CN106741974A - A kind of propeller composite radome fairing - Google Patents
A kind of propeller composite radome fairing Download PDFInfo
- Publication number
- CN106741974A CN106741974A CN201611141364.7A CN201611141364A CN106741974A CN 106741974 A CN106741974 A CN 106741974A CN 201611141364 A CN201611141364 A CN 201611141364A CN 106741974 A CN106741974 A CN 106741974A
- Authority
- CN
- China
- Prior art keywords
- mounting disc
- spinner
- groove
- composite
- blade
- 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.)
- Pending
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 28
- 239000000203 mixture Substances 0.000 claims description 3
- 230000002787 reinforcement Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 239000002023 wood Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
Abstract
The invention discloses a kind of propeller composite radome fairing, it includes composite mounting disc, composite spinner and composite annular plate；It is respectively uniformly distributed on the corresponding position in the relative one end of mounting disc and spinner after being docked with the number identical of blade and forms the blade mounting hole A and blade mounting hole B of an overall blade mounting hole；Groove is left on mounting disc outer wall between blade mounting hole A, the spinner wall end between blade mounting hole B is fixed on the groove of mounting disc；Mounting disc leaves annular groove away from one end of spinner, and annular slab is fixed at the annular groove of mounting disc.Using propeller of the invention, assembly and disassembly window need not be increased when propeller is assembled to engine and when changing the consumable accessory on rear side of propeller on casing is started, assembly and disassembly is very convenient.
Description
Technical field
The present invention relates to a kind of propeller composite radome fairing.
Background technology
When front propeller radome fairing gradually develops to composite direction, composite radome fairing and metal fairings
There is larger difference, composite radome fairing requirement product structure has globality, it is impossible to have the transitional region of complexity.Such as Fig. 1 institutes
Show, composite radome fairing includes mounting disc and the two parts of spinner 1, and the mounting disc of existing composite is by inside and outside two parts 3
With 4 compositions, the split of inside and outside two parts 3 and 4 shaping is fixed together by bonding and riveting, non-dismountable.The rear side of propeller 2
With multiple bolts, propeller is fixed on the ring flange 6 of engine by multiple nuts.To be pacified at whole propeller rear portion
Sabot is sheltered from, and propeller of having no idea normally to assemble is to engine and changes the consumable accessory on rear side of propeller, it is necessary to send out
Increase dismounting window on motivation casket 5, greatly reduce the intensity for starting casing；And assembly and disassembly difficulty is than larger.
The content of the invention
The purpose of the present invention is exactly to solve the above-mentioned problems in the prior art, there is provided a kind of propeller composite
Radome fairing, uses the propeller of the radome fairing, the consumable accessory when propeller is assembled to engine and on rear side of replacing propeller
Shi Wuxu increases assembly and disassembly window on casing is started, and assembly and disassembly is very convenient.
To achieve the above object, technical solution of the invention is：A kind of propeller composite radome fairing, its bag
Include composite mounting disc, composite spinner and composite annular plate；It is corresponding in mounting disc one end relative with spinner
Position on be respectively uniformly distributed docked with the number identical of blade after form a blade peace for overall blade mounting hole
Dress hole A and blade mounting hole B；Groove is left on mounting disc outer wall between blade mounting hole A, between blade mounting hole B
Spinner wall end is fixed on the groove of mounting disc；Mounting disc leaves annular groove away from one end of spinner, and annular slab is fixed on
At the annular groove of mounting disc.
The structure of the groove that the spinner wall end between blade mounting hole B described above is fixed on mounting disc is：Should
Spinner wall end is respectively kept with corresponding assembling circular hole with the groove of mounting disc, inside mounting disc with component location guide thereon
The corresponding position riveting in hole is fixed with plate nut A, the groove of the spinner wall end and mounting disc by with plate nut A
The screw A for matching is fixed together.Plate nut A plays a part of reinforcement, and its fixed structure is firm.
The structure that annular slab described above is fixed at the annular groove of mounting disc is：Mounting disc and annular slab assembling
Position is respectively kept with corresponding assembling circular hole, is riveted in the position corresponding with assembling circular hole thereon inside mounting disc and fixed
There is another plate nut B, mounting disc is fixed together with annular slab by the screw B matched with plate nut B.Plate nut
B plays a part of reinforcement, and its fixed structure is firm.
Annular slab described above is made up of two semicircles for forming a full circle, easily installs.
Using propeller of the invention, as long as annular slab is pulled down, it is possible on normal assembling propeller to engine and
The consumable accessory on rear side of propeller is changed, without increasing assembly and disassembly window on casing is started, assembly and disassembly is very convenient.
Brief description of the drawings
Fig. 1 is propeller, mounting disc in the prior art and the mounting structure schematic diagram for starting casing；
Fig. 2 is front view of the invention；
Fig. 3 is exploded perspective structural representation of the invention；
Fig. 4 is the front sectional view of mounting disc in the present invention.
Specific embodiment
The present invention will be further described with specific embodiment below in conjunction with the accompanying drawings.
As shown in Figure 2, Figure 3 and Figure 4, the present embodiment includes composite mounting disc 9, composite spinner 7 and composite wood
Material annular slab 10.The number with blade is respectively uniformly distributed on the corresponding position of mounting disc 9 and the relative one end of spinner 7
The blade mounting hole A 11 and blade mounting hole B 12 of overall blade mounting hole are formed after identical docking.Installed in blade
Groove 14 is left on the outer wall of mounting disc 9 between hole A 11.The wall end 13 of spinner 7 between blade mounting hole B 12 is fixed on peace
At the groove 14 of sabot 9；Its fixed structure preferably, the spinner wall end 13 be respectively kept with the groove 14 of mounting disc it is relative
The assembling circular hole answered, plate nut A is fixed with inside mounting disc 9 in the position riveting corresponding with assembling circular hole thereon, should
It is fixed together by the screw A matched with plate nut A at spinner wall end 13 and the groove 14 of mounting disc.Mounting disc 9
Leave annular groove 16 in one end away from spinner 7.Annular slab 10 is fixed at the annular groove 16 of mounting disc；Its structure is preferred
Ground, mounting disc 9 is respectively kept with corresponding assembling circular hole with the position that annular slab 10 is assembled, inside mounting disc 9 with thereon
The corresponding position riveting of assembling circular hole is fixed with another plate nut B 15, mounting disc 9 and annular slab 10 by with supporting plate spiral shell
The screw B that female B 15 matches is fixed together.It is further preferred that annular slab 10 forms a semicircle group for full circle by two
Into easily installation.
Above-described embodiment is only preferred and exemplary, and those skilled in the art can do according to the spirit of this patent
Same technological improvement, these are all covered by the protection domain of this patent.
Claims (5)
1. a kind of propeller composite radome fairing, it includes composite mounting disc and composite spinner；Its feature exists
In it also includes composite annular plate；It is respectively uniformly distributed on the corresponding position in mounting disc one end relative with spinner
There are the blade mounting hole A and blade mounting hole B that an overall blade mounting hole is formed after being docked with the number identical of blade；
Groove is left on mounting disc outer wall between blade mounting hole A, the spinner wall end between blade mounting hole B is fixed on mounting disc
Groove；Mounting disc leaves annular groove away from one end of spinner, and annular slab is fixed at the annular groove of mounting disc.
2. propeller according to claim 1 composite radome fairing, it is characterised in that：Described blade mounting hole B
Between the structure of the spinner wall end groove that is fixed on mounting disc be：Distinguish with the groove of mounting disc the spinner wall end
Corresponding assembling circular hole is left, supporting plate spiral shell is fixed with the position riveting corresponding with assembling circular hole thereon inside mounting disc
Female A, the spinner wall end is fixed together with the groove of mounting disc by the screw A matched with plate nut A.
3. propeller according to claim 1 and 2 composite radome fairing, it is characterised in that：Described annular slab is consolidated
Being scheduled on the structure at the annular groove of mounting disc is：Mounting disc is respectively kept with corresponding component location guide with the position that annular slab is assembled
Hole, another plate nut B, mounting disc and ring are fixed with inside mounting disc in the position riveting corresponding with assembling circular hole thereon
Shape plate is fixed together by the screw B matched with plate nut B.
4. propeller according to claim 3 composite radome fairing, it is characterised in that：Described annular slab is by two
Form a semicircle composition for full circle.
5. propeller according to claim 1 and 2 composite radome fairing, it is characterised in that：Described annular slab by
Two form a semicircle composition for full circle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611141364.7A CN106741974A (en) | 2016-12-12 | 2016-12-12 | A kind of propeller composite radome fairing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611141364.7A CN106741974A (en) | 2016-12-12 | 2016-12-12 | A kind of propeller composite radome fairing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106741974A true CN106741974A (en) | 2017-05-31 |
Family
ID=58876083
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611141364.7A Pending CN106741974A (en) | 2016-12-12 | 2016-12-12 | A kind of propeller composite radome fairing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106741974A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108045557A (en) * | 2017-12-15 | 2018-05-18 | 惠阳航空螺旋桨有限责任公司 | A kind of spinner |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB435919A (en) * | 1934-07-26 | 1935-10-01 | Ernest Hilton Long | Automatic variable pitch propellor for aircraft and the like |
| GB542422A (en) * | 1940-08-24 | 1942-01-08 | Constant Speed Airscrews Ltd | Improvements in aircraft |
| US4281966A (en) * | 1978-07-07 | 1981-08-04 | Societe Nationale Industrielle Aerospatiale | Multi-blade propellers |
| US4699568A (en) * | 1984-06-25 | 1987-10-13 | Hartzell Propeller Inc. | Aircraft propeller with improved spinner assembly |
| US5035379A (en) * | 1989-04-05 | 1991-07-30 | Societe Anonyme Dite Hispano-Suiza | Movable aircraft engine cowling |
| CN101112914A (en) * | 2007-09-06 | 2008-01-30 | 北京航空航天大学 | Low-reynolds number highly effective three blade propeller adapted for stratosphere |
| DE102007028142A1 (en) * | 2007-06-19 | 2008-12-24 | Fischer, Thomas, Dipl.-Ing. | Variable-pitch propeller has one or multiple propeller blades mounted at propeller hub around radial displacement axis in adjustable manner and propeller blades are connected with propeller hub by connecting element |
| CN101528543A (en) * | 2006-10-31 | 2009-09-09 | 埃尔塞乐公司 | Side-opening jet engine nacelle |
| CN102076564A (en) * | 2008-06-25 | 2011-05-25 | 斯奈克玛 | Fairing device for nacelle of an aircraft propulsion power unit |
| CN102381469A (en) * | 2010-08-06 | 2012-03-21 | 通用电气航空系统有限公司 | Propellers for aircraft |
| CN103434641A (en) * | 2013-08-25 | 2013-12-11 | 西北工业大学 | Novel propeller utilizing Magnus effect |
| US20150086374A1 (en) * | 2013-09-26 | 2015-03-26 | Ge Aviation Systems Limited | Propeller assembly and propeller blade retention assembly |
| US20160347441A1 (en) * | 2015-06-01 | 2016-12-01 | Northrop Grumman Systems Corporation | Deployable propeller |
| CN206417206U (en) * | 2016-12-12 | 2017-08-18 | 惠阳航空螺旋桨有限责任公司 | A kind of propeller composite radome fairing |
-
2016
- 2016-12-12 CN CN201611141364.7A patent/CN106741974A/en active Pending
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB435919A (en) * | 1934-07-26 | 1935-10-01 | Ernest Hilton Long | Automatic variable pitch propellor for aircraft and the like |
| GB542422A (en) * | 1940-08-24 | 1942-01-08 | Constant Speed Airscrews Ltd | Improvements in aircraft |
| US4281966A (en) * | 1978-07-07 | 1981-08-04 | Societe Nationale Industrielle Aerospatiale | Multi-blade propellers |
| US4699568A (en) * | 1984-06-25 | 1987-10-13 | Hartzell Propeller Inc. | Aircraft propeller with improved spinner assembly |
| US5035379A (en) * | 1989-04-05 | 1991-07-30 | Societe Anonyme Dite Hispano-Suiza | Movable aircraft engine cowling |
| CN101528543A (en) * | 2006-10-31 | 2009-09-09 | 埃尔塞乐公司 | Side-opening jet engine nacelle |
| DE102007028142A1 (en) * | 2007-06-19 | 2008-12-24 | Fischer, Thomas, Dipl.-Ing. | Variable-pitch propeller has one or multiple propeller blades mounted at propeller hub around radial displacement axis in adjustable manner and propeller blades are connected with propeller hub by connecting element |
| CN101112914A (en) * | 2007-09-06 | 2008-01-30 | 北京航空航天大学 | Low-reynolds number highly effective three blade propeller adapted for stratosphere |
| CN102076564A (en) * | 2008-06-25 | 2011-05-25 | 斯奈克玛 | Fairing device for nacelle of an aircraft propulsion power unit |
| CN102381469A (en) * | 2010-08-06 | 2012-03-21 | 通用电气航空系统有限公司 | Propellers for aircraft |
| CN103434641A (en) * | 2013-08-25 | 2013-12-11 | 西北工业大学 | Novel propeller utilizing Magnus effect |
| US20150086374A1 (en) * | 2013-09-26 | 2015-03-26 | Ge Aviation Systems Limited | Propeller assembly and propeller blade retention assembly |
| CN104512547A (en) * | 2013-09-26 | 2015-04-15 | 通用电气航空系统有限公司 | Propeller assembly and propeller blade retention assembly for aircrafts |
| US20160347441A1 (en) * | 2015-06-01 | 2016-12-01 | Northrop Grumman Systems Corporation | Deployable propeller |
| CN206417206U (en) * | 2016-12-12 | 2017-08-18 | 惠阳航空螺旋桨有限责任公司 | A kind of propeller composite radome fairing |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108045557A (en) * | 2017-12-15 | 2018-05-18 | 惠阳航空螺旋桨有限责任公司 | A kind of spinner |
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