CN202896882U - Shockproof structure of aircraft onboard equipment - Google Patents
Shockproof structure of aircraft onboard equipment Download PDFInfo
- Publication number
- CN202896882U CN202896882U CN 201220588173 CN201220588173U CN202896882U CN 202896882 U CN202896882 U CN 202896882U CN 201220588173 CN201220588173 CN 201220588173 CN 201220588173 U CN201220588173 U CN 201220588173U CN 202896882 U CN202896882 U CN 202896882U
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- China
- Prior art keywords
- damping
- silica gel
- connecting panel
- fine
- carbon
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- Expired - Fee Related
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Abstract
The utility model discloses a shockproof structure of aircraft onboard equipment. The shockproof structure comprises two shock absorption carbon fiber connecting plates and a plurality of shock absorption rubber rings, wherein the two shock absorption carbon fiber connecting plates are arranged vertically and symmetrically; a plurality of connecting lugs extending outwards are arranged on the circumference of each shock absorption carbon fiber connecting plate; the connecting part of the two shock absorption carbon fiber connecting plates is provided with vertically opposite connecting holes; and a plurality of shock absorption rubber rings are in one-to-one correspondence to the vertically opposite connecting holes and tightly sleeved in the vertically opposite connecting holes. The shockproof structure of the aircraft onboard equipment is simple in structure, shockproof and beneficial to normal work of the aircraft onboard equipment.
Description
Technical field
The utility model relates to a kind of aircraft, particularly the moving structure of a kind of air craft carried equipment shock-proof.
Background technology
Existing unmanned vehicle airborne equipment directly passes through screw or The Cloud Terrace lock hanging on aircraft, be subjected to airflow influence in the aircraft flight process, vibrations are large, owing to be subject to the impact of aircraft self bearing capacity, be carried at carry-on airborne equipment and be generally high-accuracy airborne equipment, high to the environmental requirement of using.The invention is created under such background.
The utility model content
The utility model purpose is in order to overcome the deficiencies in the prior art, to provide simple in structure, and damping is conducive to the moving structure of a kind of air craft carried equipment shock-proof of airborne equipment normal operation.
The purpose of this utility model is achieved through the following technical solutions:
Air craft carried equipment shock-proof moves structure, comprise the fine connecting panel of two damping carbon and damping cushion rubber, two damping carbon are fine, and connecting panel is upper and lower is symmetrical arranged, the fine connecting panel periphery of damping carbon is provided with a plurality of outward extending engaging lugs, the engaging lug of the fine connecting panel of two damping carbon be provided with upper and lower over against connecting bore, the damping cushion rubber has a plurality of, a plurality of damping cushion rubbers with upper and lower over against connecting bore one by one corresponding and be tightly placed in upper and lower over against connecting bore in to realize the captive joint of the fine connecting panel of two damping carbon.
The fine connecting panel of damping carbon is sheet, and the fine connecting panel of damping carbon middle part has circular hole, is provided with a plurality of screw connecting holes along the circular hole edge.
The damping cushion rubber comprises silica gel clamping ring and twice silica gel clamping rings on the hollow silica gel post, two, hollow silica gel post two ends be set in upper and lower over against connecting bore in, the silica gel clamping ring grips the upper and lower side of engaging lug that firmly is positioned on the fine connecting panel of top damping carbon and is connected as a single entity with hollow silica gel post upper end on two; Twice silica gel clamping rings grip the upper and lower side of engaging lug that firmly is positioned on the fine connecting panel of below damping carbon and are connected as a single entity with hollow silica gel post lower end.
The utility model has following advantage and effect with respect to prior art: during actual the use, the fine connecting panel of two damping carbon is connected with screw lock with aircraft base, aircraft load respectively, the utility model can play the vibration influence that the buffering aircraft brings to the load of loading on it because of the flight vibrations like this, particularly when aircraft carries high-accuracy load, so that the load thing that aircraft carries can work, thereby strengthen the Practical Performance of aircraft.
Description of drawings
Fig. 1 is the fine connecting board structure scheme drawing of damping carbon in the utility model.
Fig. 2 is damping rubber coil structures scheme drawing in the utility model.
Fig. 3 is damping cushion rubber master cutaway view.
Fig. 4 is that the utility model is installed on the structural representation between aircraft base, the aircraft load.
Fig. 5 is the structural representation that Fig. 4 disassembles.
The specific embodiment
Below in conjunction with embodiment and accompanying drawing the utility model is described in further detail, but embodiment of the present utility model is not limited to this.
Embodiment
Extremely shown in Figure 5 such as Fig. 1, air craft carried equipment shock-proof moves structure, comprise the fine connecting panel 1 of two damping carbon and damping cushion rubber 2, fine connecting panel 1 upper and lower being symmetrical arranged of two damping carbon, fine connecting panel 1 periphery of damping carbon is provided with a plurality of outward extending engaging lugs 11, the engaging lug 11 of the fine connecting panel 1 of two damping carbon be provided with upper and lower over against connecting bore 12, damping cushion rubber 2 has a plurality of, a plurality of damping cushion rubbers 2 with upper and lower over against connecting bore 12 one by one corresponding and be tightly placed in upper and lower over against connecting bore 12 in to realize the captive joint of the fine connecting panel 1 of two damping carbon.
As shown in Figure 1, the fine connecting panel 1 of damping carbon is sheet, and the fine connecting panel of damping carbon 1 middle part has circular hole 10, is provided with three screw connecting holes 13 along circular hole 10 edges, fine connecting panel 1 periphery of damping carbon is provided with four outward extending engaging lugs 11, and engaging lug 11 is provided with connecting bore 12.
As shown in Figures 2 and 3, damping cushion rubber 2 comprises silica gel clamping ring 22 and twice silica gel clamping rings 23 on the hollow silica gel post 21, two, hollow silica gel post 21 two ends be set in upper and lower over against connecting bore 12 in, silica gel clamping ring 22 grips the engaging lug 11 upper and lower sides that firmly are positioned on the fine connecting panel 1 of top damping carbon and is connected as a single entity with hollow silica gel post 21 upper ends on two; Twice silica gel clamping rings 23 grip the engaging lug 11 upper and lower sides that firmly are positioned on the fine connecting panel 1 of below damping carbon and are connected as a single entity with hollow silica gel post 21 lower ends.
As shown in Figure 4 and Figure 5, during actual the use, the fine connecting panel 1 of two damping carbon is connected with aircraft base 3, aircraft load 4 usefulness screw lock respectively, and aircraft load 4 can be air craft carried camera-shooting and recording device or media cylinder.The utility model can play the vibration influence that the buffering aircraft brings to the load of loading on it because of the flight vibrations like this, particularly when aircraft carries high-accuracy load, so that the load thing that aircraft carries can work, thereby strengthen the Practical Performance of aircraft.
Claims (3)
1. air craft carried equipment shock-proof moves structure, it is characterized in that: comprise the fine connecting panel of two damping carbon and damping cushion rubber, two damping carbon are fine, and connecting panel is upper and lower is symmetrical arranged, the fine connecting panel periphery of damping carbon is provided with a plurality of outward extending engaging lugs, the engaging lug of the fine connecting panel of two damping carbon be provided with upper and lower over against connecting bore, described damping cushion rubber has a plurality of, a plurality of damping cushion rubbers with upper and lower over against connecting bore one by one corresponding and be tightly placed in upper and lower over against connecting bore in to realize the captive joint of the fine connecting panel of two damping carbon.
2. described air craft carried equipment shock-proof moves structure according to claim 1, it is characterized in that: the fine connecting panel of described damping carbon is sheet, and the fine connecting panel of damping carbon middle part has circular hole, is provided with a plurality of screw connecting holes along the circular hole edge.
3. described air craft carried equipment shock-proof moves structure according to claim 1, it is characterized in that: described damping cushion rubber comprises silica gel clamping ring and twice silica gel clamping rings on the hollow silica gel post, two, hollow silica gel post two ends be set in upper and lower over against connecting bore in, the silica gel clamping ring grips the upper and lower side of engaging lug that firmly is positioned on the fine connecting panel of top damping carbon and is connected as a single entity with hollow silica gel post upper end on two; Twice silica gel clamping rings grip the upper and lower side of engaging lug that firmly is positioned on the fine connecting panel of below damping carbon and are connected as a single entity with hollow silica gel post lower end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220588173 CN202896882U (en) | 2012-11-08 | 2012-11-08 | Shockproof structure of aircraft onboard equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220588173 CN202896882U (en) | 2012-11-08 | 2012-11-08 | Shockproof structure of aircraft onboard equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202896882U true CN202896882U (en) | 2013-04-24 |
Family
ID=48117582
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220588173 Expired - Fee Related CN202896882U (en) | 2012-11-08 | 2012-11-08 | Shockproof structure of aircraft onboard equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202896882U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103738504A (en) * | 2014-01-06 | 2014-04-23 | 深圳市大疆创新科技有限公司 | Loading support for aircraft, aircraft and shock absorption method for aircraft |
| CN103754377A (en) * | 2014-01-10 | 2014-04-30 | 江苏艾锐泰克无人飞行器科技有限公司 | Aerial photography holder |
| CN104315060A (en) * | 2014-09-30 | 2015-01-28 | 徐工集团工程机械股份有限公司科技分公司 | Triangular stable support type vibration isolator |
| CN104379959A (en) * | 2014-03-31 | 2015-02-25 | 深圳市大疆创新科技有限公司 | Damping device and aircraft employing same |
| CN104512551A (en) * | 2015-01-15 | 2015-04-15 | 九江松田工程有限公司 | Unmanned aerial vehicle chemical sprinkling device |
| CN109335006A (en) * | 2018-09-27 | 2019-02-15 | 西安三翼航空科技有限公司 | A kind of damping device for unmanned vehicle engine |
-
2012
- 2012-11-08 CN CN 201220588173 patent/CN202896882U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103738504A (en) * | 2014-01-06 | 2014-04-23 | 深圳市大疆创新科技有限公司 | Loading support for aircraft, aircraft and shock absorption method for aircraft |
| CN103738504B (en) * | 2014-01-06 | 2017-04-19 | 深圳市大疆创新科技有限公司 | Loading support for aircraft, aircraft and shock absorption method for aircraft |
| CN103754377A (en) * | 2014-01-10 | 2014-04-30 | 江苏艾锐泰克无人飞行器科技有限公司 | Aerial photography holder |
| CN104379959A (en) * | 2014-03-31 | 2015-02-25 | 深圳市大疆创新科技有限公司 | Damping device and aircraft employing same |
| WO2015149263A1 (en) * | 2014-03-31 | 2015-10-08 | 深圳市大疆创新科技有限公司 | Damping device and aircraft using damping device |
| CN104379959B (en) * | 2014-03-31 | 2016-09-28 | 深圳市大疆创新科技有限公司 | Damping device and the aircraft of the described damping device of application |
| CN104315060A (en) * | 2014-09-30 | 2015-01-28 | 徐工集团工程机械股份有限公司科技分公司 | Triangular stable support type vibration isolator |
| CN104512551A (en) * | 2015-01-15 | 2015-04-15 | 九江松田工程有限公司 | Unmanned aerial vehicle chemical sprinkling device |
| CN109335006A (en) * | 2018-09-27 | 2019-02-15 | 西安三翼航空科技有限公司 | A kind of damping device for unmanned vehicle engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130424 Termination date: 20151108 |
|
| EXPY | Termination of patent right or utility model |