Unmanned aerial vehicle undercarriage

Abstract

The invention relates to the technical field of unmanned aerial vehicles, and discloses an unmanned aerial vehicle undercarriage which comprises a vehicle body, an unfolding driving assembly and at least two supporting rods, the vehicle body is used for installing an unmanned aerial vehicle, the first ends of the supporting rods are hinged to the bottom of the vehicle body, and the at least two supporting rods are symmetrically arranged with the vehicle body as the center; the periphery between the two ends of each supporting rod is sleeved with a damping sleeve, the unfolding driving assembly is installed on the machine body, and the unfolding driving assembly is connected with the supporting rods so as to drive the at least two supporting rods to be unfolded or folded synchronously. According to the unmanned aerial vehicle undercarriage, the flight stability of an unmanned aerial vehicle can be improved, and accurate photographing is facilitated to recognize insulator defects.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a UAV landing gear. Background Technology

[0002] In the operation and maintenance of power systems, drones are frequently used to inspect the condition of insulators. Drones are typically mounted on drone landing gear, which ensures safe take-off and landing of drones in scenarios such as around power poles and on mountain slopes.

[0003] Currently, during flight, because the drone's landing gear is in the deployed state, the landing gear and the drone are easily affected by airflow disturbances, causing vibrations. This results in poor flight stability and makes it impossible to accurately photograph and identify insulator defects. Summary of the Invention

[0004] The purpose of this invention is to provide a drone landing gear that can improve the flight stability of the drone and facilitate accurate photographic identification of insulator defects.

[0005] To achieve the above objectives, the present invention provides a drone landing gear, comprising: The body, which is used to mount the drone; At least two support rods, the first end of which is hinged to the bottom of the body, the at least two support rods are symmetrically arranged about the center of the body, and a damping sleeve is fitted around the outer periphery between the two ends of each support rod; An unfolding drive assembly is installed on the body and is connected to the support rods to drive at least two of the support rods to unfold or retract synchronously.

[0006] Preferably, the two support rods are distributed sequentially along the first direction; The deployment driving component includes: A bidirectional lead screw, which extends along the first direction and is mounted on the machine body; A lead screw drive assembly is mounted on the machine body and is connected to the bidirectional lead screw to drive the bidirectional lead screw to rotate. Two sliding blocks are sequentially sleeved on the outer periphery of the bidirectional lead screw along the first direction. The two sliding blocks have through holes extending along the first direction, and two support rods arranged symmetrically with respect to the center of the machine body are respectively inserted through the two through holes.

[0007] Preferably, buffer components are respectively installed on the two inner walls of the through hole opposite each other along the second direction, and the buffer components abut against the support rod; Wherein, the first direction and the second direction intersect perpendicularly.

[0008] Preferably, the two inner walls of the through hole opposite each other along the second direction are provided with guide holes extending along the second direction; The buffer component includes: An elastic element extends along a second direction, is located within the guide hole, and has a first end connected to the bottom wall of the guide hole. A pressure post, the pressure post extending along a second direction, the first end of the pressure post being located in the guide hole and connected to the second end of the elastic element; The ball bearing is located outside the guide hole, abuts against the second end of the pressing post, and abuts against the support rod; A positioning sleeve is installed on the inner wall of the through hole. The inner diameter of the positioning sleeve gradually decreases along the direction from the inner wall of the through hole to the support rod. The positioning sleeve is sleeved on the outside of the ball. The minimum inner diameter of the positioning sleeve is smaller than the diameter of the ball.

[0009] Preferably, the lead screw drive assembly includes: The first transmission gear is sleeved on the outer periphery of the bidirectional lead screw; The second transmission gear is meshed with the first transmission gear. An electric motor, the output shaft of which is connected to the gear shaft of the second transmission gear.

[0010] Preferably, a guide seat is installed at the bottom of the machine body, the bidirectional lead screw is located inside the guide seat and its two ends are rotatably connected to the guide seat, a communicating mounting cover is installed at the bottom of the guide seat, the mounting cover is located between two support rods symmetrically arranged with respect to the center of the machine body, the first ends of the two support rods are hinged to the mounting cover, and the second transmission gear and the motor are installed inside the mounting cover.

[0011] Preferably, a support member is installed at the second end of the support rod, and a receiving cavity is formed inside the support member. A sensor integrated module is installed inside the receiving cavity. The sensor integrated module includes a distance sensor and an angle sensor connected together. Both the distance sensor and the angle sensor are electrically connected to a controller, and the controller is electrically connected to the unfolding drive assembly.

[0012] Preferably, the support member is equipped with auxiliary wheels on both sides along the third direction, the auxiliary wheels extend along the third direction, the bottom surface of the auxiliary wheels is flush with the bottom surface of the support member, and the outer wall surface of the auxiliary wheels is provided with a plurality of grooves evenly distributed along its outer periphery, the grooves extending along the third direction; Wherein, the first direction and the third direction intersect perpendicularly.

[0013] Preferably, the outer wall of the damping sleeve is provided with a plurality of annular protrusions, the annular protrusions are arranged along the outer periphery of the damping sleeve, and the plurality of annular protrusions are distributed sequentially at intervals along the axial direction of the damping sleeve.

[0014] Preferably, the inner wall of the damping sleeve is provided with anti-slip texture.

[0015] Compared with the prior art, the landing gear for unmanned aerial vehicles (UAVs) according to an embodiment of the present invention has the following advantages: The drone is mounted on the body, with at least two support rods symmetrically arranged around the center of the body. Activating the deployment drive assembly drives at least two support rods to deploy or retract synchronously, so that the first end of the support rod rotates along the hinge axis, which can adjust the tilt angle of the support rod.

[0016] During flight, the support rod of the UAV landing gear is disturbed by airflow. Since the support rod is a cantilever beam, resonance will occur when the natural frequency of the cantilever beam matches the airflow frequency. Moreover, the resonance energy is concentrated between the two ends of the support rod. Therefore, this application provides a damping sleeve on the outer periphery between the two ends of the support rod, which can effectively absorb the resonance energy, reduce the vibration of the UAV landing gear, improve the flight stability of the UAV, and facilitate accurate photographing and identification of insulator defects. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the unmanned aerial vehicle landing gear according to an embodiment of the present invention; Figure 2 This is a cross-sectional schematic diagram of the unmanned aerial vehicle landing gear according to an embodiment of the present invention; Figure 3 yes Figure 2 A partially enlarged sectional view at point A in the middle; Figure 4 yes Figure 2 Enlarged section view at point B; Figure 5 This is a partially enlarged perspective view of the support member described in an embodiment of the present invention; Figure 6 This is a schematic diagram of the snap ring structure according to an embodiment of the present invention; In the diagram, 1. Body; 2. Support rod; 3. Damping sleeve; 31. Annular protrusion; 4. Deployment drive assembly; 41. Bidirectional lead screw; 42. Lead screw drive assembly; 421. First transmission gear; 422. Second transmission gear; 423. Motor; 43. Sliding block; 431. Through hole; 432. Guide hole; 433. Annular groove; 5. Buffer assembly; 51. Elastic element; 52. Pressing column; 53. Ball bearing; 54. Positioning sleeve; 6. Guide seat; 7. Mounting cover; 8. Support element; 81. Receiving cavity; 9. Sensor integrated module; 91. Housing; 10. Auxiliary wheel; 101. Groove; 11. Limiting element; 12. Blocking element; 13. Snap ring; 131. First abutment part; 132. Connecting part; 133. Second abutment part; 134. First bending part; 135. Second bending part; 136. Third bending part. Detailed Implementation

[0018] The specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples. The following examples are for illustrative purposes only and are not intended to limit the scope of the invention.

[0019] In the description of this invention, it should be understood that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" 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 the embodiments of this invention based on the specific circumstances.

[0020] In the description of this invention, it should be understood that the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Furthermore, the terms "upper," "lower," "left," "right," "front," "rear," "top," "bottom," "inner," "outer," "middle," "vertical," "horizontal," "lateral," "longitudinal," "X-axis direction," "Y-axis direction," and "Z-axis direction," etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as limiting the invention. Moreover, some of the above terms, in addition to indicating orientations or positional relationships, may also be used to indicate other meanings; for example, the term "upper" may in some cases be used to indicate a certain dependency or connection relationship. Those skilled in the art can understand the specific meaning of these terms in this application according to the specific circumstances.

[0021] like Figure 1-2 As shown, an embodiment of the present invention provides a drone landing gear, which includes a body 1, a deployment drive assembly 4, and at least two support rods 2. Body 1 is used to mount the drone; The first end of the support rod 2 is hinged to the bottom of the body 1. At least two support rods 2 are symmetrically arranged around the center of the body 1. A damping sleeve 3 is sleeved on the outer periphery between the two ends of each support rod 2. The unfolding drive assembly 4 is installed on the body 1. The unfolding drive assembly 4 is connected to the support rods 2 to drive at least two support rods 2 to unfold or retract synchronously.

[0022] It should be noted that when the drone is mounted on the body 1, at least two support rods 2 are symmetrically arranged around the center of the body 1. When the deployment drive assembly 4 is activated, it drives at least two support rods 2 to deploy or retract synchronously, so that the first end of the support rod 2 can rotate along the hinge axis, thereby adjusting the tilt angle of the support rod 2.

[0023] During the flight of the UAV landing gear, the support rod 2 is disturbed by the airflow. Since the support rod 2 is a cantilever beam, resonance will occur when the natural frequency of the cantilever beam matches the airflow frequency. Moreover, the resonance energy is concentrated between the two ends of the support rod 2. Therefore, this application provides a damping sleeve 3 on the outer periphery between the two ends of the support rod 2, which can effectively absorb the resonance energy, reduce the vibration of the UAV landing gear, improve the flight stability of the UAV, and facilitate accurate photographing and identification of insulator defects.

[0024] Preferably, the damping sleeve 3 is fitted onto the outer periphery of the center between the two ends of the support rod 2. When the UAV landing gear is disturbed by airflow during flight and impacted during landing, the vibration amplitude at the center between the two ends of the support rod 2 is the largest. Fitting the damping sleeve 3 at this position can maximize the suppression of vibration of the support rod 2.

[0025] like Figure 2 As shown, in this embodiment, the two support rods 2 are further distributed sequentially along the first direction X; The unfolding drive assembly 4 includes a bidirectional lead screw 41, a lead screw drive assembly 42, and two sliding blocks 43; A bidirectional lead screw 41 extends along the first direction X and is installed on the machine body 1. A lead screw drive assembly 42 is installed on the machine body 1. The lead screw drive assembly 42 is connected to the bidirectional lead screw 41 to drive the bidirectional lead screw 41 to rotate. Two sliding blocks 43 are sequentially sleeved on the outer periphery of the bidirectional lead screw 41 along the first direction X. The two sliding blocks 43 have through holes 431 extending along the first direction X. Two support rods 2 are respectively inserted through the two through holes 431 and arranged symmetrically with the center of the machine body 1.

[0026] It should be noted that the lead screw drive assembly 42 drives the bidirectional lead screw 41 to rotate. Two sliding blocks 43, which are sequentially sleeved on the outer periphery of the bidirectional lead screw 41 along the first direction X, move towards or away from each other along the bidirectional lead screw 41. Two support rods 2, which are symmetrically arranged around the center of the body 1, pass through the through holes 431 opened in the two sliding blocks 43 respectively. Thus, the movement of the sliding blocks 43 will cause the support rods 2 to unfold or retract, change the tilt angle of the support rods 2 to adapt to different terrain landing requirements, and reduce wind resistance during flight.

[0027] like Figure 3 As shown, in this embodiment, buffer components 5 are further installed on the two inner walls of the through hole 431 that are opposite each other along the second direction Y, and the buffer components 5 abut against the support rod 2. Among them, the first direction X and the second direction Y intersect perpendicularly.

[0028] It should be noted that buffer components 5 are respectively installed on the two inner walls opposite each other along the second direction Y of the through hole 431. The buffer components 5 abut against the support rod 2, so that when the support rod 2 swings along the second direction Y due to vibration, the buffer components 5 can buffer the support rod 2, further reduce the vibration of the UAV landing gear and improve the flight stability of the UAV.

[0029] like Figure 3 As shown, in this embodiment, the through hole 431 is further provided with guide holes 432 extending in the second direction Y on the two inner walls opposite to each other along the second direction Y; The buffer assembly 5 includes an elastic element 51, a pressure post 52, a ball bearing 53, and a positioning sleeve 54; The elastic element 51 extends along the second direction Y and is located inside the guide hole 432. The first end of the elastic element 51 is connected to the bottom wall of the guide hole 432. The pressing post 52 extends along the second direction Y and is located inside the guide hole 432 and connected to the second end of the elastic element 51. The ball 53 is located outside the guide hole 432 and abuts against the second end of the pressing post 52 and the support rod 2. The positioning sleeve 54 is installed on the inner wall of the through hole 431. The inner diameter of the positioning sleeve 54 gradually decreases along the direction from the inner wall of the through hole 431 to the support rod 2. The positioning sleeve 54 is sleeved on the outside of the ball 53. The minimum inner diameter of the positioning sleeve 54 is smaller than the diameter of the ball 53.

[0030] It should be noted that when the support rod 2 does not press the ball 53, the elastic element 51 applies force to the pressing column 52, and the pressing column 52 applies force to the ball 53. Since the minimum inner diameter of the positioning sleeve 54 is smaller than the diameter of the ball 53, the ball 53 is limited to the minimum inner diameter of the positioning sleeve 54. When the support rod 2 swings and squeezes the ball 53, the ball 53 rolls in the positioning sleeve 54 and moves away from the support rod 2. The ball 53 exerts force on the pressing post 52, and the pressing post 52 slides in the guide hole 432, compressing the elastic element 51, thereby achieving a buffering effect. When the ball 53 is no longer squeezed by the support rod 2, the elastic element 51 rebounds, pushing the pressing post 52 to slide, and the ball 53 is repositioned at the minimum inner diameter of the positioning sleeve 54.

[0031] The pressure post 52 is connected between the elastic member 51 and the ball 53, and the pressure post 52 slides in the guide hole 432, which can restrict the movement direction of the pressure post 52, thereby improving the accuracy of the direction of pushing the ball 53 to move.

[0032] In addition, the rolling friction between the ball 53 and the support rod 2 reduces the friction between them, resulting in less resistance when the support rod 2 is extended or retracted, and also reducing the wear of the support rod 2 and the ball 53.

[0033] The inner diameter of the positioning sleeve 54 gradually decreases along the inner wall of the through hole 431 to the support rod 2, that is, the inner hole of the positioning sleeve 54 has a taper, preferably 1°-5°.

[0034] like Figure 3 As shown, further, an annular groove 433 is formed on the inner wall of the through hole 431, and a positioning sleeve 54 is installed in the annular groove 433. The outer wall of the positioning sleeve 54 is provided with external threads, and the inner surface of the outer ring of the annular groove 433 is provided with internal threads. The external threads and internal threads are matched. By screwing the positioning sleeve 54 into the annular groove 433, detachable installation can be achieved.

[0035] like Figure 2 As shown, in this embodiment, the lead screw drive assembly 42 further includes a first transmission gear 421, a second transmission gear 422, and a motor 423; The first transmission gear 421 is sleeved on the outer circumference of the bidirectional lead screw 41, the second transmission gear 422 is meshed with the first transmission gear 421, and the output shaft of the motor 423 is connected to the gear shaft of the second transmission gear 422.

[0036] It should be noted that when motor 423 is started, its output shaft rotates, driving the second transmission gear 422 to rotate, which in turn drives the meshing first transmission gear 421 to rotate. The rotation of the first transmission gear 421 causes the coaxial bidirectional lead screw 41 to rotate. The rotation direction of the bidirectional lead screw 41 can be changed by changing the rotation direction of the output shaft of motor 423. Driving the bidirectional lead screw 41 through the meshing of motor 423 and gears provides more stable rotation and allows for precise adjustment of the number of rotations of the bidirectional lead screw 41.

[0037] like Figure 2As shown, in this embodiment, a guide seat 6 is further installed at the bottom of the body 1, a bidirectional lead screw 41 is located inside the guide seat 6 and its two ends are rotatably connected to the guide seat 6, a connecting mounting cover 7 is installed at the bottom of the guide seat 6, the mounting cover 7 is located between two support rods 2 symmetrically arranged with the center of the body 1, the first ends of the two support rods 2 are hinged to the mounting cover 7, and the second transmission gear 422 and the motor 423 are installed inside the mounting cover 7.

[0038] It should be noted that the bidirectional lead screw 41 is located inside the guide seat 6, and both ends are rotatably connected to the guide seat 6. The bidirectional lead screw 41 can rotate more stably, and it is not easily affected by the external environment. A connecting mounting cover 7 is installed at the bottom of the guide seat 6. The second transmission gear 422 and the motor 423 are installed inside the mounting cover 7, so that the second transmission gear 422 can mesh with the first transmission gear 421 inside the guide seat 6. The second transmission gear 422 and the motor 423 are not easily affected by the external environment, and the mounting cover 7 and the guide seat 6 serve as dustproof.

[0039] The mounting cover 7 is located between two support rods 2 arranged symmetrically around the center of the body 1. The first ends of the two support rods 2 are hinged to the mounting cover 7, making the structural fit more compact.

[0040] The mounting cover 7 and the guide seat 6 are connected by bolts.

[0041] Furthermore, the inner wall of the guide seat 6 is provided with a groove (not shown in the figure) extending along the first direction X, and two sliding blocks 43 are slidably connected to the groove.

[0042] like Figure 1-2 As shown in Figure 4, in this embodiment, a support member 8 is further installed at the second end of the support rod 2. A receiving cavity 81 is opened in the support member 8. A sensor integration module 9 is installed in the receiving cavity 81. The sensor integration module 9 includes a distance sensor and an angle sensor connected together. Both the distance sensor and the angle sensor are electrically connected to a controller. The controller is electrically connected to the deployment drive assembly 4.

[0043] It should be noted that a support member 8 is installed at the second end of the support rod 2. When the drone landing gear lands, the support member 8 contacts the ground to cushion the impact and prevent it from impacting the support rod 2 during landing.

[0044] A receiving cavity 81 is formed inside the support member 8, and a sensor integration module 9 is installed inside the receiving cavity 81. The sensor integration module 9 includes a connected distance sensor and an angle sensor. The distance sensor detects the height of the support member 8 from the ground, and the angle sensor detects the tilt angle of the support member 8.

[0045] The distance sensor and angle sensor transmit the detected data to the controller, which controls the unfolding drive assembly 4 to work. The unfolding drive assembly 4 drives the two support rods 2 to unfold or retract synchronously.

[0046] Specifically, the controller is electrically connected to the motor 423 of the lead screw drive assembly 42. The output shaft of the motor 423 rotates, which drives the second transmission gear 422 to rotate, and in turn drives the first transmission gear 421 and the bidirectional lead screw 41 to rotate. The two sliding blocks 43 slide to adjust the unfolding angle of the support rod 2 and adjust the attitude of the support member 8 to ensure that the support member 8 is parallel to the ground when the UAV landing gear lands, and the UAV landing gear can land stably.

[0047] like Figure 2 , 4 As shown in Figure 5, the sensor integration module 9 further includes a housing 91, in which the distance sensor and the angle sensor are installed; The support member 8 has an opening that connects to the receiving cavity 81. The two inner walls of the receiving cavity 81 are provided with protruding limiting members 11 near the opening. The side of the limiting member 11 away from the inner wall of the receiving cavity 81 is provided with a blocking member 12. A retaining spring 13 is installed on the side of the limiting member 11 away from the opening. One end of the retaining spring 13 abuts against the inner wall of the receiving cavity 81, and the other end of the retaining spring 13 abuts against the outer wall of the outer shell 91.

[0048] It should be noted that the distance sensor and angle sensor are installed inside the housing 91. When the housing 91 is placed into the opening of the support member 8, the blocking member 12 is compressed until it is engaged between the two limiting members 11 within the receiving cavity 81. The two ends of the retaining spring 13 abut against the inner wall of the receiving cavity 81 and the outer wall of the housing 91. Therefore, when the housing 91 is pushed into the receiving cavity 81, the retaining spring 13 adapts to the size of the housing 91 and adjusts the degree of compression. Friction is generated between the retaining spring 13 and both the inner wall of the receiving cavity 81 and the outer wall of the housing 91, preventing displacement of the housing 91 relative to the retaining spring 13 and improving the stability of the housing 91 installation. The blocking member 12 further prevents the housing 91 from falling out of the receiving cavity 81. Preferably, the opening of the support member 8 is located at the bottom of the support member 8, and the limiting member 11 is detachably installed in the receiving cavity 81.

[0049] like Figure 2 , 4 As shown, further, a retaining spring 13 is installed on the inner wall of the receiving cavity 81 opposite to the opening.

[0050] like Figure 4 , 6As shown, the retaining ring 13 further includes a first abutting portion 131, a connecting portion 132, a second abutting portion 133, a first bent portion 134, a second bent portion 135, and a third bent portion 136. The two ends of the connecting portion 132 are respectively connected to the first ends of the first bent portion 134 and the first ends of the second bent portion 135. The first bent portion 134 and the second bent portion 135 are bent in opposite directions. The second end of the first bent portion 134 is connected to the first abutting portion 131. The second end of the second bent portion 135 is connected to the first end of the second abutting portion 133. The second end of the second abutting portion 133 is connected to the first end of the third bent portion 136. The bending direction of the third bent portion 136 is the same as the bending direction of the first bent portion 134. The first abutting portion 131 abuts against the inner wall of the receiving cavity 81. The second abutting portion 133 is used to abut against the outer wall of the outer shell 91. The second bent portion 135 is installed on the limiting member 11.

[0051] It should be noted that the snap ring 13 has a multi-section deformable structure through the design of multiple bends. When the snap ring 13 is squeezed by the outer shell 91, each bend can deform in concert, thereby generating a greater elastic restoring force.

[0052] like Figure 1 As shown, in this embodiment, the support member 8 is further provided with auxiliary wheels 10 on both sides along the third direction Z. The auxiliary wheels 10 extend along the third direction Z. The bottom surface of the auxiliary wheels 10 is flush with the bottom surface of the support member 8. The outer wall surface of the auxiliary wheels 10 is provided with a plurality of grooves 101 evenly distributed along its outer periphery. The grooves 101 extend along the third direction Z. Among them, the first direction X and the third direction Z intersect perpendicularly.

[0053] It should be noted that the bottom surface of the auxiliary wheel 10 is flush with the bottom surface of the support member 8, so that the auxiliary wheel 10 and the support member 8 can make contact with the ground and support the drone together, thus distributing the impact force on the support member 8 evenly. In addition, the auxiliary wheel 10 increases the contact area between the drone landing gear and the ground, reduces local pressure, and effectively prevents the drone landing gear from sinking when it lands on soft ground.

[0054] The outer wall of the auxiliary wheel 10 is provided with a plurality of grooves 101 evenly distributed along its outer periphery. The grooves 101 extend along the third direction Z, which can increase the friction between the auxiliary wheel 10 and the ground, and can prevent debris from the ground from accumulating on the surface of the auxiliary wheel 10, thereby increasing grip.

[0055] The first direction X, the second direction Y, and the third direction Z intersect each other perpendicularly.

[0056] like Figure 1As shown, in this embodiment, the outer wall of the damping sleeve 3 is further provided with a plurality of annular protrusions 31, the annular protrusions 31 are arranged along the outer periphery of the damping sleeve 3, and the plurality of annular protrusions 31 are distributed sequentially at intervals along the axial direction of the damping sleeve 3.

[0057] It should be noted that when the drone and landing gear are in flight, the annular protrusion 31 can increase the contact area between the damping sleeve 3 and the air, forming a small airflow turbulence, which weakens the impact of the airflow on the support rod 2. At the same time, the annular protrusion 31 can enhance the structural stiffness of the damping sleeve 3, which can more stably suppress vibration and improve the flight stability of the drone.

[0058] In this embodiment, the inner wall of the damping sleeve 3 is further provided with anti-slip texture.

[0059] It should be noted that the inner wall of the damping sleeve 3 is provided with anti-slip texture. The anti-slip texture and the support rod 2 are interference fit, which can increase the friction between the damping sleeve 3 and the support rod 2, prevent the damping sleeve 3 from shifting relative to the support rod 2, and allow the damping sleeve 3 to be more stably fitted on the outer periphery of the support rod 2.

[0060] Preferably, the damping sleeve 3 is a damping sleeve made of rubber.

[0061] The working process of the present invention is as follows: the drone is installed on the body 1, and at least two support rods 2 are symmetrically arranged around the center of the body 1. The unfolding drive assembly 4 is activated to drive at least two support rods 2 to unfold or retract synchronously, so that the first end of the support rod 2 rotates along the hinge axis, and the tilt angle of the support rod 2 can be adjusted.

[0062] During the flight of the UAV landing gear, the support rod 2 is disturbed by the airflow. Since the support rod 2 is a cantilever beam, resonance will occur when the natural frequency of the cantilever beam matches the airflow frequency. Moreover, the resonance energy is concentrated between the two ends of the support rod 2. Therefore, this application provides a damping sleeve 3 on the outer periphery between the two ends of the support rod 2, which can effectively absorb the resonance energy, reduce the vibration of the UAV landing gear, improve the flight stability of the UAV, and facilitate accurate photographing and identification of insulator defects.

[0063] In summary, the embodiments of the present invention provide a drone landing gear that can improve the flight stability of the drone and facilitate accurate photographic identification of insulator defects.

[0064] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and substitutions can be made without departing from the technical principles of the present invention, and these improvements and substitutions should also be considered within the scope of protection of the present invention.

Claims

1. A landing gear for an unmanned aerial vehicle (UAV), characterized in that, include: The body, which is used to mount the drone; At least two support rods, the first end of which is hinged to the bottom of the body, the at least two support rods are symmetrically arranged about the center of the body, and a damping sleeve is fitted around the outer periphery between the two ends of each support rod; An unfolding drive assembly is installed on the body and is connected to the support rods to drive at least two of the support rods to unfold or retract synchronously.

2. The UAV landing gear according to claim 1, characterized in that, The two support rods are distributed sequentially along the first direction; The deployment driving component includes: A bidirectional lead screw, which extends along the first direction and is mounted on the machine body; A lead screw drive assembly is mounted on the machine body and is connected to the bidirectional lead screw to drive the bidirectional lead screw to rotate. Two sliding blocks are sequentially sleeved on the outer periphery of the bidirectional lead screw along the first direction. The two sliding blocks have through holes extending along the first direction, and two support rods arranged symmetrically with respect to the center of the machine body are respectively inserted through the two through holes.

3. The UAV landing gear according to claim 2, characterized in that, Buffer components are respectively installed on the two inner walls of the through hole that are opposite to each other along the second direction, and the buffer components abut against the support rod; Wherein, the first direction and the second direction intersect perpendicularly.

4. The UAV landing gear according to claim 3, characterized in that, The through hole has guide holes extending in the second direction on its two inner walls that are opposite each other along the second direction. The buffer component includes: An elastic element extends along a second direction, is located within the guide hole, and has a first end connected to the bottom wall of the guide hole. A pressure post, the pressure post extending along a second direction, the first end of the pressure post being located in the guide hole and connected to the second end of the elastic element; The ball bearing is located outside the guide hole, abuts against the second end of the pressing post, and abuts against the support rod; A positioning sleeve is installed on the inner wall of the through hole. The inner diameter of the positioning sleeve gradually decreases along the direction from the inner wall of the through hole to the support rod. The positioning sleeve is sleeved on the outside of the ball. The minimum inner diameter of the positioning sleeve is smaller than the diameter of the ball.

5. The UAV landing gear according to claim 2, characterized in that, The lead screw drive assembly includes: The first transmission gear is sleeved on the outer periphery of the bidirectional lead screw; The second transmission gear is meshed with the first transmission gear. An electric motor, the output shaft of which is connected to the gear shaft of the second transmission gear.

6. The UAV landing gear according to claim 5, characterized in that, A guide seat is installed at the bottom of the machine body. The bidirectional lead screw is located inside the guide seat and its two ends are rotatably connected to the guide seat. A connecting mounting cover is installed at the bottom of the guide seat. The mounting cover is located between two support rods that are symmetrically arranged with respect to the center of the machine body. The first ends of the two support rods are hinged to the mounting cover. The second transmission gear and the motor are installed inside the mounting cover.

7. The UAV landing gear according to claim 1, characterized in that, A support member is installed at the second end of the support rod. A receiving cavity is opened in the support member. A sensor integrated module is installed in the receiving cavity. The sensor integrated module includes a distance sensor and an angle sensor connected together. Both the distance sensor and the angle sensor are electrically connected to a controller. The controller is electrically connected to the deployment drive assembly.

8. The UAV landing gear according to claim 7, characterized in that, The support member is equipped with auxiliary wheels on both sides along the third direction. The auxiliary wheels extend along the third direction and the bottom surface of the auxiliary wheels is flush with the bottom surface of the support member. The outer wall surface of the auxiliary wheels is provided with a plurality of grooves evenly distributed along its outer periphery. The grooves extend along the third direction. Wherein, the first direction and the third direction intersect perpendicularly.

9. The UAV landing gear according to claim 1, characterized in that, The outer wall of the damping sleeve is provided with a plurality of annular protrusions, which are arranged along the outer periphery of the damping sleeve and are distributed sequentially at intervals along the axial direction of the damping sleeve.

10. The UAV landing gear according to claim 1, characterized in that, The inner wall of the damping sleeve is provided with anti-slip texture.

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