CN107472513A - A kind of hollow blade and its manufacture method for depopulated helicopter - Google Patents
A kind of hollow blade and its manufacture method for depopulated helicopter Download PDFInfo
- Publication number
- CN107472513A CN107472513A CN201710718422.6A CN201710718422A CN107472513A CN 107472513 A CN107472513 A CN 107472513A CN 201710718422 A CN201710718422 A CN 201710718422A CN 107472513 A CN107472513 A CN 107472513A
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- China
- Prior art keywords
- tubulose
- blade
- elastic supporting
- supporting beams
- hollow blade
- Prior art date
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- 238000004519 manufacturing process Methods 0.000 title claims abstract description 34
- 238000000034 method Methods 0.000 title claims abstract description 24
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 32
- 239000004917 carbon fiber Substances 0.000 claims abstract description 32
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 27
- 238000009954 braiding Methods 0.000 claims abstract description 24
- 238000005516 engineering process Methods 0.000 claims abstract description 15
- 229910052751 metal Inorganic materials 0.000 claims description 13
- 239000002184 metal Substances 0.000 claims description 13
- 238000013461 design Methods 0.000 claims description 11
- 239000000835 fiber Substances 0.000 claims description 9
- 238000002156 mixing Methods 0.000 claims description 9
- 238000003466 welding Methods 0.000 claims description 8
- 238000009941 weaving Methods 0.000 claims description 7
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 6
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 6
- 229910052799 carbon Inorganic materials 0.000 claims description 6
- 229910000679 solder Inorganic materials 0.000 claims description 5
- 238000001125 extrusion Methods 0.000 claims description 4
- 229920002492 poly(sulfone) Polymers 0.000 claims description 4
- 229910052786 argon Inorganic materials 0.000 claims description 3
- 239000002243 precursor Substances 0.000 claims description 3
- 238000004321 preservation Methods 0.000 claims description 3
- 238000002791 soaking Methods 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 3
- 239000004696 Poly ether ether ketone Substances 0.000 claims description 2
- 238000000280 densification Methods 0.000 claims description 2
- 229920002530 polyetherether ketone Polymers 0.000 claims description 2
- 239000000463 material Substances 0.000 abstract description 4
- 238000009940 knitting Methods 0.000 abstract description 2
- 238000004804 winding Methods 0.000 abstract 1
- 239000002131 composite material Substances 0.000 description 5
- 238000010438 heat treatment Methods 0.000 description 4
- 229910000838 Al alloy Inorganic materials 0.000 description 3
- 229910045601 alloy Inorganic materials 0.000 description 3
- 239000000956 alloy Substances 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 239000011157 advanced composite material Substances 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 239000003365 glass fiber Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000009510 drug design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- RTZKZFJDLAIYFH-UHFFFAOYSA-N ether Substances CCOCC RTZKZFJDLAIYFH-UHFFFAOYSA-N 0.000 description 1
- -1 ether Ketone Chemical class 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 229920000570 polyether Polymers 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 239000012779 reinforcing material Substances 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 239000002023 wood Substances 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
- B64C11/24—Hollow blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a kind of hollow blade and its manufacture method for depopulated helicopter, it is related to airborne vehicle technical field, is civilian economy type product.Including elastic supporting beams after elastic supporting beams before the tubulose welded together back-to-back and tubulose, the outside of hollow blade is surrounded by carbon fiber braiding layer, and one end of elastic supporting beams is welded with blade connection metalwork before tubulose, and the carrying for overall blade supports.Depopulated helicopter blade of the present invention, the structure without interior addition honeycomb lightweighting materials is formed using carbon fiber winding knitting skill, simple production technology is formd, overall lightweight, possesses elasticity degree of disturbing resistivity, cost can be reduced, it is safe and reliable.And aerodynamically require to be provided with rational lift profile, and the monnolithic case of noise reducing, be that a kind of reliable load of depopulated helicopter undertakes blade.
Description
Technical field
The present invention relates to Aircraft Design technical field is belonged to, advanced composite material (ACM) manufacturing process technology field is belonged to,
More particularly to a kind of hollow blade and its manufacture method for depopulated helicopter.
Background technology
The main bearing carrier of depopulated helicopter is blade, it is desirable to：1）Good aerodynamic configuration, maintain more preferable rotor special
Property；2）Reliability is good with maintainability, should reduce amount of parts and improve fastening reliability；3）Security uses the longevity with length
Life；4）Low cost.It is consequently adapted to the competition requirement of the market low price and performance of depopulated helicopter.
Because the paddle blade structure of existing helicopter is extremely complex, production technology difficulty is very big.As shown in figure 1, general set
The support beam 1 of central part, mostly hollow metal pipe, are welded after taking aluminum alloy plate materials brake forming（Leave weld seam 11）.
The front portion of support beam 1 is also provided with counterweight 115, to balance rotary inertia when blade rotates at a high speed.In order to eliminate oar in the winter time
Floating ice on leaf, heating pad 118 is with the addition of in the inside of blade wear rib 116.Honeycomb core is with the addition of at the rear portion of support beam 1
114, to mitigate the deadweight of blade, maintain the lift profile needed.In order to increase the surface strength of blade, there is provided compound glass
Fiber composite layer, carbon fibre composite can be used in the structure of blade afterbody trimmer 119.Some special technologies will
Asking needs to set blade situation test layer, i.e. strain gauge sets layer, the intensity and rigidity of blade are had no effect.Outermost
Layer is enamelled coating 113, maintains the waterproof of blade and wear-resisting feature.It is clear that such blade design will necessarily increase manufacture
Cost and low yield rate.
In Patent Application Publication CN103359285A, it is described how the adjusting apparatus of increase helicopter blade lift,
Movable adjustment sheet devices are set up in blade afterbody and windward side, it is such to design the manufacture hardly possible for undoubtedly adding helicopter blade
Degree, also bring the rational design difficulty of control rod member.Therefore depopulated helicopter blade design structure can not be used as.
Being described in Patent Application Publication CN1341534A first has process industry technology to use " clam shell " formula processing unit (plant),
And " wet " method resin dips reinforcing material technique, increase the surface pressing of carbon fibre composite using air pressure, be molded
The shape control formed in journey.Such production Technology necessarily brings that production efficiency is extremely low, and yield rate is also relatively low
As a result.Obviously such production Technology is excessively complicated, unavailable in the blade production of depopulated helicopter.
The blade design of variable cross-section shape is described in Patent Application Publication CN105358429A, is flown for fixed-wing
This design can suitably adjust the use range of thrust for device, improve propulsive force.But just must not for helicopter blade
So to design.Depopulated helicopter blade can be designed to simple aerodynamic lift shape, simplify manufacture difficulty.
In summary, the Key technique problem that depopulated helicopter blade sums up has：1）Simplify structure design；2）Simplify production
Technique；3）Lightweight；Meet intensity and rigidity, fatigue performance；4）Finally reduce cost.Otherwise it can be formed and promote unmanned plane skill
The obstacle of art.
The content of the invention
The present invention seeks to：To solve the Key technique problem of above-mentioned depopulated helicopter blade, the present invention provides a kind of use
In the hollow blade and its manufacture method of depopulated helicopter.
The technical scheme is that：
A kind of hollow blade for depopulated helicopter, the hollow blade include elasticity before the tubulose that welds together back-to-back
Elastic supporting beams after support beam and tubulose, the outside of hollow blade are surrounded by carbon fiber braiding layer, the one of elastic supporting beams before tubulose
End is welded with blade connection metalwork, and the carrying for overall blade supports.
Preferably, before the tubulose after elastic supporting beams and tubulose elastic supporting beams include respectively upper oar face, lower oar face and
Contact surface, the two is welded back-to-back in contact surface, oar face, the difference tangent connection of transition of lower oar face in correspondence.
Preferably, the blade connection metalwork end is left inlays prominent tubulose front support with elastic supporting beams before tubulose
Beam inner liner portion and with tubulose front support beam solder side.
A kind of manufacture method of hollow blade for depopulated helicopter, including step：
S1, using argon arc welding technique, elastic supporting beams contact surface after elastic supporting beams before tubulose and tubulose is welded on back-to-back
Together, then end is connected metalwork with blade and welded together；
S2, the braiding production technology using tension force, three layers of densification are formed in 45 ° of weaving carbon fibers of hollow blade surface crosswise
Carbon fiber braiding layer；
The hollow blade blank that S3, braiding are completed is put into metal die, and metal die is put into baking oven after bolt presses,
Straight forming at a temperature of less than 350 °C；
The hollow blade being molded in S4, baking oven is placed in 6-12 MPa heat preservation pressure tanks again, and forming temperature is：275-350 °C,
Soaking time 30 minutes.
Preferably, the manufacture of elastic supporting beams and elastic supporting beams after tubulose is continuously squeezed using Conform before the tubulose
Press is directly according to design shape extrusion forming.
Preferably, the braiding production technology using tension force, it is desirable to maintain the broken of 12% blending carbon fiber wire
Disconnected tension force is woven, and maintains the consistency of outer three layers of carbon fiber braiding layer.
Preferably, blending carbon fiber wire used in the carbon fiber braiding layer is 56-65%T300 carbon fibre precursors, its
Remaining is polysulfones and polyetheretherketonefiber fiber similar in carbon fiber wire diameter.
Preferably, the inner surface of the metal die is provided with equally distributed micropore, and each micropore is connected a house steward, put
After entering the blade blank that braiding is completed, the sealing of upper/lower die bolt presses, and vacuum state, maintain 1*10-2Pa negative pressure.
It is an advantage of the invention that：
Hollow blade and its manufacture method provided by the present invention for depopulated helicopter, structure and simple production process, it is full
Product lightweight is realized on the premise of sufficient intensity and rigidity, fatigue performance, finally reduces cost, thus, can be with relatively low
Cost produce the hollow blade that depopulated helicopter uses, meet that its function solves above-mentioned key core technical problem, favorably
In the popularization of unmanned air vehicle technique.
Brief description of the drawings
Below in conjunction with the accompanying drawings and embodiment the invention will be further described：
Fig. 1：Existing helicopter blade structural representation；
Fig. 2：Depopulated helicopter blade cross section structure signal of the present invention；
Fig. 3：Depopulated helicopter blade main structure assembling signal of the present invention；
Fig. 4：The section of elastic supporting beams 2 before tubulose；
Fig. 5：The section of elastic supporting beams 21 after tubulose；
Fig. 6：Blade connection metal component structure signal；
Fig. 7：The braiding signal of carbon fiber braiding layer；
Fig. 8：The blade blank that braiding is completed is put into metal mould forming signal.
In figure：1-support beam；11-support beam weld seam；111-blade situation test layer；112-glass fibre composite wood
The bed of material；113-enamelled coating；114-honeycomb core；115-counterweight；116-chafing strip；117-leading edge shield；118-heating pad；
119-trimmer；
Elastic supporting beams before 2-tubulose；Elastic supporting beams after 21-tubulose；211-go up oar face windward side；212-upper oar face is big
Arcwall face；213-lower oar face lifting surface；214-with tubulose after elastic supporting beams contact surface；215-blade tails；
22-carbon fiber braiding layer；221-longitude and latitude weaving carbon fiber；222-intersect 45 ° of weaving carbon fibers；23-blade connects
Metalwork；231-blade fixing threaded hole；232-blade connection exposed parts；233-tubulose front support beam inner liner portion；
234-with tubulose front support beam solder side；24-tubulose front support beam and tubulose rear support beam attachment weld；25-blade connects
Metalwork and tubulose front support beam attachment weld；The blade blank that 3-braiding is completed；
4-under touch tool；5-above touch tool.
Embodiment
Embodiment is substantially exemplary, and not is intended to limit the disclosed invention patent application, and
The use of the embodiment of the present disclosure.The explanation of the specific device, technology and the application that are provided only is used as example.It is described herein to show
The modification of example will be apparent for one skilled in the relevant art, and in the spirit and model without departing substantially from the disclosure
In the case of enclosing, the rule being defined herein can apply to other examples and application.In addition, aforementioned technical field, the back of the body
Itd is proposed in scape technology, the content of the invention or following detailed description it is any express or imply theoretical binding character is not present.This public affairs
Opening should be consistent with the scope of claims, and is not limited to example illustrated and described herein.
Embodiment of the disclosure can be described herein according to function and/or logical block components and various processing steps.Should
Understand, such block assembly can be by being configured to perform any number of hardware, software and/or the firmware of specified function
Component is realized.For simplicity, the aerodynamics with system, hydrodynamics, structure, control surface, manufacture and its
In terms of his function and the relevant routine techniques of individual operating components and component of system may not be described in detail here.In addition,
Technical staff in the art will be understood that embodiment of the disclosure can be carried out together with reference to various structures, and herein
Described embodiment is only the exemplary embodiment of the disclosure.
As shown in Fig. 2 a kind of depopulated helicopter proposed by the present invention uses carbon fibre composite hollow blade, it is a kind of
Simplify design, eliminate many additional bed courses and froth bed in existing blade technology, only with aluminum alloy extrusion section bar --- pipe
Elastic supporting beams 21 are used as liner after elastic supporting beams 2 and tubulose before shape, in welding after blade connection metalwork 23 can with
Outer braid carbon fiber blended ratio, form hollow blade blank.
As shown in figure 3, blade inner supporting structure proposed by the present invention is with bullet after elastic supporting beams before tubulose 2 and tubulose
Property support beam 21 use argon arc welding in the seam crossing of contact surface 214 back-to-back, before after welding inspection by tubulose elasticity branch
Support beam 2 is inserted in tubulose front support beam inner liner portion 233, and metalwork 23 is being connected with blade with tubulose front support beam solder side 234
Welding, form carrying supporting construction inside complete blade.
Need to further illustrate herein, elastic supporting beams 2 and elastic supporting beams 21 after tubulose are to pass through Conform before tubulose
The aluminium alloy extrusions that extruder is produced, itself does not have weld seam, and 6 series alloys extrudates are in T6 conditions of heat treatment, are in
Reveal the state that rigidity and intensity meet to require, be that 60% original bends even welding is also only the local losses strength of materials
Take intensity.This fully meets the constraints of blade aerodynamic load.
Additional information, Conform extruders are utilization friction roller and the mould continuously extruding aluminum of cable companies of Britain invention
The production equipment of alloy profile, it is characterized in that the physical dimension of product is determined with manufacturing tolerance by metal die, therefore can
To produce more accurately geometric tolerances product.
As shown in figs. 4 and 5, before tubulose after elastic supporting beams 2 and tubulose elastic supporting beams 21 back-to-back in contact surface 214
Seam crossing welding should also maintain：The tangent connection of transition of the upper big arcwall face 212 in oar face and lower oar face lifting surface 213, must not influence
The geometry of upper oar face windward side 211.
As shown in fig. 6, herein it may also be noticed that blade connection metalwork 23 is also that have selected at 6 series alloys extrudates
In T6 conditions of heat treatment, blade fixing threaded hole 231, blade connection exposed parts 232, tubulose are processed with mach means
Front support beam inner liner portion 233, and solder side 234.
As shown in fig. 7, carbon fiber braiding layer 22 is taken as intersected 45 ° of weaving carbon fibers 222 in figure, including through knitting device carbon
Fiber 221, all surfaces product including blade tails 215, but the blending carbon fiber wire of pretension 12% must be taken
Fracture Force tenses, under conditions of so three layers of blending carbon fiber wire could be woven required by consistency maintains.Here made
Blending carbon fiber wire is 56-65%T300 carbon fibre precursors, and remaining is polysulfones similar in carbon fiber wire diameter and polyethers ether
Ketone（PEEK- polysulfones and polyetheretherketone）Fiber.Illustrate proposed by the present invention hollow
Blade is without using bonded adhesive.So, tubulose front support beam is connected with tubulose rear support beam attachment weld 24 with blade
Metalwork is all wrapped in blending carbon fiber wire braiding layer with tubulose front support beam attachment weld 25, forms blade blank 3.
Then, according to mode as shown in Figure 8, the blade blank 3 for weaving completion is lain in metal die, uses spiral shell
The mode that bolt is fixed is touched tool 4 by under and fixed with above touching tool 5, keeps die cavity interior sealing.Because touched under metal molding die tool 4 with it is upper
Touch tool 5, it is characterised in that the inner surface of mould is provided with 0.002mm uniform micropore, and its spacing is 20mm square, connects one always
Pipe, thus after the blade blank 3 that braiding is completed is put into, the sealing of upper/lower die bolt presses, and state is vacuumized, maintain 1*
10-2Pa negative pressure.
Then, blade blank 3 is placed on together with metal die in 6-12 MPa heat preservation pressure tanks, forming temperature is：
275-350 °C, soaking time 30 minutes.Removed in stamping press tank, after cooling by hollow blade under mould gets on, through somewhat repairing
It can just be used with being directly installed on depopulated helicopter.Because through mould and quantitatively weaving the process of blending carbon fiber wire, do not have
There is unnecessary bonded adhesive, so hollow blade product remains identical deadweight, totally unnecessary carry out dynamic balancing adjustment.
The above embodiments merely illustrate the technical concept and features of the present invention, and its object is to allow person skilled in the art
Present disclosure can be understood and implemented according to this, it is not intended to limit the scope of the present invention.It is all main according to the present invention
The modification for wanting the Spirit Essence of technical scheme to be done, it should all be included within the scope of the present invention.
Claims (8)
- A kind of 1. hollow blade for depopulated helicopter, it is characterised in that：The hollow blade includes being welded on one back-to-back Elastic supporting beams before the tubulose risen（2）With elastic supporting beams after tubulose（21）, the outside of hollow blade is surrounded by carbon fiber braiding layer （22）, elastic supporting beams before tubulose（2）One end be welded with blade connection metalwork（23）, the carrying branch for overall blade Support.
- 2. hollow blade according to claim 1, it is characterised in that：Elastic supporting beams before the tubulose（2）After tubulose Elastic supporting beams（21）Include upper oar face, lower oar face and contact surface respectively, the two is welded back-to-back in contact surface, oar in correspondence Face, the difference tangent connection of transition of lower oar face.
- 3. the manufacture method of hollow blade according to claim 1, it is characterised in that the blade connects metalwork（23） Leave and elastic supporting beams before tubulose end（2）Inlay prominent tubulose front support beam inner liner portion（233）With with tubulose front support Beam solder side（234）.
- 4. the manufacture method of a kind of hollow blade for depopulated helicopter, it is characterised in that including step：S1, using argon arc welding technique, by elastic supporting beams before tubulose（2）With elastic supporting beams after tubulose（21）Contact surface is back-to-back Weld together, then end is connected metalwork with blade（23）Weld together；S2, the braiding production technology using tension force, three layers of densification are formed in 45 ° of weaving carbon fibers of hollow blade surface crosswise Carbon fiber braiding layer；The hollow blade blank that S3, braiding are completed is put into metal die, and metal die is put into baking oven after bolt presses, Straight forming at a temperature of less than 350 °C；The hollow blade being molded in S4, baking oven is placed in 6-12 MPa heat preservation pressure tanks again, and forming temperature is：275-350 °C, Soaking time 30 minutes.
- 5. the manufacture method of hollow blade according to claim 4, it is characterised in that elastic supporting beams before the tubulose （2）With elastic supporting beams after tubulose（21）Manufacture using Conform continuous extruders directly according to design shape extrusion forming.
- 6. the manufacture method of hollow blade according to claim 4, it is characterised in that the volume using tension force Knit production technology, it is desirable to maintain the disrumpent feelings tension force of 12% blending carbon fiber wire to be woven, maintain outer three layers of carbon fiber braiding layer Consistency.
- 7. the manufacture method of hollow blade according to claim 6, it is characterised in that the carbon fiber braiding layer is used Blending carbon fiber wire be 56-65%T300 carbon fibre precursors, remaining is polysulfones and polyether-ether-ketone similar in carbon fiber wire diameter Fiber.
- 8. the manufacture method of hollow blade according to claim 4, it is characterised in that the inner surface of the metal die is set There is equally distributed micropore, each micropore connects a house steward, after the blade blank that braiding is completed is put into, upper/lower die bolt pressure Tightening seal, and vacuum state, maintain 1*10-2Pa negative pressure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710718422.6A CN107472513A (en) | 2017-08-21 | 2017-08-21 | A kind of hollow blade and its manufacture method for depopulated helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710718422.6A CN107472513A (en) | 2017-08-21 | 2017-08-21 | A kind of hollow blade and its manufacture method for depopulated helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107472513A true CN107472513A (en) | 2017-12-15 |
Family
ID=60601838
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710718422.6A Pending CN107472513A (en) | 2017-08-21 | 2017-08-21 | A kind of hollow blade and its manufacture method for depopulated helicopter |
Country Status (1)
| Country | Link |
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| CN (1) | CN107472513A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111042709A (en) * | 2019-12-31 | 2020-04-21 | 安徽科蓝特铝业有限公司 | Antique door made of aluminum alloy section and preparation method of antique door |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB458312A (en) * | 1935-06-21 | 1936-12-17 | Cierva Autogiro Co Ltd | Improvements in and relating to rotor blades for aircraft sustaining rotors |
| GB625778A (en) * | 1947-03-31 | 1949-07-04 | Cierva Autogiro Co Ltd | Improvements relating to rotor blades for helicopters and the like rotary-winged aircraft |
| CN87106780A (en) * | 1987-02-02 | 1988-08-17 | 联合工艺公司 | The molding methods of pre-curing temperature resin |
| US5462408A (en) * | 1992-12-23 | 1995-10-31 | Europcopter France | Blade made of thermoplastic composite, in particular for ducted tail rotor of a helicopter, and its method of manufacture |
| CN102134372A (en) * | 2011-01-20 | 2011-07-27 | 天津市飞荣达科技有限公司 | Three-dimensional braided carbon fiber reinforced polyetheretherketone composite material and preparation method thereof |
| JP2012071805A (en) * | 2010-09-30 | 2012-04-12 | Society Of Japanese Aerospace Co Inc | Aerofoil structure using fiber reinforced composite material, and manufacturing method therefor |
| US20130164142A1 (en) * | 2011-12-23 | 2013-06-27 | Ratier Figeac | Propeller blade with reinforcing spars and boxes, and propeller comprising at least one such blade |
| CN104802982A (en) * | 2015-04-22 | 2015-07-29 | 北京航空航天大学 | Three-dimensional weaving composite integrally-formed rotor wing blade and manufacturing method thereof |
| US9499253B1 (en) * | 2010-09-09 | 2016-11-22 | Groem Brothers Aviation, Inc. | Composite rotor blade for a reaction drive rotorcraft |
| CN207523916U (en) * | 2017-08-21 | 2018-06-22 | 滁州万际航空器产业研究院有限公司 | A kind of hollow blade for unmanned helicopter |
-
2017
- 2017-08-21 CN CN201710718422.6A patent/CN107472513A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB458312A (en) * | 1935-06-21 | 1936-12-17 | Cierva Autogiro Co Ltd | Improvements in and relating to rotor blades for aircraft sustaining rotors |
| GB625778A (en) * | 1947-03-31 | 1949-07-04 | Cierva Autogiro Co Ltd | Improvements relating to rotor blades for helicopters and the like rotary-winged aircraft |
| CN87106780A (en) * | 1987-02-02 | 1988-08-17 | 联合工艺公司 | The molding methods of pre-curing temperature resin |
| US5462408A (en) * | 1992-12-23 | 1995-10-31 | Europcopter France | Blade made of thermoplastic composite, in particular for ducted tail rotor of a helicopter, and its method of manufacture |
| US9499253B1 (en) * | 2010-09-09 | 2016-11-22 | Groem Brothers Aviation, Inc. | Composite rotor blade for a reaction drive rotorcraft |
| JP2012071805A (en) * | 2010-09-30 | 2012-04-12 | Society Of Japanese Aerospace Co Inc | Aerofoil structure using fiber reinforced composite material, and manufacturing method therefor |
| CN102134372A (en) * | 2011-01-20 | 2011-07-27 | 天津市飞荣达科技有限公司 | Three-dimensional braided carbon fiber reinforced polyetheretherketone composite material and preparation method thereof |
| US20130164142A1 (en) * | 2011-12-23 | 2013-06-27 | Ratier Figeac | Propeller blade with reinforcing spars and boxes, and propeller comprising at least one such blade |
| CN104802982A (en) * | 2015-04-22 | 2015-07-29 | 北京航空航天大学 | Three-dimensional weaving composite integrally-formed rotor wing blade and manufacturing method thereof |
| CN207523916U (en) * | 2017-08-21 | 2018-06-22 | 滁州万际航空器产业研究院有限公司 | A kind of hollow blade for unmanned helicopter |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111042709A (en) * | 2019-12-31 | 2020-04-21 | 安徽科蓝特铝业有限公司 | Antique door made of aluminum alloy section and preparation method of antique door |
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Application publication date: 20171215 |