Vibration reduction structure of unmanned aerial vehicle-mounted electronic equipment

Abstract

The utility model relates to a vibration reduction structure of unmanned aerial vehicle-mounted electronic equipment, belongs to the technical field of unmanned aerial vehicle equipment, and solves the problem that fasteners in the airborne electronic equipment are likely to be loosened due to vibration in the flying process of an existing unmanned aerial vehicle. The damping structure comprises a first structural component, a second structural component, an elastic component and a locking component, the elastic component is located between the first structural component and the second structural component, the two ends of the elastic component abut against the first structural component and the second structural component respectively, and the locking component penetrates through the second structural component to be fixedly connected with the first structural component. A gap is formed between the first structural component and the second structural component. According to the vibration reduction structure, the elastic component can absorb vibration energy of the fuselage, acting force transmitted to airborne electronic equipment by vibration is offset, and the influence of vibration on the airborne electronic equipment is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle equipment, in particular to a vibration reduction structure of electronic equipment carried by an unmanned aerial vehicle. Background Art

[0002] The present invention relates to a vibration reduction structure for electronic equipment carried by unmanned aerial vehicles, which is used to reduce the vibration transmitted to the electronic equipment carried by the unmanned aerial vehicle during flight, and to reduce the impact transmitted to the electronic equipment carried by the unmanned aerial vehicle during take-off and landing. The unmanned aerial vehicle environment is worse than the use environment of general electronic products, and the working state is usually accompanied by a large amount of vibration. At present, most electronic equipment carried by unmanned aerial vehicles is directly installed on the fuselage. The vibration during flight may cause the internal fasteners of the electronic equipment to loosen, or the solder joints of the electronic components to fall off, causing failures and affecting the stability and reliability of the electronic products carried by unmanned aerial vehicles during use. Utility Model Content

[0003] In view of the above analysis, an embodiment of the utility model aims to provide a vibration reduction structure for electronic equipment on board an unmanned aerial vehicle, so as to solve the problem that the vibration during flight of the existing unmanned aerial vehicle may cause the internal fasteners of the electronic equipment to loosen.

[0004] The purpose of this utility model is mainly achieved through the following technical solutions:

[0005] A vibration reduction structure for an electronic device carried by an unmanned aerial vehicle comprises a first structural component, a second structural component, an elastic component and a locking component; the elastic component is located between the first structural component and the second structural component, and two ends of the elastic component are respectively abutted against the first structural component and the second structural component; the locking component passes through the second structural component and is fixedly connected to the first structural component; and there is a gap between the first structural component and the second structural component.

[0006] Furthermore, the first structural component includes a bottom plate and a positioning portion, the positioning portion is fixed on the bottom plate, and the elastic component is installed on the positioning portion.

[0007] Furthermore, the positioning portion is a first boss, and the elastic component is sleeved on the first boss.

[0008] Furthermore, the positioning portion is a groove, and the elastic component is arranged in the groove.

[0009] Furthermore, the first structural component also includes a first connecting portion, and the locking component is fixedly connected to the first connecting portion.

[0010] Furthermore, the first connecting portion is an axial blind hole opened on the upper portion of the positioning portion.

[0011] Furthermore, the second structural component includes a cover plate, and a through guide hole is formed on the cover plate.

[0012] Furthermore, the locking component is provided with a guide rod which matches the guide hole.

[0013] Furthermore, the second structural component also includes a device mounting portion, which is a second boss located on the cover plate, and the guide hole is opened at the center of the device mounting portion.

[0014] Furthermore, the first structural component and the second structural component further include a first limiting portion and a second limiting portion respectively, and the first limiting portion, the second limiting portion and the elastic component are coaxially arranged.

[0015] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0016] (1) The utility model provides an elastic component between the first structural component and the second structural component, so that the elastic component absorbs the vibration energy of the first structural component, offsets the force transmitted by the vibration to the second structural component, and reduces the impact of the vibration on the onboard electronic equipment.

[0017] (2) The utility model provides a guide structure between the second structural component and the locking component, so that when the locking component and the first structural component vibrate, they can generate relative displacement with the second structural component and maintain coaxiality.

[0018] (3) The utility model ensures a buffer space between the first structural component and the second structural component by setting a gap between the first structural component and the second structural component.

[0019] (4) The utility model provides a guide hole in the boss-shaped device mounting portion, so that the locking component has an overall locking function, has a compact structure, is easy to install, and reduces assembly weight.

[0020] In the present invention, the above-mentioned technical solutions can also be combined with each other to achieve more preferred combination solutions. Other features and advantages of the present invention will be described in the following content, and some advantages can be obvious from the description or understood by implementing the present invention. The purpose and other advantages of the present invention can be achieved and obtained through the contents specifically pointed out in the text and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The accompanying drawings are only used for the purpose of illustrating specific embodiments and are not to be considered as limiting the present invention. In the entire drawings, the same reference symbols represent the same components.

[0022] Figure 1 It is a schematic diagram of the assembly structure of the vibration reduction structure of the electronic equipment on board the drone in a specific embodiment;

[0023] Figure 2It is a schematic diagram of the exploded structure of the vibration reduction structure of the electronic equipment on board the drone in a specific embodiment;

[0024] Figure 3 It is a schematic cross-sectional view of the installation of a vibration reduction structure of an electronic device mounted on an unmanned aerial vehicle according to a specific embodiment.

[0025] Reference numerals:

[0026] 1-first structural component; 11-bottom plate; 12-positioning part; 13-first connecting part; 14-first limiting part; 2-second structural component; 21-cover plate; 22-guide hole; 23-equipment mounting part; 24-second limiting part; 3-elastic component; 4-locking component; 41-clamp; 42-guide rod; 421-second connecting part; 5-airborne electronic equipment; 6-screw. DETAILED DESCRIPTION

[0027] The preferred embodiments of the present invention are described in detail below in conjunction with the accompanying drawings, wherein the accompanying drawings constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not used to limit the scope of the present invention.

[0028] A specific embodiment of the utility model is as follows Figure 1 As shown, a vibration reduction structure of an unmanned aerial vehicle-mounted electronic device is disclosed, comprising a first structural component 1, a second structural component 2, an elastic component 3 and a locking component 4; the elastic component 3 is located between the first structural component 1 and the second structural component 2, and the two ends of the elastic component 3 are respectively abutted against the first structural component 1 and the second structural component 2; the locking component 4 passes through the second structural component 2 and is fixedly connected to the first structural component 1; there is a gap between the first structural component 1 and the second structural component 2.

[0029] like Figure 2 As shown, the first structural component 1 is a shell with an opening at the top, including a bottom plate 11, a positioning portion 12, a first connecting portion 13 and a first limiting portion 14. The bottom plate 11 is provided with bilaterally symmetrical lugs, and both lugs are provided with threaded through holes for fixing the first structural component 1 on the mounting plate of the drone.

[0030] The positioning portion 12 is a first boss located at the center of the bottom plate 11 or a plurality of first bosses are symmetrically arranged around the center of the bottom plate 11. The elastic component 4 is sleeved on the outer periphery of the first boss for positioning; further, the positioning portion 12 is a positioning groove, and the elastic component 3 is placed in the positioning groove for positioning. The first connecting portion 13 is used to be fixedly connected with the locking component 4. Preferably, the first connecting portion 13 is a blind hole located at the upper part of the first boss of the positioning portion 12, and is fixedly connected with the locking component 4 by thread or snap. The first limiting portion 14 is a shell side wall perpendicular to the bottom plate 11. The elastic component 4 is located in the first limiting portion 14, and the first limiting portion 14 can limit the elastic component 4.

[0031] The second structural component 2 is a cover body matching the first structural component 1, including a cover plate 21, a guide hole 22, a device mounting portion 23 and a second limiting portion 24; the cover plate 21 is arranged parallel to the bottom plate 11, and a through guide hole 22 is provided on the cover plate 21. The guide hole 22 is a through hole located at the center of the cover plate 21 or a plurality of through holes symmetrically arranged around the center of the cover plate 21, and the number of through holes is consistent with the number of the locking component 4; the guide hole 22 is used to match the locking component 4 and guide the relative sliding between the second structural component 2 and the second structural component 2. The device mounting portion 23 is located on the cover plate 21 and is used to be fixedly connected with the airborne electronic device 5. The device mounting portion 23 is a second boss located at the center of the cover plate 21. The outer side surface of the second boss is installed with an interference fit with the mounting hole on the housing of the airborne electronic device 5, and the guide hole 22 is located at the center of the second boss. The device mounting portion 23 can also be a threaded hole, a buckle or other fixed connection structure. The second limiting portion 24 is located on a side of the cover plate 21 opposite to the base plate 11, and is a shell side wall arranged on the outer periphery of the cover plate 21. The inner wall of the second limiting portion 24 matches the outer wall of the first limiting portion 14, and the second structural component 2 and the first structural component 1 are kept coaxial for secondary guiding and limiting. The second limiting portion 24 can also protect the internal structure of the vibration reduction structure to avoid bumps, damage or dust pollution.

[0032] The elastic component 3 is sleeved on the outer periphery of the positioning portion 12, and its two ends are respectively in contact with the bottom plate 11 and the cover plate 21. Preferably, the elastic component 3 is a spring, a silicone rubber ring or other elastic component, and the axial height of the elastic component 3 is greater than the height of the first limiting portion 14 and the second limiting portion 24, so that there is a buffer gap between the ends of the first limiting portion 14 and the second limiting portion 24 and the cover plate 21 and the bottom plate 11, respectively, to ensure that there is a space between the cover plate 21 and the bottom plate 11 for axial relative movement.

[0033] The locking component 4 is a nail-shaped component, including a clamping plate 41 with a clamping function, a guide rod 42 is fixed at the center of the clamping plate 41, and a second connecting portion 421 is provided at the free end of the guide rod 42. The second connecting portion 421 can be fixed and locked with the first connecting portion 13. Preferably, the second connecting portion 421 and the first connecting portion 13 are locked by threads. One end of the guide rod 42 connected to the clamping plate 41 is a smooth rod matching the guide hole 22. When the guide rod 42 passes through the guide hole 22 and is locked with the second connecting portion 421, the second structural component 2 can slide axially between the clamping plate 41 and the first structural component 1 under the guiding action of the guide hole 22 and the guide rod 42. Preferably, the locking component 4 is a flat head bolt with a partial thread on the screw. It should be noted that when the locking component 4 is in the locked state, both ends of the elastic component 3 abut against the bottom plate 11 and the cover plate 21 respectively, and there are buffer gaps between the ends of the first limiting portion 14 and the second limiting portion 24 and the cover plate 21 and the bottom plate 11 respectively.

[0034] like Figure 3 As shown, during installation, first fix the first structural component 1 to the mounting plate of the drone with screws 6, then assemble the elastic component 3 on the positioning portion 12, and then place the second structural component 2 on the elastic component 3, and make the second limiting portion 24 and the first limiting portion 14 match, and finally fix the onboard electronic device 5 to the equipment mounting portion 23, and insert the locking component 4 into the guide hole 22 and lock it with the first connecting portion 13.

[0035] When the drone fuselage equipped with the vibration reduction structure of the utility model vibrates, the mounting plate on the fuselage drives the first structural component 1 and the locking component 4 to vibrate synchronously. Since there is a buffer gap between the first structural component 1 and the second structural component 2, under the guiding action of the guide rod 42 and the guide hole 22, the first structural component 1 slides relative to the second structural component 2 during vibration, thereby changing the distance between the cover plate 21 and the bottom plate 11, causing the elastic component 3 to produce elastic deformation due to the change in axial force at both ends, thereby absorbing the vibration energy, offsetting the force of the vibration transmitted to the second structural component 2, and reducing the influence of the vibration on the airborne electronic equipment.

[0036] The utility model has a vibration reduction effect on the electronic equipment on the unmanned aerial vehicle, improves the anti-vibration and impact resistance of the electronic equipment, and makes the electronic equipment on the unmanned aerial vehicle have higher reliability during take-off, landing and flight.

Claims

1. A vibration reduction structure for an unmanned aerial vehicle electronic device, characterized in that: It comprises a first structural component (1), a second structural component (2), an elastic component (3) and a locking component (4); The elastic component (3) is located between the first structural component (1) and the second structural component (2), and two ends of the elastic component (3) are respectively in contact with the first structural component (1) and the second structural component (2); The locking component (4) passes through the second structural component (2) and is fixedly connected to the first structural component (1); There is a gap between the first structural component (1) and the second structural component (2).

2. The vibration reduction structure of the electronic device mounted on an unmanned aerial vehicle according to claim 1, characterized in that: The first structural component (1) comprises a base plate (11) and a positioning portion (12), the positioning portion (12) is fixed on the base plate (11), and the elastic component (3) is mounted on the positioning portion (12).

3. The vibration reduction structure of the electronic device mounted on an unmanned aerial vehicle according to claim 2, characterized in that: The positioning portion (12) is a first boss, and the elastic component (3) is sleeved on the first boss.

4. The vibration reduction structure of the electronic device mounted on an unmanned aerial vehicle according to claim 2, characterized in that: The positioning portion (12) is a groove, and the elastic component (3) is arranged in the groove.

5. The vibration reduction structure of the electronic device mounted on an unmanned aerial vehicle according to claim 3, characterized in that: The first structural component (1) further comprises a first connecting portion (13), and the locking component (4) is fixedly connected to the first connecting portion (13).

6. The vibration reduction structure of the electronic device mounted on an unmanned aerial vehicle according to claim 5, characterized in that: The first connecting portion (13) is an axial blind hole opened on the upper portion of the positioning portion (12).

7. The vibration reduction structure of the electronic device mounted on an unmanned aerial vehicle according to claim 1, characterized in that: The second structural component (2) comprises a cover plate (21), and a through guide hole (22) is formed on the cover plate (21).

8. The vibration reduction structure of the electronic device mounted on an unmanned aerial vehicle according to claim 7, characterized in that: The locking component (4) is provided with a guide rod (42) that matches the guide hole (22).

9. The vibration reduction structure of the electronic device mounted on an unmanned aerial vehicle according to claim 7, characterized in that: The second structural component (2) further comprises a device mounting portion (23), wherein the device mounting portion (23) is a second boss located on the cover plate (21), and the guide hole (22) is opened at the center of the device mounting portion (23).

10. The vibration reduction structure of the electronic device mounted on an unmanned aerial vehicle according to claim 1, characterized in that: The first structural component (1) and the second structural component (2) further comprise a first limiting portion (14) and a second limiting portion (24), respectively; the first limiting portion (14), the second limiting portion (24) and the elastic component (3) are coaxially arranged.

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