Anti-seismic landing gear of unmanned aerial vehicle

Abstract

The utility model discloses an unmanned aerial vehicle anti-seismic undercarriage, and belongs to the technical field of unmanned aerial vehicle undercarriages. Comprising a bottom table, the top end of the bottom table is provided with a shock absorption assembly used for shock resistance, the top end of the shock absorption assembly is connected with a connecting plate, the top end of the connecting plate is connected with a falling plate, the falling plate is internally provided with a positioning assembly used for clamping, and the side face of the falling plate is provided with a protection assembly capable of being rotationally stored. According to the unmanned aerial vehicle landing protection device, the protection assembly is arranged, a servo motor is started through an external controller to drive a gear A to rotate, the gear A drives a gear B to rotate through meshing teeth, the gear B can drive a rotating rod to rotate to the position over a landing frame plate from a horizontal storage state, the landing unmanned aerial vehicle is protected, and the service life of the unmanned aerial vehicle is prolonged.

Description

Technical Field

[0001] This application relates to the technical field of unmanned aerial vehicle landing gears, and more specifically, to an earthquake-resistant landing gear for unmanned aerial vehicles. Background Technique

[0002] Currently, unmanned aerial vehicles are mainly unmanned aircraft controlled by radio remote control equipment and self-prepared program control. Landing gears are used when unmanned aerial vehicles take off and land to facilitate placing the unmanned aerial vehicles. As more and more unmanned aerial vehicles are put into use, people's requirements for the landing gears of unmanned aerial vehicles are also getting higher and higher.

[0003] In the related art, in order to solve the problem that certain vibrations will occur when an unmanned aerial vehicle takes off and lands, which is likely to damage the unmanned aerial vehicle, the patent with the publication number CN215554099U in the prior art provides an earthquake-resistant landing gear for an unmanned aerial vehicle, including a support base, and fixed seats are installed on both sides of the bottom end of the support base. This earthquake-resistant landing gear for an unmanned aerial vehicle is provided with a telescopic rod, a first buffer spring, a second buffer spring, a support rod and a movable plate. The unmanned aerial vehicle is located above the support base. The vibrations generated during the takeoff of the unmanned aerial vehicle and the impact force generated during landing will be applied at the support base. When the support base is stressed, it will squeeze the second buffer spring downward, having a shock-absorbing effect. A support rod is sleeved inside the second buffer spring.

[0004] Although the above-mentioned prior art solution has achieved a double shock-absorbing effect by setting springs, with higher stability and improved usage effect, however, the positioning efficiency of the limit rod of the existing earthquake-resistant landing gear for unmanned aerial vehicles is low. After the unmanned aerial vehicle lands, due to the lack of an automatic protection mechanism at the top of the landing gear, it is easily exposed to sunlight, rain, and attacked by falling objects outdoors, reducing the service life of the device.

[0005] In view of this, we propose an earthquake-resistant landing gear for unmanned aerial vehicles. Content of the Utility Model

[0006] 1. Technical Problems to be Solved

[0007] The purpose of this application is to provide an earthquake-resistant landing gear for unmanned aerial vehicles, which solves the technical problems that the positioning efficiency of the limit rod of the existing earthquake-resistant landing gear for unmanned aerial vehicles is low, and after the unmanned aerial vehicle lands, the top of the landing gear lacks an automatic protection mechanism, is easily exposed to sunlight, rain, or attacked by falling objects outdoors, reducing the service life of the device, and achieves the technical effect of comprehensively protecting the unmanned aerial vehicle.

[0008] 2. Technical Solution

[0009] The present application provides an anti-seismic landing gear for a drone, including a bottom platform. At the top of the bottom platform, there is a shock-absorbing component for anti-seismic purposes. The top of the shock-absorbing component is connected to a connecting plate, and the top of the connecting plate is connected to a landing plate. Inside the landing plate, there is a positioning component for clamping, and on the side of the landing plate, there is a protective component that can be rotated and stored.

[0010] Preferably, the protective component includes a rotating rod and a gear. One end of the rotating rod is rotatably arranged on both sides of the landing plate, and the end of the rotating rod away from the landing plate is connected to a protective plate.

[0011] Preferably, the side cross-section of the protective plate is an arc surface.

[0012] Preferably, an extension rod extends from one side of the rotating rod at the rotating end. On the side wall of the landing plate on one side of the extension rod, there is a servo motor. The output end of the servo motor is provided with a gear A, and the mutually close sides of the gear A and the gear B are meshed with each other.

[0013] Preferably, the positioning component includes a moving groove. Inside the moving groove, moving clamping plates are symmetrically and slidably arranged. On the inner sides of the two moving clamping plates, there is a rubber anti-slip layer.

[0014] Preferably, at the bottom ends of the two moving grooves, lead screws are threadedly arranged. One end of each lead screw is rotatably connected to the inner wall of the landing plate. Inside the landing plate, there is a double-shaft motor, and the mutually close sides of the two lead screws are connected to the two driving ends of the double-shaft motor.

[0015] Preferably, the shock-absorbing component includes a sliding groove. The sliding grooves are symmetrically opened at the top of the bottom platform. Inside the two sliding grooves, sliding blocks are symmetrically and slidably arranged. The top of each sliding block is rotatably provided with a shock absorber. The two shock absorbers are distributed in a V shape. The top of the shock absorber is rotatably connected to the bottom end of the connecting plate.

[0016] Preferably, a sliding rod is arranged inside the sliding groove, and a buffer spring is sleeved outside the sliding rod.

[0017] 3. Beneficial effects

[0018] One or more technical solutions provided in the embodiments of the present application have at least the following technical effects or advantages:

[0019] (1) In the present application, by providing a protective component, the servo motor is started through an external controller, driving the gear A to rotate. The gear A drives the gear B to rotate through the teeth. The gear B can drive the rotating rod to rotate from the horizontal storage state to directly above the landing plate, protecting the descending drone and improving the service life of the drone.

[0020] (2) In this application, a positioning component is provided. When the biaxial motor starts, it drives the lead screw to rotate, enabling the moving clamping plates to approach each other and clamp both sides of the drone, thereby positioning the drone and allowing it to be stably placed on the landing gear. For the takeoff and landing of the drone, the moving clamping plates are automatically controlled by the biaxial motor, improving the safety of the drone. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 is the first three-dimensional structural schematic diagram of the present utility model;

[0022] Figure 2 is the three-dimensional structural schematic diagram of the protective state of the present utility model;

[0023] Figure 3 is the top-view structural schematic diagram of the present utility model;

[0024] Figure 4 is of the present utility model Figure 2 partial enlarged structural schematic diagram of part A in;

[0025] Figure 5 is the three-dimensional structural schematic diagram of the shock-absorbing component of the present utility model

[0026] Reference numeral description in the figures: 110, bottom table; 111, connecting plate; 120, landing plate; 200, protective component; 210, protective plate; 211, rotating rod; 212, extension rod; 213, gear B; 214, gear A; 215, servo motor; 300, positioning component; 310, moving clamping plate; 311, moving groove; 312, lead screw; 313, biaxial motor; 400, shock-absorbing component; 410, shock absorber; 411, sliding block; 412, sliding groove; 413, sliding rod; 414, buffer spring. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0027] The following further details this application with reference to the accompanying drawings of the specification.

[0028] Embodiment 1

[0029] Please refer to Figures 1-5, an embodiment provided by the present utility model: an anti-seismic landing gear for a drone, including a bottom platform 110. At the top of the bottom platform 110, there is a shock-absorbing component 400 for anti-seismic. The top of the shock-absorbing component 400 is connected to a connecting plate 111. The top of the connecting plate 111 is connected to a landing plate 120. Inside the landing plate 120, there is a positioning component 300 for clamping. On the side of the landing plate 120, there is a rotatable and retractable protective component 200. The protective component 200 includes a rotating rod 211 and a gear B 213. One end of the rotating rod 211 is rotatably arranged on both sides of the landing plate 120. The end of the rotating rod 211 away from the landing plate 120 is connected to a protective plate 210. The side cross-section of the protective plate 210 is an arc surface, and the arc surface is convenient for draining water and removing foreign objects. On one side of the rotating rod 211, an extension rod 212 is extended. On the side wall of the landing plate 120 on one side of the extension rod 212, there is a servo motor 215. The output end of the servo motor 215 is provided with a gear A 214. The mutually close sides of the gear A 214 and the gear B 213 are meshed with each other. The servo motor 215 is started through an external controller to drive the gear A 214 to rotate. The gear A 214 drives the gear B 213 to rotate through the teeth. The gear B 213 can drive the rotating rod 211 to rotate from the horizontal retracted state to directly above the landing plate 120 to protect the descending drone.

[0030] Embodiment Two

[0031] An anti-seismic landing gear for a drone proposed by the present utility model. Compared with Embodiment One, please refer to Figures 1-4 , the positioning component 300 includes a moving groove 311. Inside the moving groove 311, two moving clamping plates 310 are symmetrically and slidably arranged. On the inner sides of the two moving clamping plates 310, there is a rubber anti-slip layer. At the bottom ends of the two moving grooves 311, lead screws 312 are threadedly arranged. One end of the lead screw 312 is rotatably connected to the inner wall of the landing plate 120. Inside the landing plate 120, there is a dual-axis motor 313. The mutually close sides of the two lead screws 312 are connected to the two driving ends of the dual-axis motor 313. When the dual-axis motor 313 is started, it drives the lead screws 312 to rotate, enabling the moving clamping plates 310 to approach each other and clamp both sides of the drone, thereby realizing central positioning and clamping of the drone, making the drone stably placed on the landing gear. For the takeoff and landing of the drone, the moving clamping plates 310 are automatically controlled by the dual-axis motor 313.

[0032] Further, the shock absorption assembly 400 includes a chute 412 symmetrically opened at the top end of the bottom platform 110. Inside the two chutes 412, sliding blocks 411 are symmetrically and slidably arranged. At the top end of the sliding block 411, a shock absorber 410 is rotatably arranged. The two shock absorbers 410 are distributed in a V shape. The top end of the shock absorber 410 is rotatably connected to the bottom end of the connecting plate 111. Inside the chute 412, a slide bar 413 is arranged, and a buffer spring 414 is sleeved on the outer side of the slide bar 413. The drone is located above the landing plate 120. The vibration generated during the takeoff of the drone and the landing will generate a large impact force, which acts on the landing plate 120. The four shock absorbers 410 below the landing plate 120 have a good earthquake resistance effect. The two moving grooves 311 slide inside the chute 412, and the separation process will drive the buffer spring 414 to be compressed, thus achieving a double shock absorption effect and reducing the diffusion of the impact force.

[0033] In summary, when the earthquake-resistant landing gear of the drone disclosed in the embodiment of the present application is in use, the servo motor 215 is started through an external controller, driving the gear A 214 to rotate. The gear A 214 drives the gear B 213 to rotate through the teeth. The gear B 213 can drive the rotating rod 211 to rotate from the horizontal storage state to directly above the landing plate 120 to protect the descending drone. The dual-axis motor 313 is started, driving the lead screw 312 to rotate, so that the moving clamping plates 310 can approach each other to clamp both sides of the drone, thereby positioning the drone and enabling the drone to be stably placed on the landing gear. For the takeoff and landing of the drone, the moving clamping plates 310 are automatically controlled by the dual-axis motor 313. The drone is located above the landing plate 120. The vibration generated during the takeoff of the drone and the landing will generate a large impact force, which acts on the landing plate 120. The four shock absorbers 410 below the landing plate 120 have a good earthquake resistance effect. The two moving grooves 311 slide inside the chute 412, and the separation process will drive the buffer spring 414 to be compressed, thus achieving a double shock absorption effect and reducing the diffusion of the impact force.

[0034] The standard parts used in the present utility model can all be purchased from the market. The special-shaped parts can be customized according to the description in the specification and the drawings. The specific connection methods of each part all adopt conventional means such as bolts, rivets, and welding that are mature in the prior art. The machinery, parts, and equipment all adopt conventional models in the prior art. Coupled with the circuit connection adopting the conventional connection method in the prior art, it will not be elaborated here. The content not described in detail in this specification belongs to the prior art well-known to those skilled in the art.

[0035] Although the present utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or perform equivalent replacements for some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. An anti-vibration landing gear for an unmanned aerial vehicle, characterized in that: The invention comprises a bottom platform (110), wherein a shock absorbing component (400) for resisting earthquakes is arranged at the top of the bottom platform (110), a connecting plate (111) is connected to the top of the shock absorbing component (400), a landing plate (120) is connected to the top of the connecting plate (111), a positioning component (300) for clamping is arranged inside the landing plate (120), and a protective component (200) that can be rotatably stored is arranged on the side of the landing plate (120).

2. The anti-vibration landing gear of the UAV according to claim 1, characterized in that: The protection assembly (200) comprises a rotating rod (211) and a gear B (213); one end of the rotating rod (211) is rotatably arranged on both sides of the landing plate (120); and one end of the rotating rod (211) away from the landing plate (120) is connected to the protection plate (210).

3. The anti-vibration landing gear of the UAV according to claim 2, characterized in that: The side cross-section of the protection plate (210) is an arc-shaped surface.

4. The anti-vibration landing gear of the UAV according to claim 2, characterized in that: An extension rod (212) is extended from the rotating end of one side of the rotating rod (211), a servo motor (215) is arranged on the side wall of the landing plate (120) on one side of the extension rod (212), a gear A (214) is arranged at the output end of the servo motor (215), and the gear A (214) and the gear B (213) are meshed with each other at the sides close to each other.

5. The anti-vibration landing gear for unmanned aerial vehicles according to claim 1, characterized in that: The positioning assembly (300) comprises a movable groove (311), wherein movable clamping plates (310) are symmetrically and slidably arranged inside the movable groove (311), and a rubber anti-slip layer is arranged on the inner sides of the two movable clamping plates (310).

6. The anti-vibration landing gear for unmanned aerial vehicles according to claim 5, characterized in that: The bottom ends of the two movable grooves (311) are both threadedly provided with a lead screw (312), one end of the lead screw (312) is rotatably connected to the inner wall of the landing plate (120), a dual-axis motor (313) is provided inside the landing plate (120), and the sides of the two lead screws (312) close to each other are connected to the two driving ends of the dual-axis motor (313).

7. The anti-vibration landing gear for unmanned aerial vehicles according to claim 1, characterized in that: The shock absorbing assembly (400) comprises a slide groove (412), wherein the slide groove (412) is symmetrically arranged at the top end of the bottom platform (110), and sliding blocks (411) are symmetrically slidably arranged inside the two slide grooves (412), and a shock absorber (410) is rotatably arranged at the top end of the sliding block (411), and the two shock absorbers (410) are arranged in an "eight" shape, and the top end of the shock absorber (410) is rotatably connected to the bottom end of the connecting plate (111).

8. The anti-vibration landing gear for unmanned aerial vehicle according to claim 7, characterized in that: A sliding rod (413) is arranged inside the sliding groove (412), and a buffer spring (414) is sleeved on the outer side of the sliding rod (413).

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