Pressing rod type landing unmanned aerial vehicle landing mechanism and unmanned aerial vehicle

Abstract

The utility model discloses a pressing rod type landing unmanned aerial vehicle landing mechanism and an unmanned aerial vehicle, and belongs to the field of unmanned aerial vehicles. A pressing rod type landing unmanned aerial vehicle take-off and landing mechanism comprises a mounting frame and further comprises at least two sets of positioning shells fixedly mounted on the mounting frame, supporting legs are slidably connected into the positioning shells, and spring dampers fixedly connected with the positioning shells and the supporting legs are arranged in the positioning shells; the height of the supporting leg is adjusted through the adjusting piece, the ground clearance between the aircraft body and the ground can be increased, the aircraft body can be protected, the angle of the positioning shell and the angle of the supporting leg are adjusted through the adjusting piece, the supporting range of the supporting leg can be enlarged, and therefore the landing stability of the aircraft body is improved.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a lever-type landing mechanism for UAVs and the UAV itself. Background Technology

[0002] A drone is an unmanned aircraft that operates by remote control or through pre-programmed procedures. Drone technology involves multiple fields such as flight control, navigation and positioning, and wireless communication. With the continuous development of technology, drones have been widely used in aerial photography, surveying and mapping, environmental monitoring, logistics and distribution, and other fields.

[0003] As the name suggests, a lever-type landing drone uses a lever-type landing gear design. This design allows the drone to land horizontally on uneven and irregular ground. The landing gear typically includes at least three landing gear components, which are evenly distributed around the drone's circumference to ensure landing stability. During the drone's descent, the lower lever contacts and presses against the ground to form a landing fulcrum.

[0004] Existing drone landing mechanisms are mostly fixed-angle, which limits the support range of the support legs, thereby increasing the risk of the drone tipping over. Furthermore, the height of the support legs is not easy to adjust, resulting in limited ground clearance and making it impossible to avoid impacts from protruding objects on the drone. Utility Model Content

[0005] The purpose of this invention is to solve the problem in the prior art that the landing mechanism of a drone is not convenient for adjusting its angle and height, thus increasing the landing risk and difficulty. The invention proposes a lever-type landing drone landing mechanism and a drone.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] A lever-type landing unmanned aerial vehicle (UAV) takeoff and landing mechanism includes a mounting frame and at least two sets of positioning shells fixedly mounted on the mounting frame. Each positioning shell has a supporting leg slidably connected within it, and a spring damper fixedly connected to the positioning shell and the supporting leg is provided within the positioning shell. Each supporting leg has an adjustment component for extending the supporting leg. An adjustment control is mounted on the mounting frame and is used to adjust the angle of the positioning shell.

[0008] To adjust the height of the support leg and increase the ground clearance of the machine body, preferably, the adjusting component includes: a gear, rotatably mounted inside the support leg, the gear having a forming groove, wherein a U-shaped toothed plate is meshed on the gear, the side of the U-shaped toothed plate away from the gear contacts the inner wall of the support leg, and a positioning seat is rotatably mounted on the bottom of the U-shaped toothed plate; and a first nut, fixedly mounted on the support leg, wherein a bolt is internally threaded into the first nut, and one end of the bolt is slidably connected in the forming groove.

[0009] To further cushion and protect the support leg, an elastic bracket is fixedly installed on the positioning seat, and the elastic bracket has a flexible groove.

[0010] To further secure the positioning seat, a threaded pin is rotatably mounted on the U-shaped toothed plate, and a threaded sleeve is threadedly connected to the threaded pin.

[0011] To adjust the angle of the support leg and increase its contact area with the ground, preferably, the adjustment control includes: a positioning frame, fixedly installed on the mounting frame, wherein a second nut is rotatably connected inside the positioning frame, a lead screw is threaded into the second nut, and a first limiting seat is fixedly connected to the end of the lead screw away from the second nut; a second limiting seat, fixedly installed on the positioning shell, a connecting rod is rotatably installed inside the second limiting seat, and the end of the connecting rod away from the second limiting seat is rotatably connected to the first limiting seat.

[0012] To facilitate the user's rotation of the second nut, an anti-slip strip is provided on the second nut, and the anti-slip strip and the second nut are integrally formed.

[0013] To limit the movement of the support leg, preferably, a slider is fixedly installed on the support leg, and a groove that cooperates with the slider is provided on the positioning shell.

[0014] A drone also includes a body on which a camera and a propeller are fixedly mounted. The propeller is mounted on connecting arms around the body, and the mounting frame is fixedly connected to the body.

[0015] Compared with the prior art, this utility model provides a lever-type landing mechanism for unmanned aerial vehicles (UAVs) and the UAV itself, which has the following advantages:

[0016] 1. The landing mechanism and the drone of this lever-type landing drone, through the setting of the elastic support, the elastic support deforms after landing and contacting the ground due to the unevenness of the ground. This deformation can effectively absorb and disperse these impact forces, thereby protecting the body from damage.

[0017] 2. The landing mechanism and the drone of this lever-type landing drone, through the setting of spring dampers, can buffer and dissipate the impact force of the aircraft's descent, and avoid damage to the internal parts of the aircraft due to the impact force.

[0018] The parts not described in this device are the same as or can be implemented using existing technology. This utility model can increase the ground clearance between the aircraft and the ground by adjusting the height of the support legs through the adjustment component, thereby achieving the protection of the aircraft. Furthermore, by using the adjustment control to adjust the angle of the positioning shell and the support legs, the support range of the support legs can be expanded, thereby improving the stability of the aircraft's landing. Attached Figure Description

[0019] Figure 1 This is an isometric view of the landing mechanism of a pressure bar type unmanned aerial vehicle (UAV) and the UAV structure proposed in this utility model;

[0020] Figure 2 This is a partial isometric schematic diagram of a lever-type landing unmanned aerial vehicle (UAV) landing mechanism and the UAV as proposed in this utility model.

[0021] Figure 3 This is an isometric sectional view of the positioning shell structure of a lever-type landing unmanned aerial vehicle (UAV) landing mechanism proposed in this utility model.

[0022] Figure 4 This is an isometric schematic diagram of the adjustment control structure of the landing mechanism of the lever-type landing drone proposed in this utility model;

[0023] Figure 5 Exploded view of the adjusting component of the landing mechanism of a lever-type landing drone proposed in this utility model;

[0024] Figure 6 This utility model proposes a lever-type landing mechanism for unmanned aerial vehicles. Figure 5 Enlarged structural diagram at point A;

[0025] Figure 7 This is a partial exploded view of part A of the landing mechanism of a lever-type landing drone proposed in this utility model.

[0026] In the diagram: 1. Mounting bracket; 2. Adjusting component; 201. Gear; 202. U-shaped toothed plate; 203. Positioning seat; 204. First nut; 205. Bolt; 206. Elastic bracket; 3. Adjusting control; 301. Positioning frame; 302. Second nut; 303. Lead screw; 304. First limit seat; 305. Second limit seat; 306. Connecting rod; 4. Positioning shell; 5. Support leg; 6. Slider; 7. Spring damper; 8. Slide groove; 9. Camera; 10. Propeller; 11. Body. Detailed Implementation

[0027] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.

[0028] In the description of this utility model, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model 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. Therefore, they should not be construed as limitations on this utility model.

[0029] Example:

[0030] Reference Figures 1-7 A lever-type landing mechanism for unmanned aerial vehicles (UAVs) includes two mounting frames 1 and four sets of positioning shells 4. The four sets of positioning shells 4 are symmetrically fixedly mounted on the mounting frames 1 along the axis of the inclined surfaces of the two mounting frames 1. Each positioning shell 4 has a groove 8, and a T-shaped slider 6 is slidably connected in the groove 8. A support leg 5 is fixedly connected to the side of the slider 6 away from the groove 8. The support leg 5 is slidably connected inside the positioning shell 4. A spring damper 7 is fixedly connected to the positioning shell 4 and the support leg 5 inside the positioning shell 4. The spring damper 7 is a Mangniu 1 / 12MN78 external spring shock absorber, which can effectively absorb and disperse the impact force of the UAV landing. The support leg 5 is provided with an adjustment part 2 for extending the support leg 5. An adjustment control 3 for adjusting the angle of the positioning shell 4 is fixedly mounted on the mounting frame 1.

[0031] Specifically, by adjusting the height of the support leg 5 using the adjusting component 2, the ground clearance between the aircraft 11 and the ground can be increased, thus providing protection for the aircraft 11. Furthermore, by adjusting the angle of the positioning shell 4 and the support leg 5 using the adjusting component 3, the support range of the support leg 5 can be increased, thereby improving the stability of the aircraft 11 during landing.

[0032] Adjusting component 2 includes a gear 201, which is rotatably mounted inside the support leg 5. A forming groove is formed on the gear 201. A U-shaped toothed plate 202 is meshed with the gear 201. The U-shaped toothed plate 202 has teeth on only one side. A threaded pin is rotatably mounted on the U-shaped toothed plate 202, and a threaded sleeve is threadedly connected to the threaded pin. One side of the threaded sleeve contacts the support leg 5, enabling positioning of the threaded pin. The side of the U-shaped toothed plate 202 away from the gear 201 contacts the inner wall of the support leg 5. A positioning seat 203 is rotatably mounted on the bottom of the U-shaped toothed plate 202. An elastic bracket 206 is fixedly mounted on the positioning seat 203. The elastic bracket 206 can be made of elastic metal and has a tough groove. A first nut 204 is fixedly mounted on the support leg 5. A bolt 205 is threadedly connected to the first nut 204, and one end of the bolt 205 is slidably connected inside the forming groove.

[0033] Specifically, by setting the adjustment component 2, the user can use an external tool to rotate the bolt 205, which in turn drives the gear 201 to rotate, thereby adjusting the height of the U-shaped toothed plate 202, increasing the height of the support leg 5, increasing the ground clearance of the UAV, and achieving the protection of the body 11. At the same time, the positioning seat 203 can be fixed by the cooperation of the threaded pin and the threaded sleeve, and the metal elastic bracket 206 can play a role in buffering and dispersing the impact force when the support leg 5 lands.

[0034] The adjustment control 3 includes a positioning frame 301, which is fixedly installed on the mounting frame 1. A second nut 302 is rotatably connected inside the positioning frame 301. The second nut 302 is provided with an anti-slip strip, which is integrally formed with the second nut 302. A lead screw 303 is threadedly connected inside the second nut 302. A first limiting seat 304 is fixedly connected to the end of the lead screw 303 away from the second nut 302. A second limiting seat 305 is fixedly installed on the positioning shell 4. A connecting rod 306 is rotatably installed inside the second limiting seat 305. The end of the connecting rod 306 away from the second limiting seat 305 is rotatably connected to the first limiting seat 304.

[0035] Specifically, by setting the adjustment control 3, the angles of the positioning shell 4 and the support leg 5 can be adjusted, thereby increasing the contact area between the support leg 5 and the ground, making the drone more stable when landing. Furthermore, the anti-slip strips can increase the stability of the user's operation.

[0036] A drone includes a body 11, on which a camera 9 and a propeller 10 are fixedly mounted. There are four propellers 10, which are respectively mounted on connecting arms around the body 11. The mounting frame 1 is fixedly connected to the body 11.

[0037] Specifically, the design of the mounting bracket 1 facilitates the connection between the body 11 and the positioning shell 4, thereby achieving landing protection for the UAV.

[0038] Working principle: When in use, the user rotates the second nut 302. When the second nut 302 rotates, it drives the two lead screws 303 inside to rotate. Since the threads on the surfaces of the two lead screws 303 are opposite, the opposite ends of the two lead screws 303 drive the two first limit seats 304 to move in opposite directions. When the two first limit seats 304 move in opposite directions, they drive one end of the connecting rod 306 to move. At this time, the other end of the connecting rod 306 presses against the second limit seat 305, thereby realizing the angle adjustment of the positioning shell 4 and the support leg 5. By adjusting the distance between the two positioning shells 4, the support range of the support leg 5 can be increased, thereby improving the stability of the UAV landing.

[0039] Meanwhile, when using the drone in areas with complex ground conditions, the user can use external tools to turn the bolt 205. When the bolt 205 rotates inside the first nut 204, it drives the gear 201 to rotate. When the gear 201 rotates, it drives the U-shaped toothed plate 202 to move from the inside to the outside inside the support leg 5. After all four U-shaped toothed plates 202 are fully adjusted and unfolded, the ground clearance between the drone body 11 and the ground can be increased, thereby protecting the drone and preventing damage to the drone body 11 caused by the impact of protruding objects on the ground.

[0040] Furthermore, during the descent of the body 11, the elastic support 206 will first come into contact with the ground. The elastic support 206 can deform due to the unevenness of the ground. This deformation can effectively absorb and disperse these impact forces, thereby protecting the body 11 from damage. Secondly, under the inertial impact of descent, the impact force of the support leg 5 will impact the spring damper 7. The spring damper 7 can buffer and dissipate the impact force, thus avoiding excessive impact force that could damage the internal parts of the body 11.

[0041] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. A pressure bar type landing mechanism for unmanned aerial vehicles, comprising a mounting frame (1), characterized in that, Also include: At least two sets of positioning shell (4) is fixedly installed on the mounting frame (1), Wherein, the support leg (5) is slidably connected in the positioning shell (4), the spring damper (7) is arranged in the positioning shell (4) and is fixedly connected with the positioning shell (4) and the support leg (5), and the adjusting part (2) for extending the support leg (5) is arranged on the support leg (5); The control part (3) is installed on the mounting frame (1), and the control part (3) is used for angle adjustment of the positioning shell (4).

2. The compression rod landing gear mechanism of claim 1, wherein, The adjusting part (2) comprises: The gear (201) is rotatably installed in the support leg (5), and the shaped groove is formed in the gear (201), Wherein, the U-shaped tooth plate (202) is connected with the gear (201), the side of the U-shaped tooth plate (202) away from the gear (201) is in contact with the inner wall of the support leg (5), and the bottom of the U-shaped tooth plate (202) is rotatably installed with the positioning seat (203); The first nut (204) is fixedly installed on the support leg (5), Wherein, the bolt (205) is threadedly connected in the first nut (204), and one end of the bolt (205) is slidably connected in the shaped groove.

3. The compression rod landing gear mechanism of claim 2, wherein, The elastic support (206) is fixedly installed on the positioning seat (203), and the toughness groove is formed in the elastic support (206).

4. The compression rod landing gear mechanism of claim 2, wherein, The threaded shaft pin is rotatably installed on the U-shaped tooth plate (202), and the threaded sleeve is threadedly connected on the threaded shaft pin.

5. The compression rod landing gear mechanism of claim 1, wherein, The control part (3) comprises: The positioning frame (301) is fixedly installed on the mounting frame (1), Wherein, the second nut (302) is rotatably connected in the positioning frame (301), the screw rod (303) is threadedly connected in the second nut (302), and the first limiting seat (304) is fixedly connected at one end of the screw rod (303) away from the second nut (302); The second limiting seat (305) is fixedly installed on the positioning shell (4), the connecting rod (306) is rotatably installed in the second limiting seat (305), and one end of the connecting rod (306) away from the second limiting seat (305) is rotatably connected with the first limiting seat (304).

6. The compression rod landing gear mechanism of claim 5, wherein, The anti-skid strip is arranged on the second nut (302), and the anti-skid strip and the second nut (302) are integrally formed.

7. The compression rod landing gear mechanism of claim 1, wherein, The sliding block (6) is fixedly installed on the support leg (5), and the sliding groove (8) matched with the sliding block (6) is formed in the positioning shell (4).

8. A UAV comprising the compression rod landing gear of any one of claims 1-7, wherein, Further comprising a machine body (11), the camera (9) and the propeller (10) are fixedly installed on the machine body (11) respectively, the propeller (10) is installed on the connecting arm around the machine body (11), and the mounting frame (1) is fixedly connected with the machine body (11).

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