CN106985413B - A kind of forming frock for foam core filled composite material structure winglet - Google Patents
A kind of forming frock for foam core filled composite material structure winglet Download PDFInfo
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- CN106985413B CN106985413B CN201710242391.1A CN201710242391A CN106985413B CN 106985413 B CN106985413 B CN 106985413B CN 201710242391 A CN201710242391 A CN 201710242391A CN 106985413 B CN106985413 B CN 106985413B
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- winglet
- shaping mould
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- laying
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Classifications
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- 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
- B29C70/342—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 isostatic pressure
-
- 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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- 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
- B29C70/78—Moulding material on one side only of the preformed part
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The invention belongs to composite material aircraft manufacturing technology fields, are related to a kind of forming frock for foam core filled composite material structure winglet.Forming frock of the invention is made of upper shaping mould and lower shaping mould, and upper shaping mould is composite material mould, for guaranteeing the outer dimension and surface quality in its mo(u)ld top half face in winglet forming process.Lower shaping mould is composite material frame mould, for supporting the outer dimension and surface quality fixing entire part and guarantee its mo(u)ld bottom half face in winglet forming process, lower forming model face is Varying-thickness composite material type face, docking region with upper shaping mould in its leading edge has thickness weakened section, to guarantee the pressure field uniformity in winglet leading edge deep camber region.Forming frock for foam core filled composite material structure winglet of the invention is easy to operate, demoulding is easy, it solves the problems, such as that the deep camber parts with complex structures pressurization of similar winglet is non-uniform, and well ensures the internal soundness and surface quality of part.
Description
Technical field
The invention belongs to composite material aircraft manufacturing technology fields, are related to a kind of for foam core filled composite material structural fin
The forming frock of tip winglet.
Background technique
Composite material is due to its high specific strength, and high specific stiffness, designability are strong, fatigue crack-resistant performance is good, corrosion-resistant, ruler
The advantages that very little stability is good and is convenient for large area monolithic molding, it has also become one of the present age most important Aircraft Structure Materials.It is multiple
The position and dosage that condensation material is applied aboard have become one of the outstanding feature for measuring aircaft configuration advance.Boeing
B787 " dream " civil aircraft of development, for composite material dosage up to 50%, the A350 aircraft that Air Passenger company will release is compound
Material utilization amount is up to 52%.Research and it was verified that install winglet additional on wing, can effectively reduce resistance, improve aircraft
Fuel utilization ratio, so the structure of winglet, is widely used aboard.To mitigate construction weight, protect simultaneously
Product rigidity is demonstrate,proved, more and more winglets use foam core filled composite material structure.But foam core filled composite material knot
Since its type face is complicated, the reasons such as partial region curvature is big are difficult to manufacture structure winglet, and internal soundness and table after manufacture
Face quality is difficult to control.
Summary of the invention
The purpose of the present invention is to provide it is a kind of design rationally, be simple to manufacture, form after internal soundness qualification, surface quality
The controllable forming frock for foam core filled composite material structure winglet.
The technical scheme is that the forming frock for foam core filled composite material structure winglet is by upper molding
Mould and lower shaping mould composition, upper shaping mould are polymer matrix composites mold, and upper shaping mould carries out on upper shaping mould laying mould
Laying and molding, upper shaping mould mo(u)ld bottom half face are consistent with winglet mo(u)ld top half face；Lower shaping mould is polymer matrix composites frame mould,
By longitudinal and transverse direction partition and forming surface board group at, the molding panel of lower shaping mould carried out on lower shaping mould laying mould laying and
Molding, lower shaping mould is glued together with longitudinal and transverse direction partition altogether by molding panel to be formed, and longitudinal and transverse direction partition forms upper
Type face is corresponding with the lower profile forms of foam core filled composite material structure winglet, the outer dimension of longitudinal and transverse direction partition
Less than the outer dimension in winglet mo(u)ld bottom half face, forms panel and be glued to above longitudinal and transverse direction partition, form the rear of panel
And the size in wingtip root direction is greater than the size in winglet mo(u)ld bottom half face, the wingtip root for forming panel is equipped with winglet root
Portion's support platform, molding panel are Varying-thickness composite material face, form the upper of the mo(u)ld bottom half face of panel and longitudinal and transverse direction partition
Type face is consistent, and the mo(u)ld top half face for forming panel is consistent with winglet mo(u)ld bottom half face, corresponding with winglet leading edge in molding panel
There is the thickness change area of 5-10mm in region, and thickness is increased from leading edge to rear direction；When in use, by winglet to be formed
It is put on lower shaping mould, then upper shaping mould is fastened on winglet, solidified, when demoulding, first remove upper shaping mould, then
Winglet is removed from lower shaping mould, completes part removal.
The upper shaping mould is manufactured by fabric prepreg identical with winglet, after the solidification of required prepreg
Thickness in monolayer is 0.1mm-0.2mm, and upper shaping mould carries out laying and molding on upper shaping mould laying mould, and laying is [± 45/0/
± 45], with a thickness of 0.3-0.6mm, upper shaping mould laying mould is manufactured using numerical control processing, type face and winglet mo(u)ld top half face one
It causes, material is Steel material or aluminum material.
The lower shaping mould is frame structure, and frame is made of longitudinal and transverse direction partition and bottom plate, longitudinal and transverse direction every
It is connected between plate using U-shaped slot form, longitudinal and transverse direction partition is connect with bottom plate using L-type angle section, longitudinal and transverse direction partition
And bottom plate, by being manufactured using numerical control processing, the molding panel of lower shaping mould is by fabric prepreg system identical with winglet
It makes, lower shaping mould laying mould is manufactured using numerical control processing, and type face is consistent with winglet mo(u)ld bottom half face, and material is Steel material or aluminium
Material.
Hem width degree is docked with upper shaping mould in the molding panel of lower shaping mould region corresponding with winglet leading edge
For 10mm, use laying for [± 45/ ± 45], with a thickness of 0.2-0.4mm, in the thickness change region of lower shaping mould molding panel
With a thickness of even transition, transitional region width is 5-10mm, transits to Hou Qu, thick area is with a thickness of 0.6-1.2mm, laying
[±45/0/±45/±45/0/±45]。
Respectively there are two groups of location holes on the upper shaping mould and lower shaping mould, is used to position in upper and lower molding.
The forming frock for foam core filled composite material structure winglet be suitable for sandwich material be foam,
Exterior skin is fibre reinforced composites, type face is complex-curved winglet structure.
This programme the utility model has the advantages that
Forming frock of the invention is made of upper shaping mould and lower shaping mould, and upper shaping mould is composite material mould, is used for
Guarantee the outer dimension and surface quality in its mo(u)ld top half face in winglet forming process.Lower shaping mould is composite material frame mould,
For supporting fixed entire part in winglet forming process and guaranteeing the outer dimension and surface quality in its mo(u)ld bottom half face, it is lower at
Pattern type face is Varying-thickness composite material type face, and docking region with upper shaping mould in its leading edge has thickness weakened section, to guarantee the wing
The pressure field uniformity in the tip small nose of wing deep camber region.It is of the invention for foam core filled composite material structure winglet
Forming frock is easy to operate, demoulding is easy, and the deep camber parts with complex structures pressurization for solving similar winglet is non-uniform
Problem, and well ensure the internal soundness and surface quality of part.Foam core filled composite material knot is used in the present invention
The forming frock of structure winglet uses the composable mold of upper shaping mould and lower shaping mould, by upper shaping mould and lower shaping mould at
Type panel bit combination is to guarantee mold relative position and type face precision.In forming process, upper shaping mould has deformability,
It can equably pressurize to winglet mo(u)ld top half face in forming process, lower molding plane plate thickness area has rigidity, to guarantee wingtip
For winglet in the middle outer dimension of forming process, the lower thin area of shaping mould panel is semi-rigid region, and it is big to improve winglet leading edge
The pressurization uniformity of area of curvature, to guarantee the up-front surface quality of winglet.The present invention and traditional rigid metal mould
Tool is compared, and mold weight is not only alleviated, and also improves the pressurization that mold in forming process treats forming part deep camber position
Uniformity ensure that the internal soundness and surface quality of part after molding.
Detailed description of the invention
Fig. 1 is the forming frock schematic diagram for foam core filled composite material structure winglet of the invention, wherein 1
It is upper shaping mould, 2 be lower shaping mould, and upper shaping mould has been fastened at this time on lower shaping mould.
Fig. 2 is that shaping mould is illustrated under the forming frock for foam core filled composite material structure winglet of the invention
Figure, wherein 3 be lower shaping mould molding panel, and 4 be that lower shaping mould molding panel leading edge docks thin area with upper shaping mould, 5 be it is lower at
Pattern lateral partitions, 6 be lower shaping mould longitudinal baffle, and 7 be lower shaping mould molding panel winglet root support platform, and 8 are
Lower shaping mould and upper shaping mould mold location hole.
Fig. 3 is shaping mould laying mould under the forming frock for foam core filled composite material structure winglet of the invention
Schematic diagram, wherein 9 be lower shaping mould laying mould, and 10 be lower shaping mould laying mould close to the thin laying area of leading edge locus, width
10mm, 11 be lower shaping mould laying mould thickness change region, width 5-10mm.
Fig. 4 is that shaping mould manufacture is shown under the forming frock for foam core filled composite material structure winglet of the invention
Be intended to, wherein 12 be lower shaping mould chassis base, molding panel and longitudinal and transverse direction partition be glued altogether together as shown in this figure at
For lower shaping mould.
Fig. 5 is shaping mould laying mould on the forming frock for foam core filled composite material structure winglet of the invention
Schematic diagram, wherein 13 be upper shaping mould laying mould.
Specific embodiment
It elaborates with reference to the accompanying drawing to the present invention.
Forming frock for foam core filled composite material structure winglet is made of upper shaping mould 1 and lower shaping mould 2,
Upper shaping mould 1 is polymer matrix composites mold, mold mo(u)ld bottom half face and foam core filled composite material structure winglet mo(u)ld top half face
Unanimously.Upper shaping mould 1 carries out lay-up molding on upper shaping mould laying mould 13.Lower shaping mould 2 is composite material frame mould, by indulging
It forms to partition 5, lateral partitions 6, lower shaping mould chassis base 12 and lower shaping mould molding panel 3, was manufactured in lower shaping mould 2
The fiberglass sheet material of 8mm thickness is first carried out numerical control processing, by lower shaping mould lateral partitions 5, lower shaping mould longitudinal baffle by Cheng Zhong
6 and lower shaping mould chassis base 12 complete the process, lower shaping mould lateral partitions 5 and lower shaping mould longitudinal baffle 6 composition after processing
Mo(u)ld top half face it is corresponding with the lower profile forms of foam core filled composite material structure winglet, then, use and foam core
The identical fabric prepreg of composite structure winglet skin material carries out laying on lower shaping mould laying mould 9,
The lower shaping mould for forming Varying-thickness forms panel 3, the mo(u)ld top half face of lower shaping mould laying mould 9 and foam core filled composite material structural fin
The mo(u)ld bottom half face of tip winglet is consistent.It is used two layers in the lower shaping mould laying mould that width is 10mm close to the thin laying area 10 of leading edge locus
+ 45 ° of fabric prepregs are carried out in 11 laying of lower shaping mould laying mould thickness change region that width is 5-10mm, 4 intercalations
Uniformly excessively, other region layings are [+45/0/+45/45/0/+45], and there are winglet roots on lower shaping mould molding panel 3
Portion's support platform 7 and lower shaping mould and upper shaping mould mold location hole 8, and winglet root support platform 7 is used to support and determines
When position winglet part, lower shaping mould and upper shaping mould molding location hole 8 are molded for lower shaping mould 2 with upper shaping mould 1
Positioning.It, will be by longitudinal baffle 5, lateral partitions 6,12 groups of lower shaping mould chassis base after the completion of lower shaping mould molding 3 laying of panel
At composite material frame tip upside down on the lower shaping mould molding panel 3 of laying completion and carry out splicing co-curing, complete lower molding
The manufacture of mould 2.
In the manufacturing process of foam core filled composite material structure winglet, foam core is completed in first numerical control processing, so
Afterwards in foam core outer surface paving glue film, then in film surface laying fabric prepreg, forms winglet and wait for admittedly
Change part.Winglet part to be solidified is put on lower shaping mould 2 again, winglet part root to be solidified and lower shaping mould
It forms panel winglet root support platform 7 to be bonded, completes the positioning of winglet part to be solidified.Then, by upper molding
Mould 1 molds location hole 8 and the molding of lower about 2 shaping mould by shaping mould under two groups and upper shaping mould and fixes.Then, it is lower at
Pattern molding 3 non-pad pasting face side of panel patch sealant tape simultaneously is completed to encapsulate, finally that entire tooling is to be solidified with winglet
Part is put into togerther autoclave and is solidified.During demoulding, encapsulation auxiliary material is first removed, shaping mould 1 is then unloaded,
The winglet part after solidification is removed from lower shaping mould 2 again, completes the knockout course of part.
In above-mentioned technical proposal, the lower shaping mould laying mould 9, upper shaping mould laying mould 13 use metal material
The overall dimensions of Q235A steel numerical control processing manufacture molding upper shaping mould 1 and lower shaping mould 2 to guarantee.Upper shaping mould 1 and under
Shaping mould 2 is formed using fabric prepreg identical with winglet part, and in forming process, tooling is identical as part
Thermal expansion coefficient ensure that the dimensional accuracy and Forming Quality of part.Lower shaping mould molding panel 3 is increased using Varying-thickness fiber
Strong composite material maintains mold is whole still to have rigidity while guaranteeing winglet leading edge deep camber position uniform pressurization,
To guarantee the outer dimension and surface quality of final molding winglet.
Claims (4)
1. a kind of forming frock for foam core filled composite material structure winglet is used for foam core filled composite material structure
The forming frock of winglet is made of upper shaping mould and lower shaping mould, upper shaping mould be polymer matrix composites mold, at
Pattern carries out laying and molding on upper shaping mould laying mould, and upper shaping mould mo(u)ld bottom half face is consistent with winglet mo(u)ld top half face；It is lower at
Pattern is polymer matrix composites frame mould, by longitudinal and transverse direction partition and forming surface board group at the molding panel of lower shaping mould
Laying is carried out on lower shaping mould laying mould and molding, lower shaping mould are glued together with longitudinal and transverse direction partition altogether by molding panel
The mo(u)ld top half face of molding, longitudinal and transverse direction partition composition is opposite with the lower profile forms of foam core filled composite material structure winglet
Answer, the outer dimension of longitudinal and transverse direction partition is less than the outer dimension in winglet mo(u)ld bottom half face, molding panel be glued to it is longitudinal and
Above lateral partitions, the size of the rear and wingtip root direction that form panel is greater than the size in winglet mo(u)ld bottom half face, molding
The wingtip root of panel is equipped with winglet root support platform, and molding panel is Varying-thickness composite material face, forms panel
Mo(u)ld bottom half face it is consistent with the mo(u)ld top half face of longitudinal and transverse direction partition, the mo(u)ld top half face for forming panel is consistent with winglet mo(u)ld bottom half face,
In use, winglet to be formed is put on lower shaping mould, then upper shaping mould is fastened on winglet, consolidate
Change, when demoulding, first removes upper shaping mould, then winglet is removed from lower shaping mould, complete part removal；Its feature exists
In having a thickness change area of 5-10mm in corresponding with the winglet leading edge region of molding panel, thickness is from leading edge to rear side
To increase；The upper shaping mould is manufactured by fabric prepreg identical with winglet, single after required prepreg solidification
For layer with a thickness of 0.1mm-0.2mm, upper shaping mould carries out laying and molding on upper shaping mould laying mould, laying for [± 45/0/ ±
45], with a thickness of 0.3-0.6mm, upper shaping mould laying mould is manufactured using numerical control processing, type face and winglet mo(u)ld top half face one
It causes, material is Steel material or aluminum material；The molding panel of lower shaping mould region corresponding with winglet leading edge with it is upper
It is 10mm that shaping mould, which docks hem width degree, uses laying for [± 45/ ± 45], and with a thickness of 0.2-0.4mm, lower shaping mould forms panel
Thickness change region with a thickness of even transition, transitional region width is 5-10mm, transits to Hou Qu, thick area is with a thickness of 0.6-
1.2mm, laying are [± 45/0/ ± 45/ ± 45/0/ ± 45].
2. a kind of forming frock for foam core filled composite material structure winglet according to claim 1, special
Sign is that the lower shaping mould is frame structure, and frame is made of longitudinal and transverse direction partition and bottom plate, longitudinal and transverse direction partition
Between connected using U-shaped slot form, longitudinal and transverse direction partition and bottom plate use L-type angle section to connect, longitudinal and transverse direction partition and
Bottom plate is manufactured using numerical control processing, and the molding panel of lower shaping mould is manufactured by fabric prepreg identical with winglet,
Lower shaping mould laying mould is manufactured using numerical control processing, and type face is consistent with winglet mo(u)ld bottom half face, and material is Steel material or aluminium
Material.
3. a kind of forming frock for foam core filled composite material structure winglet according to claim 1, special
Sign is respectively there are two groups of location holes on the upper shaping mould and lower shaping mould, is used to position in upper and lower molding.
4. a kind of forming frock for foam core filled composite material structure winglet according to claim 1, special
Sign is, the forming frock for foam core filled composite material structure winglet be suitable for sandwich material be foam,
Exterior skin is fibre reinforced composites, type face is complex-curved winglet structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710242391.1A CN106985413B (en) | 2017-04-13 | 2017-04-13 | A kind of forming frock for foam core filled composite material structure winglet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710242391.1A CN106985413B (en) | 2017-04-13 | 2017-04-13 | A kind of forming frock for foam core filled composite material structure winglet |
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| CN106985413A CN106985413A (en) | 2017-07-28 |
| CN106985413B true CN106985413B (en) | 2019-05-14 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109016562B (en) * | 2018-07-12 | 2021-04-23 | 江苏新扬新材料股份有限公司 | Preparation method of wingtip winglet |
| CN109435272B (en) * | 2018-09-30 | 2021-02-09 | 航天材料及工艺研究所 | Variable-thickness composite material integral framework forming method and forming die thereof |
| CN109130244B (en) * | 2018-10-31 | 2021-04-09 | 山西平阳重工机械有限责任公司 | Forming die and forming method for deep-cavity multi-window composite material part |
| CN110682556B (en) * | 2019-09-19 | 2022-04-19 | 中航复合材料有限责任公司 | Molding process method for variable-width and variable-thickness composite plate spring |
| CN115071157A (en) * | 2022-06-24 | 2022-09-20 | 江苏恒铭达航空设备有限公司 | Aviation composite winglet assembly forming process |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103273662A (en) * | 2013-05-24 | 2013-09-04 | 航天材料及工艺研究所 | Preparation method of low heat expansion carbon fiber reinforced resin matrix composite material mold |
| CN203427236U (en) * | 2013-08-05 | 2014-02-12 | 南京甬博数控科技有限公司 | Composite material mould with reinforced structures |
| CN104768726A (en) * | 2012-10-31 | 2015-07-08 | 波音公司 | System and method for manufacturing monolithic structures using expanding internal tools |
| CN204566716U (en) * | 2015-02-13 | 2015-08-19 | 哈尔滨新科锐工艺装备制造有限公司 | The accurate forming frock of aircraft composite |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ITTO20070507A1 (en) * | 2007-07-11 | 2009-01-12 | Alenia Aeronautica Spa | PROCESS OF MANUFACTURING OF A STRUCTURE OF A MONOLITHIC WING WITH AN INTEGRAL PROFILE |
-
2017
- 2017-04-13 CN CN201710242391.1A patent/CN106985413B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104768726A (en) * | 2012-10-31 | 2015-07-08 | 波音公司 | System and method for manufacturing monolithic structures using expanding internal tools |
| CN103273662A (en) * | 2013-05-24 | 2013-09-04 | 航天材料及工艺研究所 | Preparation method of low heat expansion carbon fiber reinforced resin matrix composite material mold |
| CN203427236U (en) * | 2013-08-05 | 2014-02-12 | 南京甬博数控科技有限公司 | Composite material mould with reinforced structures |
| CN204566716U (en) * | 2015-02-13 | 2015-08-19 | 哈尔滨新科锐工艺装备制造有限公司 | The accurate forming frock of aircraft composite |
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