CN106697262A - Composite propeller shank connecting structure for propeller - Google Patents
Composite propeller shank connecting structure for propeller Download PDFInfo
- Publication number
- CN106697262A CN106697262A CN201611141247.0A CN201611141247A CN106697262A CN 106697262 A CN106697262 A CN 106697262A CN 201611141247 A CN201611141247 A CN 201611141247A CN 106697262 A CN106697262 A CN 106697262A
- Authority
- CN
- China
- Prior art keywords
- propeller
- composite
- metal component
- metal parts
- connecting structure
- 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 49
- 239000002184 metal Substances 0.000 claims abstract description 28
- 229910052751 metal Inorganic materials 0.000 claims abstract description 28
- 239000004744 fabric Substances 0.000 claims abstract description 12
- 239000002023 wood Substances 0.000 claims description 4
- 239000011248 coating agent Substances 0.000 description 5
- 238000000576 coating method Methods 0.000 description 5
- 239000000463 material Substances 0.000 description 4
- 238000006073 displacement reaction Methods 0.000 description 3
- 230000013011 mating Effects 0.000 description 3
- 238000010894 electron beam technology Methods 0.000 description 2
- 238000009659 non-destructive testing Methods 0.000 description 2
- 150000001875 compounds Chemical class 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/02—Hub construction
- B64C11/04—Blade mountings
- B64C11/06—Blade mountings for variable-pitch blades
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses a composite propeller shank connecting structure for a propeller. The composite propeller shank connecting structure comprises a metal component, a composite bearing beam and a composite fabric layer, wherein the metal component is integrally molded; one end, connected with a propeller hub, of the metal component is a matching surface matched with a propeller bearing, an eccentric pin connected with the propeller hub extends from the end, and the other end of the metal component is provided with a cylinder; the outer wall of the cylinder is provided with double spiral bulges symmetrically arranged relative to the axis; the composite bearing beam is arranged in a spiral groove between the double spiral bulges at the outer wall of the metal component; the composite fabric layer is arranged at the outer surface of the composite bearing beam. The composite propeller shank connecting structure is high in connection strength, simple in structure and low in cost, and is applied to composite propeller blades of minitype free variable pitch propellers.
Description
Technical field
The present invention relates to a kind of propeller composite material blade root attachment structure.
Background technology
Propeller mainly includes blade and propeller hub two parts, and propeller hub is generally metal structure, and blade is progressively to composite
Direction is developed.Most propellers belong in the air can free variable-pitch propeller, the blade of propeller can be according to aircraft control system
Change blade angle in real time in the air.The attachment structure of free variable-pitch propeller requirement blade and propeller hub can ensure fast and reliable
Displacement, attachment structure need to be using parts such as bearings, therefore propeller shank must select metal structure.Propeller shank is metal
Structure, blade blade is composite structure, and metal structure is different with composite structure material attribute, metal and composite
Connection is the significant difficulty of composite material blade design.So, only large-size propeller blade uses composite structure now,
Its propeller shank attachment structure is：Propeller shank outside is metal-coating, and the surface with bearing fit is left on metal-coating, gold
Category jacket internal lays the bearing beam of composite, and composite material load-carrying beam is made up of multilayer layer of cloth, embedding in the end of bearing beam
Enter composite reverse wedge layer of cloth, make bearing beam in reverse wedge structure, play a part of to bear blade centrifugal force.Bearing beam inside is equipped with
Support tube, prevents composite internally conquassation under the action of the centrifugal force；Entirety enters stove curing molding, metal-coating and composite wood
Material is integrally formed, and then metal-coating is welded into one with the metalwork electron beam with cam pin.Because bearing beam is adopted
Reverse wedge structure is used, the space of propeller shank is occupied, metal-coating must make split-type structural, it is necessary to pass through weldering with cam pin
Connect and be integrally formed both.This attachment structure complex structure, it is necessary to electron beam welding, the assembling Various Complex technique such as reverse wedge,
Cause the cost of blade very high, the price of one piece blade exceeds well over one whole price of small propeller.Therefore this connection is tied
Structure is difficult the application on small propeller blade.
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 bonding strength is high, structure
Simply, low cost, applies the propeller composite material blade root on small-sized free variable-pitch propeller composite material blade to connect
Binding structure.
To achieve the above object, technical solution of the invention is：A kind of propeller composite material blade root connection
Structure, it includes metal parts, composite material load-carrying beam and composite layer of cloth；Metal parts is integrally formed, and it connects with propeller hub
The one end for connecing is the mating surface coordinated with propeller bearing, and leans out the cam pin being connected with propeller hub, and the other end is cylinder, cylinder
Outer wall on have the symmetrically arranged double helix in relative axle center raised；Helicla flute between the double helix projection of metal parts outer wall
Interior laying composite material load-carrying beam, composite layer of cloth is laid in the outside of composite material load-carrying beam.
Operation principle of the invention：Propeller shank metal parts is designed with cam pin, and crank is constituted with propeller hub internal structure
Slide block mechanism, it is ensured that the displacement requirement of propeller.Propeller shank metal parts leaves the mating surface coordinated with propeller bearing, puts
It is set to part bearing, it is ensured that the displacement of propeller blade.Propeller shank metal parts is designed with double helix projection, double helix projection
Between helicla flute in place the bearing beam of composite, so, blade composite portions bear when propeller rotates at a high speed
Centrifugal force can be transferred on metal parts.To prevent composite material load-carrying beam and metal parts lift-off, in outside, winding is compound
Material layer of cloth, bears the shearing force of blade.
It is very simple that composite layer of cloth of the present invention lays mode, it is not necessary to uses reverse wedge structure, and cam pin need not electricity
Beamlet is welded, and is integrally formed, and bonding strength is high, simple structure, low cost, applies in small-sized free variable-pitch propeller composite
On blade.And facilitate metal part and the join domain of composite portions to carry out Non-Destructive Testing, solve composite material blade
Root cannot Non-Destructive Testing problem.
Brief description of the drawings
Fig. 1 is front sectional view of the invention；
Fig. 2 is the structural representation of metal parts in the present invention；
Fig. 3 is the front sectional view of metal parts in the present invention；
Fig. 4 is the right view of metal parts 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 1, Figure 2, Figure 3 and Figure 4, the present embodiment includes metal parts 1, composite material load-carrying beam 2 and composite wood
Material layer of cloth 3.Metal parts 1 is integrally formed, and its one end being connected with propeller hub is the mating surface 7 coordinated with propeller bearing, and is visited
Go out the cam pin 6 being connected with propeller hub, the other end is cylinder, have the relative symmetrically arranged double helix in axle center raised on the outer wall of cylinder
4、5.Laying composite material load-carrying beam 2 in helicla flute 8 between the double helix projection 4,5 of the outer wall of metal parts 1, in composite wood
Expect that composite layer of cloth 3 is laid in the outside of bearing beam 2.
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 (1)
1. a kind of propeller composite material blade root attachment structure, it is characterised in that it includes that metal parts, composite hold
Power beam and composite layer of cloth；Metal parts is integrally formed, and its one end being connected with propeller hub is and matching somebody with somebody that propeller bearing coordinates
Conjunction face, and the cam pin being connected with propeller hub is leant out, the other end is cylinder, has relative axle center symmetrically arranged double on the outer wall of cylinder
Spiral salient；Composite material load-carrying beam is laid in helicla flute between the double helix projection of metal parts outer wall, in composite wood
Expect the outside laying composite layer of cloth of bearing beam.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611141247.0A CN106697262A (en) | 2016-12-12 | 2016-12-12 | Composite propeller shank connecting structure for propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611141247.0A CN106697262A (en) | 2016-12-12 | 2016-12-12 | Composite propeller shank connecting structure for propeller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106697262A true CN106697262A (en) | 2017-05-24 |
Family
ID=58936638
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611141247.0A Pending CN106697262A (en) | 2016-12-12 | 2016-12-12 | Composite propeller shank connecting structure for propeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106697262A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112550692A (en) * | 2021-01-06 | 2021-03-26 | 惠阳航空螺旋桨有限责任公司 | Propeller blade root and connection structure of propeller root and propeller hub |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE598169C (en) * | 1931-02-17 | 1934-06-06 | Gustav Schwarz G M B H | Method of securing a propeller wing in a hub or metal sleeve |
| GB1319235A (en) * | 1969-07-18 | 1973-06-06 | Dowty Rotol Ltd | Devices of fibrous-reinforced plastics material |
| US4260332A (en) * | 1979-03-22 | 1981-04-07 | Structural Composite Industries, Inc. | Composite spar structure having integral fitting for rotational hub mounting |
| GB8512686D0 (en) * | 1985-05-20 | 1985-06-26 | Secretary Trade Ind Brit | Articles secured together |
| US5319850A (en) * | 1990-12-27 | 1994-06-14 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Method of fixing stemmed blade for a flow-straightening stage of a gas turbine engine |
| RU2058251C1 (en) * | 1991-05-14 | 1996-04-20 | Акционерное общество Научно-производственное предприятие "Аэросила" | Method of manufacture of propeller composite blades |
| US6443701B1 (en) * | 1999-01-29 | 2002-09-03 | MüHLBAUER LUFTFAHRTTECHNIK GMBH | Blade root for propeller and rotor blades |
| CN102837823A (en) * | 2011-04-13 | 2012-12-26 | 国家宇航研究所-奥尼拉 | Rotary wing paddle, rotor comprising at least two of such paddles and method to implement such rotor |
-
2016
- 2016-12-12 CN CN201611141247.0A patent/CN106697262A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE598169C (en) * | 1931-02-17 | 1934-06-06 | Gustav Schwarz G M B H | Method of securing a propeller wing in a hub or metal sleeve |
| GB1319235A (en) * | 1969-07-18 | 1973-06-06 | Dowty Rotol Ltd | Devices of fibrous-reinforced plastics material |
| US4260332A (en) * | 1979-03-22 | 1981-04-07 | Structural Composite Industries, Inc. | Composite spar structure having integral fitting for rotational hub mounting |
| GB8512686D0 (en) * | 1985-05-20 | 1985-06-26 | Secretary Trade Ind Brit | Articles secured together |
| US5319850A (en) * | 1990-12-27 | 1994-06-14 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Method of fixing stemmed blade for a flow-straightening stage of a gas turbine engine |
| RU2058251C1 (en) * | 1991-05-14 | 1996-04-20 | Акционерное общество Научно-производственное предприятие "Аэросила" | Method of manufacture of propeller composite blades |
| US6443701B1 (en) * | 1999-01-29 | 2002-09-03 | MüHLBAUER LUFTFAHRTTECHNIK GMBH | Blade root for propeller and rotor blades |
| CN102837823A (en) * | 2011-04-13 | 2012-12-26 | 国家宇航研究所-奥尼拉 | Rotary wing paddle, rotor comprising at least two of such paddles and method to implement such rotor |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112550692A (en) * | 2021-01-06 | 2021-03-26 | 惠阳航空螺旋桨有限责任公司 | Propeller blade root and connection structure of propeller root and propeller hub |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170524 |