CN205877048U - Universal bumper shock absorber - Google Patents
Universal bumper shock absorber Download PDFInfo
- Publication number
- CN205877048U CN205877048U CN201620642175.7U CN201620642175U CN205877048U CN 205877048 U CN205877048 U CN 205877048U CN 201620642175 U CN201620642175 U CN 201620642175U CN 205877048 U CN205877048 U CN 205877048U
- Authority
- CN
- China
- Prior art keywords
- shock attenuation
- reducing structure
- shock reducing
- spring
- attenuation body
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn - After Issue
Links
Landscapes
- Vibration Dampers (AREA)
- Vibration Prevention Devices (AREA)
Abstract
Universal bumper shock absorber relates to a bumper shock absorber of installing on many rotor crafts. Do not have the shock attenuation facility for solving current aircraft, start, descend, during flight vibrations big, flight is unstable, the fragile problem of part designs. It includes the vibroseis connecting plate, is fixed with a plurality of shock attenuation body coupling pipe on the vibroseis connecting plate, still includes the shock attenuation body the same with shock attenuation body coupling pipe quantity, the shock attenuation body is done by rubber, and the shock attenuation body is equipped with axial through -hole, and the inner of each shock attenuation body is overlapped respectively in the outer end of each shock attenuation body coupling pipe, and the outer end of every shock attenuation body is all overlapped and is equipped with an external cover of shock attenuation, is equipped with the spring in the external cover of shock attenuation, and the one end top of spring is on the shock attenuation body, and sheathe in that the shock attenuation is external on the other end top of spring. The advantage is when engine work produces vibrations, and the accessible shock attenuation body carries out axial and radial shock attenuation with the spring, reduce to start, descend and the vibrations during flight, flight steadily, parts are not fragile.
Description
Technical field:
This utility model relates to amortisseur field, is specifically related to a kind of amortisseur being arranged on multi-rotor aerocraft.
Background technology:
Along with the continuous maturation of vehicle technology, there is aircraft range of good performance the lightest, controllable
Also constantly expanding.
But existing aircraft is not owing to having damping facility, starts, land, flight time vibrations big, flight instability, parts
Fragile, service life is short.
Summary of the invention:
Technical problem to be solved in the utility model is to provide one can reduce vibrations, reduces parts damages, and enhancing flies
The universal damper being arranged on multi-rotor aerocraft of line stabilization.
Above-mentioned purpose is achieved in that it includes vibroseis connecting plate, vibroseis connecting plate is fixed with several and subtracts
Shake body connecting tube, also includes the shock reducing structure identical with shock reducing structure connecting tube quantity, and described shock reducing structure is made by rubber, and shock reducing structure sets
Having axial through hole, the inner of each shock reducing structure to be respectively fitted over the outer end of each shock reducing structure connecting tube, the outer end of each shock reducing structure is overlapped
Being provided with a shock reducing structure overcoat, be provided with spring in shock reducing structure overcoat, one end of spring withstands on shock reducing structure, the other end top of spring
Outside shock reducing structure on set.
The utility model has the advantages that: during installation, each shock reducing structure overcoat is fixed in the frame of multi-rotor aerocraft, will
Electromotor is arranged on vibroseis connecting plate, when electromotor work produces vibrations, can be carried out axially by shock reducing structure and spring
With radial direction damping, reducing vibrations when startup, landing and flight, flight stability, parts are hardly damaged, and service life is long.
Accompanying drawing illustrates:
Fig. 1 is structural representation of the present utility model.
Detailed description of the invention:
With reference to Fig. 1, it includes vibroseis connecting plate 1, vibroseis connecting plate is fixed with several shock reducing structure connecting tubes 2,
Also including the shock reducing structure 3 identical with shock reducing structure connecting tube quantity, described shock reducing structure is made by rubber, and shock reducing structure is provided with axial leading to
Hole, the inner of each shock reducing structure is respectively fitted over the outer end of each shock reducing structure connecting tube, and the outer end of each shock reducing structure is arranged with one and subtracts
Shaking external set 4, be provided with spring 5 in shock reducing structure overcoat, one end of spring withstands on shock reducing structure, and the other end of spring withstands on shock reducing structure
Put outward.
Claims (1)
1. universal damper, is characterized in that: include vibroseis connecting plate (1), vibroseis connecting plate is fixed with several dampings
Body connecting tube (2), also includes the shock reducing structure (3) identical with shock reducing structure connecting tube quantity, and described shock reducing structure is made by rubber, damping
Body is provided with axial through hole, and the inner of each shock reducing structure is respectively fitted over the outer end of each shock reducing structure connecting tube, the outer end of each shock reducing structure
All being arranged with a shock reducing structure overcoat (4), be provided with spring (5) in shock reducing structure overcoat, one end of spring withstands on shock reducing structure, spring
The other end withstand on and put outside shock reducing structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620642175.7U CN205877048U (en) | 2016-06-27 | 2016-06-27 | Universal bumper shock absorber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620642175.7U CN205877048U (en) | 2016-06-27 | 2016-06-27 | Universal bumper shock absorber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205877048U true CN205877048U (en) | 2017-01-11 |
Family
ID=57691268
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620642175.7U Withdrawn - After Issue CN205877048U (en) | 2016-06-27 | 2016-06-27 | Universal bumper shock absorber |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205877048U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105952832A (en) * | 2016-06-27 | 2016-09-21 | 辽宁天行健航空科技有限公司 | Universal vibration damper |
-
2016
- 2016-06-27 CN CN201620642175.7U patent/CN205877048U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105952832A (en) * | 2016-06-27 | 2016-09-21 | 辽宁天行健航空科技有限公司 | Universal vibration damper |
| CN105952832B (en) * | 2016-06-27 | 2019-04-16 | 重庆国飞通用航空设备制造有限公司 | Universal damper |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170713 Address after: 402360 Dazu County, Chongqing hi tech Industrial Development Zone (AEON) Patentee after: Chongqing flying general aviation equipment manufacturing Co., Ltd. Address before: 111000 Liaoning Province, Liaoyang City Hongwei District Liaoyang grand road No. 9 Patentee before: LIAONING TIANXIANGJIAN AEROSPACE TECHNOLOGY CO., LTD. |
|
| TR01 | Transfer of patent right | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20170111 Effective date of abandoning: 20190416 |
|
| AV01 | Patent right actively abandoned |