CN210769996U - Shock absorption support in unmanned aerial vehicle - Google Patents
Shock absorption support in unmanned aerial vehicle Download PDFInfo
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- CN210769996U CN210769996U CN201822134229.0U CN201822134229U CN210769996U CN 210769996 U CN210769996 U CN 210769996U CN 201822134229 U CN201822134229 U CN 201822134229U CN 210769996 U CN210769996 U CN 210769996U
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- damping
- aerial vehicle
- unmanned aerial
- fixed connection
- ball
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Abstract
The utility model provides a shock absorber support in unmanned aerial vehicle comprises damping station, shock attenuation ball (3), spacing post (4) three, the damping station divide into damping station (1) and damping station (2) down, it is used to lead the sensor to go up damping station (1) installation, damping station (2) are provided with down shock attenuation ball (3) with spacing post (4), damping station (2) link firmly with unmanned aerial vehicle's frame or flight control mainboard rigidity down, shock attenuation ball (3) handle go up damping station (1) with damping station (2) link together down, spacing post (4) with go up damping station (1) clearance fit.
Description
Technical Field
The utility model relates to a support, especially an unmanned aerial vehicle shock absorber support.
Background
When the traditional shock absorption is sponge shock absorption, the main material is EPDM, and the consistency is poor due to the raw material formula proportion error, climate temperature difference, humidity change, technological process, difference of processing equipment and personnel and the like during production and processing. Because aircraft motor, screw, fuselage material, external load, ambient temperature and the structure of aircraft etc. also lead to the suitability difference in the adaptability, can not be to the more perfect adaptation of common various general models on the market, through a large amount of flight sample experiment record analysis, motor and screw can't the complete effectual filtering of resonance that produces at the during operation when flight.
SUMMERY OF THE UTILITY MODEL
In order to solve the technical problem, through a large amount of vector analysis and trial-made finished product trial flight tests, the damping ball is used for achieving damping of the inertial sensor, and through proper fit clearance of the limiting column and the hole, the inertial sensor is restrained from acquiring wrong data.
The technical scheme of the utility model is that: the utility model provides a shock absorber support in unmanned aerial vehicle comprises damping station, shock attenuation ball (3), spacing post (4) three, the damping station divide into damping station (1) and damping station (2) down, it is used to lead the sensor to go up damping station (1) installation, damping station (2) are provided with down shock attenuation ball (3) with spacing post (4), damping station (2) link firmly with unmanned aerial vehicle's frame or flight control mainboard rigidity down, shock attenuation ball (3) handle go up damping station (1) with damping station (2) link together down, spacing post (4) with go up damping station (1) clearance fit.
The utility model has the advantages that:
(1) the modular design of the utility model is convenient for installation and management;
(2) the connecting structure of the shock absorption ball of the utility model has the advantages of convenient and simple installation, good shock absorption effect due to the use of the silicon rubber material;
(3) the utility model discloses a spacing post lateral displacement guarantees the attitude adjustment of aircraft when flying, the problem of rocking.
Drawings
FIG. 1 is a perspective view of the present invention;
FIG. 2 is a front view of the present invention;
FIG. 3 is a perspective view of the damping table of the present invention;
FIG. 4 is a structural view of the damping ball of the present invention;
fig. 5 is a structure diagram of the spacing column of the present invention.
In the figure, 1: an upper damping table; 2: a lower damping table; 3: a shock absorbing ball; 4: a limiting column; 1.1: a limiting hole; 1.2: an upper fixing connection hole; 1.3: an upper damping ball fixing hole; 2.1: a limiting post fixing hole; 2.2: a lower fixing connection hole; 2.3: a lower damping ball fixing hole; 3.1: a first groove; 3.2: a second groove; 3.3: a third groove; 3.4: a fourth groove; 4.1: a limiting section; 4.2: and a fixed segment.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and examples.
The embodiment of the utility model discloses a referring to fig. 1-5, a shock absorber support in unmanned aerial vehicle comprises shock attenuation platform, shock attenuation ball (3), spacing post (4) three, the shock attenuation platform divide into shock attenuation platform (1) and shock attenuation platform (2) down, it is used to lead the sensor to go up shock attenuation platform (1) installation, shock attenuation platform (2) are provided with down shock attenuation ball (3) with spacing post (4), shock attenuation platform (2) link firmly with unmanned aerial vehicle's frame or flight control mainboard rigidity down, shock attenuation ball (3) handle go up shock attenuation platform (1) with shock attenuation platform (2) link together down, spacing post (4) with go up shock attenuation platform (1) clearance fit.
Wherein, spacing post (4) rigid connection is to unmanned aerial vehicle's frame or on flying to control the mainboard.
The design is modular and convenient for installation and management.
Specific speaking, go up shock attenuation platform (1) and present the square that has trapezoidal breach, go up fixed connection hole (1.2), 4 including 2 spacing holes (1.1), 4 and go up shock attenuation ball fixed orifices (1.3), shock attenuation platform (2) down appear H shape, including 2 spacing post fixed orifices (2.1), 4 down fixed connection hole (2.2), 4 shock attenuation ball fixed orifices (2.3), 4 down go up fixed connection hole (1.2) and be located down on 4 angles of shock attenuation platform (2), be central symmetry, 2 spacing hole (1.1) is located two diagonal angles go up the next door of fixed connection hole (1.2), 4 fixed connection hole (2.2) and 4 down go up fixed connection hole (1.2) and correspond the setting, 2 spacing post fixed orifices (2.1) and 2 spacing hole (1.1) correspond the setting.
Specifically speaking, 4 lower fixed connection hole (2.2) and unmanned aerial vehicle's frame or flight control mainboard fixed connection, 4 go up fixed connection hole (1.2) and inertial navigation sensor fixed connection.
Specific speaking, damping ball (3) are 4, and the shape is multisection structure, including 4 annular groove, and top-down is first recess (3.1), second recess (3.2), third recess (3.3) and fourth recess (3.4) in proper order, it establishes to go up damping ball fixed orifices (1.3) inlay on second recess (3.2), lower damping ball fixed orifices (2.3) inlay and establish on fourth recess (3.4).
Specifically speaking, spacing post (4) are 2, every spacing post (4) top-down is spacing section (4.1) and canned paragraph (4.2) in proper order, the diameter of canned paragraph (4.2) is less than spacing section (4.1), canned paragraph (4.2) are fixed spacing post fixed orifices (2.1), spacing section (4.1) with spacing hole (1.1) clearance fit.
Specifically, the clearance fit between the limiting section (4.1) and the limiting hole (1.1) is 0.2 mm.
The limiting columns play a role in limiting and guiding, and the upper damping table is guaranteed to move up and down, and meanwhile movement of the upper damping table in all directions is limited.
Specifically speaking, the limiting column (4) is made of aviation aluminum.
The limit column is 6063AL/H59-Cu (H68-Cu), wherein 6063AL is used as aviation aluminum, and has the characteristics of light weight, excellent processing performance, excellent weldability, extrudability and electroplatability, good corrosion resistance, toughness, easiness in polishing, coating, excellent anodic oxidation effect and the like. [ H59-Cu (H68-Cu) only as the second alternative ]. The limiting column is mainly used for limiting the situation that the transverse displacement is too large due to the fact that the damping ball is too soft. Therefore, the problem of attitude adjustment and shaking of the airplane during flying is effectively solved, and dangerous actions such as crash and the like are reduced.
Specifically, the upper damping table (1) and the lower damping table (2) are made of ABS engineering plastics.
Specifically speaking, the damping ball (3) is made of rubber.
The rubber material has better damping characteristic.
The damping system is specially designed through long-term test, the damping ball material is made of a silicon rubber material with extremely good super-soft toughness, the upper damping table and the lower damping table are made of ABS engineering plastics (or other materials), the upper damping table and the lower damping table are connected together through the damping ball, and the installation is convenient and simple. The vibration absorption effect can obviously cross the resonance area, and high-frequency vibration and noise are attenuated.
The above-described embodiment represents only one embodiment of the present invention, but should not be construed as limiting the scope of the present invention. It should be noted that, for those skilled in the art, without departing from the spirit of the present invention, several changes and modifications can be made, which are within the scope of the present invention.
Claims (10)
1. The utility model provides a shock absorber support in unmanned aerial vehicle comprises damping platform, shock attenuation ball (3), spacing post (4) three, characterized by: the damping table is divided into damping table (1) and lower damping table (2), go up damping table (1) installation and be used to lead the sensor, damping table (2) are provided with down damping ball (3) with spacing post (4), damping table (2) link firmly with unmanned aerial vehicle's frame or flight control mainboard rigidity down, damping ball (3) handle go up damping table (1) with damping table (2) link together down, spacing post (4) with go up damping table (1) clearance fit.
2. The shock absorbing mount in an unmanned aerial vehicle according to claim 1, wherein: and the limiting column (4) is rigidly connected to a frame of the unmanned aerial vehicle or a flight control main board.
3. The shock absorbing mount in an unmanned aerial vehicle according to claim 1, wherein: go up shock attenuation platform (1) and present the square that has trapezoidal breach, go up fixed connection hole (1.2), 4 including 2 spacing holes (1.1), 4 and go up shock attenuation ball fixed orifices (1.3), shock attenuation platform (2) down presents the H shape, including 2 spacing post fixed orifices (2.1), 4 down fixed connection hole (2.2), 4 shock attenuation ball fixed orifices (2.3), 4 down go up fixed connection hole (1.2) and be located down on 4 angles of shock attenuation platform (2), be central symmetry, 2 spacing hole (1.1) is located two diagonal angles go up the next door of fixed connection hole (1.2), 4 down fixed connection hole (2.2) and 4 go up fixed connection hole (1.2) and correspond the setting, 2 spacing post fixed orifices (2.1) and 2 spacing hole (1.1) corresponds the setting.
4. The shock absorbing mount in an unmanned aerial vehicle according to claim 3, wherein: 4 fixed connection hole (2.2) and unmanned aerial vehicle's frame or fly to control mainboard fixed connection down, 4 go up fixed connection hole (1.2) and inertial navigation sensor fixed connection.
5. The shock absorbing mount in an unmanned aerial vehicle according to claim 3, wherein: the damping ball (3) is 4, and the shape is multisection structure, including 4 annular groove, and top-down is first recess (3.1), second recess (3.2), third recess (3.3) and fourth recess (3.4) in proper order, it establishes to go up damping ball fixed orifices (1.3) inlay on second recess (3.2), lower damping ball fixed orifices (2.3) inlay and establish on fourth recess (3.4).
6. The shock absorbing mount in an unmanned aerial vehicle according to claim 3, wherein: the number of the limiting columns (4) is 2, each limiting column (4) is sequentially a limiting section (4.1) and a fixing section (4.2) from top to bottom, the diameter of the fixing section (4.2) is smaller than that of the limiting section (4.1), the fixing section (4.2) is fixed in the limiting column fixing hole (2.1), and the limiting section (4.1) is in clearance fit with the limiting hole (1.1).
7. The shock absorbing mount in an unmanned aerial vehicle according to claim 6, wherein: the clearance fit between the limiting section (4.1) and the limiting hole (1.1) is 0.2 mm.
8. The shock absorbing mount in an unmanned aerial vehicle according to claim 1, wherein: the limiting column (4) is made of aviation aluminum.
9. The shock absorbing mount in an unmanned aerial vehicle according to claim 1, wherein: the upper damping table (1) and the lower damping table (2) are made of ABS engineering plastics.
10. The shock absorbing mount in an unmanned aerial vehicle according to claim 1, wherein: the damping ball (3) is made of rubber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822134229.0U CN210769996U (en) | 2018-12-20 | 2018-12-20 | Shock absorption support in unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822134229.0U CN210769996U (en) | 2018-12-20 | 2018-12-20 | Shock absorption support in unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN210769996U true CN210769996U (en) | 2020-06-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822134229.0U Active CN210769996U (en) | 2018-12-20 | 2018-12-20 | Shock absorption support in unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114353793A (en) * | 2022-03-17 | 2022-04-15 | 天津时空经纬测控技术有限公司 | Vibration reduction mounting plate applied to sensitive device |
-
2018
- 2018-12-20 CN CN201822134229.0U patent/CN210769996U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114353793A (en) * | 2022-03-17 | 2022-04-15 | 天津时空经纬测控技术有限公司 | Vibration reduction mounting plate applied to sensitive device |
| CN114353793B (en) * | 2022-03-17 | 2022-06-24 | 天津时空经纬测控技术有限公司 | Vibration reduction mounting plate applied to sensitive device |
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