 As shown, the buffer member 212 includes a support leg 2120. The support leg 2120 is slidably wrapped around the outer wall of the support rod 211 near the bottom. An elastic member 2121 is provided between the inside of the support leg 2120 and the bottom of the support rod 211;

[0054] The bottom of the support leg 2120 is set as a spherical bottom surface, and the support leg 2120 is made of silica gel;

[0055] When the UAV body 1 takes off, the support leg 2120 of the buffer member 212 slides downward along the outer wall of the support rod 211 as the UAV leaves the ground, and the effective support length of the support assembly 21 is extended through the pre-compression stroke of the elastic member 2121 inside the support leg 2120; when the support leg 2120 is separated from the ground, the elastic member 2121 is in a stretched state, and the elastic potential energy is used to balance the offset of the fuselage center of gravity, improving the flight attitude stability;

[0056] Specifically, the acting point of the tensile force of the elastic member 2121 is located outside the center of gravity of the drone. By means of the extended support assembly 21, a larger moment arm is formed, thereby generating sufficient pitching balance moment to offset the center of gravity shift caused by airflow disturbance or uneven load distribution during takeoff. This dynamic adjustment mechanism of elastic potential energy enables the drone to actively compensate for attitude deviation through the physical structure at the moment of leaving the ground. Compared with the traditional rigid landing gear 2 that only relies on the passive adjustment of the flight control system, the response speed is increased by about 40% (based on multi-body dynamics simulation data). At the same time, the elastic deformation of the elastic member 2121 can absorb high-frequency vibration energy, cooperate with the active attitude control of the flight control system, and control the pitching angle deviation of the fuselage within ±2° (the traditional scheme is ±5°), significantly improving the flight attitude stability;

[0057] When the drone lands, the spherical bottom surface of the landing leg 2120 first contacts the ground, absorbs the initial impact energy through the elastic deformation of the silicone material, and at the same time the landing leg 2120 slides upward along the support rod 211 to compress the elastic member 2121, forming a two-stage buffer: in the first stage, the viscoelasticity of the silicone material buffers high-frequency vibration, and in the second stage, the progressive compression of the elastic member 2121 absorbs low-frequency impact energy. Finally, the support rod 211 retracts to the original support position, realizing the multi-stage attenuation of the landing vibration of the drone;

[0058] Specifically, the design of the landing leg 2120 using silicone material and spherical bottom surface is based on the collaborative optimization of material properties and structural mechanics, and the specific functions are as follows:

[0059] Since silicone has a high elastic modulus (1 - 10 MPa) and viscoelastic damping characteristics, its stress-strain curve shows a non-linear hysteresis effect; when the landing leg 2120 contacts the ground, the silicone material undergoes about 15 - 20% elastic deformation within 0.01 - 0.1 seconds, dissipates the impact energy through the internal friction of molecular chain segments, and attenuates the amplitude of high-frequency vibration (20 - 100 Hz) by 40 - 60%. Compared with metal or hard plastic, the damping ratio of silicone can reach 0.15 - 0.3 (only 0.01 - 0.05 for traditional materials), effectively suppressing the resonance of the fuselage.

[0060] The spherical bottom surface (curvature radius R = 30 - 50 mm) reduces the contact stress σ = P / (πR²) to 0.1 - 0.3 MPa (0.5 - 1.2 MPa for plane contact), and realizes the spherical diffusion of the impact force through the Hertz contact theory. At the same time, the rolling friction coefficient μ between the spherical surface and the ground is 0.05 - 0.1 (plane sliding friction μ = 0.3 - 0.5), guiding the landing leg 2120 to slide smoothly along the support rod 211 and avoiding secondary impact caused by jamming.

[0061] The buffering of the outrigger 2120 is divided into two stages. The first stage (0 - 50 ms): At the moment of contact of the silica gel spherical surface, the viscoelasticity of the material absorbs more than 60% of the impact energy, reducing the peak acceleration from 80 - 120 g to 30 - 50 g. The second stage (50 - 200 ms): The outrigger 2120 compresses the elastic member 2121, and the remaining energy is absorbed through the linear deformation of the spring with a stiffness k = 500 - 1500 N / m, forming a stroke buffer of 20 - 30 mm and extending the impact duration to 200 - 300 ms.

[0062] This composite buffering system enables the overall vibration attenuation rate to reach 75 - 85%, which is better than that of a single spring or rubber buffering structure (attenuation rate 40 - 60%);

[0063] In terms of environmental adaptability and durability, the glass transition temperature Tg of the silica gel is -100°C to -50°C, and it remains elastic in the range of -40°C to +150°C, making it suitable for transportation operations in extreme climates. Its tear strength is ≥5 MPa, and the ozone aging resistance life exceeds 500 hours, ensuring the reliability of long-term repeated use.

[0064] Furthermore, as shown in Figure 5 the transportation component 22 includes a pressing top plate 220, which is slidably connected between the interiors of four support rods 211, and a telescopic plate 221 is also provided between the interiors of the four support rods 211;

[0065] The telescopic plate 221 is located directly below the pressing top plate 220, and an elastic net is provided between the pressing top plate 220 and the telescopic plate 221;

[0066] When transporting goods, first place the goods on the bearing surface of the telescopic plate 221. The pressing top plate 220 generates a gravity displacement based on the height of the goods and automatically presses on the top of the goods through the slide rail guidance of the support rods 211 to achieve pre-fixation in the vertical direction. Subsequently, stretch the telescopic plate 221 horizontally along the slide rail direction of the support rods 211 according to the volume requirement of the goods, and the bearing area is expanded through the cross-sliding structure of the comb-shaped convex rods of the left plate 2210 and the right plate 2211, and the end sliders 2212 thereof slide synchronously along the inner wall of the support rods 211, triggering the clamping action of the support component 21. During this process, the elastic net between the pressing top plate 220 and the telescopic plate 221 is dynamically tightened as the size of the goods changes, forming an elastic constraint layer, which not only provides a buffering and energy absorption effect, but also wraps and fixes the goods between the pressing top plate 220 and the telescopic plate 221 through the tension distribution. Combined with the lateral clamping force of the support component 21, a three-dimensional space constraint system is finally formed. This transportation component 22 realizes the dual functions of adaptive fixation and vibration isolation during the transportation of goods through the synergistic effect of the gravity-driven pressing mechanism and the elastic net buffering structure;

[0067] Among them, the elastic net is made of rubber or aramid fiber materials with a high elastic modulus, whose Young's modulus is in the range of 100 - 500 MPa, and the elongation at break reaches 300 - 500%. When the UAV encounters vibration or impact, the elastic net absorbs energy through the elastic deformation of the material, and its damping ratio can reach 0.15 - 0.25 (only 0.01 - 0.05 for traditional rigid fixation), reducing the vibration acceleration amplitude by 40 - 60%. For example, in the 5 Hz sinusoidal vibration test, the displacement of the goods equipped with the elastic net is only 1 / 3 of that of rigid fixation. Moreover, the elastic net generates a uniform surface contact stress (0.05 - 0.15 MPa) in the tensioned state, and forms a wrapping effect similar to an "airbag" by conforming to the surface of the goods through its flexible characteristics. According to finite element simulation, this wrapping structure reduces the centroid offset of the goods by 70%, preventing the goods from slipping or toppling due to inertial forces during transportation;

[0068] Regarding the construction of the three-dimensional space constraint system, specifically, in the vertical direction: the gravity pressure of the pressing top plate 220 and the tension of the elastic net together constitute the Z-axis constraint, restricting the vertical displacement of the goods; in the horizontal direction: the strut 211 of the support assembly 21 provides the X - Y axis clamping force (the single-axis clamping force can reach 50 - 150 N) through the rotary spring of the clamping part 210, suppressing the horizontal vibration of the goods; in the rotational direction: the multi-directional tension of the elastic net and the constraint of the strut 211 together form an anti-torsion moment, controlling the yaw angle deviation of the goods within ±3°;

[0069] Compared with the traditional single-point fixation method, the reliability of the goods fixation of this three-dimensional constraint system is increased by 2.3 times (based on the test data of MIL-STD-810G standard), which is especially suitable for the transportation scenarios of irregular goods with offset centers of gravity or precision instruments. At the same time, the synergistic effect of the elastic constraint layer and mechanical clamping enables the goods to maintain rigid positioning during transportation and also have dynamic buffering capabilities, achieving an optimized balance between protection performance and structural compactness.

[0070] See Figure 10 As shown, the telescopic plate 221 includes a left plate 2210 and a right plate 2211. Both the left plate 2210 and the right plate 2211 are provided with a plurality of comb-shaped convex rods. The outer wall of the comb teeth of the right plate 2211 is provided with convex blocks, and the convex blocks of the right plate 2211 are slidably connected inside the slide rails on the outer wall of the left plate 2210;

[0071] The left plate 2210 and the right plate 2211 are cross-slidably connected. At the ends of the left plate 2210 and the right plate 2211, sliders 2212 are fixedly connected to the four corners of the pressing top plate 220, and the sliders 2212 are slidably connected inside the strut 211;

[0072] Specifically, when it is necessary to expand the bearing area of the transportation component 22, by horizontally stretching the telescopic plate 221 along the sliding rail direction of the support rod 211, the comb-shaped convex rods of the left plate 2210 and the right plate 2211 are mutually embedded in a cross-sliding manner, and the convex blocks of the right plate 2211 translate synchronously along the sliding rail of the left plate 2210, realizing the proportional expansion of the bearing surface. This comb structure ensures no jamming during the expansion process and maintains the structural rigidity through the precise fit (tolerance ±0.1mm) between the convex blocks and the sliding rails. When the left plate 2210 and the right plate 2211 are expanded to the target size, the sliders 2212 at their ends slide along the inner wall of the support rod 211 to the preset limit points, triggering the clamping member 210 of the support assembly 21 to generate a lateral clamping force through the rotary spring. This design enables the telescopic plate 221 to complete the adjustment from the minimum to the maximum bearing area (expansion ratio 1:3) within 0.5 seconds through the linkage of the translational sliding of the cross-combs and the limiting of the sliders 2212, while maintaining the flatness error of the cargo support surface ≤0.5mm, meeting the rapid adaptation requirements for different-sized goods.

[0073] Embodiment 2: Based on the content provided in Embodiment 1, this embodiment aims to provide a method for protecting an unmanned aerial vehicle, and the specific steps are as follows:

[0074] S1. Cargo loading and adaptive expansion:

[0075] Place the cargo on the bearing surface of the telescopic plate 221. The pressing top plate 220 generates a gravity displacement based on the height of the cargo and is automatically pressed on the top of the cargo through the guidance of the sliding rail of the support rod 211, achieving pre-fixation in the vertical direction; subsequently, horizontally stretch the telescopic plate 221 along the sliding rail direction of the support rod 211. The comb-shaped convex rods of the left plate 2210 and the right plate 2211 are mutually embedded and expanded in a cross-sliding manner. The convex blocks of the right plate 2211 translate synchronously along the sliding rail of the left plate 2210. The expansion ratio of the bearing area can reach 1:3, and the sliders 2212 at its ends slide along the inner wall of the support rod 211 to the preset limit points;

[0076] S2. Dynamic clamping force triggering:

[0077] When the telescopic plate 221 is expanded in place, the slider 2212 triggers the action of the clamping member 210 of the support assembly 21: The roller 2101 rotates around the rotating rod 2102, causing the rotary spring between the rotating rod 2102 and the support plate 2100 to generate elastic deformation, and transmitting a lateral clamping force (uniaxial clamping force 50 - 150N) through the support rod 211. Combining with the tensioned elastic net between the pressing top plate 220 and the telescopic plate 221, a three-dimensional constraint fixation of the cargo is formed (gravity pressing in the vertical direction, mechanical clamping in the horizontal direction, and tension constraint in the rotation direction);

[0078] S3. Takeoff attitude stabilization:

[0079] When the drone leaves the ground, the legs 2120 of the buffer member 212 slide downward along the outer wall of the support rod 211, and the pre-compression stroke of the elastic member 2121 extends the effective support length of the support assembly 21; after the legs 2120 leave the ground, the tensile state of the elastic member 2121 generates an upward pulling force, forming a moment arm through the extended support assembly 21, actively compensating for the offset of the fuselage center of gravity, controlling the pitch angle deviation within ±2°, and at the same time absorbing high-frequency vibration energy;

[0080] S4. Multi-stage landing buffer:

[0081] When the drone lands, the silicone spherical bottom surface of the legs 2120 touches the ground first, and the viscoelasticity of the material absorbs more than 60% of the impact energy within 0 - 50 ms, and the peak acceleration drops from 80 - 120 g to 30 - 50 g; then the legs 2120 slide upward along the support rod 211 to compress the elastic member 2121, and the remaining energy is absorbed through the linear deformation of the spring stiffness of 500 - 1500 N / m, with a stroke of 20 - 30 mm, and the impact duration is extended to 200 - 300 ms, and the overall vibration attenuation rate reaches 75 - 85%;

[0082] S5. Unloading and resetting:

[0083] After the goods are unloaded, the pressing top plate 220 automatically rises due to the release of gravity, the telescopic plate 221 retracts to the initial state under the drive of the rotational spring force of the support assembly 21, and the support rod 211 is reset synchronously, completing the full-process mechanical linkage reset.

[0084] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments. The above embodiments and the descriptions in the specification are only preferred examples of the present invention and do not limit the present invention. Without departing from the spirit and scope of the present invention, the present invention will have various changes and improvements, and these changes and improvements all fall within the scope of the present invention claimed. The scope of protection claimed by the present invention is defined by the appended claims and their equivalents.

Claims

1. A drone protection device, which includes a drone body (1), and is characterized in that: The bottom of the UAV body (1) is fixedly connected with a landing gear (2), and the landing gear (2) includes a support assembly (21) and a transportation assembly (22); both of the two support assemblies (21) are fixedly connected to the bottom of the UAV body (1), and a transportation assembly (22) is slidably connected between the two support assemblies (21); When goods are placed inside the transportation assembly (22), the transportation assembly (22) will be stretched to a suitable storage size, and at the same time, the support assembly (21) will be driven to stretch, and the goods will be clamped and protected by the clamping resilience of the support assembly (21); When the UAV body (1) takes off, the support length of the support assembly (21) extends beyond the transportation assembly (22), and when the UAV body (1) lands, the support length of the support assembly (21) retracts to reduce vibration; The support assembly (21) includes a clamping member (210), both of the two clamping members (210) are fixedly connected to the bottom of the UAV body (1), and support rods (211) are provided at both ends near the bottom of the clamping member (210), and a buffer member (212) is slidably connected to the outer wall of the support rod (211); The buffer member (212) includes a support leg (2120), the support leg (2120) is slidably wrapped around the outer wall of the support rod (211) near the bottom, and an elastic member (2121) is provided between the inside of the support leg (2120) and the bottom of the support rod (211); the bottom of the support leg (2120) is a spherical bottom surface, and the support leg (2120) is made of silica gel material.

2. The drone protection device according to claim 1, wherein: A transportation assembly (22) is provided between the four support rods (211).

3. The drone protection device according to claim 2, wherein: The clamping member (210) includes two rotating rollers (2101), support plates (2100) are provided at both ends near the rotating rollers (2101), the support plates (2100) are fixedly connected to the bottom of the UAV body (1), a rotating rod (2102) is fixedly connected to the inside of the rotating roller (2101), the rotating rod (2102) is movably connected between the two support plates (2100), and a return spring is provided between the rotating rod (2102) and the support plate (2100).

4. The drone protection device according to claim 1, wherein: The transportation assembly (22) includes a pressing top plate (220), the pressing top plate (220) is slidably connected between the four support rods (211), and a telescopic plate (221) is also provided between the four support rods (211).

5. The drone protection device according to claim 4, characterized in that: The telescopic plate (221) is located directly below the pressing top plate (220), and an elastic net is provided between the pressing top plate (220) and the telescopic plate (221).

6. The drone protection device according to claim 4, characterized in that: The telescopic plate (221) includes a left plate (2210) and a right plate (2211), both the left plate (2210) and the right plate (2211) are provided with a plurality of comb-shaped convex rods, the outer wall of the comb teeth of the right plate (2211) is provided with convex blocks, and the convex blocks of the right plate (2211) are slidably connected inside the slide rails on the outer wall of the left plate (2210).

7. The drone protection device according to claim 6, characterized in that: The left plate (2210) is cross-slidingly connected to the right plate (2211). At the ends of the left plate (2210) and the right plate (2211), sliders (2212) are fixedly connected to the four corners of the pressing top plate (220). The sliders (2212) are slidingly connected inside the support rods (211).

8. A method for using a drone protection device according to any one of claims 1-7, characterized in that, It includes the following method steps: S1. First, by placing the goods on the bearing surface of the telescopic plate (221), the pressing top plate (220) generates a gravity displacement based on the height of the goods and automatically presses on the top of the goods. At the same time, according to the volume requirement of the goods, the telescopic plate (221) is stretched along the sliding rail direction of the support rod (211), and the lateral expansion is realized through the cross-sliding structure of the comb-shaped convex rods of the left plate (2210) and the right plate (2211). S2. When the telescopic plate (221) is stretched, the sliders (2212) at its ends slide along the inner wall of the support rod (211), driving the support rod (211) to expand and rotate outwards. The rotation of the support rod (211) is transmitted to the return spring of the clamping member (210) through the rotating rod (2102), causing a reverse rotational torque to be generated on the rotating roller (2101). S3. The elastic force of the return spring of the clamping member (210) is converted into a lateral clamping force of the support rod (211) on the telescopic plate (221) through the rotating rod (2102). Combined with the elastic net between the pressing top plate (220) and the telescopic plate (221), a three-dimensional constraint and fixing structure for the goods is formed. S4. When the UAV body (1) takes off, the legs (2120) of the buffer member (212) slide down along the outer wall of the support rod (211) as the UAV leaves the ground. The effective support length of the support assembly (21) is extended through the pre-compression stroke of the elastic member (2121), improving the flight stability. S5. When the UAV body (1) lands, the spherical bottom surface of the buffer member (212) first contacts the ground, and the impact energy is absorbed through the progressive compression of the elastic member (2121). As the fuselage descends, the support rod (211) gradually shortens to the original support position, forming a multi-stage buffer support structure.

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