Unmanned aerial vehicle landing damping device

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle landing damping device which comprises a mounting plate, supporting seats are connected to the lower ends of the left side and the right side of the mounting plate through damping rods respectively, hollow pipes are vertically and fixedly arranged at the tops of the two opposite ends of the supporting seats respectively, and vertically-arranged sliding rods are slidably connected into the hollow pipes. The top end of the sliding rod penetrates out of the interior of the hollow pipe and is fixedly connected with the lower end of the mounting plate, a first permanent magnet matched with the interior of the hollow pipe in size is arranged in the hollow pipe, and a second permanent magnet repelling the first permanent magnet is fixedly arranged at the bottom end of the sliding rod. Due to the fact that the opposite faces of the first permanent magnet and the second permanent magnet are in the like pole repulsion state, the second permanent magnet can achieve the buffering and damping effect when getting close to the first permanent magnet, the safety of the unmanned aerial vehicle is protected, meanwhile, the damping rod has the damping effect, and the situation that the mounting plate rebounds rapidly under the repulsion effect of the first permanent magnet and the second permanent magnet, and vibration is caused can be prevented.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, and in particular to a landing shock absorbing device for unmanned aerial vehicles. Background Art

[0002] Unmanned aircraft, also known as "drones", are unmanned aircraft that are controlled by radio remote control equipment and self-contained program control devices. When landing, drones usually vibrate with the ground, which not only affects the balance of the aircraft, but may also cause damage to its own parts, so it is necessary to set up a shock-absorbing structure.

[0003] The existing shock absorption method usually sets a shock absorbing pad and a shock absorbing spring at the bottom of the drone. The effect of the shock absorbing pad is not obvious, and the shock absorbing spring usually converts the gravity of the drone into elastic force when in use. The shock absorbing spring is easy to rebound on the drone after being compressed, thereby causing recoil to the drone and affecting the balance of the drone. Utility Model Content

[0004] The utility model aims to provide a UAV landing shock absorbing device, which solves the problem in the prior art that when the UAV is landing, the shock absorbing spring is compressed and rebounds, making it difficult for the UAV to maintain balance.

[0005] In order to solve the above technical problems, the utility model adopts the following technical solutions:

[0006] A landing shock-absorbing device for an unmanned aerial vehicle comprises a mounting plate, wherein the lower ends of the left and right sides of the mounting plate are respectively connected to support seats through damping rods, hollow tubes are respectively vertically fixedly arranged on the tops of the opposite ends of the support seats, a vertically arranged sliding rod is slidably connected inside the hollow tube, the top end of the sliding rod passes through the interior of the hollow tube and is fixedly connected to the lower end of the mounting plate, a first permanent magnet matching the internal size of the hollow tube is arranged inside the hollow tube, and a second permanent magnet that repels the first permanent magnet is fixedly arranged at the bottom end of the sliding rod.

[0007] A further technical solution is that the hollow tube is provided with symmetrically arranged adjustment grooves that are connected to the interior of the hollow tube, and the outer side of the hollow tube is vertically opened with adjustment grooves that penetrate the interior of the hollow tube. Adjustment screws are respectively provided on both sides of the first permanent magnet, and one end of the adjustment screw away from the first permanent magnet passes through the adjustment groove and out of the interior of the hollow tube, and is threadedly engaged with a fixing nut.

[0008] A further technical solution is that a limiting ring is provided at the top pipe opening of the hollow tube, and one end of the slide rod placed in the hollow tube is connected to the second permanent magnet through a limiting block, and the outer ring diameter of the limiting block is larger than the inner ring diameter of the limiting ring.

[0009] A further technical solution is that movable grooves are provided at both opposite ends of the support seat, and the L-shaped support leg is rotatably connected in the movable groove. An annular groove is provided in the movable groove at the end away from the groove, and an annular block matching the annular groove is fixedly connected to one end of the support seat placed inside the movable groove. A locking component for locking the rotation of the support leg is provided on the support seat.

[0010] A further technical solution is that the locking assembly includes a locking bolt, a threaded hole penetrating the inside of the movable groove is provided on the outside of the support seat, the threaded hole and the locking bolt are threadedly engaged, and a plurality of pin holes are provided on the outer wall of the support leg. When the support leg is rotated and set in the movable groove, the pin hole can be rotated to align with the threaded hole.

[0011] A further technical solution is that a conical block is fixedly connected to one end of the support leg away from the support seat.

[0012] A further technical solution is that a buffer sleeve made of rubber material is fixedly provided on the outer wall of the support seat.

[0013] Compared with the prior art, the utility model has the following beneficial effects: by arranging the hollow tube, the sliding rod, the first permanent magnet and the second permanent magnet, when the drone lands, the drone will generate a downward impact force on the mounting plate, thereby causing the sliding rod to slide downward inside the hollow tube, causing the second permanent magnet to approach the first permanent magnet; since the opposing surfaces of the first permanent magnet and the second permanent magnet are in a state of like-charge repulsion, the second permanent magnet will have a buffering and shock-absorbing effect when it approaches the first permanent magnet, thereby protecting the safety of the drone; at the same time, the damping rod has a damping effect, which can prevent the mounting plate from rebounding quickly under the repulsive effect of the first permanent magnet and the second permanent magnet, causing vibration. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 The utility model is a three-dimensional schematic diagram of a UAV landing shock absorbing device.

[0015] Figure 2 It is a cross-sectional view of the slide rod, hollow tube, first permanent magnet and second permanent magnet of the utility model.

[0016] Figure 3 This is a side view of the supporting leg of the utility model in the second state.

[0017] Figure 4 This is a cross-sectional connection diagram of the support seat and the support leg of the utility model.

[0018] Icon: 1-mounting plate, 2-damping rod, 3-support seat, 4-hollow tube, 5-sliding rod, 6-first permanent magnet, 7-second permanent magnet, 8-adjusting slot, 9-adjusting screw, 10-fixing nut, 11-limiting ring, 12-limiting block, 13-support leg, 14-annular groove, 15-annular block, 16-locking bolt, 17-threaded hole, 18-pin hole, 19-tapered block, 20-movable slot. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical solution and advantages of the utility model more clear, the utility model is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the utility model and are not used to limit the utility model.

[0020] Embodiment 1:

[0021] See also Figures 1 to 4 The utility model shows a shock absorbing device for landing of an unmanned aerial vehicle. The lower ends of the left and right sides of the mounting plate 1 are respectively connected to a support seat 3 through a damping rod 2. The damping rod 2 is an existing structure and is not described in detail here. The tops of the opposite ends of the support seat 3 are respectively vertically fixed with a hollow tube 4. The inside of the hollow tube 4 is slidably connected with a vertically arranged sliding rod 5. The top of the sliding rod 5 passes through the inside of the hollow tube 4 and is fixedly connected to the lower end of the mounting plate 1. The inside of the hollow tube 4 is provided with a first permanent magnet 6 that matches the internal size of the hollow tube 4. The bottom end of the sliding rod 5 is fixedly provided with a second permanent magnet 7 that repels the first permanent magnet 6. In actual use, the unmanned aerial vehicle body is mounted Above the mounting plate 1, when the drone lands, the support seat 3 first contacts the ground. Due to inertia and its own gravity, the drone will generate a downward impact force on the mounting plate 1, thereby causing the slide bar 5 to slide downward inside the hollow tube 4, causing the second permanent magnet 7 to approach the first permanent magnet 6. Since the opposing surfaces of the first permanent magnet 6 and the second permanent magnet 7 are in a state of like-charge repulsion, the second permanent magnet 7 will have a buffering and shock-absorbing effect when it approaches the first permanent magnet 6, thereby protecting the safety of the drone. At the same time, the damping rod 2 has a damping effect, which can prevent the mounting plate 1 from rebounding quickly under the repulsive effect of the first permanent magnet 6 and the second permanent magnet 7, causing vibration to the drone body.

[0022] The hollow tube 4 is provided with adjustment grooves 8 which are symmetrically arranged and connected with the inside of the hollow tube 4. The outer side of the hollow tube 4 is vertically opened with adjustment grooves 8 which penetrate the inside of the hollow tube 4. Adjustment screws 9 are respectively provided on both sides of the first permanent magnet 6. The end of the adjustment screw 9 away from the first permanent magnet 6 passes through the inside of the hollow tube 4 through the adjustment groove 8, and is threadedly engaged with a fixing nut 10. By setting the adjustment groove 8, the adjustment screw 9 can be moved to make the first permanent magnet 6 move in the hollow tube 4 and then fixed by threading the fixing nut 10 with the adjustment screw 9. Then, the size of the magnetic force can be adjusted by the distance between the first permanent magnet 6 and the second permanent magnet 7, so as to adjust the elastic potential energy and thus adjust the shock absorption effect of the drone.

[0023] Through the above technical solution, please refer to Figure 2As shown, a limiting ring 11 is provided at the top pipe opening of the hollow tube 4, and one end of the slide rod 5 placed in the hollow tube 4 is connected to the second permanent magnet 7 through a limiting block 12. The outer ring diameter of the limiting block 12 is larger than the inner ring diameter of the limiting ring 11. The limiting ring 11 and the limiting block 12 can enable the slide rod 5 to completely slide out of the hollow tube 4 under the repulsive effect of the first permanent magnet 6 and the second permanent magnet 7, thereby affecting the subsequent shock absorption.

[0024] Embodiment 2:

[0025] Through the above technical solution, please refer to Figures 1 to 4 As shown, movable grooves 20 are provided at opposite ends of the support seat 3, and the L-shaped support legs 13 are rotatably connected in the movable grooves 20. An annular groove 14 is provided in the movable groove 20 at one end away from the groove. An annular block 15 matching the annular groove 14 is fixedly connected to one end of the support seat 3 placed inside the movable groove 20. A locking assembly for locking the rotation of the support legs 13 is provided on the support seat 3. When the user needs to land the drone on an uneven ground such as an outdoor lawn, the support legs 13 can be rotated relative to the support seat 3 in the movable grooves 20, so that the support legs 13 located at both ends of the same support seat 3 are in an eight-shaped shape, and then the support legs 13 are fixed by the locking assembly, so that they can land more stably on the uneven grass. By providing the annular grooves 14 and the annular blocks, the support legs 13 can be prevented from slipping out of the movable grooves 20 when the support legs 13 are rotated.

[0026] Through the above technical solution, the locking assembly includes a locking bolt 16, a threaded hole 17 penetrating the interior of the movable groove 20 is provided on the outer side of the support seat 3, the threaded hole 17 and the locking bolt 16 are threadedly engaged, and a plurality of pin holes 18 are provided on the outer wall of the support leg 13. When the support leg 13 is rotated and set in the movable groove 20, the pin hole 18 can be rotated to be aligned with the threaded hole 17. By providing a plurality of pin holes 18, it is more convenient to fix the support leg 13 with the locking bolt 16.

[0027] One end of the support leg 13 away from the support base 3 is fixedly connected with a conical block 19. By setting the conical block 19, when the drone is landing on an uneven ground such as an outdoor lawn, the bottom of the conical block 19 can penetrate the bottom surface of the lawn to prevent the bottom of the support leg 13 from being in unstable contact with the uneven ground such as the lawn, thereby affecting the landing stability of the drone.

[0028] A rubber cushion sleeve is fixed on the outer wall of the support seat 3. By setting the cushion sleeve, when landing on a relatively flat ground, the cushion sleeve contacts the ground to buffer and reduce shock. At the same time, it can also prevent the ground from contacting the support seat 3 and causing damage to the support seat 3.

[0029] Although the utility model is described herein with reference to a plurality of illustrative embodiments of the utility model, it should be understood that those skilled in the art may devise many other modifications and implementations that fall within the scope and spirit of the principles disclosed herein. More specifically, within the scope of the disclosure, drawings, and claims of the present application, various modifications and improvements may be made to the components and / or layout of the subject combination layout. In addition to the modifications and improvements made to the components and / or layout, other uses will also be apparent to those skilled in the art.

Claims

1. A UAV landing shock absorbing device, comprising a mounting plate (1), characterized in that: The lower ends of the left and right sides of the mounting plate (1) are respectively connected to a support seat (3) via a damping rod (2); the tops of the two opposite ends of the support seat (3) are respectively vertically fixed with a hollow tube (4); a vertically arranged sliding rod (5) is slidably connected inside the hollow tube (4); the top end of the sliding rod (5) passes through the interior of the hollow tube (4) and is fixedly connected to the lower end of the mounting plate (1); a first permanent magnet (6) matching the internal dimensions of the hollow tube (4) is provided inside the hollow tube (4); and a second permanent magnet (7) that repels the first permanent magnet (6) is fixedly provided at the bottom end of the sliding rod (5).

2. The UAV landing shock absorbing device according to claim 1, characterized in that: The hollow tube (4) is provided with adjustment grooves (8) which are symmetrically arranged and are both connected to the interior of the hollow tube (4); the outer side of the hollow tube (4) is vertically provided with adjustment grooves (8) which penetrate the interior of the hollow tube (4); adjustment screws (9) are respectively provided on both sides of the first permanent magnet (6); one end of the adjustment screw (9) away from the first permanent magnet (6) passes through the adjustment groove (8) and out of the interior of the hollow tube (4), and is threadedly engaged with a fixing nut (10).

3. The UAV landing shock absorbing device according to claim 1, characterized in that: A limiting ring (11) is provided at the top pipe opening of the hollow tube (4); one end of the sliding rod (5) placed in the hollow tube (4) is connected to the second permanent magnet (7) via a limiting block (12); and the outer ring diameter of the limiting block (12) is larger than the inner ring diameter of the limiting ring (11).

4. The UAV landing shock absorption device according to claim 1, characterized in that: The support seat (3) is provided with movable grooves (20) at opposite ends, and the L-shaped support leg (13) is rotatably connected in the movable groove (20). An annular groove (14) is provided in the movable groove (20) at one end away from the notch. An annular block (15) matching the annular groove (14) is fixedly connected to one end of the support seat (3) placed inside the movable groove (20). A locking component for locking the support leg (13) in rotation is provided on the support seat (3).

5. The UAV landing shock absorbing device according to claim 4, characterized in that: The locking assembly comprises a locking bolt (16); a threaded hole (17) penetrating the interior of the movable groove (20) is provided on the outer side of the support seat (3); the threaded hole (17) and the locking bolt (16) are threadedly engaged; a plurality of pin holes (18) are provided on the outer wall of the support leg (13); when the support leg (13) is rotatably disposed in the movable groove (20), the pin holes (18) can be rotated to align with the threaded holes (17).

6. The UAV landing shock absorbing device according to claim 5, characterized in that: One end of the support leg (13) away from the support seat (3) is fixedly connected to a conical block (19).

7. The UAV landing shock absorbing device according to claim 1, characterized in that: A buffer sleeve made of rubber is fixedly provided on the outer wall of the support seat (3).

Images