Unmanned aerial vehicle load damping device and unmanned aerial vehicle

Abstract

The utility model relates to the technical field of damping of unmanned aerial vehicles, in particular to an unmanned aerial vehicle load damping device which comprises a plurality of adjusting bolts, a plurality of connecting rods, a plurality of connecting rods, a plurality of connecting rods, a plurality of connecting rods and a plurality of connecting rods, the threaded parts of the adjusting bolts are connected to a load, and the adjusting bolts are circumferentially distributed; the elastic assembly is arranged on the adjusting bolt in a sleeving manner; a plurality of guide mounting holes are formed in the hanging plate, the guide mounting holes are arc-shaped holes, an inlet hole is formed in one end of each guide mounting hole, and the inner diameter of each inlet hole is larger than the diameter of the head of the corresponding adjusting bolt; the inner diameter of the guide mounting hole is smaller than the diameter of the head of the adjusting bolt and larger than the outer diameter of the adjusting bolt; according to the utility model, the load can be conveniently disassembled and assembled, the damping amount can be conveniently adjusted, and meanwhile, higher connection strength can be provided.

Description

A drone load shock absorption device and a drone Technical Field

[0001] This utility model relates to the field of drone vibration reduction technology, and in particular to a drone load vibration reduction device and a drone. Background Technology

[0002] Unmanned helicopter loads typically utilize rigid connections (such as bolted and pin connections) and flexible connections (such as shock-absorbing balls and wire mesh). Rigid connections are generally suitable for applications where vibration is not a critical factor and the load is relatively large. Their advantages include a strong connection between the load and the airframe, no relative displacement, good overall rigidity of the unmanned helicopter, and improved flight attitude control. However, they also have disadvantages: airframe vibration can be transmitted to the load, resulting in significant load vibration, making them unsuitable for loads with specific vibration requirements (such as electro-optical pods). Flexible connections are typically suitable for applications where vibration is a critical factor and the load is relatively light. Their advantages include: airframe vibration is isolated from the load by the damping device, maintaining stable load operation. However, they have disadvantages: lower connection strength between the load and the airframe, making the UAV's flight attitude more susceptible to interference; the damping device is not adjustable; and the load's weight must strictly correspond to the damping parameters of the device. Therefore, this application proposes a UAV load damping device. Summary of the Invention

[0003] The purpose of this invention is to provide a drone load shock absorption device to solve the problem of low connection strength in current drone load shock absorption devices.

[0004] To achieve the above objectives, this utility model provides the following technical solution:

[0005] A shock absorption device for unmanned aerial vehicle (UAV) loads, used for load shock absorption, the shock absorption device comprising:

[0006] Multiple adjusting bolts, the threaded portions of which are connected to the load, and which are arranged in a circumferential pattern;

[0007] An elastic component, which is sleeved on the adjusting bolt;

[0008] The mounting plate has multiple guide mounting holes, which are arc-shaped. One end of each guide mounting hole has an inlet hole. The inner diameter of the inlet hole is larger than the head diameter of the adjusting bolt, while the inner diameter of the guide mounting hole is smaller than the head diameter of the adjusting bolt and larger than the outer diameter of the adjusting bolt.

[0009] Furthermore, the resilient component includes:

[0010] An elastic element, which is sleeved on the adjusting bolt;

[0011] An end component, the end component being located at the end of the elastic member away from the load.

[0012] Furthermore, the elastic element is a spring, and the end component is a spring sleeve.

[0013] Furthermore, a fixing hole is provided at the end of the guide mounting hole away from the entry hole. The inner diameter of the countersunk of the fixing hole is larger than the head diameter of the adjusting bolt, and the diameter of the fixing hole is equal to the inner diameter of the guide mounting hole.

[0014] Furthermore, the distance between adjacent adjusting bolts is the same.

[0015] This utility model also discloses a drone equipped with any one of the drone load shock absorption devices described above, including:

[0016] The mounting plate is fixedly connected to the body of the machine.

[0017] Furthermore, the drone also includes:

[0018] A load support is fixedly connected between the hanging plate and the machine body. The load support is a flat plate structure and has a disassembly hole. The inner diameter of the disassembly hole is larger than the outer diameter of the circumference formed by the adjusting bolt, and the inner diameter of the disassembly hole is smaller than the diameter of the circumference formed by the connecting hole.

[0019] Furthermore, the load support is provided with wing plates at both ends, the wing plates are triangular plates, and the other side of the wing plates is fixed to the fuselage.

[0020] In summary, the present invention has the following advantages compared with the prior art:

[0021] The UAV load damping device disclosed in this embodiment connects the load by setting a hanging plate with bolts fitted with elastic components and connecting bolts, which can easily disassemble and assemble the load and adjust the damping amount, while also providing high connection strength. Attached Figure Description

[0022] Figure 1 is a structural schematic diagram of the UAV load shock absorption device disclosed in Embodiment 1 of this utility model.

[0023] Figure 2 is a schematic diagram of the structure of the hanging plate in the UAV load shock absorption device disclosed in Embodiment 1 of this utility model.

[0024] Figure 3 is a schematic diagram showing the connection between the body structure of the UAV disclosed in Embodiment 2 and the shock absorption device in Embodiment 1.

[0025] Figure label:

[0026] 10. Load; 11. Connecting seat; 20. Adjusting bolt; 30. Elastic component; 31. Elastic element; 32. End component; 40. Hanging plate; 41. Guide mounting hole; 42. Entry hole; 43. Fixing hole; 44. Connecting hole; 50. Load support; 51. Wing plate; 52. Disassembly and assembly hole; 60. Airframe. 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. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the protection scope of the present utility model.

[0028] Example 1

[0029] As shown in Figures 1 and 2, one embodiment of this utility model provides a drone load damping device for damping the load 10. The damping device includes:

[0030] A plurality of adjusting bolts 20, the threaded portions of which are connected to the load 10, and which are arranged in a circumferential pattern;

[0031] Elastic component 30, which is sleeved on the adjusting bolt 20;

[0032] The mounting plate 40 is provided with a plurality of guide mounting holes 41. The guide mounting holes 41 are arc-shaped holes. One end of the guide mounting holes 41 is provided with an inlet hole 42. The inner diameter of the inlet hole 42 is larger than the head diameter of the adjusting bolt 20. The inner diameter of the guide mounting hole 41 is smaller than the head diameter of the adjusting bolt 20 and larger than the outer diameter of the adjusting bolt 20.

[0033] In this embodiment, the load 10 is provided with a connecting seat 11 for connecting the adjusting bolt 20. The connecting seat 11 is a planar structure with a threaded hole, such as a columnar or cylindrical structure. The specific shape of the connecting seat 11 is determined by the operator based on the structure of the load 10. It is only necessary that the load 10 has a planar structure with a threaded hole. The adjusting bolt 20 is installed into the threaded hole of the connecting seat 11. The elastic component 30 is sleeved on the adjusting bolt 20. When installing the load 10, the head of the adjusting bolt 20 is inserted into the inlet hole 42. The hanging plate 40 is rotated so that the adjusting bolt 20 is located at the end of the guide mounting hole 41 away from the inlet hole 42. At this time, the hanging plate 40 presses on the end of the elastic component 30 away from the load 10. When there is vibration, the elastic component 30 absorbs the vibration by compression to achieve an ideal shock absorption effect. When it is necessary to adjust the compression of the elastic component 30, the compression of the elastic component 30 can be adjusted by rotating the adjusting bolt 20. At the same time, the adjusting bolt 20 can also connect to the load 10.

[0034] Specifically, in this embodiment, the adjusting bolt 20 is an internal hex bolt, and the elastic component 30 includes an elastic element 31 and an end component 32. The elastic element 31 is sleeved on the adjusting bolt 20 and is a spring. The end component 32 is located at the end of the elastic element 31 away from the load 10 and is a spring sleeve. The end component 32 is a cylindrical shape with openings at both ends, and one end of the end component 32 is annular. The end component 32 is inserted into the elastic element 31.

[0035] In other embodiments of this example, the elastic component 30 may also be of other structures, such as the elastic element 31 being an elastic rubber sleeve and the end component 32 being a gasket structure.

[0036] In this embodiment, the end component 32 is located between the elastic member 31 and the hanging plate 40, which reduces the friction between the elastic member 31 and the hanging plate 40.

[0037] As shown in Figure 2, the mounting plate 40 is a ring structure, the guide mounting hole 41 is an arc-shaped waist-shaped hole provided on the mounting plate 40, the entry hole 42 is a round hole, the inner diameter of the entry hole 42 is smaller than the outer diameter of the end component 32, and the outer edge of the mounting plate 40 is provided with a connecting hole 44, which is used to connect the drone. In this embodiment, there are two adjusting bolts 20 and two guide mounting holes 41.

[0038] Preferably, the distance between adjacent adjusting bolts 20 is the same, that is, the plurality of adjusting bolts 20 are evenly distributed in a circumferential shape.

[0039] In a preferred embodiment of this example, a fixing hole 43 is provided at the end of the guide mounting hole 41 away from the entry hole 42. The inner diameter of the countersunk surface of the fixing hole 43 is larger than the head diameter of the adjusting bolt 20, and the diameter of the fixing hole 43 is equal to the inner diameter of the guide mounting hole 41. When fixing the adjusting bolt 20, the head of the adjusting bolt 20 is inserted into the fixing hole 43. When disassembling the load 10, the load 10 is pressed to disengage from the fixing hole 43, and then the load 10 is rotated in the opposite direction to move the adjusting bolt 20 to the entry hole 42, thereby disassembling the load 10.

[0040] Example 2

[0041] As shown in Figure 3, as another embodiment 1 of this utility model, this embodiment also discloses a drone, which includes a body 60 and a mounting plate 40 fixedly connected to the body 60.

[0042] As a preferred embodiment of this invention, as shown in Figure 3, a load support 50 is also provided between the hanging plate 40 and the body 60. The load support 50 is fixedly connected to the body 60, and the hanging plate 40 is fixedly connected to the load support 50. The load support 50 is a flat plate structure, and a disassembly hole 52 is provided on the load support 50. The inner diameter of the disassembly hole 52 is larger than the outer diameter of the circumference formed by the adjusting bolt 20, and the inner diameter of the disassembly hole 52 is smaller than the diameter of the circumference formed by the connecting hole 44.

[0043] As a preferred embodiment of this invention, as shown in FIG3, the load support 50 is provided with wing plates 51 at both ends. The wing plates 51 are triangular plates, and the other side of the wing plates 51 is fixed to the body 60. In this embodiment, the wing plates 51 and the load support 50 are an integral structure, and the body 60 and the wing plates 51 are fixedly connected by anti-loosening bolts.

[0044] In other embodiments of this example, the wing plate 51 and the load support 50 may be connected in other ways, such as by screws or welding.

[0045] The terminology used in this invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The singular forms “a,” “the,” and “the” used in this invention and the appended claims are also intended to include the plural forms unless the context clearly indicates otherwise. It should also be understood that the term “and / or” as used herein refers to and includes any or all possible combinations of one or more of the associated listed items.

[0046] It should be understood that although the terms first, second, third, etc., may be used in this invention to describe various information, this information should not be limited to these terms. These terms are only used to distinguish information of the same type from one another. For example, without departing from the scope of this invention, first information may also be referred to as second information, and similarly, second information may also be referred to as first information. Depending on the context, the word "if" as used herein may be interpreted as "when," "when," or "in response to determination."

[0047] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A shock absorption device for unmanned aerial vehicle (UAV) loads, used for shock absorption of loads (10), characterized in that, The shock absorption device includes: multiple adjusting bolts (20), the threaded portions of which are connected to the load (10), and the multiple adjusting bolts (20) are circumferentially distributed; an elastic component (30), which is sleeved on the adjusting bolts (20); and a mounting plate (40), which has multiple guide mounting holes (41), the guide mounting holes (41) being arc-shaped holes, one end of which has an inlet hole (42), the inner diameter of which is larger than the head diameter of the adjusting bolt (20), and the inner diameter of which is smaller than the head diameter of the adjusting bolt (20) and larger than the outer diameter of the adjusting bolt (20).

2. The UAV load damping device according to claim 1, characterized in that, The elastic component (30) includes: an elastic element (31) sleeved on the adjusting bolt (20); and an end member (32) located at the end of the elastic element (31) away from the load (10).

3. The UAV load shock absorption device according to claim 2, characterized in that, The elastic element (31) is a spring, and the end component (32) is a spring sleeve.

4. The UAV load damping device according to claim 2, characterized in that, A fixing hole (43) is provided at one end of the guide mounting hole (41) away from the entry hole (42). The inner diameter of the countersunk of the fixing hole (43) is larger than the head diameter of the adjusting bolt (20), and the diameter of the fixing hole (43) is equal to the inner diameter of the guide mounting hole (41).

5. The UAV load damping device according to claim 1, characterized in that, The distance between adjacent adjusting bolts (20) is the same.

6. A drone, characterized in that, The device is equipped with a drone load shock absorption device according to any one of claims 1-5, comprising: a body (60), wherein the mounting plate (40) is fixedly connected to the body (60).

7. The UAV according to claim 6, characterized in that, The drone also includes a load support (50), which is fixedly connected between the mounting plate (40) and the body (60). The load support (50) is a flat plate structure and has a disassembly hole (52). The inner diameter of the disassembly hole (52) is larger than the outer diameter of the circumference formed by the adjusting bolt (20).

8. The UAV according to claim 7, characterized in that, The load support (50) is provided with wing plates (51) at both ends. The wing plates (51) are triangular plates, and the other side of the wing plates (51) is fixed to the body (60).

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