Unmanned aerial vehicle landing protection device

Abstract

The utility model discloses an unmanned aerial vehicle landing protection device which comprises an unmanned aerial vehicle body, a laser range finder is fixedly arranged in the center of the bottom of the unmanned aerial vehicle body, H-shaped supports are hinged to the left side and the right side of the bottom of the unmanned aerial vehicle body, and buffer mechanisms are fixedly arranged in the H-shaped supports. Compared with the prior art, the unmanned aerial vehicle has the advantages that the unmanned aerial vehicle can more accurately sense the ground position through cooperation of the laser range finder and other devices, and therefore stable landing is achieved; through the design of the H-shaped support and the buffer mechanism, impact force during landing is effectively absorbed, damage to the unmanned aerial vehicle body and a landing area is reduced, and the device adopts relatively simple structural design, is easy to manufacture and install, is low in cost and is wide in applicability.

Description

Technical Field

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

[0002] With the continuous development of drone technology, it is widely used in civil fields such as aerial photography, surveying and mapping, power inspection, and military fields such as intelligence reconnaissance, border patrol, and material distribution. During use, drones are easily affected by external environments such as wind speed and terrain when landing, which may cause unexpected situations and threaten the safety of people or facilities in the surrounding environment. In order to solve the above problems, various drone landing protection devices have been proposed in the prior art. However, most protection devices often lack sufficient stability and accuracy, which affects the protection effect and lacks effective buffering of landing impact. Utility Model Content

[0003] A technical problem

[0004] The utility model provides a landing protection device for a UAV, aiming to solve the problem that a traditional landing protection device for a UAV lacks sufficient stability and accuracy, and lacks effective buffering of landing impact.

[0005] 2. Technical Content

[0006] In order to solve the above technical problems, the technical solution of the utility model is: a UAV landing protection device, including a UAV body, a laser rangefinder is fixedly provided at the bottom center of the UAV body, H-shaped brackets are hingedly provided on the left and right sides of the bottom of the UAV body, a buffer mechanism is fixedly provided inside the H-shaped bracket, and an electric push rod is hingedly provided at the bottom of the UAV body near the two H-shaped brackets, and the piston end of the electric push rod is hinged to the H-shaped bracket.

[0007] Furthermore, the H-shaped bracket includes two hinged rods and a crossbeam, the two hinged rods are hinged at the bottom of the drone body, the crossbeam is fixed between the two hinged rods, and the buffer mechanism is fixed at the bottom of the crossbeam.

[0008] Furthermore, the buffer mechanism includes a cavity fixed at both ends of the bottom of the beam, and also includes an insertion rod inserted into the bottom of the cavity, a limit plate is fixedly provided at one end of the insertion rod extending into the cavity, a damper is provided between the bottom surface of the cavity and the limit plate, a spring is provided on the outside of the damper, and a buffer rod is fixedly connected between the bottoms of the insertion rod.

[0009] Furthermore, when the H-shaped bracket is opened at the maximum angle, the insertion rod is perpendicular to the ground.

[0010] Furthermore, when the H-shaped bracket is opened at the maximum angle, the lowest point of the buffer rod is lower than the bottom end of the H-shaped bracket.

[0011] Furthermore, the buffer rod is made of rubber material.

[0012] Three technical effects

[0013] Compared with the prior art, the utility model has the following advantages:

[0014] 1. Improved the landing stability of the drone: Through the cooperation of laser rangefinders and other devices, the drone can sense the ground position more accurately, thus achieving stable landing.

[0015] 2. Enhanced cushioning effect on landing impact: The design of the H-shaped bracket and buffer mechanism effectively absorbs the impact force during landing and reduces damage to the drone body and landing area.

[0016] 3. Simple structure and easy to implement: This device adopts a relatively simple structural design, is easy to manufacture and install, has low cost and wide applicability. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a three-dimensional structure diagram of a drone landing protection device of the utility model. Figure 1 .

[0018] Figure 2 This is a three-dimensional structure diagram of a drone landing protection device of the utility model. Figure 2 .

[0019] Figure 3 The utility model is a schematic diagram of the main structure of a landing protection device for an unmanned aerial vehicle.

[0020] Figure 4 The utility model is a left-side structural schematic diagram of a landing protection device for an unmanned aerial vehicle.

[0021] Figure 5 The utility model is a schematic diagram of the structure of a landing protection device for an unmanned aerial vehicle (UAV) viewed from above.

[0022] Figure 6 It is a structural schematic diagram of the A area of ​​a UAV landing protection device of the utility model.

[0023] As shown in the figure: 1. UAV body; 2. Laser rangefinder; 3. H-shaped bracket; 4. Electric push rod; 5. Cavity; 6. Insert rod; 7. Limit plate; 8. Damper; 9. Spring; 10. Buffer rod; 301, Articulated rod; 302, Crossbeam. DETAILED DESCRIPTION

[0024] In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "inside", "outside", "center", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are merely for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation structure and operation, and therefore cannot be understood as a limitation on the present invention.

[0025] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "provided with", "installed", "connected", "connected", etc. should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection, it can be a mechanical connection, it can be an electrical connection, it can be a direct connection, it can be indirectly connected through an intermediate medium, and it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0026] The utility model is further described in detail below in conjunction with the accompanying drawings.

[0027] Example 1

[0028] Combined with Figure 1 To Attachment Figure 6 A drone landing protection device includes a drone body 1, a laser rangefinder 2 is fixedly provided at the bottom center of the drone body 1, H-shaped brackets 3 are hingedly provided on both sides of the bottom of the drone body 1, a buffer mechanism is fixedly provided inside the H-shaped brackets 3, and an electric push rod 4 is hingedly provided near the two H-shaped brackets 3 at the bottom of the drone body 1, and the piston end of the electric push rod 4 is hinged to the H-shaped bracket 3. The H-shaped bracket 3 includes two hinged rods 301 and a crossbeam 302, the two hinged rods 301 are hinged at the bottom of the drone body 1, the crossbeam 302 is fixedly provided between the two hinged rods 301, and the buffer mechanism is fixedly provided at the bottom of the crossbeam 302.

[0029] In this embodiment, the buffer mechanism includes a cavity 5 fixed at both ends of the bottom of the beam 302, and also includes an insertion rod 6 inserted at the bottom of the cavity 5. A limit plate 7 is fixed at one end of the insertion rod 6 extending into the cavity 5. A damper 8 is provided between the bottom surface of the cavity 5 and the limit plate 7. A spring 9 is provided on the outside of the damper 8. A buffer rod 10 is fixedly connected between the bottoms of the insertion rod 6.

[0030] Through the above structural design, when the drone body lands, the laser rangefinder 2 detects the height of the drone body 1 from the bottom surface. When it reaches the preset value, the electric push rod 4 is immediately started to open the H-shaped bracket 3, and the buffer mechanism contacts the ground first. Under the action of the damper and the spring, the rod is slowly inserted into the cavity to provide buffering for the landing of the drone until the two bottom ends of the H-shaped bracket 3 contact the ground. At this time, the drone body 1 relies on the two H-shaped brackets 3 and the two buffer rods 10 for support, which is stable and reliable. The automatic start of the electric push rod can be achieved by the built-in main control chip of the laser rangefinder 2, or a PLC controller can be set at the bottom of the drone body, and the electric push rod 4, the laser rangefinder 2 and the PLC controller are electrically connected and programmed by the PLC controller. The PLC controller is an existing mature technology and will not be described in detail in this technical solution.

[0031] Example 2

[0032] A drone landing protection device includes a drone body 1, a laser rangefinder 2 is fixedly provided at the bottom center of the drone body 1, H-shaped brackets 3 are hingedly provided on both left and right sides of the bottom of the drone body 1, a buffer mechanism is fixedly provided inside the H-shaped brackets 3, an electric push rod 4 is hingedly provided near the two H-shaped brackets 3 at the bottom of the drone body 1, and the piston end of the electric push rod 4 is hinged to the H-shaped bracket 3. The H-shaped bracket 3 includes two hinged rods 301 and a crossbeam 302, the two hinged rods 301 are hinged at the bottom of the drone body 1, the crossbeam 302 is fixedly provided between the two hinged rods 301, and the buffer mechanism is fixedly provided at the bottom of the crossbeam 302.

[0033] The buffer mechanism includes a cavity 5 fixed at both ends of the bottom of the beam 302, and also includes an insertion rod 6 inserted at the bottom of the cavity 5. A limit plate 7 is fixed at one end of the insertion rod 6 extending into the cavity 5. A damper 8 is provided between the bottom surface of the cavity 5 and the limit plate 7. A spring 9 is provided on the outside of the damper 8. A buffer rod 10 is fixedly connected between the bottoms of the insertion rod 6.

[0034] When the H-shaped bracket 3 opens at the maximum angle, the insertion rod 6 is perpendicular to the bottom surface. When the H-shaped bracket 3 opens at the maximum angle, the lowest point of the buffer rod 10 is lower than the bottom end of the H-shaped bracket 3. The buffer rod 10 is made of rubber material.

[0035] Compared with the previous embodiment, when the H-shaped bracket is opened to the maximum value (that is, when the electric push rod 4 is extended to the maximum value), the insertion rod 6 in the buffer mechanism is just perpendicular to the horizontal ground, and the lowest point of the buffer rod 10 is lower than the bottom end of the H-shaped bracket 3. As the drone body 1 falls, the buffer rod 10 made of rubber material first contacts the ground, and the insertion rod 6 can be extended into the cavity 5 in the vertical direction, providing a better buffering effect and avoiding poor extension and retraction of the insertion rod due to the difference between the insertion direction of the insertion rod and the force direction.

[0036] The above description of the utility model and its implementation methods is not restrictive. The drawings show only one implementation method of the utility model, and the actual structure is not limited thereto. In short, if ordinary technicians in this field are inspired by it and design structural methods and embodiments similar to the technical solution without creativity without departing from the purpose of the invention of the utility model, they should all fall within the protection scope of the utility model.

Claims

1. A drone landing protection device, comprising a drone body (1), characterized in that: A laser rangefinder (2) is fixedly provided at the center of the bottom of the drone body (1); H-shaped brackets (3) are hingedly provided on both left and right sides of the bottom of the drone body (1); a buffer mechanism is fixedly provided inside the H-shaped brackets (3); electric push rods (4) are hingedly provided near the two H-shaped brackets (3) at the bottom of the drone body (1); and a piston end of the electric push rod (4) is hingedly provided with the H-shaped brackets (3).

2. The UAV landing protection device according to claim 1, characterized in that: The H-shaped bracket (3) comprises two hinged rods (301) and a crossbeam (302), the two hinged rods (301) are hinged at the bottom of the drone body (1), the crossbeam (302) is fixedly arranged between the two hinged rods (301), and the buffer mechanism is fixedly arranged at the bottom of the crossbeam (302).

3. The UAV landing protection device according to claim 2, characterized in that: The buffer mechanism comprises a cavity (5) fixedly arranged at both ends of the bottom of the cross beam (302), and also comprises an insertion rod (6) inserted into the bottom of the cavity (5), one end of the insertion rod (6) extending into the cavity (5) is fixedly provided with a limit plate (7), a damper (8) is provided between the bottom surface of the cavity (5) and the limit plate (7), a spring (9) is sleeved on the outside of the damper (8), and a buffer rod (10) is fixedly connected between the bottoms of the insertion rod (6).

4. The UAV landing protection device according to claim 3, characterized in that: When the H-shaped bracket (3) is opened at the maximum angle, the insertion rod (6) is perpendicular to the ground.

5. The UAV landing protection device according to claim 4, characterized in that: When the H-shaped bracket (3) is opened at the maximum angle, the lowest point of the buffer rod (10) is lower than the bottom end of the H-shaped bracket (3).

6. The UAV landing protection device according to claim 5, characterized in that: The buffer rod (10) is made of rubber material.

Images