A gimbal damping device based on a high-damping honeycomb core composite structure

Abstract

This invention discloses a gimbal vibration damping device based on a high-damping honeycomb core composite structure, relating to the field of unmanned aerial vehicle (UAV) technology. It includes an upper damping plate, a lower damping plate, a honeycomb damping unit, and a damping connection unit. The upper damping plate is used to connect to the UAV body; the lower damping plate is used to mount airborne equipment; the damping connection unit is disposed between the upper and lower damping plates, with both ends connected to the upper and lower damping plates respectively; the honeycomb damping unit is disposed between the upper and lower damping plates, arranged side-by-side with the damping connection unit, and located within the entire... The centroid region of the gimbal vibration damping device based on a high-damping honeycomb core composite structure; the two ends of the honeycomb vibration damping unit are connected to the upper and lower vibration damping plates respectively. The honeycomb vibration damping unit is made of a material used to provide damping loss factor in the low frequency band, and honeycomb cells are densely arranged on the honeycomb vibration damping unit. The honeycomb cells are used for elastic deformation in the high frequency band. The gimbal vibration damping device based on the high-damping honeycomb core composite structure can significantly improve the overall structure's broadband vibration damping effect through a dual-path coupling damping mechanism of honeycomb vibration damping unit and vibration damping connection unit.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a gimbal vibration reduction device based on a high-damping honeycomb core composite structure. Background Technology

[0002] With the increasing maturity of drone technology, the payload and endurance of multi-rotor drones have been rapidly improved, and they are widely used in civilian and military fields such as power line inspection, aerial reconnaissance, and real-time target tracking and monitoring.

[0003] A drone gimbal is a support device used by drones to mount and fix mission payloads such as cameras. It is characterized by the diversity of materials and the complexity of its structure. Its function is to achieve stable observation of specific targets while isolating the impact of aircraft vibration and attitude maneuvers on image quality. It can keep long-focal-length cameras in a stable position in unstable environments through the gimbal device, minimizing the impact of external interference on the acquired data or information.

[0004] Because drones are subject to their own vibrations and significant environmental interference during flight, the vision system is unable to capture clear images and videos. In this system, gimbal performance is crucial for the stable operation of the vision system.

[0005] Most existing drone gimbal vibration reduction devices mitigate vibration by utilizing elastic structures such as rubber damping balls. While these balls offer significant buffering against high-frequency vibrations, their effectiveness is less pronounced during drone flight due to low-frequency vibrations caused by strong winds. Furthermore, while existing gimbal vibration reduction structures can influence overall vibration reduction by altering the number, distribution, and shape of the damping balls, they suffer from the following drawbacks: 1. Under prolonged alternating loads (especially under alternating high and low temperatures or high-frequency vibration conditions), the rubber damping balls connecting the gimbal and the drone are prone to stress fatigue cracking. During flight, crack propagation leads to a reduction in the effective load-bearing cross-section of the damping balls, triggering a domino effect of failure: after a single ball breaks, the load on the remaining damping balls increases sharply by 50%-80% (finite element simulation data), causing an imbalance in system stiffness distribution and stress concentration, potentially leading to the gimbal detaching from the drone body in extreme cases. 2. Some gimbals adopt a static strength redundancy design in an attempt to improve stability, but this has instead triggered a series of negative effects. This approach not only increases the rotational inertia of various parts of the gimbal, but also causes the power consumption of the drive motor to rise, significantly shortening the drone's flight time. Summary of the Invention

[0006] The purpose of this invention is to provide a gimbal vibration reduction device based on a high-damping honeycomb core composite structure to solve the problems existing in the prior art. The gimbal vibration reduction device based on the high-damping honeycomb core composite structure can significantly improve the overall structure's broadband vibration reduction effect through a dual-path coupling damping mechanism of honeycomb vibration reduction unit and vibration reduction connection unit.

[0007] To achieve the above objectives, the present invention provides the following solution: The present invention provides a gimbal vibration reduction device based on a high-damping honeycomb core composite structure, including an upper vibration reduction plate, a lower vibration reduction plate, a honeycomb vibration reduction unit, and a vibration reduction connection unit;

[0008] The upper damping plate is used to connect the drone body;

[0009] The lower damping plate is used to mount airborne equipment;

[0010] The vibration damping connection unit is disposed between the upper vibration damping plate and the lower vibration damping plate, and both ends of the vibration damping connection unit are respectively connected to the upper vibration damping plate and the lower vibration damping plate;

[0011] The honeycomb vibration damping unit is disposed between the upper vibration damping plate and the lower vibration damping plate, and is arranged side by side with the vibration damping connection unit. It is located in the centroid region of the entire gimbal vibration damping device based on the high-damping honeycomb core composite structure. The two ends of the honeycomb vibration damping unit are respectively connected to the upper vibration damping plate and the lower vibration damping plate. The honeycomb vibration damping unit is made of a material that provides a damping loss factor in the low-frequency band, and honeycomb cells are densely arranged on the honeycomb vibration damping unit. The honeycomb cells are used for elastic deformation in the high-frequency band.

[0012] Preferably, the cellular vibration damping unit has multiple vibration damping layers, each of which is arranged and connected sequentially along the arrangement direction of the upper and lower vibration damping plates, and the vibration damping layers located on both sides are respectively connected to the upper and lower vibration damping plates, and each of the vibration damping layers has an array of cellular cells.

[0013] Preferably, the damping layers on both sides are each connected to the upper damping plate and the lower damping plate by a plurality of flexible damping columns.

[0014] Preferably, the damping layer includes a honeycomb cell array arranged in the same straight line direction, the honeycomb cell array including a first honeycomb cell row and a second honeycomb cell row arranged along the array direction of each of the honeycomb cell arrays, the first honeycomb cell row and the second honeycomb cell row extending in a direction perpendicular to each of the honeycomb cell arrays;

[0015] Both the first and second cell rows include the cell cells arrayed along their extension direction. A first connecting piece connects adjacent cell cells in the first cell row, and a second connecting piece connects adjacent cell cells in the second cell row. Each first connecting piece in the first cell row is connected to each cell cell in the second cell row, and each second connecting piece in the second cell row is connected to each cell cell in the first cell row. Adjacent cell groups are connected to each other via corresponding cell cells and either the first or second connecting piece.

[0016] The first connecting piece and the second connecting piece are spaced apart along the thickness direction of the damping layer.

[0017] Preferably, the honeycomb cells have a regular polygonal structure, and the honeycomb cells in the damping layer are evenly distributed.

[0018] Preferably, the cellular damping units are all made of shape memory alloy, which is used to provide a damping loss factor in the low-frequency range.

[0019] Preferably, the vibration damping connection unit includes a plurality of vibration damping balls with a flexible structure, each vibration damping ball being evenly distributed between the upper vibration damping plate and the lower vibration damping plate, and both ends of the vibration damping ball being connected to the upper vibration damping plate and the lower vibration damping plate, respectively.

[0020] Preferably, the honeycomb vibration damping unit is located at the middle position between the upper vibration damping plate and the lower vibration damping plate, and each of the vibration damping balls is evenly surrounding the outer periphery of the honeycomb vibration damping unit.

[0021] Preferably, the damping ball has a hollow structure and is filled with damping fluid.

[0022] Preferably, the damping ball is provided with an upper stop and a lower stop at both ends of the upper damping plate and the lower damping plate, respectively, and the damping ball is connected to the upper stop and the lower stop respectively.

[0023] The upper damping plate and the lower damping plate are respectively provided with a plurality of mounting holes. The connecting parts at both ends of the damping ball pass through the mounting holes on the upper damping plate and the lower damping plate respectively. The upper stop and the lower stop respectively abut against the side of the upper damping plate and the lower damping plate away from the damping ball, and the damping ball abuts between the upper damping plate and the lower damping plate.

[0024] The present invention achieves the following technical effects compared to the prior art:

[0025] This invention discloses a gimbal vibration reduction device based on a high-damping honeycomb core composite structure, which mainly targets the wide-frequency vibration spectrum characteristics (low-frequency rotor vibration 0.1-50Hz, high-frequency motor harmonics 1-5kHz) present in UAV operations. This invention employs an impedance matching design between the vibration reduction connection unit and the honeycomb vibration reduction unit to form a segmented frequency domain damping response. In the low-frequency range (<100Hz): because the honeycomb vibration reduction unit is made of a material designed to provide a damping loss factor in the low-frequency range, it effectively dissipates large-amplitude low-frequency energy, and works in conjunction with the vibration reduction connection unit to further dissipate this energy. In the high-frequency range (>500Hz): the honeycomb vibration reduction unit reduces dynamic stiffness through elastic deformation of the honeycomb cells, avoiding high-frequency resonance transmission, and works in conjunction with the vibration reduction connection unit to effectively dissipate high-frequency vibration energy. As described above, the gimbal vibration reduction device based on the high-damping honeycomb core composite structure can significantly improve the overall structure's broadband vibration reduction effect and comprehensively achieve vibration isolation through the dual-path coupling damping mechanism of the vibration reduction connection unit and the honeycomb vibration reduction unit. Attached Figure Description

[0026] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0027] Figure 1 This is an exploded view of the overall structure in one embodiment of the present invention;

[0028] Figure 2 This is a top view of the overall structure in one embodiment of the present invention;

[0029] Figure 3 This is a side view of the overall structure in one embodiment of the present invention;

[0030] Figure 4 This is a schematic diagram of the overall structure of the honeycomb vibration damping unit in one embodiment of the present invention;

[0031] Figure 5 This is a top view of a honeycomb vibration damping unit according to an embodiment of the present invention;

[0032] Figure 6 This is a side view of a honeycomb vibration damping unit according to an embodiment of the present invention;

[0033] Figure 7 This is a schematic diagram of the structure of the damping ball in one embodiment of the present invention;

[0034] Figure 8 This is a cross-sectional view of the damping ball in one embodiment of the present invention;

[0035] Figure 9 This is a schematic diagram of the structure of a flexible vibration damping column in one embodiment of the present invention;

[0036] Figure 10 This is a cross-sectional view of a flexible vibration damping column according to an embodiment of the present invention;

[0037] Among them, 1-upper damping plate, 2-flexible damping column, 3-honeycomb damping unit, 4-dampening connection unit, 5-lower damping plate, 6-dampening ball, 7-upper stop, 8-lower stop, 9-honeycomb cell, 10-first connecting piece, 11-second connecting piece, 12-connecting hole, 13-dampening layer, 14-connecting part, 15-damping fluid. Detailed Implementation

[0038] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0039] The purpose of this invention is to provide a gimbal vibration reduction device based on a high-damping honeycomb core composite structure to solve the problems existing in the prior art. The gimbal vibration reduction device based on the high-damping honeycomb core composite structure can significantly improve the overall structure's broadband vibration reduction effect through a dual-path coupling damping mechanism of honeycomb vibration reduction unit and vibration reduction connection unit.

[0040] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0041] like Figures 1 to 10As shown, this embodiment provides a gimbal vibration damping device based on a high-damping honeycomb core composite structure, including an upper damping plate 1, a lower damping plate 5, a honeycomb damping unit 3, and a damping connection unit 4. Preferably, both the upper damping plate 1 and the lower damping plate 5 are made of carbon fiber composite material, preferably carbon fiber epoxy resin. The upper damping plate 1 and the lower damping plate 5, made of carbon fiber composite material, can guide the vibration transmission path due to their high specific stiffness. Specifically, because the stiffness of the carbon fiber composite material along the fiber direction is much higher than that in the vertical direction, the vibration can be transmitted to the honeycomb damping unit 3 and the damping connection unit 4 by changing the layup angle of the carbon fibers, while simultaneously dissipating the vibration energy. The upper damping plate 1 is used to connect the UAV body; the lower damping plate 5 is used to mount airborne equipment; the damping connection unit 4 is disposed between the upper damping plate 1 and the lower damping plate 5, and both ends of the damping connection unit 4 are connected to the upper damping plate 1 and the lower damping plate 5 respectively; the honeycomb damping unit 3 is disposed between the upper damping plate 1 and the lower damping plate 5. The lower damping plate 5 is arranged side by side with the damping connection unit 4 and is located in the centroid region of the entire gimbal damping device based on the high-damping honeycomb core composite structure. The two ends of the honeycomb damping unit 3 are connected to the upper damping plate 1 and the lower damping plate 5 respectively. The honeycomb damping unit 3 is made of a material that provides damping loss factor in the low frequency band. Preferably, the honeycomb damping unit 3 can be made of shape memory alloy or carbon fiber composite material. The material itself of shape memory alloy or carbon fiber composite material provides damping loss factor in the low frequency band. The honeycomb damping unit 3 is densely provided with honeycomb cells 9, which are porous structures. The honeycomb cells 9 are interconnected to form a unit network, thereby constituting the honeycomb damping unit 3. The porosity of the honeycomb damping unit 3 is about 85%. The honeycomb cells 9 are used for elastic deformation in the high frequency band. Specifically, the mechanical properties of the honeycomb cells 9 and the entire honeycomb damping unit 3 can be deformed under impact to absorb a large amount of energy, thereby achieving the purpose of vibration reduction. Due to the unique geometry of the honeycomb structure of the honeycomb vibration damping unit 3, vibrations from the horizontal and vertical directions are diffracted and scattered when they encounter the honeycomb boundary, thereby reducing energy transfer.

[0042] This invention discloses a gimbal vibration reduction device based on a high-damping honeycomb core composite structure, which mainly targets the wide-frequency vibration spectrum characteristics (low-frequency rotor vibration 0.1-50Hz, high-frequency motor harmonics 1-5kHz) present in UAV operations. This invention employs an impedance matching design between the vibration reduction connection unit 4 and the honeycomb vibration reduction unit 3 to form a segmented frequency-domain damping response. In the low-frequency range (<100Hz): because the honeycomb vibration reduction unit 3 is made of a material designed to provide a damping loss factor in the low-frequency range, its ability to provide a damping loss factor in the low-frequency range effectively dissipates large-amplitude low-frequency energy, and works in conjunction with the vibration reduction connection unit 4 to effectively dissipate large-amplitude low-frequency energy. In the high-frequency range (>500Hz): the vibration reduction connection unit 4 effectively dissipates high-frequency vibration energy, and the honeycomb vibration reduction unit 3 reduces dynamic stiffness through the elastic deformation of the honeycomb cells 9, avoiding the transmission of high-frequency resonance. As described above, the overall structure of the gimbal vibration reduction device based on the high-damping honeycomb core composite structure can significantly improve the overall structure's broadband vibration reduction effect and comprehensively achieve vibration isolation through the dual-path coupling damping mechanism of the vibration reduction connection unit 4 and the honeycomb vibration reduction unit 3.

[0043] Furthermore, the gimbal vibration damping device based on a high-damping honeycomb core composite structure disclosed in this invention is applied to unmanned aerial vehicles (UAVs). When the UAV takes off, the upper damping plate 1, the lower damping plate 5, the damping connection unit 4, and the honeycomb damping unit 3 simultaneously absorb high- and low-frequency vibrations caused by the propeller, motor, and aerodynamics. Through local deformation, mechanical energy is converted into heat energy for dissipation, thereby reducing the energy transmitted to the airborne equipment. When the UAV hovers in the air and encounters a sudden gust of wind, the honeycomb damping unit 3 can withstand the force evenly, and its porous honeycomb structure can resist strong wind disturbances from all directions, resulting in superior bending resistance.

[0044] Furthermore, current mainstream gimbal vibration damping systems generally rely on the optimization of the number and layout of rubber damping balls 6, but this has significant drawbacks: the rubber damping balls 6 are prone to stress fatigue cracks under long-term alternating loads, especially in scenarios with severe temperature differences or high-frequency vibrations, leading to a decline in damping performance. To address this, this invention proposes a composite vibration damping architecture, which utilizes the synergistic effect of the honeycomb structure of the honeycomb damping unit 3, and the upper and lower damping plates 1 and 5 made of carbon fiber composite materials to achieve efficient absorption and dispersion of vibration energy. Specifically, the honeycomb structure converts mechanical energy into heat energy dissipation through elastic deformation, while the upper and lower damping plates 1 and 5, made of carbon fiber composite materials, can directionally guide the vibration transmission path due to their high specific stiffness. The combination of these two components improves the system's internal energy absorption efficiency by more than 40%.

[0045] Moreover, traditional gimbals often employ a "vibration isolator + damping ball 6" stacking scheme to achieve vibration suppression, leading to the following contradictions: 1) Excessive weight: The combination of metal vibration isolators and multi-layer damping balls 6 increases the structural mass by 30%-50%, severely affecting the drone's endurance; 2) Dimensional limitations: Linearly arranged damping units can only cope with vibrations in a single direction, making it difficult to suppress multi-axial composite vibrations caused by changes in flight attitude. This invention overcomes the above limitations through two-stage innovation: 1) Material topology optimization: Using honeycomb damping units 3 instead of solid vibration isolators, maintaining equivalent stiffness even with a porosity of 85%, achieving a 60% weight reduction while increasing specific strength; 2) Multi-dimensional vibration reduction reconstruction: Arranging honeycomb damping units 3 as the core damping layer 13 in the gimbal's center of mass region, its hyperelastic properties can simultaneously respond to X / Y / Z axial vibrations. Finite element simulation verification shows that this design achieves a triaxial vibration attenuation rate of over 92% simultaneously, and the total mass of the entire device is reduced to 1 / 3 of the traditional scheme.

[0046] In one specific embodiment, the honeycomb vibration damping unit 3 is provided with multiple vibration damping layers 13. Each vibration damping layer 13 is arranged and connected sequentially along the arrangement direction of the upper vibration damping plate 1 and the lower vibration damping plate 5. The vibration damping layers 13 located on both sides are connected to the upper vibration damping plate 1 and the lower vibration damping plate 5 respectively. Each vibration damping layer 13 is arrayed with honeycomb cells 9. By setting multiple vibration damping layers 13, the vibration damping effect of the entire honeycomb vibration damping unit 3 on the entire device is ensured, and the bending resistance of its own structure is improved.

[0047] In this embodiment, multiple flexible damping columns 2 are connected between the damping layers 13 on both sides and the upper damping plate 1 and the lower damping plate 5, respectively. The flexible damping columns 2 are connected between the honeycomb damping unit 3 and the upper damping plate 1 and the lower damping plate 5, respectively, to avoid a hard connection between the honeycomb damping unit 3 and the upper damping plate 1 and the lower damping plate 5, thereby avoiding the transmission of vibration from the honeycomb damping unit 3 to the upper damping plate 1 and the lower damping plate 5, which would cause damage to the upper damping plate 1 and the lower damping plate 5. Preferably, the flexible damping column 2 has a dumbbell-shaped structure. The upper damping plate 1, the lower damping plate 5, and the corresponding damping layer 13 are all provided with connecting holes 12 so that the middle part of the flexible damping column 2 can pass through. This allows one end of the flexible damping column 2 to abut against the outer wall of the upper damping plate 1 or the lower damping plate 5, and the other end to abut against the outer wall of the damping layer 13 away from the upper damping plate 1 or the lower damping plate 5. Preferably, the flexible damping column 2 is a rubber damping column with a hollow structure, and preferably each flexible damping column 2 is evenly distributed at the outer periphery of the damping layer 13.

[0048] In this embodiment, the damping layer 13 includes 9 groups of honeycomb cells arrayed along the same straight direction. Each group of 9 honeycomb cells includes a first row of 9 honeycomb cells and a second row of 9 honeycomb cells arranged along the array direction of each group. The first row of 9 honeycomb cells and the second row of 9 honeycomb cells extend in a direction perpendicular to the array of each group of 9 honeycomb cells. Both the first row of 9 honeycomb cells and the second row of 9 honeycomb cells include honeycomb cells 9 arrayed along their extension direction. A first connecting piece 10 connects adjacent honeycomb cells 9 on the first row of 9 honeycomb cells. A second connecting piece 11 connects adjacent honeycomb cells 9 on the first honeycomb cell 9 row. Each first connecting piece 10 on the first honeycomb cell 9 row is connected to each honeycomb cell 9 on the second honeycomb cell 9 row, and each second connecting piece 11 on the second honeycomb cell 9 row is connected to each honeycomb cell 9 on the first honeycomb cell 9 row. Adjacent groups of honeycomb cells 9 are connected to the first connecting piece 10 or the second connecting piece 11 through corresponding honeycomb cells 9. The first connecting pieces 10 and the second connecting pieces 11 are spaced apart along the thickness direction of the damping layer 13. Preferably, a connecting hole 12 is provided on the first connecting piece 10 or the second connecting piece 11, and one end of the flexible damping column 2 connected to the damping layer 13 abuts against the first connecting piece 10 or the second connecting piece 11.

[0049] In one specific embodiment, the honeycomb cells 9 have a regular polygonal structure, and each honeycomb cell 9 in the damping layer 13 is evenly distributed. The honeycomb damping unit 3, through the elastic deformation of the regular polygonal honeycomb cells 9, causes vibration to diffract and scatter, and converts mechanical energy into heat energy for dissipation. Specifically, when the UAV hovers in the air and encounters a sudden gust of wind, the regular polygonal honeycomb cells 9 can be subjected to uniform force. At the same time, because each honeycomb cell 9 in the damping layer 13 is evenly distributed, the entire honeycomb damping unit 3 can resist strong wind disturbances from all directions, and has better bending resistance. Preferably, the honeycomb cells 9 have a regular hexagonal structure to fully expand the range of vibration diffraction and scattering.

[0050] Preferably, the honeycomb vibration damping units 3 are all made of shape memory alloy, which provides a damping loss factor in the low-frequency range. During the manufacturing process, the honeycomb vibration damping units 3 are installed between the upper damping plate 1 and the lower damping plate 5 at room temperature or low temperature. This ensures that after being combined with the vibration damping connection unit 4, the entire device has a high damping loss factor in the low-frequency range and low stiffness in the high-frequency range. Specifically, shape memory alloy, as a novel functional material, exhibits a martensitic low-temperature stable phase at room temperature. The high damping of shape memory alloy is mainly due to the viscosity of the boundaries of the martensitic variants within the alloy. Furthermore, under load, viscoelastic displacement occurs between the boundaries, causing strain to lag behind stress, and vibration energy is converted into internal energy, thereby achieving a vibration damping effect.

[0051] In one specific embodiment, the vibration damping connection unit 4 includes a plurality of vibration damping balls 6 with a flexible structure. Preferably, the vibration damping balls 6 are made of rubber material. Each vibration damping ball 6 is evenly distributed between the upper vibration damping plate 1 and the lower vibration damping plate 5, and both ends of the vibration damping ball 6 are connected to the upper vibration damping plate 1 and the lower vibration damping plate 5 respectively. The vibration damping ball 6 has both a vibration damping function and can fix the position of the upper vibration damping plate 1 and the lower vibration damping plate 5. Furthermore, by combining the honeycomb vibration damping unit 3 made of shape memory alloy, and considering the wide frequency vibration spectrum characteristics (low-frequency rotor vibration 0.1-50Hz, high-frequency motor harmonics 1-5kHz) in UAV operations, the honeycomb vibration damping unit 3 made of shape memory alloy and the damping ball 6 are impedance matched to form a segmented frequency domain damping response: Low frequency band (<100Hz): The high loss factor (tanδ≥0.8) of the shape memory alloy effectively dissipates large amplitude low-frequency energy, and works in conjunction with the damping ball 6 to dissipate large amplitude low-frequency energy; High frequency band (>500Hz): The damping ball 6 effectively dissipates high-frequency vibration energy, and the honeycomb cell 9 elastic element of the honeycomb vibration damping unit 3 reduces dynamic stiffness and avoids high-frequency resonance transmission.

[0052] In one specific embodiment, the honeycomb damping unit 3 is located at the middle position between the upper damping plate 1 and the lower damping plate 5, so that the honeycomb damping unit 3 is located in the center of mass region of the entire gimbal damping device based on the high-damping honeycomb core composite structure, and each damping ball 6 is uniformly surrounded on the outer periphery of the honeycomb damping unit 3. The uniform distribution of the damping balls 6 on the outer periphery and the honeycomb damping unit 3 in the middle can maintain the balance of the center of mass and at the same time have the function of resisting bending. Preferably, each damping ball 6 is divided into multiple groups, and each group contains multiple damping balls 6. The damping balls 6 in each group are uniformly distributed, and each group of damping balls 6 is uniformly surrounded on the outer periphery of the honeycomb damping unit 3, so as to be able to adapt to the polygonal structure of the upper damping plate 1 and the lower damping plate 5. For example, both the upper damping plate 1 and the lower damping plate 5 include a middle base structure and protruding structures that are equally spaced around the outer periphery of the middle base structure. Each group of damping balls 6 can be respectively set at the position of each protruding structure, thereby fully ensuring the bending performance and connection strength of the entire structure.

[0053] In one specific embodiment, the damping sphere 6 has a hollow structure and is filled with damping fluid 15. This invention improves the damping sphere 6 by adding damping fluid 15 inside. By increasing the damping fluid 15, the high-frequency damping effect of the entire damping sphere 6 can be significantly enhanced, effectively dissipating high-frequency vibration energy. Simultaneously, it works in conjunction with the honeycomb damping unit 3 to achieve vibration damping in both horizontal and vertical directions. Alternatively, a material capable of dissipating high-frequency vibration energy can be used to fill the damping sphere 6.

[0054] In one specific embodiment, the damping ball 6 has an upper stop 7 and a lower stop 8 at each end corresponding to the upper damping plate 1 and the lower damping plate 5, respectively. A connecting part 14 connects the damping ball 6 to both the upper stop 7 and the lower stop 8. Preferably, the damping ball 6, the upper stop 7, the lower stop 8, and the two connecting parts 14 are integrally molded from rubber material. Multiple mounting holes are provided on the upper damping plate 1 and the lower damping plate 5. The connecting parts 14 at both ends of the damping ball 6 pass through the mounting holes on the upper damping plate 1 and the lower damping plate 5. The upper stop 7 and the lower stop 8 abut against the side of the upper damping plate 1 and the lower damping plate 5 away from the damping ball 6, and the damping ball 6 abuts between the upper damping plate 1 and the lower damping plate 5, so that the upper damping plate 1 and the lower damping plate 5 are connected through the damping ball 6, ensuring the structural integrity. It should be noted that the external structure of the damping ball 6, the upper damping plate 1 and the lower damping plate 5 are all larger than the mounting hole. The structure of the connecting part 14 is adapted to the structure of the mounting hole. During installation, the upper damping plate 1 and the lower damping plate 5 are squeezed into and pass through the mounting hole to complete the fixation of both ends of the damping ball 6 to the upper damping plate 1 and the lower damping plate 5 respectively.

[0055] Any adaptive changes made according to actual needs are within the scope of protection of this invention.

[0056] It should be noted that, for those skilled in the art, it is obvious that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0057] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. A gimbal vibration damping device based on a high-damping honeycomb core composite structure, characterized in that, Includes upper damping plate, lower damping plate, honeycomb damping unit, and damping connection unit; The upper damping plate is used to connect the drone body; The lower damping plate is used to mount airborne equipment; The vibration damping connection unit is disposed between the upper vibration damping plate and the lower vibration damping plate, and both ends of the vibration damping connection unit are respectively connected to the upper vibration damping plate and the lower vibration damping plate; the vibration damping connection unit includes a plurality of vibration damping balls with a flexible structure, each vibration damping ball being evenly distributed between the upper vibration damping plate and the lower vibration damping plate, and both ends of the vibration damping ball being respectively connected to the upper vibration damping plate and the lower vibration damping plate; the vibration damping balls are made of rubber material; The honeycomb vibration damping unit is disposed between the upper and lower vibration damping plates and is arranged side by side with the vibration damping connection unit, located in the centroid region of the entire gimbal vibration damping device based on the high-damping honeycomb core composite structure. The two ends of the honeycomb vibration damping unit are respectively connected to the upper and lower vibration damping plates. The honeycomb vibration damping unit is made of a material that provides a damping loss factor in the low-frequency range, and densely arranged with honeycomb cells for elastic deformation in the high-frequency range. The honeycomb vibration damping unit has multiple damping layers, each arranged and connected sequentially along the arrangement direction of the upper and lower vibration damping plates. The damping layers on both sides are connected to the upper and lower vibration damping plates respectively. Each damping layer has an array of honeycomb cells. The honeycomb cells are interconnected to form a unit network, thereby constituting the honeycomb vibration damping unit. In the low-frequency range, i.e. when the vibration frequency is less than 100Hz, the characteristic of the honeycomb vibration reduction unit to provide damping loss factor in the low-frequency range is utilized to dissipate large-amplitude low-frequency energy, and the vibration reduction connection unit is used in conjunction to dissipate large-amplitude low-frequency energy. In the high-frequency range, i.e., when the vibration frequency is greater than 500Hz, the high-frequency vibration energy is dissipated through the vibration damping connection unit, and the honeycomb vibration damping unit reduces the dynamic stiffness through the elastic deformation of the honeycomb cells to avoid the transmission of high-frequency resonance.

2. The gimbal vibration reduction device based on a high-damping honeycomb core composite structure according to claim 1, characterized in that, The vibration damping layers located on both sides are each connected to the upper vibration damping plate and the lower vibration damping plate by multiple flexible vibration damping columns.

3. The gimbal vibration reduction device based on a high-damping honeycomb core composite structure according to claim 2, characterized in that, The vibration damping layer includes honeycomb cell groups arranged in an array along the same straight line direction. Each honeycomb cell group includes a first honeycomb cell row and a second honeycomb cell row arranged along the array direction of each honeycomb cell group. The first honeycomb cell row and the second honeycomb cell row extend in a direction perpendicular to each honeycomb cell group array. Both the first and second cell rows include the cell cells arrayed along their extension direction. A first connecting piece connects adjacent cell cells in the first cell row, and a second connecting piece connects adjacent cell cells in the second cell row. Each first connecting piece in the first cell row is connected to each cell cell in the second cell row, and each second connecting piece in the second cell row is connected to each cell cell in the first cell row. Adjacent cell groups are connected to each other via corresponding cell cells and either the first or second connecting piece. The first connecting piece and the second connecting piece are spaced apart along the thickness direction of the damping layer.

4. The gimbal vibration reduction device based on a high-damping honeycomb core composite structure according to claim 3, characterized in that, The honeycomb cells have a regular polygonal structure, and each of the honeycomb cells in the damping layer is evenly distributed.

5. The gimbal vibration reduction device based on a high-damping honeycomb core composite structure according to claim 1, characterized in that, The cellular vibration damping units are all made of shape memory alloy, which is used to provide damping loss factor in the low frequency band.

6. The gimbal vibration reduction device based on a high-damping honeycomb core composite structure according to claim 5, characterized in that, The honeycomb vibration damping unit is located at the middle position of the upper vibration damping plate and the lower vibration damping plate, and each of the vibration damping balls is evenly surrounded on the outer periphery of the honeycomb vibration damping unit.

7. The gimbal vibration reduction device based on a high-damping honeycomb core composite structure according to claim 6, characterized in that, The damping ball has a hollow structure and is filled with damping fluid.

8. The gimbal vibration reduction device based on a high-damping honeycomb core composite structure according to claim 7, characterized in that, The damping ball is provided with an upper stop and a lower stop at both ends of the upper damping plate and the lower damping plate, respectively, and the damping ball is connected to the upper stop and the lower stop respectively. The upper damping plate and the lower damping plate are respectively provided with a plurality of mounting holes. The connecting parts at both ends of the damping ball pass through the mounting holes on the upper damping plate and the lower damping plate respectively. The upper stop and the lower stop respectively abut against the side of the upper damping plate and the lower damping plate away from the damping ball, and the damping ball abuts between the upper damping plate and the lower damping plate.

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