CN109676958A - Molding carbon fibre composite aerofoil of co-curing and preparation method thereof - Google Patents
Molding carbon fibre composite aerofoil of co-curing and preparation method thereof Download PDFInfo
- Publication number
- CN109676958A CN109676958A CN201811432386.8A CN201811432386A CN109676958A CN 109676958 A CN109676958 A CN 109676958A CN 201811432386 A CN201811432386 A CN 201811432386A CN 109676958 A CN109676958 A CN 109676958A
- Authority
- CN
- China
- Prior art keywords
- aerofoil
- precast body
- head
- molding
- carbon fibre
- 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.)
- Granted
Links
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 title claims abstract description 39
- 229910052799 carbon Inorganic materials 0.000 title claims abstract description 39
- 239000000835 fiber Substances 0.000 title claims abstract description 39
- 238000000465 moulding Methods 0.000 title claims abstract description 39
- 239000002131 composite material Substances 0.000 title claims abstract description 35
- 238000002360 preparation method Methods 0.000 title claims abstract description 12
- 238000001723 curing Methods 0.000 title description 15
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 47
- 239000004917 carbon fiber Substances 0.000 claims abstract description 47
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 47
- 238000004519 manufacturing process Methods 0.000 claims abstract description 18
- 238000012545 processing Methods 0.000 claims abstract description 18
- 239000002184 metal Substances 0.000 claims description 38
- 229910052751 metal Inorganic materials 0.000 claims description 38
- 239000000463 material Substances 0.000 claims description 11
- 239000011248 coating agent Substances 0.000 claims description 7
- 239000011247 coating layer Substances 0.000 claims description 7
- 238000000576 coating method Methods 0.000 claims description 7
- 239000003292 glue Substances 0.000 claims description 7
- 239000010410 layer Substances 0.000 claims description 6
- 238000013461 design Methods 0.000 claims description 4
- 239000004744 fabric Substances 0.000 claims description 3
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 claims 1
- 239000010931 gold Substances 0.000 claims 1
- 229910052737 gold Inorganic materials 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 7
- 238000005253 cladding Methods 0.000 abstract description 6
- 238000007711 solidification Methods 0.000 abstract description 5
- 230000008023 solidification Effects 0.000 abstract description 5
- 230000009286 beneficial effect Effects 0.000 abstract description 3
- 230000007797 corrosion Effects 0.000 description 7
- 238000005260 corrosion Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 4
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 230000004992 fission Effects 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 229920007790 polymethacrylimide foam Polymers 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000011981 development test Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 150000002118 epoxides Chemical class 0.000 description 1
- 238000002386 leaching Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000010297 mechanical methods and process Methods 0.000 description 1
- 230000005226 mechanical processes and functions Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 229920001721 polyimide Polymers 0.000 description 1
- 239000009719 polyimide resin Substances 0.000 description 1
- 238000007781 pre-processing Methods 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 229910001256 stainless steel alloy Inorganic materials 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/345—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using matched moulds
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/70—Completely encapsulating inserts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3085—Wings
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention belongs to the fields that uses of carbon fibre composite, in particular to utilize the preparation method of carbon fibre composite co-curing molding aerofoil and the aerofoil.The molding carbon fibre composite aerofoil of co-curing, it is characterized by comprising head precast body and aerofoil precast bodies, head precast body and aerofoil precast body are cementing integral, and have carbon fiber prepreg laying in the surface of head precast body and aerofoil precast body cladding curing molding.The present invention decomposes the structure of aerofoil, it is produced using the technique of parts processing combination and solidification, first time molding first is carried out to head precast body, head precast body and airfoil body structure are subjected to second of composite molding again, parts processing can reduce the difficulty of various components processing, improve production efficiency, it is also beneficial to improve the precision of product, further, the reduction of difficulty of processing meets the production requirement of requirements at the higher level but also more complex profile structure is processed into possibility.
Description
Technical field
The invention belongs to the fields that uses of carbon fibre composite, in particular to are formed using carbon fiber composite co-curing
The preparation method of aerofoil and the aerofoil.
Background technique
Missile wing is the main force support structure part of guided missile.Carbon Fiber Reinforced Composite Wing can reduce the quality of one guided missile of on-hook, increase
Big range and payload.By many years development test, we solve the mould design and manufacture and band of large scale complex component
There are the process difficulties such as the skeleton entirety laying of major joint, solidification, demoulding, has captured the technology keys such as splicing, assembling, succeeded in developing
Satisfactory Carbon Fiber Reinforced Composite Wing.
Traditional missile wing is mostly made of metal material (such as: steel, aluminium alloy, titanium alloy), can be very good to meet load
With high temperature resistant requirement, still, such metal elastic wing structure weight is larger, will affect the technical indicators such as the effective range of guided missile.Phase
Than for, composite material has many advantages, such as that specific strength is high, specific stiffness is big, designability is strong, thus, it is widely used in recent years
To aerospace structure, currently, composite material is centainly applied in missile wing, still, for increasing with complex internal reinforcement
The processing and manufacturing technical difficulty of strong missile wing structure, composite structure is very big, and production cost greatly improves or even can not be real
It now processes, therefore, it is very urgent to develop a kind of high temperature resistant composite missile wing structure.
Summary of the invention
In view of the deficiencies of the prior art,
Technical scheme is as follows:
The molding carbon fibre composite aerofoil of co-curing, it is characterised in that: including head precast body and aerofoil precast body, head
Portion's precast body and aerofoil precast body are cementing integral, and have in the surface of head precast body and aerofoil precast body cladding curing molding
Carbon fiber prepreg laying.
The head precast body includes metal lining, and the surrounding curing molding of metal lining has carbon fibre preform,
Carbon fibre preform links into an integrated entity with metal lining.
The outer surface of the metal lining is at least provided with one and the limiting section of carbon fibre preform cooperation.
The aerofoil precast body include intermediate prefabricated body and above and below intermediate prefabricated body two sides edge precast body,
Intermediate prefabricated body and head precast body are glued.
The intermediate prefabricated body includes core, and the surface of core is equipped with profile-followed carbon fiber prepreg.
The preparation method of the molding carbon fibre composite aerofoil of co-curing, it is characterised in that: the following steps are included:
Step 1: production head preform mold and unitary mould, and complete the processing of metal lining；And it is made of light material
Aerofoil core, edge core；
Step 2: by metal lining in being located in head preform mold, and carbon fibre initial rinse is used around metal lining
Material is filled, and curing molding obtains head precast body；
Step 3: head precast body and aerofoil core that step 2 obtains being positioned in unitary mould, and pass through splicing
Mode makes head precast body and aerofoil core connect into an entirety, and carries out integral coating laying with carbon fiber prepreg, makes
Standby airfoil body structure out；
Step 4: placing edge core in the two sides up and down of the aerofoil core of airfoil body structure, and carry out covering with knitted fabric
Laying, molding, injecting glue simultaneously solidify, and wait until complete aerofoil.
The integral coating laying includes following laying step: entirety a, is laid on head precast body and aerofoil core
The carbon fiber prepreg of cladding forms integral coating layer, b, upper and lower surface laying shape and aerofoil core in aerofoil core
C, upper and lower surface shape identical aerofoil laying repeats the thickness that a-b reaches design to the carbon fiber prepreg being laid with.
The integral coating layer and aerofoil laying is laid with altogether 33 layers, and pre-compacted of every 11 layers of progress.
The differential seat angle of the carbon fiber of carbon fiber prepreg used in carbon fiber prepreg described in a and b is
±45°。
Head core is additionally provided with around the head precast body of airfoil body structure in step 3.
In conclusion the invention has the following advantages:
1, the present invention decomposes the structure of aerofoil, is produced using the technique of parts processing combination and solidification, first correct
Portion's precast body carries out first time molding, then head precast body and airfoil body structure are carried out second of composite molding, and fission adds
Work can reduce the difficulty of various components processing, improve production efficiency, and the precision for being also beneficial to improve product further adds
The reduction of work difficulty meets the production requirement of requirements at the higher level but also more complex profile structure is processed into possibility.
2, the present invention ensure that the specific strength of aerofoil is high, specific modulus is big, fatigue resistance using metal lining as inserts
It is good, the surrounding of metal lining is coated on carbon fiber prepreg, it is ensured that metal lining it is corrosion-resistant, extend it and use the longevity
Life makes aerofoil using carbon fibre composite, so that aerofoil low vibration, low noise, and there is efficient and light weight, corrosion resistant spy
Property.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of aerofoil of the present invention；
Fig. 2 is the schematic cross-sectional view of Fig. 1；
Fig. 3 is the structural schematic diagram of metal lining；
Fig. 4 is the schematic diagram of the core of the structure of intermediate prefabricated body；
Fig. 5 is the schematic diagram of the carbon fiber laying of intermediate prefabricated body.
Specific embodiment
Following further describes the present invention with reference to the drawings.
As depicted in figs. 1 and 2, the molding carbon fibre composite aerofoil of co-curing, it is characterised in that: prefabricated including head
Body 6 and aerofoil precast body 7, head precast body 6 and aerofoil precast body 7 are cementing integral and pre- in head precast body 6 and aerofoil
The surface cladding curing molding of body 7 processed has carbon fiber prepreg laying 8.
Aerofoil of the present invention is made of head precast body and aerofoil precast body, is added using separate machined mode
Work, the mode of separate machined can reduce the difficulty of processing of various components, improve production efficiency, and the precision of product can also obtain
Guarantee, further, but also more complex profile structure is processed into possibility, satisfaction is higher to be wanted for the reduction of difficulty of processing
The production requirement asked；The present invention, as inserts, ensure that the specific strength of aerofoil is high, specific modulus is big, resist tired using metal lining
Labor is good, and the surrounding of metal lining is coated on carbon fiber prepreg, it is ensured that metal lining it is corrosion-resistant, extend its use
Service life makes aerofoil using carbon fibre composite, so that aerofoil low vibration, low noise, and there is efficient and light weight, it is corrosion resistant
Characteristic.
The head precast body 6 includes metal lining 1, and the shape of the metal lining 1 is rounded, and metal lining is also
Equipped with inner hole, the hole wall of inner hole is equipped with the keyway 11 of transmitting torque, and the material of the metal lining is stainless steel or titanium
Alloy；The surrounding curing molding of metal lining 1 has carbon fibre preform 2, and the carbon fibre preform can use carbon
Fiber prepreg material is laid with, and can also be laminated and be made using chopped carbon fiber material heap, carbon fibre preform and metal liner
Set links into an integrated entity.
As shown in figure 3, the outer surface of the metal lining 1 is at least provided with one and the limit of carbon fibre preform cooperation
Portion 12, the limiting section of setting increase the circumferential limit between metal lining and carbon fibre preform, avoid going out between the two
Now opposite movement, the two reliability both guaranteed, the limiting section are metal lining circumferential surface is arranged in arc-shaped
Strip projected parts, strip projected parts are axially arranged on the outer peripheral surface of metal lining, the limiting section can also using it is rectangular, three
The other shapes such as angular.
The aerofoil precast body 7 includes intermediate prefabricated body 3 and the edge of two sides is prefabricated above and below intermediate prefabricated body
Body 4 and 5, intermediate prefabricated body 3 and head precast body 6 are glued, and aerofoil precast body is also processed using separately molding mode, first
Edge precast body, is then placed on the two sides up and down of the intermediate prefabricated body of aerofoil by the processing for carrying out aerofoil intermediate prefabricated body, point
Opening processing reduces whole difficulty of processing and processing cost.
As shown in Figures 4 and 5, the intermediate prefabricated body 3 includes core 30, and the surface of core 30 is equipped with profile-followed carbon fiber
It ties up prepreg 31, the core and edge precast body above-mentioned to form using PMI Foam machining, the core is one
The section of the component of variable cross-section, core and head precast body junction is less than the section of core end, when laying, is laid with
It shortens in the length of the profile-followed carbon fiber prepreg of core surface with the increase of the laying number of plies, for example, first core
The profile-followed laying on surface is routed to the other end from one end of core, and the profile-followed laying of second core surface is spread from one end of core
It is set to from other end 0.5cm, with the increase of the number of plies of laying, the length for the profile-followed carbon fiber prepreg that core surface is laid with
Degree constantly shortens, and ensure that the structural strength of head precast body Yu aerofoil precast body weld using the above structure, will not go out
The problem of existing weld fracture.The dosage that also can be reduced carbon fiber prepreg simultaneously, so that the production cost of product obtains effectively
Control.
The preparation method of the molding carbon fibre composite aerofoil of co-curing is illustrated below；
The preparation method of the molding carbon fibre composite aerofoil of co-curing, it is characterised in that: the following steps are included:
Step 1: production head preform mold and unitary mould, and complete the processing of metal lining；And it is made of light material
Aerofoil core, front and back edge core；The light material is PMI foam.
Step 2: by metal lining in being located in head preform mold, and carbon fiber is used around metal lining
Prepreg is filled, and curing molding obtains head precast body；
Step 3: head precast body and aerofoil core that step 2 obtains being positioned in unitary mould, and pass through splicing
Mode makes head precast body and aerofoil core connect into an entirety, and carries out integral coating laying with carbon fiber prepreg, makes
Standby airfoil body structure out；
Step 4: on the outside of the head of airfoil body structure, front and rear edge placement head core and front and back edge core, and with warp
Braided fabric carries out covering laying, and molding, injecting glue simultaneously solidify, and waits until complete aerofoil, uses glue-injection machine automatically complete during injecting glue
At injecting glue process, when mold gas outlet has the glue of continuous bubble-free to emerge, closing gas outlet, glue-injection machine works on, directly
There is the pressure of 0.2-0.3Mpa to die cavity, closes gum-injecting port, after injecting glue is complete, then solidified, described is cured as mold
Temperature is heated to 130 DEG C of then heat preservation two hours, after completing solidification, deviates from product, polishes, modifies, finished product is made.
The invention firstly uses carbon fibre composites to prepare aerofoil, compared to more traditional metal aerofoil, has rigidity more
Good, anti-cladding is strong, damping shock absorption is good, corrosion-resistant, and the service life is long etc. a little, secondly, the present invention is using first to head and aerofoil
Separate machined preprocessing, then overall time co-curing forms, and reduces assemble flow, improves production efficiency, reduces
The production cost of aerofoil realizes inexpensive production.
The integral coating laying includes following laying step: entirety a, is laid on head precast body and aerofoil core
The carbon fiber prepreg of cladding forms integral coating layer 310, b, upper and lower surface laying shape and aerofoil core in aerofoil core
The identical aerofoil laying 311 of upper and lower surface shape, c, repeat a-b and reach the thickness of design to the carbon fiber prepreg being laid with,
It carries out replacing laying with profile-followed carbon fiber prepreg using whole, avoids occurring structural strength weakness zone in one direction,
Ensure that the overall structural strength of aerofoil, in actual mechanical process, the integral coating layer that is formed in a with a thickness of 0.125mm, b
The aerofoil laying of middle formation with a thickness of 0.125mm.
The integral coating layer and aerofoil laying is laid with altogether 33 layers, and pre-compacted of every 11 layers of progress, described
Precuring be to vacuumize and be compacted, ensure that between the carbon fiber prepreg after being laid be not in defect, avoid the occurrence of
The problem of product quality defect.
The differential seat angle of the carbon fiber of carbon fiber prepreg used in carbon fiber prepreg described in a and b is
± 45 °, laying is carried out using the carbon fiber prepreg of different angle, avoids one party occur using the carbon fiber in same direction
Upward mechanics is weak, is conducive to the structural strength for improving product, for example, during practical laying: pre- using 0 ° of carbon fiber in a
Leaching material carries out laying, then carries out laying using 45 ° of carbon fiber prepreg in b, when then recycling a-b, carbon fiber prepreg in a
Laying, -45 ° of progress layings of carbon fiber prepreg use in b are carried out using 90 ° of carbon fiber prepregs.
The resin that carbon fiber prepreg uses in the present invention for span polyimide resin, viscosity in 200-600mPa.S,
Epoxide number is between 0.4-0.6.
In conclusion the invention has the following advantages:
1, the present invention decomposes the structure of aerofoil, is produced using the technique of parts processing combination and solidification, first correct
Portion's precast body carries out first time molding, then head precast body and airfoil body structure are carried out second of composite molding, and fission adds
Work can reduce the difficulty of various components processing, improve production efficiency, be also beneficial to improve the precision of product, further, drop
The reduction of low difficulty meets the production requirement of requirements at the higher level but also more complex profile structure is processed into possibility.
2, the present invention ensure that the specific strength of aerofoil is high, specific modulus is big, fatigue resistance using metal lining as inserts
It is good, the surrounding of metal lining is coated on carbon fiber prepreg, it is ensured that metal lining it is corrosion-resistant, extend it and use the longevity
Life makes aerofoil using carbon fibre composite, so that aerofoil low vibration, low noise, and there is efficient and light weight, corrosion resistant spy
Property.
Claims (10)
1. the molding carbon fibre composite aerofoil of co-curing, it is characterised in that: including head precast body and aerofoil precast body,
Head precast body and aerofoil precast body are cementing integral, and coat curing molding on the surface of head precast body and aerofoil precast body
There is carbon fiber prepreg laying.
2. the molding carbon fibre composite aerofoil of co-curing according to claim 1, it is characterised in that: the head
Precast body includes metal lining, and the surrounding curing molding of metal lining has carbon fibre preform, carbon fibre preform and gold
Belong to bushing to link into an integrated entity.
3. the molding carbon fibre composite aerofoil of co-curing according to claim 2, it is characterised in that: the metal liner
The outer surface of set is at least provided with one and the limiting section of carbon fibre preform cooperation.
4. the molding carbon fibre composite aerofoil of co-curing according to claim 1, it is characterised in that: the aerofoil
Precast body include intermediate prefabricated body and above and below intermediate prefabricated body two sides edge precast body, intermediate prefabricated body and head are pre-
Body processed is glued.
5. the molding carbon fibre composite aerofoil of co-curing according to claim 4, it is characterised in that: the centre
Precast body includes core, and the surface of core is equipped with profile-followed carbon fiber prepreg.
6. the preparation method of the molding carbon fibre composite aerofoil of co-curing, it is characterised in that: the following steps are included:
Step 1: production head preform mold and unitary mould, and complete the processing of metal lining；And it is made of light material
Aerofoil core, edge core；
Step 2: by metal lining in being located in head preform mold, and carbon fibre initial rinse is used around metal lining
Material is filled, and curing molding obtains head precast body；
Step 3: head precast body and aerofoil core that step 2 obtains being positioned in unitary mould, and pass through splicing
Mode makes head precast body and aerofoil core connect into an entirety, and carries out integral coating laying with carbon fiber prepreg, makes
Standby airfoil body structure out；
Step 4: placing edge core in the two sides up and down of the aerofoil core of airfoil body structure, and carry out covering with knitted fabric
Laying, molding, injecting glue simultaneously solidify, and wait until complete aerofoil.
7. the preparation method of the molding carbon fibre composite aerofoil of co-curing according to claim 6, it is characterised in that:
The integral coating laying includes following laying step: a, the carbon that integral coating is laid on head precast body and aerofoil core
Fiber prepreg material, formed integral coating layer, b, aerofoil core upper and lower surface be laid with shape and aerofoil core upper and lower surface
C, shape identical aerofoil laying repeats the thickness that a-b reaches design to the carbon fiber prepreg being laid with.
8. the preparation method of the molding carbon fibre composite aerofoil of co-curing according to claim 7, it is characterised in that:
The integral coating layer and aerofoil laying is laid with altogether 33 layers, and pre-compacted of every 11 layers of progress.
9. the preparation method of the molding carbon fibre composite aerofoil of co-curing according to claim 7, it is characterised in that:
The differential seat angle of the carbon fiber of carbon fiber prepreg used in carbon fiber prepreg described in a and b is ± 45 °.
10. the preparation method of the molding carbon fibre composite aerofoil of co-curing according to claim 6, feature exist
In: head core is additionally provided with around the head precast body of the airfoil body structure in step 3.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811432386.8A CN109676958B (en) | 2018-11-28 | 2018-11-28 | Co-curing molded carbon fiber composite material airfoil and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811432386.8A CN109676958B (en) | 2018-11-28 | 2018-11-28 | Co-curing molded carbon fiber composite material airfoil and preparation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109676958A true CN109676958A (en) | 2019-04-26 |
| CN109676958B CN109676958B (en) | 2021-08-06 |
Family
ID=66184430
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811432386.8A Active CN109676958B (en) | 2018-11-28 | 2018-11-28 | Co-curing molded carbon fiber composite material airfoil and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109676958B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110588897A (en) * | 2019-11-01 | 2019-12-20 | 连云港神鹰复合材料科技有限公司 | Preparation method of integrally-formed carbon fiber bogie swing bolster safety crane |
| CN113830287A (en) * | 2021-10-11 | 2021-12-24 | 贵州贵飞飞机设计研究院有限公司 | Control surface with separated beam body edge strip and web plate surface and manufacturing method thereof |
| CN113910641A (en) * | 2021-10-11 | 2022-01-11 | 成都锐美特新材料科技有限公司 | Carbon fiber composite material product, preparation method thereof and wearable seat |
| CN116353094A (en) * | 2023-03-29 | 2023-06-30 | 中国科学院力学研究所 | Plate manufacturing process of high-speed water surface aircraft |
| CN117073467A (en) * | 2023-09-04 | 2023-11-17 | 北京爱思达航天科技有限公司 | Light composite material flying wing capable of carrying devices and preparation method thereof |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06219392A (en) * | 1992-12-23 | 1994-08-09 | Eurocopter France | Thermoplastic composite material made vane for duct-equipped rear rotary wing of helicopter and method of injection molding of said vane |
| US6117376A (en) * | 1996-12-09 | 2000-09-12 | Merkel; Michael | Method of making foam-filled composite products |
| CN102092135A (en) * | 2010-12-13 | 2011-06-15 | 中国航空工业集团公司北京航空材料研究院 | Method for improving rigidity of wing surface structure of composite material |
| CN106114819A (en) * | 2016-07-22 | 2016-11-16 | 中国航空工业集团公司西安飞机设计研究所 | A kind of composite airfoil structure |
| CN106170609A (en) * | 2014-04-07 | 2016-11-30 | 株式会社Ihi | The composite wing and the manufacture method of the composite wing |
| CN106426987A (en) * | 2016-11-25 | 2017-02-22 | 江西洪都航空工业集团有限责任公司 | Forming method of integrally formed airfoil structure |
| CN107984774A (en) * | 2017-12-15 | 2018-05-04 | 江西长江化工有限责任公司 | A kind of composite material empennage technology of preparing |
| CN108082445A (en) * | 2016-08-24 | 2018-05-29 | 波音公司 | Wing and its manufacturing method |
| CN207902733U (en) * | 2018-01-19 | 2018-09-25 | 北京京东尚科信息技术有限公司 | The aerofoil leading edge structure of Fixed Wing AirVehicle |
-
2018
- 2018-11-28 CN CN201811432386.8A patent/CN109676958B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06219392A (en) * | 1992-12-23 | 1994-08-09 | Eurocopter France | Thermoplastic composite material made vane for duct-equipped rear rotary wing of helicopter and method of injection molding of said vane |
| US6117376A (en) * | 1996-12-09 | 2000-09-12 | Merkel; Michael | Method of making foam-filled composite products |
| CN102092135A (en) * | 2010-12-13 | 2011-06-15 | 中国航空工业集团公司北京航空材料研究院 | Method for improving rigidity of wing surface structure of composite material |
| CN106170609A (en) * | 2014-04-07 | 2016-11-30 | 株式会社Ihi | The composite wing and the manufacture method of the composite wing |
| CN106114819A (en) * | 2016-07-22 | 2016-11-16 | 中国航空工业集团公司西安飞机设计研究所 | A kind of composite airfoil structure |
| CN108082445A (en) * | 2016-08-24 | 2018-05-29 | 波音公司 | Wing and its manufacturing method |
| CN106426987A (en) * | 2016-11-25 | 2017-02-22 | 江西洪都航空工业集团有限责任公司 | Forming method of integrally formed airfoil structure |
| CN107984774A (en) * | 2017-12-15 | 2018-05-04 | 江西长江化工有限责任公司 | A kind of composite material empennage technology of preparing |
| CN207902733U (en) * | 2018-01-19 | 2018-09-25 | 北京京东尚科信息技术有限公司 | The aerofoil leading edge structure of Fixed Wing AirVehicle |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110588897A (en) * | 2019-11-01 | 2019-12-20 | 连云港神鹰复合材料科技有限公司 | Preparation method of integrally-formed carbon fiber bogie swing bolster safety crane |
| CN110588897B (en) * | 2019-11-01 | 2021-03-26 | 连云港神鹰复合材料科技有限公司 | Preparation method of integrally-formed carbon fiber bogie swing bolster safety crane |
| CN113830287A (en) * | 2021-10-11 | 2021-12-24 | 贵州贵飞飞机设计研究院有限公司 | Control surface with separated beam body edge strip and web plate surface and manufacturing method thereof |
| CN113910641A (en) * | 2021-10-11 | 2022-01-11 | 成都锐美特新材料科技有限公司 | Carbon fiber composite material product, preparation method thereof and wearable seat |
| CN113910641B (en) * | 2021-10-11 | 2023-06-02 | 成都锐美特新材料科技有限公司 | Carbon fiber composite material product, preparation method thereof and wearable seat |
| CN116353094A (en) * | 2023-03-29 | 2023-06-30 | 中国科学院力学研究所 | Plate manufacturing process of high-speed water surface aircraft |
| CN117073467A (en) * | 2023-09-04 | 2023-11-17 | 北京爱思达航天科技有限公司 | Light composite material flying wing capable of carrying devices and preparation method thereof |
| CN117073467B (en) * | 2023-09-04 | 2024-07-26 | 北京爱思达航天科技有限公司 | Light composite material flying wing capable of carrying devices and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109676958B (en) | 2021-08-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109676958A (en) | Molding carbon fibre composite aerofoil of co-curing and preparation method thereof | |
| DK176335B1 (en) | Process for manufacturing wind turbine blades | |
| CN107521124A (en) | Carbon fiber dual platen reinforced structure part and its manufacture method | |
| CN103477069B (en) | For keeping the module of at least one lining | |
| CN103342167A (en) | Method for making scaled composite material wing model | |
| US8337740B2 (en) | Reinforced internal composite structures | |
| EP2679806A1 (en) | Method for manufacturing wind turbine blades, blades for propellers, wings or similar structures, and structure in the shape of a blade produced by means of said method | |
| US8197625B2 (en) | Process of manufacturing composite structures with embedded precured tools | |
| CN103407171B (en) | Integral forming method for sewing enhanced cross connector made of fiber reinforced resin matrix composite | |
| TR201810926T4 (en) | A method for manufacturing an elongated composite structure. | |
| CN104696167B (en) | A kind of blunt trailing edge wind turbine blade and its implementation and method | |
| CN109094058A (en) | Light composite material bullet support and its manufacturing method | |
| CN110370676A (en) | A kind of method that the soft tooling realization L-type reinforcing rib of high intensity answers material product co-curing with c-type mount structure | |
| CN112622308B (en) | Carbon fiber composite material arm section and preparation method thereof | |
| CN111707145B (en) | Loading, ablation and heat-proof integrated composite material missile wing and rudder for hypersonic missile and preparation method thereof | |
| CN109664524A (en) | Forming process of fiber reinforced composite material reinforcing beam and vehicle using same | |
| CN206999679U (en) | Carbon fiber dual platen reinforced structure part | |
| EP2266784A1 (en) | Method for producing a sandwich component having a honeycomb core | |
| JP2012510395A (en) | Plane member for aircraft and method for manufacturing the same | |
| CN111075829A (en) | Hybrid fiber reinforced resin matrix composite material hinge and manufacturing method thereof | |
| CN114889233B (en) | Light rib and forming method thereof | |
| CN114872876B (en) | Main bearing airfoil surface box-type load transfer mechanism and manufacturing method thereof | |
| CN116353101A (en) | Blade, manufacturing method thereof and aircraft | |
| CN208529790U (en) | Fan blade | |
| CN112793670A (en) | Reinforced pipe and manufacturing method thereof |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: Carbon fiber composite wing surface formed by co curing and its preparation method Granted publication date: 20210806 Pledgee: Bank of Nanjing Co.,Ltd. Changzhou Branch Pledgor: JIANGSU SANQIANG COMPOSITE MATERIAL Co.,Ltd. Registration number: Y2024980030672 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right |