A shock absorber

Abstract

The present invention discloses a shock absorber, comprising a connector 1, a connector 2 and a plurality of shock-absorbing wires, wherein the two ends of the shock-absorbing wires are respectively connected to the connector 1 and the connector 2, and the connection of the shock-absorbing wires on the connector 1 forms a connection surface 1, and the connection of the shock-absorbing wires on the connector 2 forms a connection surface 2, and the connection surface 1 is inclined to the connection surface 2. The shock absorber of the present invention realizes multi-dimensional shock absorption of a single element, has a good shock absorption effect, can effectively simplify the vibration isolation mechanism of the aircraft, reduce the required assembly space, improve the compactness of the structure, reduce waste weight, and improve the carrying capacity of the unmanned aerial vehicle.

Description

Technical Field

[0001] The invention relates to the technical field of shock absorbing structures, and in particular to a shock absorber. Background Art

[0002] A shock absorber is an elastic damping device installed between the equipment and the fixed surface. It can effectively attenuate the vibration or noise transmission between the fixed surface and the equipment to achieve the purpose of vibration reduction. In the field of drones, one of the important factors affecting the flight status of drones is that the inertial sensors used for attitude resolution will be adversely affected by vibration. Resonance or random vibration will cause data errors in the sensors, which will cause fatal errors in attitude resolution. Therefore, vibration reduction devices are usually required to reduce the error caused by low-frequency vibration during the flight of drones. In the prior art, rubber damping balls are usually used to isolate the flight control components of the drone, and the elastic deformation of rubber is used to isolate or reduce vibration. However, traditional damping balls only have a good vibration isolation effect in one direction, and have a poor vibration isolation effect on other directions. In addition, they have poor stability and a short life. When the vibration amplitude is too large, the ball will fall off. Usually, the damping balls need to be installed at an angle and multiple balls need to cooperate with each other. At this time, additional mounting brackets are required, or dampers along the vertical direction and the horizontal direction need to be separately set. As a result, the traditional damping device has a complex and non-compact structure, requires a large assembly space, is inconvenient to install, has a large number of components, and is heavy, which seriously affects the loading capacity of the drone. Summary of the invention

[0003] The technical problem to be solved and the technical task proposed by the present invention are to improve the existing technology and provide a vibration absorber to solve the problems that the vibration absorber in the current technology has a single vibration isolation direction, requires a complex structural combination to achieve multi-directional vibration isolation, requires a large assembly space, has a large number of components, and has a large amount of waste.

[0004] In order to solve the above technical problems, the technical solution of the present invention is:

[0005] A vibration damper includes a connector 1, a connector 2 and a plurality of vibration damping wires, wherein the two ends of the vibration damping wires are respectively connected to the connector 1 and the connector 2, and the connection of the vibration damping wires on the connector 1 forms a connection surface 1, and the connection of the vibration damping wires on the connector 2 forms a connection surface 2, and the connection surface 1 is inclined to the connection surface 2. The vibration damper described in the present invention has a multi-dimensional vibration damping function. The traditional vibration damper uses a plurality of identical vibration damping wires connected between the connector 1 and the connector 2, so that the plane formed by the connection of the vibration damping wires on the connector 1 is parallel to the plane formed by the connection of the vibration damping wires on the connector 2, and the connector 1 and the connector 2 are parallel to each other. Therefore, the traditional vibration damper can only achieve the vibration damping function in a single direction (the direction of the connection line between the connector 1 and the connector 2). Therefore, if the traditional vibration damper is used to achieve multi-dimensional vibration damping, it is necessary to set up additional vibration dampers. For example, if a group of vibration dampers for vertical vibration damping is set up, if lateral vibration damping is also to be achieved, it is also necessary to set up a group of vibration dampers for lateral vibration damping. This requires a large additional installation space, and the large number of components also brings additional waste weight, which seriously affects the structural compactness and carrying capacity of the UAV. The shock absorber used in the present invention has a connection surface one that is inclined to the connection surface two, so that the vibration-damping wires connected between the connecting member one and the connecting member two are of different shapes and lengths, so that the vibration-damping direction of each vibration-damping wire is different. After these vibration-damping wires are combined together, the overall shock absorber has a better vibration-damping effect in multiple dimensions, that is, a single shock absorber achieves multi-dimensional vibration reduction. Compared with traditional shock absorbers, it can effectively reduce the number of shock absorbers used, reduce the required assembly space, improve the structural compactness of the UAV, reduce waste weight, and improve the carrying capacity.

[0006] Furthermore, the angle between the first connecting surface and the second connecting surface is 60-70°, which enables the shock absorber to achieve a better shock absorption effect in multiple dimensions.

[0007] Furthermore, the angle between the connection surface 1 and the connection surface 2 is 66.5°, which has excellent vibration reduction effect in multiple dimensions.

[0008] Furthermore, the vibration-damping wire is a steel cable with a diameter of 1 to 1.5 mm. The diameter of the vibration-damping wire can be selected according to flight control components of different weights to ensure that the vibration-damping effect of flight control components of different weights can meet the requirements.

[0009] Furthermore, the vibration damping wire is a steel cable with a diameter of 1.2 mm.

[0010] Furthermore, the connecting member 1 is a flat plate parallel to the connecting surface 1, and the connecting member 2 is a flat plate parallel to the connecting surface 2. The structure is simple, easy to process and manufacture, convenient to install, and easy to adapt to the needs of various installation environments.

[0011] Furthermore, there are four vibration-damping wires, two of which are bent into a C-shape, and the other two are bent into a spiral shape. The structure is simplified and easy to process while ensuring multi-dimensional vibration reduction. The vibration-damping wire bent into a C-shape and the vibration-damping wire bent into a spiral shape have different vibration-damping directions. When combined together, the vibration absorber has good vibration-damping effects in multi-dimensional directions.

[0012] Furthermore, all the vibration-damping wires connected to the connector 1 and the connector 2 are formed by bending a long steel wire, which can improve the overall structural stability of the shock absorber, reduce the separation and detachment of the vibration-damping wire from the connector 1 and the connector 2, and ensure that the shock absorber can work stably for a long time.

[0013] Furthermore, the connecting piece 1 and the connecting piece 2 are provided with connecting holes for the long steel wire to pass through, and the connection stability between the vibration damping wire and the connecting piece 1 and the connecting piece 2 is good, thereby reducing the occurrence of the vibration damping wire falling off.

[0014] An aircraft vibration isolation mechanism comprises a plurality of the above-mentioned shock absorbers, and the plurality of shock absorbers are arranged at intervals in the circumferential direction of a flight control component. The plurality of shock absorbers are combined together to form a stable and excellent vibration reduction effect on the flight control component, effectively reducing the error influence caused by low-frequency vibration during the flight of the UAV, and improving the flight stability and accuracy. The single shock absorber described in the present invention can realize multi-dimensional vibration reduction, and compared with traditional shock absorbers, the number of shock absorbers used can be effectively reduced, the overall structure of the aircraft vibration isolation mechanism can be simplified, the space required for installation can be reduced, the waste weight can be reduced, and the carrying capacity of the UAV can be improved.

[0015] Compared with the prior art, the present invention has the advantages of:

[0016] The shock absorber described in the present invention realizes multi-dimensional vibration reduction of a single component, has good vibration reduction effect, can effectively simplify the vibration isolation mechanism of the aircraft, is easy to install, reduces the required assembly space, improves the compactness of the structure, reduces waste weight, and improves the carrying capacity of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 is a schematic diagram of the structure of the shock absorber;

[0018] Figure 2 is a schematic diagram of the side structure of the shock absorber;

[0019] Figure 3 It is the structural schematic diagram of the vibration damping wire;

[0020] Figure 4 It is a schematic diagram of the connection structure between the flight control component and the shock absorber. DETAILED DESCRIPTION

[0021] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0022] A shock absorber disclosed in an embodiment of the present invention has a compact structure, good shock absorption effect, can achieve multi-dimensional shock absorption, has good stability in use, long service life, requires a small assembly space, improves structural compactness, reduces waste weight, and improves load-bearing capacity.

[0023] like Figures 1 to 4 As shown, the vibration damper 6 mainly includes a connecting member 1 61, a connecting member 2 62 and a plurality of vibration damping wires 63, the two ends of the vibration damping wire 63 are respectively connected to the connecting member 1 61 and the connecting member 2 62, and the connection of the vibration damping wire 63 on the connecting member 1 61 forms a connecting surface 1 64, and the connection of the vibration damping wire 63 on the connecting member 2 62 forms a connecting surface 2 65, the connecting surface 1 64 is inclined to the connecting surface 2 65, and the vibration damping wire 63 connected between the connecting member 1 61 and the connecting member 2 62 has a plurality of different shapes and lengths, so that the connecting surface 1 64 is inclined to the connecting surface 2 65, and the vibration damping wires 63 of different shapes and lengths have different vibration damping directions. After the plurality of vibration damping wires 63 of different shapes and lengths are combined together, a single vibration damper 6 is finally realized to have good vibration damping function in multiple dimensional directions, thereby reducing the use amount of the vibration damper and improving the vibration damping effect;

[0024] The angle between the connection surface 1 64 and the connection surface 2 65 is 60-70°, preferably, the angle between the connection surface 1 64 and the connection surface 2 65 is 66.5°, so that the vibration reduction effect of the vibration absorber 6 in different directions is balanced, and the overall vibration reduction effect is improved; and the vibration reduction wire 63 is a steel wire cable with a diameter of 1-1.5 mm, preferably a 1.2 mm steel wire cable, and the diameter of the vibration reduction wire 63 can be selected according to flight control components of different weights, ensuring that the vibration reduction effect of flight control components of different weights can meet the requirements;

[0025] In this embodiment, the connecting member 1 61 is a flat plate parallel to the connecting surface 1 64, and the connecting member 2 62 is a flat plate parallel to the connecting surface 2 65, which has a simple structure and is easy to manufacture.

[0026] In the present embodiment, there are four vibration damping wires 63, two of which are bent roughly into a C shape, and the other two are bent roughly into a spiral shape, and the vibration damper 6 is of a symmetrical structure, that is, the two C-shaped vibration damping wires 63 are symmetrically connected to the connecting member 1 61 and the connecting member 2 62, and the two spiral vibration damping wires 63 are also symmetrically connected to the connecting member 1 61 and the connecting member 2 62. The vibration damping direction of the C-shaped vibration damping wire 63 is mainly the direction of the connecting line of the two ends of the C-shaped vibration damping wire 63, and the vibration damping direction of the spiral vibration damping wire 63 is mainly the spiral axial direction of the spiral vibration damping wire 63 and the direction perpendicular to the spiral axial direction. The vibration damping direction of the spiral vibration damping wire 63 is different from that of the C-shaped vibration damping wire 63, so that the vibration damping wires 63 of different shapes and lengths are combined to make the connecting surface 1 64 inclined to the connecting surface 2 65 and realize a good vibration damping function in multiple dimensions.

[0027] Furthermore, all the vibration-damping wires 63 connected to the connector 1 61 and the connector 2 62 are formed by bending a long steel wire, and the connector 1 61 and the connector 2 62 are provided with connecting holes for the long steel wire to pass through, and the long steel wire is fixed in the connecting holes, which can improve the overall structural stability of the vibration absorber 6, reduce the separation and detachment of the vibration-damping wire 63 from the connector 1 61 and the connector 2 62, and ensure that the vibration absorber 6 can work stably for a long time and ensure a stable vibration reduction effect.

[0028] The flight control component of the drone is installed in the shell of the fuselage. In order to avoid resonance or random vibration that may cause data errors in the sensor, thereby causing fatal errors in attitude calculation, the flight control component 5 is usually fixed in the shell through an aircraft vibration isolation mechanism;

[0029] The aircraft vibration isolation mechanism includes a plurality of shock absorbers 6 arranged at intervals in the circumferential direction of the flight control assembly 5. In this embodiment, four shock absorbers 6 are specifically used, which are distributed at the four corners of the flight control assembly 5 to ensure the overall stability of the flight control assembly 5. Specifically, the connecting piece 1 61 is directly connected to the flight control assembly 5, and the connecting piece 2 62 is fixedly connected to the mounting seat fixed on the shell. When it is installed in the fuselage of the drone, the connecting surface 1 64 is parallel to the horizontal plane, and the connecting surface 2 65 is inclined to the horizontal plane. There is no need to set up an adapter to carry the flight control assembly 5, and then the connecting piece 1 61 is connected to the adapter. The structure of this embodiment is more compact, reducing the required assembly space and reducing waste weight. When assembling, the connecting piece 1 61 and the connecting piece 2 62 of the shock absorber 6 are facing the center of gravity of the flight control, ensuring that the four shock absorbers 6 can work together to effectively reduce vibrations in multiple directions and multiple frequencies, improve the vibration reduction effect, and improve the stability of the drone flight.

[0030] The single shock absorber 6 used in this embodiment has a multi-dimensional shock absorption function, which can achieve horizontal and vertical shock absorption during the flight of the UAV, so there is no need to separately set vertical shock absorbers and horizontal shock absorbers as in the prior art, which can reduce the number of shock absorbers, improve the compactness of the structure of the shock absorption device, reduce the required assembly space, reduce waste weight, and improve the bearing capacity;

[0031] Connector 1 61 and connector 2 62 may also be special-shaped structures, specifically triangular prisms, L-shaped plates, etc., and may be set to specific shapes according to actual installation and connection needs. The most important thing is that the vibration-damping wire 63 connected between connector 1 61 and connector 2 62 is in several different shapes and lengths, and the connection surface 1 64 formed by the connection of the vibration-damping wire 63 on connector 1 61 is inclined to the connection surface 2 65 formed by the connection of the vibration-damping wire 63 on connector 2 62, thereby ensuring that a single shock absorber achieves multi-dimensional vibration reduction.

[0032] The above are only preferred embodiments of the present invention. It should be noted that the above preferred embodiments should not be regarded as limiting the present invention, and the protection scope of the present invention should be based on the scope defined by the claims. For ordinary technicians in this technical field, several improvements and modifications can be made without departing from the spirit and scope of the present invention, and these improvements and modifications should also be regarded as the protection scope of the present invention.

Claims

1. A shock absorber, characterized in that: The invention comprises a connecting member 1 (61), a connecting member 2 (62) and a plurality of vibration-damping wires (63), wherein two ends of the vibration-damping wires (63) are respectively connected to the connecting member 1 (61) and the connecting member 2 (62), and a connecting surface 1 (64) is formed at the connecting portion of the vibration-damping wires (63) on the connecting member 1 (61), and a connecting surface 2 (65) is formed at the connecting portion of the vibration-damping wires (63) on the connecting member 2 (62), and the connecting surface 1 (64) is inclined to the connecting surface 2 (65). Vibration-damping wires (63) of different shapes and / or lengths are provided between the connecting member 1 (61) and the connecting member 2 (62), and different vibration-damping wires (63) have different vibration-damping directions to achieve multi-dimensional vibration-damping.

2. The shock absorber according to claim 1, characterized in that: The angle between the first connecting surface (64) and the second connecting surface (65) is 60-70 degrees.

3. The shock absorber according to claim 2, characterized in that: The angle between the first connecting surface (64) and the second connecting surface (65) is 66.5°.

4. The shock absorber according to claim 1, characterized in that: The vibration-damping wire (63) is a steel cable with a diameter of 1 to 1.5 mm.

5. The shock absorber according to claim 4, characterized in that The vibration-damping wire (63) is a steel cable with a diameter of 1.2 mm.

6. The shock absorber according to claim 1, characterized in that The connecting member 1 (61) is a flat plate parallel to the connecting surface 1 (64), and the connecting member 2 (62) is a flat plate parallel to the connecting surface 2 (65).

7. The vibration absorber according to claim 1, characterized in that: The vibration-damping wires (63) are provided in four pieces, two of which are bent into a C shape, and the other two are bent into a spiral shape.

8. The shock absorber according to claim 1, characterized in that All the vibration-damping wires (63) connected to the first connecting piece (61) and the second connecting piece (62) are formed by bending a long steel wire.

9. The vibration absorber according to claim 8, characterized in that The connecting piece 1 (61) and the connecting piece 2 (62) are provided with connecting through holes for the long steel wire to pass through.

10. An aircraft vibration isolation mechanism, characterized in that: It comprises a plurality of shock absorbers as claimed in any one of claims 1 to 9, and the plurality of shock absorbers (6) are arranged at intervals in the circumferential direction of the flight control component (5).

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