CN203612206U - Combined twisting damper - Google Patents
Combined twisting damper Download PDFInfo
- Publication number
- CN203612206U CN203612206U CN201320791845.8U CN201320791845U CN203612206U CN 203612206 U CN203612206 U CN 203612206U CN 201320791845 U CN201320791845 U CN 201320791845U CN 203612206 U CN203612206 U CN 203612206U
- Authority
- CN
- China
- Prior art keywords
- inner core
- urceolus
- utility
- model
- recipient
- 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.)
- Expired - Lifetime
Links
- 238000005987 sulfurization reaction Methods 0.000 claims description 3
- 238000009434 installation Methods 0.000 description 7
- 230000009286 beneficial effect Effects 0.000 description 1
Images
Landscapes
- Vibration Dampers (AREA)
Abstract
The utility model provides a combined twisting damper, and aims to solve the problems that the number of propeller hub supporting arms is greater than 6, space can't meet the structural arrangement of mounting area, and structural interference occurs. According to the utility model, the technical scheme is as follows: the combined twisting damper comprises an outer barrel, inner barrels, extruding barrels and a rubber layer vulcanizing between each inner barrel and each extruding barrel, the outer barrel adopts an integrated structure, the inner barrels, the extruding barrels and the rubber layers are independent of one another, the outer barrel is fixed on a central piece through four bolts, and each inner barrel is fixed on a crossing pin through a key.
Description
Technical field
The present invention relates to helicopter design field, relate in particular to a kind of combined torsional damper.
Background technology
At present, for the mounting structure of the torsional damper of helicopter, referring to Fig. 1 and Fig. 4, it is arranged in propeller hub center piece 3 by bolt 5 by urceolus 1, and inner core 2 is arranged on propeller hub cross pin 4 by key 6, and each propeller hub support arm is installed 1 torsional damper.Its shortcoming is: because each propeller hub support arm is installed 1 torsional damper, the installation position of each torsional damper will be connected by 4 bolts 5 with the auricle stretching out in center piece 3 by the auricle stretching out on urceolus 1, and connecting portion needs certain installing space.If propeller hub support arm quantity is little≤and 6, space can meet installation position structural arrangement; If propeller hub support arm quantity > 6, space can not meet installation position structural arrangement, occurs constructive interference phenomenon.
Utility model content
The technical problems to be solved in the utility model: propose a kind of combined torsional damper, can not meet installation position structural arrangement to solve propeller hub support arm quantity > 6, space, occur the problem of constructive interference.Simplified structure, minimizing number of parts, alleviate propeller hub weight simultaneously.
The technical solution of the utility model: a kind of combined torsional damper configuration, comprising: urceolus, inner core, recipient and the sulfuration rubber layer composition between inner core and recipient; Urceolus is 1 integral structure, and on urceolus, plum blossom-shaped arranges 7 recipients 7, the interior inner core 2 that arranges of each recipient 7; Inner core 2, recipient 7 and rubber layer 8 are separately independently, and urceolus is bolted in center piece by 4, and inner core is fixed on cross pin by key.
The beneficial effects of the utility model: this torsional damper adopts array configuration for helicopter hub, adopt combined torsional damper to solve that propeller hub space is arranged, the problem of constructive interference; Simultaneously number of parts has reduced 30%, propeller hub weight saving 10%.
Accompanying drawing explanation
Fig. 1 is the scheme of installation of the existing torsional damper for helicopter.
Fig. 2 is scheme of installation 1 of the present utility model.
Fig. 3 is scheme of installation 2 of the present utility model.
Fig. 4 is the structural representation of the existing torsional damper for helicopter.
Fig. 5 is structural representation Fig. 1 of the present utility model.
Fig. 6 is structural representation Fig. 2 of the present utility model.
The specific embodiment
Below the utility model is described in further details.Referring to Fig. 5, Fig. 6, a kind of combined torsional damper configuration, it is made up of urceolus 1, inner core 2, recipient 7 and the rubber layer 8 of sulfuration between inner core and recipient.Urceolus 1 is 1 integral structure, and on urceolus 1, plum blossom-shaped arranges 7 recipients 7, the interior inner core 2 that arranges of each recipient 7.Inner core 2, recipient 7 and rubber layer 8 are separately independently, form 1 combined torsional damper in structure, but in function, are again separately independently.
Principle of work of the present utility model is: referring to Fig. 2, Fig. 3, integral type urceolus 1 is fixed in center piece 3 by 4 bolts 5, and inner core 2 is fixed on cross pin 4 by key 6 separately.An embodiment of the present utility model (7 support arm propeller hub) proves, adopts combined torsional damper to solve that propeller hub space is arranged, the problem of constructive interference; Simultaneously number of parts has reduced 30%, propeller hub weight saving 10%.
Claims (1)
1. a combined torsional damper configuration, is characterized in that, comprising: urceolus, inner core, recipient and the sulfuration rubber layer composition between inner core and recipient; Urceolus is 1 integral structure, and on urceolus, plum blossom-shaped arranges 7 recipients, in each recipient, inner core is set; Inner core, recipient and rubber layer are separately independently, and urceolus is bolted in center piece by 4, and inner core is fixed on cross pin by key.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320791845.8U CN203612206U (en) | 2013-12-04 | 2013-12-04 | Combined twisting damper |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320791845.8U CN203612206U (en) | 2013-12-04 | 2013-12-04 | Combined twisting damper |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203612206U true CN203612206U (en) | 2014-05-28 |
Family
ID=50764866
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320791845.8U Expired - Lifetime CN203612206U (en) | 2013-12-04 | 2013-12-04 | Combined twisting damper |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203612206U (en) |
-
2013
- 2013-12-04 CN CN201320791845.8U patent/CN203612206U/en not_active Expired - Lifetime
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201304875Y (en) | Rubber bushing | |
| CN202628935U (en) | Engine crankshaft shock absorber | |
| CN203362986U (en) | Motorcycle rear shock absorber with inner spring and outer spring | |
| CN102745072B (en) | Novel suspension device for back stay of gear box | |
| CN203612206U (en) | Combined twisting damper | |
| CN202274036U (en) | Air spring | |
| CN201329798Y (en) | Structure of engine suspending bracket | |
| CN203331771U (en) | Series connection type spring and shock absorber arrangement structure | |
| CN202596387U (en) | Connecting hinge for covering cap of airplane trailing edge | |
| CN201779198U (en) | Multifunctional support shock absorber | |
| CN203945913U (en) | Novel trailer balance shaft | |
| CN202169089U (en) | Rotor head group of model helicopter and model helicopter comprising same | |
| CN204196649U (en) | A kind of torsion beam rear suspension bush assembly | |
| CN204020450U (en) | A kind of combination cantilever assembly | |
| CN203125927U (en) | Extruder machine barrel structure | |
| CN202418367U (en) | Bimetal bushing | |
| CN202768709U (en) | Automobile double-cylinder damper with suspended piston rod | |
| CN209743374U (en) | Improved eccentric wheel | |
| CN103174793A (en) | Motorcycle damper | |
| CN202531732U (en) | Novel pile driver shock-absorbing mechanism | |
| CN201786718U (en) | Integral component for lower bearing gland and connecting pipe of vertical submersible slurry pump | |
| CN204400447U (en) | A kind of suspender of large-scale cylinder shaped piece | |
| CN202929254U (en) | Super-flexible optical cable with large core number for field operations | |
| CN203511348U (en) | Structure of outer protective plate for automobile electric seat | |
| CN203362929U (en) | Rubber lining with guide function in automobile suspension |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140528 |
|
| CX01 | Expiry of patent term |