Bionic landing gear and unmanned aerial vehicle suitable for rapid landing

Abstract

The application belongs to the technical field of unmanned aerial vehicle accessories, and particularly relates to a bionic landing gear suitable for rapid landing and an unmanned aerial vehicle, which comprises a claw, the claw comprising a hinged arm, a claw body and a claw tip, the claw body being hinged to the claw tip, the claw body being hinged to the hinged arm, the lower end of a secondary arm being provided with a third hinged shaft, the secondary arm being hinged to the middle part of the hinged arm, the hinged arm being provided with a first protrusion, the first protrusion being provided with a first perforation, the third hinged shaft being located between the first protrusion and a second hinged shaft, the claw tip being provided with a second protrusion, the second protrusion being provided with a second perforation, the second protrusion being located between the first hinged shaft and the second hinged shaft, and a third linear tension mechanism, the free end of the third linear tension mechanism being sequentially arranged in the first perforation and the second perforation and being fixedly connected to the claw tip. The purpose is to solve the problem that the existing landing gear structure defects cause a great back pressure on the landing gear when the unmanned aerial vehicle lands, and even cause damage to the structure of the unmanned aerial vehicle.

Description

Technical Field

[0001] This invention belongs to the field of drone accessory technology, specifically relating to a biomimetic landing gear and drone suitable for rapid landing. Background Technology

[0002] The landing gear of a drone is a component on the bottom of the drone used to support it during takeoff, landing, or on the ground. It is a crucial and indispensable part of the drone.

[0003] Currently, common drone landing gear typically consists of four support rods with latching devices at the top for docking with the bottom of the drone's shell. These four support rods serve to support the drone. However, during drone landings, especially for heavier drones, the impact force can create significant recoil forces on the landing gear, potentially damaging the drone's structure. Therefore, traditional landing gear suffers from poor environmental adaptability and cannot meet the landing requirements of multi-rotor drones in complex environments, such as sloping landing surfaces or highly maneuverable situations.

[0004] By observing insects such as locusts and dragonflies, it's easy to see that they land with multiple legs touching the ground and utilize foot-sensing and leg-coordination during takeoff and landing, enabling them to land stably on any complex terrain, including tree branches and grass. Considering that the landing of multi-rotor drones has similar needs to the habitats of birds and flying insects, applying biomimetic methods to the design of new drone landing gear can effectively solve the problems of traditional landing gear and apply it to the landing scenarios of multi-rotor drones under high-sensitivity maneuvers. Summary of the Invention

[0005] The purpose of this invention is to provide a biomimetic landing gear suitable for rapid landing, in order to solve the problem that existing landing gear structural defects cause a large recoil force on the landing gear during drone landing, which can even damage the drone's structure in severe cases.

[0006] To achieve the above-mentioned technical objectives, the technical solution adopted by the present invention is as follows:

[0007] A biomimetic landing gear suitable for rapid descent includes:

[0008] Connector;

[0009] Main arm, which is fixedly connected to the connecting seat;

[0010] A secondary arm, the upper end of which is connected to the main arm;

[0011] The claw includes a hinged arm, a claw body, and a claw tip. The claw body has a first hinge shaft and a second hinge shaft at both ends. The claw body is hinged to the claw tip via the first hinge shaft and to the hinged arm via the second hinge shaft. The lower end of the auxiliary arm has a third hinge shaft, and the auxiliary arm is hinged to the middle of the hinged arm via the third hinge shaft.

[0012] The hinge arm is provided with a first protrusion, and the first protrusion has a first through hole along the length direction of the hinge arm. The third hinge shaft is located between the first protrusion and the second hinge shaft.

[0013] The claw tip is provided with a second protrusion, and the second protrusion has a second through hole along the length direction of the claw tip. The second protrusion is located between the first hinge shaft and the second hinge shaft.

[0014] The third linear tension mechanism has one end fixedly connected to the main arm, and the free end of the third linear tension mechanism is sequentially inserted into the first and second through holes and fixedly connected to the claw tip.

[0015] Further specifying, the auxiliary arm is a spring damper comprising a cylinder and a rod, with the rod passing through the cylinder. This structural design, by using the spring damper as the auxiliary arm, after completing the connection between the main arm and the pawl, utilizes the damping effect of the spring damper to absorb the impact during UAV landing, further enhancing the landing gear's cushioning performance and demonstrating strong practicality.

[0016] Furthermore, the upper end of the auxiliary arm is hinged to the main arm, and an elastic positioning mechanism is provided between the main arm and the auxiliary arm. This elastic positioning mechanism provides a pulling force in the opposite direction to the auxiliary arm when it rotates relative to the main arm. This structural design, through the hinge between the auxiliary arm and the main arm, combined with the elastic positioning mechanism, forms a new buffer mechanism, further enhancing the landing gear's buffering performance and demonstrating strong practicality.

[0017] Further specified, the end of the auxiliary arm away from the pawl is provided with a hinge post, and the auxiliary arm is hinged to the main arm via the hinge post;

[0018] The elastic positioning mechanism includes a first linear tension mechanism and a second linear tension mechanism, both of which are fixedly connected to the main arm;

[0019] The first linear tension mechanism is used to provide a clockwise rotational tension to the auxiliary arm when the auxiliary arm rotates counterclockwise around the hinge post;

[0020] The second linear tension mechanism provides a counterclockwise tension to the auxiliary arm when it rotates clockwise around the hinge post. This structural design, through the first and second linear tension mechanisms forming an elastic positioning mechanism, maintains the hinge angle between the main arm and the auxiliary arm when no external force is applied, and simultaneously provides a tension in the opposite direction to the auxiliary arm when it rotates relative to the main arm. The structure is simple and easy to install.

[0021] Furthermore, both the first and second linear tension mechanisms include a spring and a rope. This structural design, using springs and ropes to form the first and second linear tension mechanisms, is simple in structure, easy to install, and highly practical.

[0022] Furthermore, the elastic positioning mechanism also includes a first fixed post, a second fixed post, a first connecting block, and a second connecting block, wherein the first fixed post and the second fixed post are both fixedly installed on the main arm;

[0023] The first connecting block is fixedly installed on the auxiliary arm and located above the line connecting the hinge column and the second fixed column. The two ends of the first linear tension mechanism are fixedly connected to the first fixed column and the first connecting block, respectively.

[0024] The second connecting block is fixedly installed on the auxiliary arm and located below the line connecting the hinge column and the second fixed column. The two ends of the second linear tension mechanism are fixedly connected to the second fixed column and the second connecting block, respectively. This structural design, through the elastic positioning mechanism pulling the first and second connecting blocks, achieves the purpose of providing a pulling force in the opposite direction to the auxiliary arm when it rotates relative to the main arm. It has a simple structure, is easy to install, and is highly practical.

[0025] Furthermore, a fixed pulley is rotatably mounted on the main arm, and the second linear tension mechanism is wound around the fixed pulley. This structural design, by limiting the path of the second linear tension mechanism through the fixed pulley, ensures that the second linear tension mechanism is as close as possible to the main arm and auxiliary arm, avoiding safety hazards caused by the exposed second linear tension mechanism, and is highly practical.

[0026] Furthermore, the third linear tension mechanism comprises a spring and a rope. This structural design, using a spring and a rope to form the third linear tension mechanism, is simple in structure, easy to install, and highly practical.

[0027] Furthermore, the lower end surfaces of the articulated arm, claw body, and claw tip are all roughened surfaces. This structural design, through the addition of roughened surfaces, increases the friction between the claw and the landing platform, providing an anti-slip effect and enhancing practicality.

[0028] The present invention also discloses an unmanned aerial vehicle (UAV), including a fuselage and four of the above-mentioned biomimetic landing gears suitable for rapid landing, wherein the four connecting seats are fixedly connected to the fuselage and are symmetrically distributed on the bottom of both sides of the fuselage.

[0029] The invention employing the above technical solution has the following advantages:

[0030] 1. Through the cooperation of the articulated arm, claw body, claw tip and third linear tension mechanism, a multi-stage buffer structure is formed to absorb the recoil force borne by the UAV when it lands. The structure is simple, the buffer effect is good, and the probability of damage to the UAV structure can be reduced.

[0031] 2. The buffer mechanism is composed of three sections: hinged arm, claw body, and claw tip, which are hinged together. It has a good stopping effect on uneven or sloping ground and is highly practical.

[0032] 3. By using a spring damper as a secondary arm, after completing the connection between the main arm and the pawl, the damping effect of the spring damper is used to absorb the impact of the UAV during landing, which can further enhance the buffering performance of the landing gear and has strong practicality.

[0033] 4. By hinged between the secondary boom and the main boom, and in conjunction with the elastic positioning mechanism, a new buffer mechanism is formed, which further enhances the buffering performance of the landing gear and has strong practicality.

[0034] 5. Through three sets of mutually cooperating buffer mechanisms, mimicking the leg structure of insects, the system works together to cushion the drone during landing, further enhancing the buffering effect and providing additional protection for the drone, making it highly practical.

[0035] 6. An elastic positioning mechanism is formed by the first linear tension mechanism and the second linear tension mechanism. When no external force is applied, it maintains the hinge angle between the main arm and the auxiliary arm. At the same time, when the auxiliary arm rotates relative to the main arm, it provides a tension force in the opposite direction to the auxiliary arm. The structure is simple and easy to install.

[0036] 7. The first linear tension mechanism, the second linear tension mechanism, and the third linear tension mechanism are constructed using springs and ropes. The structure is simple, easy to install, and highly practical.

[0037] 8. By using the elastic positioning mechanism to pull the first connecting block and the second connecting block, the purpose of providing a pulling force in the opposite direction to the auxiliary arm when the auxiliary arm rotates relative to the main arm is achieved. The structure is simple, easy to install, and highly practical.

[0038] 9. The rough surface design increases the friction between the claws and the landing platform, providing an anti-slip effect and enhancing practicality. Attached Figure Description

[0039] The present invention can be further illustrated by the non-limiting embodiments given in the accompanying drawings;

[0040] Figure 1 This is a schematic diagram of the structure of a biomimetic landing gear suitable for rapid landing and a UAV embodiment of the present invention when the landing gear is in flight.

[0041] Figure 2 This is a schematic diagram of the internal structure of a biomimetic landing gear suitable for rapid landing and an embodiment of an unmanned aerial vehicle when the landing gear is in flight.

[0042] Figure 3 for Figure 2 Enlarged structural diagram at point A;

[0043] Figure 4 This is a schematic diagram of the structure of a biomimetic landing gear suitable for rapid landing and an embodiment of a UAV, showing the landing gear just coming into contact with the landing platform.

[0044] Figure 5 This is a schematic diagram of the structure of a biomimetic landing gear suitable for rapid landing and an embodiment of a UAV, after the landing gear has landed on a horizontal landing platform.

[0045] Figure 6 This is a schematic diagram of the structure of a biomimetic landing gear suitable for rapid landing and an unmanned aerial vehicle embodiment of the present invention after the landing gear lands on an uneven landing platform.

[0046] Figure 7 This is a schematic diagram of the structure of a biomimetic landing gear suitable for rapid landing and an embodiment of a UAV, after the landing gear lands on an inclined landing platform.

[0047] The symbols for the main components are explained below:

[0048] Connector 1

[0049] Main boom 2, first linear tension mechanism 21, first fixed column 210,

[0050] Second linear tension mechanism 22, second fixed column 220, third linear tension mechanism 23, third fixed column 230

[0051] Protective shell 3, auxiliary boom 30, cylinder 301, rod 302,

[0052] First connecting block 31, second connecting block 32, hinged column 33, fixed pulley 34.

[0053] Hinge arm 41, first protrusion 410

[0054] Claw body 42, first hinge shaft 421, second hinge shaft 422, third hinge shaft 423

[0055] Claw tip 43, second protrusion 430. Detailed Implementation

[0056] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that similar or identical parts are referred to by the same reference numerals in the drawings or description. Implementations not shown or described in the drawings are forms known to those skilled in the art. In addition, directional terms mentioned in the embodiments, such as "up," "down," "top," "bottom," "left," "right," "front," and "back," are only for reference to the directions in the drawings and are not intended to limit the scope of protection of the present invention.

[0057] like Figures 1 to 7 As shown, a biomimetic landing gear suitable for rapid descent according to the present invention includes:

[0058] Connector 1;

[0059] Main boom 2 is fixedly connected to connecting seat 1;

[0060] The auxiliary arm 30 is connected to the main arm 2 at its upper end.

[0061] The claw includes a hinged arm 41, a claw body 42, and a claw tip 43. The claw body 42 has a first hinge shaft 421 and a second hinge shaft 422 at both ends. The claw body 42 is hinged to the claw tip 43 via the first hinge shaft 421 and to the hinged arm 41 via the second hinge shaft 422. The lower end of the auxiliary arm 30 has a third hinge shaft 423. The auxiliary arm 30 is hinged to the middle part of the hinged arm 41 via the third hinge shaft 423.

[0062] The hinge arm 41 is provided with a first protrusion 410, and the first protrusion 410 is provided with a first through hole along the length direction of the hinge arm 41. The third hinge shaft 423 is located between the first protrusion 410 and the second hinge shaft 422.

[0063] The claw tip 43 is provided with a second protrusion 430, and the second protrusion 430 is provided with a second through hole along the length direction of the claw tip 43. The second protrusion 430 is located between the first hinge shaft 421 and the second hinge shaft 422.

[0064] The third linear tension mechanism 23 has one end fixedly connected to the main arm 2, and the free end of the third linear tension mechanism 23 is sequentially inserted into the first through hole and the second through hole and fixedly connected to the claw tip 43.

[0065] The secondary arm 30 is a spring damper comprising a cylinder 301 and a rod 302, with the rod 302 passing through the cylinder 301. In practice, a hydraulic damper can also be used as a buffer mechanism depending on the actual situation. In this embodiment, by using a spring damper as the secondary arm 30, and after completing the connection between the main arm 2 and the pawl, the damping effect of the spring damper is used to absorb the impact of the UAV landing, further enhancing the landing gear's buffering performance and demonstrating strong practicality.

[0066] The spring damper is covered with a protective shell 3. The protective shell 3 protects the spring damper from damage caused by accidental impacts, making it highly practical.

[0067] The upper end of the auxiliary boom 30 is hinged to the main boom 2. An elastic positioning mechanism is provided between the main boom 2 and the auxiliary boom 30. The elastic positioning mechanism is used to provide a pulling force in the opposite direction to the auxiliary boom 30 when it rotates relative to the main boom 2. In practice, depending on the situation, the auxiliary boom 30 can also be directly fixedly connected to the main boom 2 to achieve the connection between the auxiliary boom 30 and the main boom 2. In this embodiment, the hinge between the auxiliary boom 30 and the main boom 2, combined with the elastic positioning mechanism, forms a new buffer mechanism, which further enhances the buffering performance of the landing gear and has strong practicality.

[0068] A hinge post 33 is provided at the end of the auxiliary arm 30 away from the foot claw, and the auxiliary arm 30 is hinged to the main arm 2 via the hinge post 33;

[0069] The elastic positioning mechanism includes a first linear tension mechanism 21 and a second linear tension mechanism 22, both of which are fixedly connected to the main arm 2.

[0070] The first linear tension mechanism 21 is used to provide a clockwise rotation tension to the auxiliary arm 30 when the auxiliary arm 30 rotates counterclockwise around the hinge post 33;

[0071] The second linear tension mechanism 22 provides a counterclockwise tension to the auxiliary arm 30 when it rotates clockwise around the hinge post 33. Alternatively, depending on the actual situation, a torsion spring can be installed between the auxiliary arm 30 and the main arm 2 as an elastic positioning mechanism to provide a tension in the opposite direction when the auxiliary arm 30 rotates relative to the main arm 2. In this embodiment, the first linear tension mechanism 21 and the second linear tension mechanism 22 constitute an elastic positioning mechanism. When no external force is applied, the hinge angle between the main arm 2 and the auxiliary arm 30 is maintained. Simultaneously, when the auxiliary arm 30 rotates relative to the main arm 2, a tension in the opposite direction is provided to the auxiliary arm 30. The structure is simple and easy to install.

[0072] Both the first linear tension mechanism 21 and the second linear tension mechanism 22 include a spring and a rope. In practice, an elastic rope can also be used directly as the linear tension mechanism, depending on the actual situation. In this embodiment, the first linear tension mechanism 21 and the second linear tension mechanism 22 are constructed using a spring and a rope, which is simple in structure, easy to install, and highly practical.

[0073] The elastic positioning mechanism also includes a first fixed column 210, a second fixed column 220, a first connecting block 31 and a second connecting block 32, with the first fixed column 210 and the second fixed column 220 both fixedly installed on the main arm 2;

[0074] The first connecting block 31 is fixedly installed on the auxiliary arm 30 and located above the line connecting the hinge column 33 and the second fixed column 220. The two ends of the first linear tension mechanism 21 are fixedly connected to the first fixed column 210 and the first connecting block 31, respectively.

[0075] The second connecting block 32 is fixedly installed on the auxiliary arm 30 and located below the line connecting the hinge column 33 and the second fixed column 220. The two ends of the second linear tension mechanism 22 are fixedly connected to the second fixed column 220 and the second connecting block 32, respectively. In practice, other connection methods can be selected to install the first linear tension mechanism 21 and the second linear tension mechanism 22 according to the actual situation. For example, a pulley can be set at the top of the auxiliary arm 30 so that the first linear tension mechanism 21 is connected to the back of the auxiliary arm 30 via the pulley. In this embodiment, the first connecting block 31 and the second connecting block 32 are pulled by the elastic positioning mechanism to achieve the purpose of providing a pulling force in the opposite direction to the auxiliary arm 30 when the auxiliary arm 30 rotates relative to the main arm 2. The structure is simple, easy to install, and highly practical.

[0076] A fixed pulley 34 is rotatably mounted on the main boom 2, and the second linear tension mechanism 22 is wound around the fixed pulley 34. The fixed pulley 34 limits the path of the second linear tension mechanism 22, so that the second linear tension mechanism 22 is as close as possible to the main boom 2 and the auxiliary boom 30, avoiding the safety hazards caused by the exposed second linear tension mechanism 22, which is highly practical.

[0077] The third linear tension mechanism 23 includes a spring and a rope. In practice, an elastic rope can also be used directly as the linear tension mechanism, depending on the actual situation. In this embodiment, the third linear tension mechanism 23 is constructed using a spring and a rope, which has a simple structure, is easy to install, and is highly practical.

[0078] A third fixing column 230 is also fixedly installed on the main boom 2, and the third linear tension mechanism 23 is fixedly connected to the main boom 2 via the third fixing column 230.

[0079] The lower surfaces of the articulated arm 41, claw body 42, and claw tip 43 are all roughened. The roughened surfaces increase the friction between the claw and the landing platform, providing an anti-slip effect and enhancing practicality.

[0080] A drone includes a fuselage and four biomimetic landing gears suitable for rapid landing, the four connecting seats 1 being fixedly connected to the fuselage and symmetrically distributed on the bottom of both sides of the fuselage.

[0081] In this embodiment, when the drone is in flight, such as Figure 1-3 As shown, the auxiliary arm 30 maintains a balanced state under the action of the first linear tension mechanism 21 and the second linear tension mechanism 22. The hinge arm 41, claw body 42 and claw tip 43 of the claw maintain the state in which the central axes of the first perforation and the second perforation coincide and the central axis passes through the third fixed column 230 under the action of the third linear tension mechanism 23.

[0082] When the drone lands, the claw tip 43 of the landing gear first contacts the landing platform. Under the reaction force of the landing platform, it overcomes the prestress of the third linear tension mechanism 23, causing the claw tip 43 to rotate around the first hinge axis 421, the claw body 42 to rotate around the second hinge axis 422, and the hinge arm 41 to rotate around the third hinge axis 423 (e.g., Figure 4 As shown), the state in which the central axes of the first perforation and the second perforation coincide and the central axis passes through the third fixing post 230 is disrupted;

[0083] At the same time, the rod 302 in the auxiliary arm 30 retracts into the cylinder 301 to absorb the impact force. The auxiliary arm 30 overcomes the prestress of the second linear tension mechanism 22 and rotates clockwise around the hinge column 33.

[0084] Up to the lower end faces of the articulated arm 41, claw body 42, and claw tip 43, all are in contact with the landing platform (e.g., Figures 5-7 As shown in the figure, at this time, the landing gear is tightened by the elastic force of the third linear tension mechanism 23 and the elastic force of the second linear tension mechanism 22, thereby forming support for the UAV.

[0085] The foregoing has provided a detailed description of a biomimetic landing gear and unmanned aerial vehicle (UAV) suitable for rapid landing, as provided by the present invention. The specific embodiments described are merely for the purpose of helping to understand the method and core ideas of the present invention. It should be noted that those skilled in the art can make various improvements and modifications to the present invention without departing from its principles, and these improvements and modifications also fall within the protection scope of the claims of the present invention.

Claims

1. A biomimetic landing gear suitable for rapid descent, characterized in that, include: Connector (1); Main arm (2), which is fixedly connected to connecting seat (1); A secondary arm (30), the upper end of which is connected to the main arm (2); The claw includes a hinge arm (41), a claw body (42), and a claw tip (43). The claw body (42) has a first hinge shaft (421) and a second hinge shaft (422) at both ends. The claw body (42) is hinged to the claw tip (43) via the first hinge shaft (421). The claw body (42) is hinged to the hinge arm (41) via the second hinge shaft (422). The lower end of the auxiliary arm (30) is provided with a third hinge shaft (423). The auxiliary arm (30) is hinged to the middle part of the hinge arm (41) via the third hinge shaft (423). The hinge arm (41) is provided with a first protrusion (410), the first protrusion (410) is provided with a first through hole along the length direction of the hinge arm (41), and the third hinge shaft (423) is located between the first protrusion (410) and the second hinge shaft (422). The claw tip (43) is provided with a second protrusion (430), and the second protrusion (430) is provided with a second through hole along the length direction of the claw tip (43). The second protrusion (430) is located between the first hinge shaft (421) and the second hinge shaft (422). The third linear tension mechanism (23) has one end fixedly connected to the main arm (2), and the free end of the third linear tension mechanism (23) is sequentially inserted into the first through hole and the second through hole and fixedly connected to the claw tip (43). The upper end of the auxiliary arm (30) is hinged to the main arm (2). An elastic positioning mechanism is provided between the main arm (2) and the auxiliary arm (30) of the cylinder. The elastic positioning mechanism is used to provide a pulling force in the opposite direction to the auxiliary arm (30) when the auxiliary arm (30) rotates relative to the main arm (2). The auxiliary arm (30) has a hinge post (33) at the end away from the claw, and the auxiliary arm (30) is hinged to the main arm (2) via the hinge post (33); The elastic positioning mechanism includes a first linear tension mechanism (21) and a second linear tension mechanism (22), both of which are fixedly connected to the main arm (2). The first linear tension mechanism (21) is used to provide a clockwise rotational tension to the auxiliary arm (30) when the auxiliary arm (30) rotates counterclockwise around the hinge post (33); The second linear tension mechanism (22) is used to provide a counterclockwise tension to the auxiliary arm (30) as the auxiliary arm (30) rotates clockwise around the hinge post (33).

2. The biomimetic landing gear suitable for rapid landing according to claim 1, characterized in that: The auxiliary arm (30) is a spring damper comprising a cylinder (301) and a rod (302), wherein the rod (302) is inserted inside the cylinder (301).

3. The biomimetic landing gear suitable for rapid landing according to claim 1, characterized in that: Both the first linear tension mechanism (21) and the second linear tension mechanism (22) include a spring and a rope.

4. A biomimetic landing gear suitable for rapid landing according to claim 1, characterized in that: The elastic positioning mechanism further includes a first fixed column (210), a second fixed column (220), a first connecting block (31), and a second connecting block (32), wherein the first fixed column (210) and the second fixed column (220) are both fixedly installed on the main arm (2); The first connecting block (31) is fixedly installed on the auxiliary arm (30) and located above the line connecting the hinge column (33) and the second fixed column (220). The two ends of the first linear tension mechanism (21) are fixedly connected to the first fixed column (210) and the first connecting block (31) respectively. The second connecting block (32) is fixedly installed on the auxiliary arm (30) and located below the line connecting the hinge column (33) and the second fixed column (220). The two ends of the second linear tension mechanism (22) are fixedly connected to the second fixed column (220) and the second connecting block (32) respectively.

5. A biomimetic landing gear suitable for rapid landing according to claim 4, characterized in that: A fixed pulley (34) is rotatably mounted on the main arm (2), and the second linear tension mechanism (22) is wound around the fixed pulley (34).

6. A biomimetic landing gear suitable for rapid landing according to claim 1, characterized in that: The third linear tension mechanism (23) includes a spring and a rope.

7. A biomimetic landing gear suitable for rapid landing according to claim 1, characterized in that: The lower end surfaces of the hinge arm (41), claw body (42), and claw tip (43) are all rough surfaces.

8. An unmanned aerial vehicle (UAV), characterized in that: It includes a fuselage and four biomimetic landing gears as described in any one of claims 1-7, suitable for rapid landing, wherein the four connecting seats (1) are fixedly connected to the fuselage and symmetrically distributed on the bottom of both sides of the fuselage.

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