Undercarriage and unmanned aerial vehicle

Abstract

The utility model provides an undercarriage and an unmanned aerial vehicle, and belongs to the technical field of undercarriages of unmanned aerial vehicles, the undercarriage is applied to the unmanned aerial vehicle and comprises an upper buffer unit and a lower buffer unit, and the upper buffer unit is used for connecting the unmanned aerial vehicle and a middle conduction unit; the lower buffering unit is arranged at the end, away from the middle conduction unit, of the upper buffering unit. Through a multi-stage buffer structure formed by the upper buffer unit, the middle conduction unit and the lower buffer unit, step-by-step absorption and dissipation of impact energy are achieved, vertical and transverse multi-directional impact caused by rugged terrains can be efficiently eliminated, the impact is prevented from being directly transmitted to kernel components of the unmanned aerial vehicle, the equipment damage risk is greatly reduced, and the service life of the unmanned aerial vehicle is prolonged. The problem that a traditional single buffer structure is difficult to deal with multidirectional impact on complex terrains is solved.

Description

Technical Field

[0001] This application belongs to the field of unmanned aerial vehicle (UAV) landing gear technology, specifically relating to a landing gear and an UAV. Background Technology

[0002] As a core load-bearing component of UAVs, the landing gear of UAVs that can adapt to various terrains plays a crucial role in supporting the airframe during takeoff and cushioning impacts during landing. Its performance directly determines the safety of UAV takeoff and landing and the reliability of missions in complex scenarios such as geological exploration and disaster relief. It is a core component for expanding the application boundaries of UAVs in various terrains.

[0003] In complex terrain operation scenarios, the impacts faced by UAVs during landing are characterized by multidirectionality and uncertainty. The core shortcomings of existing UAV landing gear lie in the design defects of the buffer system: most landing gears rely solely on a single spring or damper component for buffering, lacking a multi-component collaborative buffering mechanism. This not only fails to effectively absorb the vertical and lateral impact energy from rugged terrain, but also makes it difficult to attenuate impact vibrations through the synergistic effect of damping and elasticity. Consequently, the impact is easily transmitted directly to the core components of the airframe, causing equipment damage. At the same time, the rebound control capability of a single buffer structure is weak, often triggering secondary impacts and further exacerbating takeoff and landing risks. Utility Model Content

[0004] Therefore, the technical problem to be solved by this application is to provide a landing gear and a drone that can mitigate multi-directional impacts through a multi-level buffer structure, adapt to complex terrain, and have anti-slip and weight reduction capabilities, thereby improving take-off and landing safety and mission adaptability.

[0005] To address the aforementioned problems, this application provides a landing gear for use in unmanned aerial vehicles (UAVs), comprising:

[0006] Upper buffer unit, which is used to connect the UAV and the middle transmission unit;

[0007] The lower buffer unit is disposed at the end of the upper buffer unit opposite to the middle conduction unit.

[0008] Optionally, the upper buffer unit includes a first damping element and a first elastic element. The fixed end of the first damping element is disposed on the middle transmission unit, and the telescopic end of the first damping element is disposed on the drone. The first elastic element is sleeved on the first damping element so that both ends of the first elastic element abut against the drone and the middle transmission unit, respectively.

[0009] Optionally, the lower buffer unit includes a second elastic element, a telescopic assembly, and a strip base plate. The telescopic assembly is disposed between the strip base plate and the middle transmission unit. The telescopic assembly includes a telescopic end, and the second elastic element is sleeved on the telescopic end so that both ends of the second elastic element abut against the middle transmission unit and the fixed end of the telescopic assembly, respectively.

[0010] Optionally, the lower buffer unit further includes a support plate, a fourth elastic element, a first sliding guide mechanism, and a buffer mechanism; the first sliding guide mechanism is disposed on the strip base plate with the telescopic component as the center of symmetry; the support plate includes a first end and a second end; the first end of the support plate is hinged to the corresponding first sliding guide mechanism; the second end of the support plate is hinged to the middle transmission unit; the buffer mechanism is disposed on the telescopic component with the telescopic component as the center of symmetry; and the first ends of the two support plates are connected to the buffer mechanism.

[0011] Optionally, the first sliding guide mechanism includes a sliding groove formed on the strip base plate. The sliding groove is symmetrically arranged on both sides of the telescopic component with the telescopic component as the center of symmetry. A sliding block is provided on the sliding groove, and the sliding block slides relative to the sliding groove.

[0012] Optionally, the buffer mechanism includes a fixed rod, a side plate, and a fourth elastic element. The telescopic assembly includes a fixed end, the side plate is disposed outside the fixed end of the telescopic assembly, the fixed rod is disposed horizontally on the side plate, a sliding plate is disposed at the first end of the support plate, the two support plates are slidably sleeved on the fixed rod through the sliding plate, and the fourth elastic element is sleeved on the fixed rod between the side plate and the sliding plate.

[0013] Optionally, the lower buffer unit further includes a second damping element and a third elastic element. The fixed end of the second damping element is hinged to the strip base plate, and the telescopic end of the second damping element is hinged to the support plate. The third elastic element is sleeved on the telescopic end of the second damping element so that both ends of the third elastic element abut against the support plate and the fixed end of the second damping element, respectively.

[0014] Optionally, the landing gear further includes a second sliding guide assembly, which includes a guide rod and a positioning plate. The central transmission unit includes a lifting plate with a guide hole. The guide rod is disposed in the guide hole so that the central transmission unit moves vertically relative to the guide rod. The end of the guide rod is connected to the positioning plate.

[0015] The second aspect of this application provides a drone, including a visual perception module, a drone body, and a landing gear as described in any one of the above, wherein the landing gear is disposed at the bottom of the drone body, and the visual perception module is disposed on the side wall of the drone body.

[0016] Optionally, the visual perception module includes a fixed plate, a rotating shaft, and an image acquisition module mounting plate. Two fixed plates are symmetrically arranged on the UAV body, and the rotating shaft is arranged between the two fixed plates. The image acquisition module mounting plate is arranged on the rotating shaft, and an image acquisition module is arranged on the image acquisition module mounting plate so that the image acquisition module rotates relative to the UAV body.

[0017] By employing the above technical solution, this utility model application has at least the following beneficial effects:

[0018] This application provides a landing gear and a drone. Through a multi-level buffer structure consisting of an upper buffer unit, a middle transmission unit, and a lower buffer unit, it achieves the gradual absorption and dissipation of impact energy. This effectively mitigates vertical and lateral impacts from rugged terrain, preventing direct transmission of impacts to the drone's core components and significantly reducing the risk of equipment damage. It solves the problem that traditional single-level buffer structures struggle to cope with multi-directional impacts from complex terrain. Simultaneously, the multi-level buffer structure distributes uneven forces during landing, allowing the landing gear to adapt to differences in terrain forces and preventing excessive localized stress that could lead to rollover.

[0019] This invention reduces the overall weight of the landing gear without compromising structural strength by setting up a load-reducing through hole on the fixed inclined plate. The square groove in the lifting plate also reduces the load, and the reinforcing frame enhances the structural strength of the lifting plate. In addition, the drive shaft rotates, and the fixed block drives the image acquisition module mounting plate to adjust the angle, so that the image acquisition module can adapt to different shooting needs and improve the mission adaptability of the UAV. Attached Figure Description

[0020] Figure 1 This is a three-dimensional schematic diagram of the landing gear structure according to an embodiment of this application;

[0021] Figure 2 This is a top view of the landing gear structure according to an embodiment of this application;

[0022] Figure 3 This is a bottom view of the landing gear structure according to an embodiment of this application;

[0023] Figure 4 This is a schematic diagram of the drone body, upper buffer unit, and middle transmission unit according to an embodiment of this application.

[0024] Figure 5This is a schematic diagram of the lower buffer unit structure according to an embodiment of this application;

[0025] Figure 6 This is a cross-sectional view of the lower buffer unit structure according to an embodiment of this application.

[0026] The reference numerals in the attached figures are as follows:

[0027] 1. UAV body; 2. Fixing plate; 3. Motor; 4. Rotating shaft; 5. Fixing block; 6. Image acquisition module mounting plate; 7. Bolt; 8. Positioning plate; 9. Guide rod; 10. Lifting plate; 11. First limiting plate; 12. First damping component; 13. First elastic component; 14. Square groove; 15. Reinforcing frame; 16. Fixing inclined plate; 17. Load-reducing through hole; 18. Rectangular frame; 19. Fixing part; 20. Strip base plate; 21. Second elastic component; 22. Sliding groove; 23. Sliding block; 24. First double-plate hinge seat; 25. Support plate; 26. Second double-plate hinge seat; 27. Rotating seat; 28. Fixing seat; 29. ​​Second damping component; 30. Third elastic component; 31. Sliding plate; 32. Side plate; 33. Fixing rod; 34. Second limiting plate; 35. Fourth elastic component; 36. Rubber pad. Detailed Implementation

[0028] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.

[0029] 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 utility model, "a plurality of" means two or more, unless otherwise explicitly specified.

[0030] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., 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; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0031] The preferred embodiments of the present invention will be described below with reference to the accompanying drawings. It should be understood that the preferred embodiments described herein are for illustration and explanation only and are not intended to limit the present invention.

[0032] See also Figures 1 to 6 As shown, according to an embodiment of this application, a landing gear is provided for use in a drone, including an upper buffer unit and a lower buffer unit. The upper buffer unit is used to connect the drone to a middle transmission unit; the lower buffer unit is disposed at the end of the upper buffer unit away from the middle transmission unit.

[0033] The landing gear uses a multi-level buffer structure consisting of an upper buffer unit, a middle transmission unit, and a lower buffer unit to achieve the gradual absorption and dissipation of impact energy. It can effectively mitigate vertical and lateral impacts from rugged terrain, prevent the impact from being directly transmitted to the core components of the UAV, significantly reduce the risk of equipment damage, and solve the problem that traditional single buffer structures cannot cope with multi-directional impacts from complex terrain.

[0034] The upper buffer unit is used to connect the drone and the middle transmission unit. As the connection hub between the drone body 1 and the middle transmission unit, one end of the upper buffer unit is fixedly connected to the bottom of the drone body 1 through a detachable connection to ensure connection strength and ease of assembly; the other end forms a relatively movable linkage with the middle transmission unit, which realizes stable force transmission and reserves an adaptation stroke for buffering action.

[0035] The middle transmission unit receives the impact load transmitted by the upper buffer unit and distributes it evenly to the lower buffer unit. It also serves as a structural support and motion guide, ensuring that both the upper and lower buffer units provide structural support and motion guidance, and ensuring the coordinated operation of the upper and lower buffer units to avoid buffer failure caused by force deviation.

[0036] The lower buffer unit is located at the end of the upper buffer unit away from the middle transmission unit. As the terminal execution unit of the multi-level buffer, the lower buffer unit transmits the residual impact energy and directly contacts the ground to provide support, adapting to the landing requirements of complex terrain.

[0037] The central transmission unit includes a lifting plate 10, a fixed inclined plate 16, and a rectangular frame 18. The size of the rectangular frame 18 is larger than that of the lifting plate 10. The rectangular frame 18 and the lifting plate 10 are connected by multiple fixed inclined plates 16.

[0038] Specifically, at least two fixed inclined plates 16 are provided on the same side of both the rectangular frame 18 and the lifting plate 10.

[0039] More specifically, while ensuring the strength of the central transmission unit, the fixed inclined plate 16 is provided with several load-reducing through holes 17; the lifting plate 10 is provided with a square groove 14 in the middle, and a reinforcing frame 15 is provided on the square groove 14; to reduce the weight of the central transmission unit.

[0040] In another embodiment, the upper buffer unit includes a first damping member 12 and a first elastic member 13. The fixed end of the first damping member 12 is disposed on the middle transmission unit, and the telescopic end of the first damping member 12 is disposed on the drone. The first elastic member 13 is sleeved on the first damping member 12 so that the two ends of the first elastic member 13 abut against the drone and the middle transmission unit respectively.

[0041] The first damping element 12 is fixed at its fixed end on the middle transmission unit, and is fixed on the middle transmission unit in a ring array to ensure balanced force. The telescopic end of the first damping element 12 is set on the drone, and is fixed at the bottom of the drone.

[0042] The first elastic element 13 is sleeved on the first damping element 12, so that the two ends of the first elastic element 13 abut against the drone and the central transmission unit respectively; the inner diameter of the first elastic element 13 is adapted to the outer diameter of the fixed end of the first damping element 12, and is coaxially sleeved on the first damping element 12.

[0043] Specifically, the length of the first elastic element 13 is slightly greater than the free state length of the first damping element 12. The two ends of the first elastic element 13 are respectively abutted against the bottom of the drone and the top of the middle transmission unit to ensure that the first elastic element 13 only undergoes elastic deformation along the axial direction, avoiding twisting or displacement during the buffering process.

[0044] The specific implementation process is as follows: When the UAV lands and generates an impact, the impact force is transmitted through the body to the top of the first elastic element 13. The first elastic element 13 first undergoes axial compression deformation, quickly absorbing the initial impact energy and achieving the first stage of energy buffering. Simultaneously, the telescopic end of the first damping element 12 contracts downward with the impact load, attenuating the impact vibration through the viscous resistance of the damping medium, effectively suppressing the secondary impact generated by the rebound of the first elastic element 13. The two work together to form a composite buffering effect of elastic energy absorption and damping vibration reduction.

[0045] In another embodiment, the lower buffer unit includes a second elastic member 21, a telescopic assembly, and a strip base plate 20. The telescopic assembly is disposed between the strip base plate 20 and the middle transmission unit. The telescopic assembly includes a telescopic end, and the second elastic member 21 is sleeved on the telescopic end so that both ends of the second elastic member 21 abut against the fixed ends of the middle transmission unit and the telescopic assembly, respectively.

[0046] The strip-shaped base plate 20 is arranged symmetrically in a long strip shape, serving as the basic load-bearing component of the lower buffer unit. A rubber pad 36 is fixedly connected to the bottom of the strip-shaped base plate 20, and friction strips are evenly spaced on the rubber pad 36. The friction strips have a trapezoidal cross-section to enhance the contact friction with the ground and prevent slipping on wet or soft terrain. The top of the strip-shaped base plate 20 is a flat structure used to install the telescopic components.

[0047] Each strip-shaped base plate 20 is equipped with a telescopic component, which includes a fixed part 19 and a telescopic part. The telescopic part is at least partially disposed within the fixed part 19 and moves axially relative to the fixed part 19. The fixed part 19 is disposed on the strip-shaped base plate 20 at one end away from the telescopic part, and the telescopic part is disposed on the central transmission component at one end away from the fixed part 19. A second elastic element 21 is sleeved on the telescopic part, and its two ends abut against the central transmission component and the strip-shaped base plate 20, respectively. The second elastic element 21 undergoes elastic deformation only along the axial direction of the telescopic rod and does not produce lateral displacement or torsion. When the telescopic rod is impacted and contracts, the second elastic element 21 is simultaneously compressed, absorbing the impact energy through elastic potential energy to achieve secondary buffering.

[0048] In another embodiment, the lower buffer unit further includes a support plate 25, a fourth elastic element 35, a first sliding guide mechanism, and a buffer mechanism; the first sliding guide mechanism is arranged on the strip base plate 20 with the telescopic component as the center of symmetry, the support plate 25 includes a first end and a second end, the first end of the support plate 25 is hinged to the corresponding first sliding guide mechanism, the second end of the support plate 25 is hinged to the middle transmission unit, the buffer mechanism is arranged on the telescopic component with the telescopic component as the center of symmetry, and the first ends of the two support plates 25 are connected to the buffer mechanism.

[0049] The support plate 25 includes a first end and a second end. There are two support plates 25. The first end is hinged to the first double-plate hinge seat 24 by a pin. The first double-plate hinge seat 24 is connected to the rectangular frame 18 at one end away from the support plate 25. The second end is hinged to the second double-plate hinge seat 26 by a pin. The second double-plate hinge seat 26 is connected to the first sliding guide mechanism at one end away from the support plate 25.

[0050] The first sliding guide mechanism is set on the strip base plate 20 with the telescopic component as the center of symmetry; the buffer mechanism is set on the telescopic component with the telescopic component as the center of symmetry; the first ends of the two support plates 25 are connected to the buffer mechanism; the first sliding guide mechanism, the buffer mechanism and the telescopic component form a buffer through the synergistic effect of damping and elastic energy absorption, effectively dissipating lateral and oblique impact energy.

[0051] In another embodiment, the first sliding guide mechanism includes a sliding groove 22 formed on the strip base plate 20. The sliding groove 22 is symmetrically arranged on both sides of the telescopic component with the telescopic component as the center of symmetry. A sliding block 23 is provided on the sliding groove 22, and the sliding block 23 slides relative to the sliding groove 22.

[0052] The sliding groove 22 is symmetrically arranged on the strip base plate 20 with the telescopic component as the center of symmetry. The sliding block 23 is slidably connected to the sliding groove 22, and the end of the sliding block 23 facing away from the sliding groove 22 is connected to the first double-plate hinge seat 24. The sliding groove 22 is symmetrically arranged with the telescopic component as the center of symmetry, providing a directional sliding trajectory for the sliding block 23, ensuring that the sliding block 23 moves smoothly only along the length direction of the strip base plate 20, ensuring that the multi-level buffer structure functions in an orderly manner, and improving the stability of multi-directional impact mitigation.

[0053] In another embodiment, the buffer mechanism includes a fixed rod 33, a side plate 32, and a fourth elastic element 35. The telescopic assembly includes a fixed end, the side plate 32 is disposed outside the fixed end of the telescopic assembly, the fixed rod 33 is disposed horizontally on the side plate 32, the first end of the support plate 25 is provided with a sliding plate 31, the two support plates 25 are slidably sleeved on the fixed rod 33 through the sliding plate 31, and the fourth elastic element 35 is sleeved on the fixed rod 33 between the side plate 32 and the sliding plate 31.

[0054] The telescopic assembly includes a fixed end, namely a fixed part 19. A side plate 32 is fixedly disposed on the outside of the fixed part 19 of the telescopic assembly. A hole is provided on the side plate 32, and a fixing rod 33 is disposed in the hole and fixed relative to the hole, that is, there is no horizontal movement between the two.

[0055] The support plate 25 has a sliding plate 31 at its first end, which is also the outer side of the first double-plate hinge seat 24 of the support plate 25. The two are fixed to each other. The support plate 25 is slidably mounted on the fixed rod 33 via the sliding plate 31 mounted on the first double-plate hinge seat 24. When the support plate 25 rotates toward the strip base plate 20, the first ends of the two support plates 25 move toward the telescopic assembly. The support plates 25 disperse and transmit the force through angle changes, achieving force balance and attitude self-adaptation.

[0056] The buffer mechanism also includes a second limiting plate 34, with a second limiting plate 34 respectively provided at both ends of the fixing rod 33. The second limiting plate 34 restricts the sliding stroke of the sliding plate 31 to prevent it from detaching from the fixing rod 33. The fourth elastic element 35 is compressed when the sliding plates 31 approach each other, absorbing impact energy through elastic deformation, forming an additional buffer layer, and improving the overall buffering performance.

[0057] In another embodiment, the lower buffer unit further includes a second damping member 29 and a third elastic member 30. The fixed end of the second damping member 29 is hinged to the strip base plate 20, and the telescopic end of the second damping member 29 is hinged to the support plate 25. The third elastic member 30 is sleeved on the telescopic end of the second damping member 29 so that both ends of the third elastic member 30 abut against the support plate 25 and the fixed end of the second damping member 29, respectively.

[0058] The fixed end of the second damping member 29 is hinged to the strip base plate 20, and the telescopic end of the second damping member 29 is hinged to the support plate 25. A fixed seat 28 is provided on the strip base plate 20, and a rotating seat 27 is provided on the support plate 25. The fixed end of the second damping member 29 is hinged to the fixed seat 28 through a pin, so that the fixed end of the second damping member 29 is hinged to the strip base plate 20, and the telescopic end of the second damping member 29 is hinged to the rotating seat 27 through a pin, so that the telescopic end of the second damping member 29 is hinged to the support plate 25.

[0059] The third elastic element 30 is sleeved on the telescopic end of the second damping element 29, so that the two ends of the third elastic element 30 abut against the rotating seat 27 and the fixed end of the second damping element 29 respectively.

[0060] The third elastic element 30 is coaxially sleeved on the outside of the telescopic section of the second damping element 29, absorbing impact energy through elastic deformation. The second damping element 29 is an axial compression damper, which plays a vibration reduction role through the viscous resistance of the damping medium. While the third elastic element 30 absorbs impact energy and deforms, the telescopic end of the second damping element 29 moves synchronously with the rotating seat 27. Its damping force can quickly attenuate the vibration caused by the impact, preventing the vibration from being continuously transmitted to the UAV body 1 and protecting the core precision components from vibration damage.

[0061] When the impact load generated by the drone landing is transmitted to the support plate 25, the angle change of the support plate 25 drives the rotating seat 27 to move, thereby compressing the third elastic element 30. Its elastic potential energy can efficiently absorb the residual impact energy in the vertical, horizontal and oblique directions. Especially for the asymmetric impact caused by rugged terrain, it can compensate for the insufficient buffering of the second elastic element 21 by deformation adaptive buffering strength, forming a three-level energy dissipation path.

[0062] In another embodiment, the landing gear further includes a second sliding guide assembly, which includes a guide rod 9 and a positioning plate 8. The central transmission unit includes a lifting plate 10, on which a guide hole is provided. The guide rod 9 is disposed in the guide hole so that the central transmission unit moves vertically relative to the guide rod 9. The end of the guide rod 9 is connected to the positioning plate 8.

[0063] The lifting plate 10 is provided with guide holes, that is, the lifting plate 10 is provided with guide holes at equal intervals along the circumference. The number of guide holes is the same as the number of the first damping element 12. The guide rod 9 is provided in the corresponding guide hole so that the middle transmission unit moves vertically relative to the guide rod 9. The top end of the guide rod 9 is connected to the positioning plate 8.

[0064] The drone body 1 is detachably connected to the positioning plate 8 by bolts 7 so that the drone body 1 can be mounted on the landing gear.

[0065] The second sliding guide assembly also includes a first limiting plate 11, which is located at the end of the guide rod 9 away from the positioning plate 8 to prevent the middle transmission unit from detaching from the guide rod 9.

[0066] The guide rod 9 passes through the guide hole on the lifting plate 10, forming a vertical guide constraint structure, which limits the lifting plate 10 to moving up and down only along the axial direction of the guide rod 9, thus preventing lateral offset, tilting or twisting during the buffering process. This directional constraint ensures that the first elastic element 13 and the first damping element 12 of the upper buffer unit always undergo elastic deformation and damping expansion and contraction in the vertical direction, without generating lateral force.

[0067] The second aspect of this application provides a drone, including a visual perception module, a drone body 1, and a landing gear as described above. The landing gear is disposed at the bottom of the drone body 1, and the visual perception module is disposed on the side wall of the drone body 1.

[0068] In another embodiment, the visual perception module includes a fixed plate 2, a rotating shaft 4, and an image acquisition module mounting plate 6. The two fixed plates 2 are symmetrically arranged on the UAV body 1, and the rotating shaft 4 is arranged between the two fixed plates 2. The image acquisition module mounting plate 6 is arranged on the rotating shaft 4, and an image acquisition module is arranged on the image acquisition module mounting plate 6 so that the image acquisition module rotates relative to the UAV body 1.

[0069] The mounting plates 2 consist of two symmetrically arranged L-shaped alloy plates, vertically fixed to the side wall mounting plane of the UAV body 1 by screws. The rotating shaft 4 is rotatably mounted between the two mounting plates 2 via bearings. A fixing block 5 is provided on the image acquisition module mounting plate 6, and the fixing block 5 is fixedly mounted to the rotating shaft 4 so that the two can rotate synchronously. The image acquisition module is mounted on the side of the image acquisition module mounting plate 6 opposite to the fixing block 5. The image acquisition module will not interfere with the ground or landing gear structure, and its adjustable shooting angle can cover multiple perspectives required for UAV operations, such as horizontal, overhead, and low-angle shots. Combined with the multi-terrain adaptability of the landing gear, it can achieve accurate visual perception in complex scenarios.

[0070] Specifically, the visual perception module also includes a drive unit, which is fixedly installed on the outside of one of the fixed plates 2 via a flange. Its output shaft is fixedly connected to the rotating shaft 4 to provide power for the rotation of the rotating shaft 4.

[0071] More specifically, the driving component is motor 3. Motor 3 provides rotational power to the rotating shaft 4, which drives the image acquisition module mounting plate 6 to rotate synchronously through the fixing block 5, enabling flexible adjustment of the image acquisition module's shooting angle to adapt to different shooting scenarios and improve the drone's mission adaptability.

[0072] The first elastic element 13, the second elastic element 21, the third elastic element 30 and the fourth elastic element 35 are all springs; the first damping element 12 and the second damping element 29 are both dampers.

[0073] The specific working process of the landing gear is as follows:

[0074] First, complete the functional debugging and fixation work before the drone takes off and lands. According to the shooting angle required for the mission, start motor 3. Motor 3 drives the rotating shaft 4 to rotate. The rotating shaft 4 drives the image acquisition module mounting plate 6 to rotate synchronously through the fixing block 5 until the angle of the image acquisition module meets the shooting requirements. Then, turn off motor 3 to achieve flexible adaptation of the shooting angle.

[0075] Subsequently, the UAV body 1 is securely installed on the positioning plate 8 using bolts 7. At this time, the landing gear is in a ready-to-work state. The weight-reducing through hole 17 on the fixed inclined plate 16 and the square groove 14 of the lifting plate 10 work together to reduce weight, while the reinforcing frame 15 ensures the structural strength of the lifting plate 10.

[0076] When the drone descends and lands, the rubber pad 36 first contacts the ground. At this time, the ground generates an upward impact force, which the rubber pad 36 initially cushions with its own elasticity. At the same time, the friction structure on its surface increases the adhesion to the ground, preventing the landing gear from slipping. As the drone's own weight continues to act, the upward impact force gradually increases and is transmitted upward to the strip base plate 20, thereby triggering the multi-stage buffer structure.

[0077] First, the telescopic section of the telescopic part contracts downward relative to the fixed part 19, compressing the second elastic element 21 sleeved on its outer side, absorbing part of the impact energy through elastic deformation. Meanwhile, the second double-plate hinge seat 26 moves downward, reducing the angle between the support plate 25 and the strip base plate 20. The rotating seat 27 between adjacent support plates 25 rotates with the angle change, causing the second damping element 29 to shorten, compressing the third elastic element 30 on its outer side. The elastic force of the third elastic element 30 and the damping force of the second damping element 29 form a buffer, further mitigating the multi-directional impact force. During this process, the first double-plate hinge seat 24 drives the two sliding plates 31 to move closer to each other along the fixed rod 33, squeezing the fourth elastic element 35. The elastic deformation of the fourth elastic element 35 forms a third-level buffer, dissipating some energy. Meanwhile, the UAV body 1 drives the guide rod 9 to slide downward relative to the lifting plate 10 through the positioning plate 8, so that the UAV body 1 will exert a downward force on the first damping element 12 and the first elastic element 13. The first elastic element 13 is compressed to absorb energy through elastic deformation, while the first damping element 12 attenuates the vibration generated by the impact through damping, preventing the spring rebound from causing a secondary impact.

[0078] After the impact energy is fully released, the compressed first elastic element 13, second elastic element 21, third elastic element 30 and fourth elastic element 35 all drive each structure back to its initial state through elastic restoring force, the telescopic part extends and resets, and the sliding block 23 and sliding plate 31 return to their initial positions, preparing for the next take-off and landing.

[0079] It will be readily understood by those skilled in the art that the aforementioned advantageous methods can be freely combined and superimposed without conflict.

[0080] The above are merely preferred embodiments of this application and are not intended to limit this application. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this application should be included within the protection scope of this application. The above are merely preferred embodiments of this application. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of this application, and these improvements and modifications should also be considered within the protection scope of this application.

Claims

1. A landing gear, characterized in that, The application is applied to a UAV, comprising: an upper buffering unit for connecting the UAV and a middle conducting unit; a lower buffering unit arranged at one end of the upper buffering unit away from the middle conducting unit.

2. A landing gear according to claim 1, characterised in that The upper buffering unit comprises a first damping member (12) and a first elastic member (13), the fixed end of the first damping member (12) is arranged on the middle conducting unit, the telescopic end of the first damping member (12) is arranged on the UAV, and the first elastic member (13) is sleeved on the first damping member (12) so that the two ends of the first elastic member (13) are respectively arranged against the UAV and the middle conducting unit.

3. A landing gear according to claim 1, wherein, The lower buffering unit comprises a second elastic member (21), a telescopic assembly and a strip-shaped bottom plate (20), the telescopic assembly is arranged between the strip-shaped bottom plate (20) and the middle conducting unit, the telescopic assembly comprises a telescopic end, and the second elastic member (21) is sleeved on the telescopic end so that the two ends of the second elastic member (21) are respectively arranged against the middle conducting unit and the fixed end of the telescopic assembly.

4. A landing gear according to claim 3, characterised in that The lower buffering unit further comprises a support plate (25), a fourth elastic member (35), a first sliding guide mechanism and a buffering mechanism, the first sliding guide mechanism is arranged on the strip-shaped bottom plate (20) with the telescopic assembly as the center of symmetry, the support plate (25) comprises a first end and a second end, the first end of the support plate (25) is hinged to the corresponding first sliding guide mechanism, the second end of the support plate (25) is hinged to the middle conducting unit, the buffering mechanism is arranged on the telescopic assembly with the telescopic assembly as the center of symmetry, and the first ends of the two support plates (25) are connected to the buffering mechanism.

5. A landing gear according to claim 4, characterised in that The first sliding guide mechanism comprises a sliding groove (22) formed in the strip-shaped bottom plate (20), the sliding groove (22) is symmetrically arranged on both sides of the telescopic assembly with the telescopic assembly as the center of symmetry, a sliding block (23) is arranged on the sliding groove (22), and the sliding block (23) slides relative to the sliding groove (22).

6. A landing gear according to claim 4, wherein, The buffering mechanism comprises a fixed rod (33), a side plate (32) and a fourth elastic member (35), the telescopic assembly comprises a fixed end, the side plate (32) is arranged outside the fixed end of the telescopic assembly, the fixed rod (33) is arranged on the side plate (32) in the horizontal direction, the first end of the support plate (25) is provided with a sliding plate (31), the two support plates (25) are sleeved on the fixed rod (33) through the sliding plate (31), and the fourth elastic member (35) is sleeved on the fixed rod (33) between the side plate (32) and the sliding plate (31).

7. A landing gear according to claim 4, wherein, The lower buffering unit further comprises a second damping member (29) and a third elastic member (30), a fixed end of the second damping member (29) is hinged to the strip-shaped bottom plate (20), an extension end of the second damping member (29) is hinged to the support plate (25), and the third elastic member (30) is sleeved on the extension end of the second damping member (29) so that both ends of the third elastic member (30) are respectively abutted against the support plate (25) and the fixed end of the second damping member (29).

8. A landing gear according to claim 1, wherein, The landing gear further comprises a second sliding guide assembly, the second sliding guide assembly comprises a guide rod (9) and a positioning plate (8), the middle transmission unit comprises a lifting plate (10), the lifting plate (10) is provided with a guide hole, the guide rod (9) is arranged in the guide hole so that the middle transmission unit moves vertically relative to the guide rod (9), and an end of the guide rod (9) is connected to the positioning plate (8).

9. A drone, characterized in that, The visual perception module, the unmanned aerial vehicle body (1) and the landing gear as claimed in any one of claims 1 to 8 are comprised, the landing gear is arranged at the bottom of the unmanned aerial vehicle body (1), and the visual perception module is arranged on the side wall of the unmanned aerial vehicle body (1).

10. The unmanned aerial vehicle of claim 9, wherein, The visual perception module comprises a fixed plate (2), a rotating shaft (4) and an image acquisition module mounting plate (6), two fixed plates (2) are symmetrically arranged on the unmanned aerial vehicle body (1), the rotating shaft (4) is arranged between the two fixed plates (2), the image acquisition module mounting plate (6) is arranged on the rotating shaft (4), and the image acquisition module mounting plate (6) is provided with an image acquisition module so that the image acquisition module rotates relative to the unmanned aerial vehicle body (1).

Images