A damping rubber bushing for a drone rotor system

Abstract

The utility model discloses a kind of unmanned aerial vehicle rotor system damper rubber bushings, it is related to unmanned aerial vehicle rotor damping technical field, including the first connecting part and the second connecting part of each other inlaying connection, the side of second connecting part to first connecting part is fixed and arranged with extension, the outer edge surface of extension and the inner edge surface of first connecting part are attached;The end of first connecting part away from second connecting part is equipped with first connecting assembly, first connecting assembly is connected with rotor shaft, the end of second connecting part away from first connecting part is equipped with second connecting assembly, second connecting assembly is connected with rotor body;Wherein, second connecting assembly and second connecting part between are equipped with elastic module, to absorb the vibration energy when rotor body rotates;When driving rotor shaft rotates, rotor shaft in the process of synchronous driving rotor body rotation, the energy between rotor body and rotor shaft can be absorbed by the elastic module arranged, improve the stability of rotor and complete machine.

Description

Technical Field

[0001] This utility model relates to the field of rotor damping technology for unmanned aerial vehicles (UAVs), and in particular to a rubber bushing for a damper in a UAV rotor system. Background Technology

[0002] The rubber bushing of the rotor system of a UAV is an elastic element installed at the connection between the rotor and the hub. Its core function is to absorb the vibration generated by the rotor rotation through the damping properties of the rubber material, reduce the vibration transmitted to the fuselage, and improve flight stability and structural safety.

[0003] Rubber bushings are typically composed of a rubber elastomer and a metal or composite material skeleton, forming a "rubber-metal" laminated structure. For example: spherical elastic bearings: through the alternating bonding of rubber and metal layers, a flexible connection between the rotor and the hub is achieved, which can withstand the centrifugal force of the blades while allowing the blades to flap and oscillate; oscillation dampers: the rubber bushing acts as a damping source, working in conjunction with metal components to absorb blade oscillation energy through shear deformation, suppressing high-frequency vibrations.

[0004] Currently, vibration reduction designs for UAV rotor systems primarily employ rubber bushings or metal springs as dampers. Traditional rubber bushings are often made of silicone or fluororubber, absorbing vibration energy through elastic deformation. However, existing technologies have the following shortcomings: 1. Uneven stress distribution: Existing rubber bushings are prone to local stress concentration when subjected to high-frequency vibration, which shortens their service life; 2. Dynamic response hysteresis: The damping coefficient of the existing rubber bushing is fixed and cannot adapt to the vibration frequency changes of the UAV under different flight conditions. Utility Model Content

[0005] This utility model provides a damper rubber bushing for a drone rotor system, which can solve the following problems existing in the prior art: 1) Existing rubber bushings are prone to localized stress concentration when subjected to high-frequency vibration, which shortens their service life; 2) Dynamic response hysteresis: The damping coefficient of the existing rubber bushing is fixed and cannot adapt to the vibration frequency changes of the UAV under different flight conditions.

[0006] A damper rubber bushing for a drone rotor system includes a first connecting part and a second connecting part that are interlocked and connected to each other. An extension is fixedly provided on the side of the second connecting part that is close to the first connecting part, and the outer edge of the extension is in contact with the inner edge of the first connecting part. The first connecting part is provided with a first connecting component at the end away from the second connecting part, and the first connecting component is connected to the rotor shaft. The second connecting part is provided with a second connecting component at the end away from the first connecting part, and the second connecting component is connected to the rotor body. An elastic module is provided between the second connecting component and the second connecting part to absorb the vibration energy when the rotor body rotates.

[0007] Preferably, the elastic module includes a support cylinder coaxially arranged in the second connecting part, one end of the support cylinder being connected to the second connecting assembly, and the other end extending into the first connecting part; The bearing cylinder is fitted with an elastic bushing, and the outer edge of the elastic bushing is fixedly connected to the second connecting part and the inner edge of the extension part.

[0008] Preferably, annular cavities are formed on both axial sides of the elastic bushing.

[0009] As the annular cavity extends axially towards both ends, its cross-sectional dimensions gradually increase.

[0010] Preferably, the first connecting portion is configured in a trumpet shape, and the second connecting portion and the extension portion are configured in a cylindrical shape, with their inner diameters being equal to the inner diameters of the second connecting portion.

[0011] Preferably, the elastic bushing is fixedly connected to the bearing cylinder, the second connecting part, and the extension part by means of adhesive bonding.

[0012] Preferably, a first limiting part is fixedly provided at the end of the first connecting part, and a second limiting part that cooperates with and connects with the first limiting part is correspondingly fixedly provided on the second connecting part; The first limiting part has several sets of first positioning holes, and the second limiting part has several sets of second positioning holes. Metal wires are threaded through the first positioning holes and the second positioning holes to bind and fix the first limiting part and the second limiting part.

[0013] Preferably, a first limiting cylinder is fixedly provided at the end of the first connecting portion away from the first limiting portion; The first connecting assembly includes a first bearing rod that is helically connected to the first limiting cylinder. A first connecting ring is fixedly arranged at the end of the first bearing rod away from the first limiting cylinder. The first connecting ring is fixedly connected to the rotor shaft by fastening bolts.

[0014] Preferably, a second limiting cylinder is fixedly arranged at the end of the bearing cylinder away from the first connecting part, and the second connecting assembly includes a second bearing rod that is helically connected to the second limiting cylinder. A second connecting ring is fixedly arranged at the end of the second bearing rod away from the second limiting cylinder, and the second connecting ring is fixedly connected to the rotor body by fastening bolts.

[0015] Preferably, the first bearing rod is provided with a first locking nut screwed on it, and the first locking nut abuts against the end of the first limiting cylinder; the second bearing rod is provided with a second locking nut screwed on it, and the second locking nut abuts against the end of the second limiting cylinder.

[0016] Preferably, the ends of the limiting cylinders on both sides that are close to the locking nut are respectively provided with several sets of through first limiting holes, and the locking nut is provided with several sets of through second limiting holes. Metal wires are passed through the first limiting holes and the second limiting holes to bind and fix the limiting cylinders and the locking nut.

[0017] This utility model provides a rubber bushing for a damper in a drone rotor system, which has the following advantages: 1) By setting the first connecting component and the second connecting component, the damper can be installed between the rotor shaft and the rotor body. When the rotor shaft is driven to rotate, the rotor shaft can absorb the energy between the rotor body and the rotor shaft through the elastic module during the synchronous drive of the rotor body to rotate, thereby improving the stability of the rotor and the whole machine. 2) By setting an elastic bushing with elasticity between the bearing cylinders, the vibration force of the rotor body is transmitted to the bearing cylinder through the second connecting component during the rotation of the rotor body. The elastic bushing can absorb the vibration transmitted by the bearing cylinder, achieve the effect of vibration reduction, and ensure the stability of the rotor body during rotation. 3) By opening annular cavities at both ends of the elastic bushing, this utility model can further reduce the radial stiffness at both ends of the elastic bushing. This allows the second connecting component to further absorb vibration energy through the annular cavities during the transmission of vibration to the bearing cylinder, avoiding local stress concentration when subjected to high-frequency vibration and extending service life. At the same time, during the compression of the elastic bushing, the annular cavity can deform and adaptively adjust the damping coefficient to match the vibration frequency of the rotor body at different speeds. Furthermore, the annular cavity can evenly disperse local stress, preventing material fatigue fracture. 4) This utility model fixes the first bearing rod and the first limiting cylinder by a spiral connection, and fixes the first connecting ring to the rotor shaft by a bolt connection, thereby facilitating disassembly and replacement. Attached Figure Description

[0018] Figure 1 A three-dimensional structural diagram of a rubber bushing for a damper in a drone rotor system provided by this utility model. Figure 1 ; Figure 2 A three-dimensional structural diagram of a rubber bushing for a damper in a drone rotor system provided by this utility model. Figure 2 ; Figure 3 An exploded structural diagram of a rubber bushing for a damper in a drone rotor system provided by this utility model; Figure 4An exploded cross-sectional view of a rubber bushing for a damper in a drone rotor system provided by this utility model; Figure 5 A cross-sectional structural diagram of a rubber bushing for a damper in a drone rotor system provided by this utility model; Figure 6 A schematic diagram of the internal structure of a rubber bushing for a damper in a drone rotor system provided by this utility model; Figure 7 A schematic diagram of the structure of the elastic bushing in the damper rubber bushing of a UAV rotor system provided by this utility model; Figure 8 This utility model provides a structural schematic diagram of the installation of a rubber bushing for a damper in a drone rotor system.

[0019] Explanation of reference numerals in the attached figures: 1. First connecting part; 2. Second connecting part; 3. First bearing rod; 4. Bearing cylinder; 5. Elastic bushing; 6. Second limiting hole; 101. First limiting part; 102. First limiting cylinder; 103. First positioning hole; 201. Second limiting part; 202. Extension part; 203. Second positioning hole; 301. First connecting ring; 302. First locking nut; 401. Second limiting cylinder; 402. Second bearing rod; 403. Second connecting ring; 404. Second locking nut; 501. Annular cavity; 601. First limiting hole. Detailed Implementation

[0020] The specific embodiments of this utility model are described in detail below, but it should be understood that the protection scope of this utility model is not limited to the specific embodiments.

[0021] Example 1 like Figures 1 to 4 As shown in the figure, the present invention provides a rubber bushing for a damper of a drone rotor system, including a first connecting part 1 and a second connecting part 2 that are fitted together. The first connecting part 1 is arranged in a trumpet shape, and the second connecting part 2 is arranged in a cylindrical shape. An extension 202 is fixedly arranged on the side of the second connecting part 2 that is close to the first connecting part 1. The extension 202 is cylindrical, and its inner diameter is equal to that of the second connecting part 2. The outer edge of the extension 202 is in contact with the inner edge of the first connecting part 1. Specifically, this embodiment does not limit the specific dimensions of the first connecting part 1 and the second connecting part 2, as long as they meet the actual application requirements.

[0022] In one embodiment of this invention, the first connecting portion 1 has a first connecting component at its end away from the second connecting portion 2, and the first connecting component is connected to the rotor shaft. The second connecting portion 2 has a second connecting component at its end away from the first connecting portion 1, and the second connecting component is connected to the rotor body (see reference...). Figure 8 ); Among them, an elastic module is provided between the second connecting component and the second connecting part 2 to absorb the vibration energy when the rotor body rotates; Specifically, in this embodiment, the damper can be installed between the rotor shaft and the rotor body through the first connecting component and the second connecting component. When the rotor shaft is driven to rotate, the rotor shaft can absorb the energy between the rotor body and the rotor shaft through the deployed elastic module during the synchronous rotation of the rotor body, thereby improving the stability of the rotor and the whole machine.

[0023] Example 2 Based on Example 1, please refer to Figures 3-7 The elastic module includes a support cylinder 4 coaxially arranged in the second connecting part 2. One end of the support cylinder 4 is connected to the second connecting component, and the other end extends into the first connecting part 1. An elastic bushing 5 is sleeved on the support cylinder 4. The outer edge of the elastic bushing 5 is fixedly connected to the inner edge of the second connecting part 2 and the extension part 202. It can be noted that, in this embodiment, by setting an elastic bushing 5 between the support cylinders 4, the vibration force of the rotor body is transmitted to the support cylinder 4 through the second connecting component during rotation. The elastic bushing 5 can absorb the vibration transmitted by the support cylinder 4, achieve the effect of vibration reduction, and ensure the stability of the rotor body during rotation.

[0024] It should also be noted that the elastic bushing 5 in this embodiment can be made of silicone material. In addition, it can also be made of acrylic rubber (ACM) or hydrogenated nitrile rubber (HNBR). This embodiment does not limit the specific materials used, as long as they meet the actual application requirements.

[0025] In addition, the damper in this embodiment is 60% lighter than that of a metal spring damper, which can further improve the drone's endurance.

[0026] As a further solution in this embodiment, please refer to Figures 6-7The elastic bushing 5 has annular cavities 501 on both sides of its axial direction. As it extends axially towards both ends, the cross-sectional dimensions of the annular cavities 501 gradually increase. It can be noted that by opening annular cavities 501 at both ends of the elastic bushing 5, the radial stiffness at both ends of the elastic bushing 5 can be further reduced. This allows the second connecting assembly to absorb vibration energy through the annular cavities 501 during the transmission of vibration to the bearing cylinder 4, avoiding local stress concentration when subjected to high-frequency vibration and extending its service life. At the same time, during the compression of the elastic bushing 5, the annular cavity 501 can deform and adaptively adjust the damping coefficient to match the vibration frequency of the rotor body at different speeds. Furthermore, the annular cavity can uniformly disperse local stress, preventing material fatigue fracture.

[0027] Accordingly, the damping angle of the elastic bushing 5 in this embodiment is 16°-18°, which is suitable for high-frequency vibration of the wing body.

[0028] In this embodiment, the elastic bushing 5 is fixedly connected to the bearing cylinder 4, the second connecting part 2, and the extension part 202 by adhesive bonding. It can be noted that in this embodiment, adhesive is used to bond the elastic bushing 5 to the bearing cylinder 4, the second connecting part 2, and the extension part 202. The bonding performance parameters are shown in the table below.

[0029] In addition, the axial dynamic stiffness of the damper in this embodiment is 1.0527×106N / m±10%, and the maximum displacement amplitude is 4.75mm (reference load is 5000N).

[0030] (5) When the axial load frequency is 9.67 Hz, the damping coefficient of the viscoelastic damper is 5299 Ns / m ± 10%; when the axial load frequency is 5.125 Hz, the damping coefficient of the viscoelastic damper is 9813 Ns / m ± 10%. Please see Figures 1-4 In order to fix the first connecting part 1 and the second connecting part 2, in this embodiment, the end of the first connecting part 1 is fixedly provided with a first limiting part 101, and the second connecting part 2 is correspondingly fixedly provided with a second limiting part 201 that cooperates with and connects to the first limiting part 101. The first limiting part 101 is provided with a plurality of first positioning holes 103, and the second limiting part 201 is provided with a plurality of second positioning holes 203. Metal wires are passed through the first positioning holes 103 and the second positioning holes 203 to bind and fix the first limiting part 101 and the second limiting part 201. It can be noted that when connecting the first connecting part 1 and the second connecting part 2, a plurality of metal wires can be passed between the first positioning holes 103 and the second positioning holes 203 respectively, and the fixed connection of the first limiting part 101 and the second limiting part 201 can be achieved by binding. In addition, the first limiting part 101 and the second limiting part 201 implemented in this city can also be connected by bolt fixing. This embodiment does not limit this, as long as it meets the actual application requirements.

[0031] In this embodiment, a first limiting cylinder 102 is fixedly arranged at one end of the first connecting part 1 away from the first limiting part 101. The first connecting assembly includes a first bearing rod 3 that is helically connected to the first limiting cylinder 102. A first connecting ring 301 is fixedly arranged at one end of the first bearing rod 3 away from the first limiting cylinder 102. The first connecting ring 301 is fixedly connected to the rotor shaft by fastening bolts. It can be noted that in this embodiment, by fixing the first bearing rod 3 and the first limiting cylinder 102 by a helium connection and fixing the first connecting ring 301 to the rotor shaft by a bolt connection, it is easy to disassemble and replace. Accordingly, you may refer to Figures 2-5 A second limiting cylinder 401 is fixedly arranged at one end of the bearing cylinder 4 away from the first connecting part 1. The second connecting assembly includes a second bearing rod 402 that is helically connected to the second limiting cylinder 401. A second connecting ring 403 is fixedly arranged at one end of the second bearing rod 402 away from the second limiting cylinder 401. The second connecting ring 403 is fixedly connected to the rotor body by fastening bolts. It can be noted that in this embodiment, by fixing the second bearing rod 402 and the second limiting cylinder 401 by a helically connected manner, and fixing the second connecting ring 403 to the rotor body by a bolted manner, the convenience of disassembly and assembly is further improved.

[0032] In this embodiment, to prevent mechanical vibration or impact from causing relative slippage between the threads of the bearing rod and the limiting cylinder, resulting in loss of preload, please refer to [reference needed]. Figures 1-4 A first locking nut 302 is helically sleeved on the first bearing rod 3, and the first locking nut 302 abuts against the end of the first limiting cylinder 102. A second locking nut 404 is helically sleeved on the second bearing rod 402, and the second locking nut 404 abuts against the end of the second limiting cylinder 401. It can be explained that by helically sleeved locking nuts on the bearing rod, the connection stability between the bearing rod and the limiting cylinder is further improved, and the phenomenon of relative sliding between the bearing rod and the limiting cylinder is avoided. In addition, you can refer to Figure 1Several sets of through first limiting holes 601 are respectively opened at the ends of the limiting cylinders on both sides near the locking nut, and several sets of through second limiting holes 6 are correspondingly opened on the locking nut. Metal wires are passed through the first limiting holes 601 and the second limiting holes 6 to bind and fix the limiting cylinders and the locking nut. It can be noted that after the locking nut and the limiting cylinder are spirally connected, the locking nut and the limiting cylinder can be fixedly connected by passing several sets of metal wires through the corresponding first limiting holes 601 and second limiting holes 6 and binding them.

[0033] A method for installing a rubber bushing of a damper in a UAV rotor system includes the following steps: Please see Figures 1-4 S1. The first connecting part 1 and the second connecting part 2 are fixedly connected by the first limiting part 101 and the second limiting part 201. S2. The first bearing rod 3 and the first limiting cylinder 102 are fixed by a screw connection, and the first connecting ring 301 is fixed to the rotor shaft by a bolt connection. S3. Fix the second bearing rod 402 and the second limiting cylinder 401 by means of a spiral connection, and fix the second connecting ring 403 to the rotor body by means of a bolt connection.

[0034] The above-disclosed embodiments are only a few specific examples of the present utility model. However, the embodiments of the present utility model are not limited thereto. Any changes that can be conceived by those skilled in the art should fall within the protection scope of the present utility model.

Claims

1. A damper rubber bushing for a UAV rotor system, characterized in that, It includes a first connecting part (1) and a second connecting part (2) that are interlocked and connected. The second connecting part (2) is provided with an extension part (202) on the side of the first connecting part (1) and the outer edge of the extension part (202) is in contact with the inner edge of the first connecting part (1). The first connecting part (1) is provided with a first connecting component at one end away from the second connecting part (2), and the first connecting component is connected to the rotor shaft. The second connecting part (2) is provided with a second connecting component at one end away from the first connecting part (1), and the second connecting component is connected to the rotor body. Among them, an elastic module is provided between the second connecting component and the second connecting part (2) to absorb the vibration energy when the rotor body rotates.

2. A drone rotor system damper rubber bushing as claimed in claim 1, wherein, The elastic module includes a bearing cylinder (4) coaxially arranged in the second connecting part (2), one end of the bearing cylinder (4) is connected to the second connecting component, and the other end extends into the first connecting part (1); The bearing cylinder (4) is fitted with an elastic bushing (5), and the outer edge of the elastic bushing (5) is fixedly connected to the inner edge of the second connecting part (2) and the extension part (202).

3. A drone rotor system damper rubber bushing as claimed in claim 2, wherein, The elastic bushing (5) has annular cavities (501) on both sides of its axial direction. As the annular cavity (501) extends axially towards both ends, its cross-sectional dimensions gradually increase.

4. The rubber bushing for a damper of a UAV rotor system as described in claim 1, characterized in that, The first connecting part (1) is provided in a trumpet-shaped structure, and the second connecting part (2) and the extension part (202) are provided in a cylindrical structure, with their inner diameter being equal to that of the second connecting part (2).

5. A drone rotor system damper rubber bushing as claimed in claim 2, wherein, The elastic bushing (5) is fixedly connected to the bearing cylinder (4), the second connecting part (2) and the extension part (202) by means of adhesive bonding.

6. A drone rotor system damper rubber bushing as claimed in claim 5, wherein, The first connecting part (1) is fixedly provided with a first limiting part (101) at its end, and the second connecting part (2) is correspondingly fixedly provided with a second limiting part (201) that cooperates with and connects to the first limiting part (101). The first limiting part (101) is provided with a number of first positioning holes (103), and the second limiting part (201) is provided with a number of second positioning holes (203). Metal wires are passed through the first positioning holes (103) and the second positioning holes (203) to bind and fix the first limiting part (101) and the second limiting part (201).

7. A drone rotor system damper rubber bushing as claimed in claim 6, wherein, The first connecting part (1) is fixedly provided with a first limiting cylinder (102) at the end away from the first limiting part (101); The first connecting assembly includes a first bearing rod (3) that is helically connected to the first limiting cylinder (102). A first connecting ring (301) is fixedly arranged at one end of the first bearing rod (3) away from the first limiting cylinder (102). The first connecting ring (301) is fixedly connected to the rotor shaft by fastening bolts.

8. A drone rotor system damper rubber bushing as claimed in claim 7, wherein, The bearing cylinder (4) is fixedly provided with a second limiting cylinder (401) at one end away from the first connecting part (1). The second connecting assembly includes a second bearing rod (402) that is spirally connected to the second limiting cylinder (401). A second connecting ring (403) is fixedly provided at one end of the second bearing rod (402) away from the second limiting cylinder (401). The second connecting ring (403) is fixedly connected to the rotor body by fastening bolts.

9. A drone rotor system damper rubber bushing as claimed in claim 8, wherein, The first bearing rod (3) is provided with a first locking nut (302) screwed on it, and the first locking nut (302) abuts against the end of the first limiting cylinder (102). The second bearing rod (402) is provided with a second locking nut (404) screwed on it, and the second locking nut (404) abuts against the end of the second limiting cylinder (401).

10. A drone rotor system damper rubber bushing as claimed in claim 9, wherein, Several sets of through first limiting holes (601) are respectively opened at the ends of the limiting cylinders on both sides that are close to the locking nut. Several sets of through second limiting holes (6) are correspondingly opened on the locking nut. Metal wires are passed through the first limiting holes (601) and the second limiting holes (6) to bind and fix the limiting cylinders and the locking nut.

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