CN108407335A - A kind of composite material shape for hat Material Stiffened Panel integral forming method - Google Patents
A kind of composite material shape for hat Material Stiffened Panel integral forming method Download PDFInfo
- Publication number
- CN108407335A CN108407335A CN201810268781.0A CN201810268781A CN108407335A CN 108407335 A CN108407335 A CN 108407335A CN 201810268781 A CN201810268781 A CN 201810268781A CN 108407335 A CN108407335 A CN 108407335A
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- Prior art keywords
- shape
- hat
- vacuum bag
- stringer
- core model
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- 239000000463 material Substances 0.000 title claims abstract description 40
- 239000002131 composite material Substances 0.000 title claims abstract description 16
- 238000000034 method Methods 0.000 title claims abstract description 16
- 238000000465 moulding Methods 0.000 claims abstract description 19
- 230000015572 biosynthetic process Effects 0.000 claims abstract description 16
- 238000004519 manufacturing process Methods 0.000 claims abstract description 16
- 238000007711 solidification Methods 0.000 claims abstract description 14
- 230000008023 solidification Effects 0.000 claims abstract description 14
- 229920001971 elastomer Polymers 0.000 claims abstract description 9
- 239000005060 rubber Substances 0.000 claims abstract description 9
- 239000011347 resin Substances 0.000 claims description 8
- 229920005989 resin Polymers 0.000 claims description 8
- 238000005538 encapsulation Methods 0.000 claims description 6
- 239000000835 fiber Substances 0.000 claims description 5
- 239000003795 chemical substances by application Substances 0.000 claims description 3
- 238000005520 cutting process Methods 0.000 claims description 3
- 239000003822 epoxy resin Substances 0.000 claims description 3
- 229920000647 polyepoxide Polymers 0.000 claims description 3
- 238000009877 rendering Methods 0.000 claims description 3
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 claims description 2
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 2
- 229920006231 aramid fiber Polymers 0.000 claims description 2
- 239000004917 carbon fiber Substances 0.000 claims description 2
- 239000004643 cyanate ester Substances 0.000 claims description 2
- 239000003365 glass fiber Substances 0.000 claims description 2
- 239000007769 metal material Substances 0.000 claims description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 2
- 229920001568 phenolic resin Polymers 0.000 claims description 2
- 239000005011 phenolic resin Substances 0.000 claims description 2
- 239000004033 plastic Substances 0.000 claims description 2
- 229920003023 plastic Polymers 0.000 claims description 2
- 229920001721 polyimide Polymers 0.000 claims description 2
- 239000009719 polyimide resin Substances 0.000 claims description 2
- 230000000694 effects Effects 0.000 description 3
- 239000000945 filler Substances 0.000 description 3
- 239000012528 membrane Substances 0.000 description 3
- 230000002787 reinforcement Effects 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 239000004593 Epoxy Substances 0.000 description 1
- 239000004743 Polypropylene Substances 0.000 description 1
- 230000001680 brushing effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- LNEPOXFFQSENCJ-UHFFFAOYSA-N haloperidol Chemical compound C1CC(O)(C=2C=CC(Cl)=CC=2)CCN1CCCC(=O)C1=CC=C(F)C=C1 LNEPOXFFQSENCJ-UHFFFAOYSA-N 0.000 description 1
- 238000002386 leaching Methods 0.000 description 1
- 208000020442 loss of weight Diseases 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- -1 polypropylene Polymers 0.000 description 1
- 229920001155 polypropylene Polymers 0.000 description 1
- 238000012805 post-processing Methods 0.000 description 1
- QQONPFPTGQHPMA-UHFFFAOYSA-N propylene Natural products CC=C QQONPFPTGQHPMA-UHFFFAOYSA-N 0.000 description 1
- 125000004805 propylene group Chemical group [H]C([H])([H])C([H])([*:1])C([H])([H])[*:2] 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 229920002379 silicone rubber Polymers 0.000 description 1
- 239000004945 silicone rubber 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
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
- B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
-
- 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
- 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
-
- 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
- B29L2031/3082—Fuselages
-
- 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)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention belongs to composite molding fields, are related to a kind of composite material shape for hat Material Stiffened Panel integral forming method.The present invention using support core model vacuum bag cylinder, be unfolded by the intracavitary in shape for hat stringer, vacuum bag cylinder global formation shape for hat Material Stiffened Panel is utilized to realize, support core model can be such that vacuum bag intracavitary in shape for hat stringer is preferably unfolded, bridge formation of the vacuum bag in small space is avoided, later stage quality risk is reduced.Vacuum bag and support core model cost are far below air bag and rubber mandrel, and support core model cost is relatively low and reusable, therefore greatly reduces shape for hat Material Stiffened Panel global formation manufacturing cost.Since support core model has been taken out before the solidification of shape for hat Material Stiffened Panel, the bridge formation in solidification process is avoided.Compared to traditional scheme, vacuum bag is easily extracted out of shape for hat stringer after the completion of manufacture, greatly reduces demoulding difficulty and risk, realizes the manufacture of large scale shape for hat Material Stiffened Panel global formation.
Description
Technical field
The invention belongs to composite molding fields, are related to a kind of composite material shape for hat Material Stiffened Panel integral forming method.
Background technology
With the development of aero-manufacturing technology, the dosage of composite material is more than 50% on airliner of new generation, from
Traditional non-bearing part, secondary bearing member are transitioned into main load-bearing part.Shape for hat Material Stiffened Panel due to its higher rigidity and loss of weight efficiency,
It is largely used on the positions such as airframe, wing.Shape for hat Material Stiffened Panel due to shape for hat stringer hollow-core construction, with traditional structure
Integral forming method have larger difference, difficulty also larger.
Traditional shape for hat reinforcement sheet metal forming generally uses air-bag method or rubber core modulus method.But two schemes can not expire
Requirement of the foot to composite material low cost and reliability manufacture.Air-bag method is to use molding side of the rubber pneumatic bag as transmission medium
Case, the disadvantage is that the manufacturing cost of air bag is higher, and poor reliability, recycling rate of waterused is extremely low, is oozed in use in the presence of breakage
The risk of gas.After curing molding, the more difficult extraction of air bag is not suitable for the molding of large-sized composite material component.Rubber core modulus method
It is to support core mold using solid rubber core model as shape for hat stringer, the scheme for extracting core model after solidification.The disadvantage is that siding at
Rubber mandrel is also easy to produce moderate finite deformation by high temperature and pressure when type, and product molding surface size is poor, and not due to core model pressure transmission effect
Good, skin areas compression effect is poor, and product quality is bad.
It is clearly that cannot be satisfied aviation aircraft to product moral for requiring stringent aviation, above two scheme
What high quality required.
Invention content
The object of the invention is directed to shape for hat Material Stiffened Panel global formation demand, has invented a kind of utilize and has supported core model auxiliary vacuum
The molding scheme of bag is to realize that vacuum bag direct weighting is molded shape for hat Material Stiffened Panel.
Technical solution of the invention comprises the steps of：
(1) prepreg in stringer tooling is first manufactured into shape for hat stringer, then cuts stringer size according to actual size；
(2) after cutting vacuum bag cylinder according to shape for hat stringer length, encapsulation surplus is reserved, support core model is put into vacuum
Vacuum bag is strutted in bag, four corners of support core model are bonded with the interior cavity of shape for hat stringer, for carrying the vacuum of release layer
Bag, is directly placed into shape for hat stringer cavity；It, need to be in vacuum bag outer wrapping release materials or brushing for the vacuum bag of no release layer
Releasing agent；
(3) shape for hat stringer positioned on covering, encapsulated, then vacuumized and be compacted stringer on covering；
(4) support core model is extracted, vacuum bag stays in the long an actor's rendering of an operatic tune of shape for hat；
(5) into autoclave global formation, vacuum bag and other release materials are extracted after solidification, you can complete manufacture.
The prepreg is fiber-reinforced resin base prepreg, and fiber is carbon fiber, glass fibre or aramid fiber, tree
Fat is epoxy resin, bimaleimide resin, polyimide resin, phenolic resin or cyanate ester resin.
The shape for hat stringer is uncured, precuring or solidification is completed.
The support core model is hollow thin-wall structure, and material is plastics, rubber, metal or composite material.
The autoclave is overall shaped into co-curing molding, is glued molding, second bonding molding altogether.
The present invention has the advantage that and advantageous effect：The present invention is using support core model vacuum bag cylinder intracavitary in shape for hat stringer
Expansion, to realize that, using vacuum bag cylinder global formation shape for hat Material Stiffened Panel, support core model can make vacuum bag in shape for hat stringer
Intracavitary is preferably unfolded, and avoids bridge formation of the vacuum bag in small space, reduces later stage quality risk.Vacuum bag and support
Core model cost is far below air bag and rubber mandrel, and support core model cost is relatively low and reusable, therefore greatly reduces shape for hat
Material Stiffened Panel global formation manufacturing cost.Since support core model has been taken out before the solidification of shape for hat Material Stiffened Panel, avoid solid
Bridge formation during change.Compared to traditional scheme, vacuum bag is easily extracted out of shape for hat stringer after the completion of manufacture, is greatly reduced de-
Mould difficulty and risk realize the manufacture of large scale shape for hat Material Stiffened Panel global formation.
Description of the drawings
Fig. 1 is to realize step schematic diagram using the method for support core model and tubular vacuum bag manufacture shape for hat Material Stiffened Panel.
Specific implementation mode
(1) prepreg in stringer tooling is first manufactured into shape for hat stringer, then cuts stringer size according to actual size；
(2) after cutting vacuum bag cylinder according to stringer length, encapsulation surplus is reserved, support core model is put into vacuum bag
Vacuum bag is strutted, for carrying the vacuum bag of release layer, can be directly placed into shape for hat stringer cavity；For the true of no release layer
Empty bag in vacuum bag outer wrapping release materials or can brush releasing agent；
(3) shape for hat stringer is positioned on covering, then vacuumizes and be compacted stringer on covering, is allowed in subsequent operation
In do not generate sliding dislocation；
(4) support core model is extracted, vacuum bag stays in the long an actor's rendering of an operatic tune of shape for hat；
(5) into solidification of hot-press tank, vacuum bag and other release materials are extracted after solidification, you can complete manufacture.
Embodiment 1
Certain large-sized composite material shape for hat Material Stiffened Panel unmanned plane wing, 12.5 meters of length are selected and first cure shape for hat stringer,
Then with for the global formation scheme be glued altogether of solidification covering.Material selection fibre reinforced medium temperature epoxy prepreg.Choosing
The tubular vacuum bag RBG500 produced with AIRTEK companies, support core model select the hollow thin-wall pipe of polypropylene material.It first will be pre-
Leaching material laying demoulds post-processing to stringer nominal size to the enterprising solidification of hot-press tank molding of shape for hat stringer molding die.Then will
Support core model, which is put into vacuum bag, struts vacuum bag, and extra vacuum bag is fixed on support core model side.Support core model is put into
The shape for hat stringer inner cavity cleaned out.Then filler filling and glued membrane paving are carried out, carries out vacuum bag leak test inspection after the completion.It protects
After vacuum bag is demonstrate,proved without breakage leakage, shape for hat stringer is navigated on the good covering of laying, is vacuumized shape for hat stringer on covering
It is fixed, support core model is extracted.Carry out auxiliary material lay and the encapsulation of vacuum bag bag making.It completes after being glued altogether, by shape for hat stringer
Interior RBG500 vacuum bags, which are extracted, completes part manufacture.
Embodiment 2
Certain shape for hat reinforcement rear body siding verifies part, and 3.6 meters of length selects the global formation side of stringer and covering co-curing
Case.Material selection fibre reinforced high temperature bimaleimide resin prepreg.AIRTEK companies are selected to produce sheet vacuum bag
Tubular is made with GS-213 sealing joint strips in DPT1000, and support core model selects the hollow pipe of silicone rubber material.First prepreg is spread
It is laminated on shape for hat stringer molding die and blank is made, tailored blank to stringer nominal size.Then stringer blank is put into molding
Compacting in cavity plate.Support core model is put into vacuum bag and struts vacuum bag, extra vacuum bag is fixed on support core model side.It will
Support core model is put into shape for hat stringer blank inner cavity.Then filler filling and glued membrane paving are carried out, carries out vacuum bag leak test after the completion
It checks.After ensureing that vacuum bag is revealed without breakage, stringer shaping mould and shape for hat stringer are navigated on the good covering of laying, vacuumized
Shape for hat stringer is fixed on covering, support core model is extracted.Carry out auxiliary material lay and the encapsulation of vacuum bag bag making.It completes altogether
After solidification, DPT1000 vacuum bags in shape for hat stringer are extracted and complete part manufacture.
Embodiment 3
Certain shape for hat reinforcement middle fuselage siding 1:1 exemplary authentication part, 4.6 meters of length select precuring stringer and cured illiteracy
The global formation scheme that skin is glued altogether.Material selection fibre reinforced High temperature epoxy resins prepreg.Select AIRTEK companies
Sheet vacuum bag DPT1000 is produced, tubular is made in the GS-213 sealing joint strips produced with AIRTEK companies, and support core model is selected poly-
The hollow pipe of propylene material.Blank, tailored blank to stringer name will first be made on prepreg laying to shape for hat stringer molding die
Adopted size.Then stringer blank is put into molding concave die and is compacted, precuring is carried out into autoclave, and 140 ° of solidification temperature, Gu
Change 1.5 hours time.Support core model is put into vacuum bag and struts vacuum bag, extra vacuum bag is fixed on support core model side
Side.Support core model is put into shape for hat stringer blank inner cavity.Then filler filling and glued membrane paving are carried out, carries out vacuum bag after the completion
Leak test inspection.After ensureing that vacuum bag is revealed without breakage, stringer shaping mould and shape for hat stringer are navigated on the good covering of laying, taken out
Vacuum is fixed on covering by shape for hat stringer, and support core model is extracted.Carry out auxiliary material lay and the encapsulation of vacuum bag bag making.It is complete
After co-curing, DPT1000 vacuum bags in shape for hat stringer are extracted and complete part manufacture.
Claims (5)
1. a kind of composite material shape for hat Material Stiffened Panel integral forming method, which is characterized in that comprise the steps of：Including following step
Suddenly：(1) prepreg in stringer tooling is first manufactured into shape for hat stringer, then cuts stringer size according to actual size；
(2) after cutting vacuum bag cylinder according to shape for hat stringer length, encapsulation surplus is reserved, support core model is put into vacuum bag
Vacuum bag is strutted, four corners of support core model are bonded with the interior cavity of shape for hat stringer, for carrying the vacuum bag of release layer, directly
It connects and is put into shape for hat stringer cavity；For the vacuum bag of no release layer, in vacuum bag outer wrapping release materials or demoulding need to be brushed
Agent；
(3) shape for hat stringer positioned on covering, encapsulated, then vacuumized and be compacted stringer on covering；
(4) support core model is extracted, vacuum bag stays in the long an actor's rendering of an operatic tune of shape for hat；
(5) into autoclave global formation, vacuum bag and other release materials are extracted after solidification, you can complete manufacture.
2. a kind of composite material shape for hat Material Stiffened Panel integral forming method described in accordance with the claim 1, it is characterized in that：Described
Prepreg be fiber-reinforced resin base prepreg, fiber be carbon fiber, glass fibre or aramid fiber, resin be epoxy resin,
Bimaleimide resin, polyimide resin, phenolic resin or cyanate ester resin.
3. a kind of composite material shape for hat Material Stiffened Panel integral forming method described in accordance with the claim 1, it is characterized in that：Described
Shape for hat stringer is uncured, precuring or solidification is completed.
4. a kind of composite material shape for hat Material Stiffened Panel integral forming method described in accordance with the claim 1, it is characterized in that：Described
Support core model is hollow thin-wall structure, and material is plastics, rubber, metal or composite material.
5. forming method described in accordance with the claim 1, it is characterized in that：The autoclave be overall shaped into co-curing molding,
It is glued molding, second bonding molding altogether.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810268781.0A CN108407335B (en) | 2018-03-28 | 2018-03-28 | Integral forming method for cap-shaped reinforced wall plate made of composite material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810268781.0A CN108407335B (en) | 2018-03-28 | 2018-03-28 | Integral forming method for cap-shaped reinforced wall plate made of composite material |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108407335A true CN108407335A (en) | 2018-08-17 |
| CN108407335B CN108407335B (en) | 2020-10-20 |
Family
ID=63133795
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810268781.0A Active CN108407335B (en) | 2018-03-28 | 2018-03-28 | Integral forming method for cap-shaped reinforced wall plate made of composite material |
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| Country | Link |
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| CN (1) | CN108407335B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109573332A (en) * | 2018-12-25 | 2019-04-05 | 重庆具码科技有限公司 | A kind of engine packing box |
| CN111152482A (en) * | 2019-12-17 | 2020-05-15 | 中国航空制造技术研究院 | Preparation method of cap-shaped reinforced wall plate preform suitable for RFI (radio frequency interference) process |
| CN112571815A (en) * | 2020-10-29 | 2021-03-30 | 成都飞机工业（集团）有限责任公司 | Rib positioning method of reinforced wall plate |
| CN112659418A (en) * | 2020-11-23 | 2021-04-16 | 航天特种材料及工艺技术研究所 | Integrated forming die and manufacturing method for composite material curved surface reinforced wall plate |
| CN114147994A (en) * | 2021-11-24 | 2022-03-08 | 航天特种材料及工艺技术研究所 | A kind of composite material cabin structure integral molding method |
| CN114506095A (en) * | 2020-11-16 | 2022-05-17 | 中国商用飞机有限责任公司 | Core mould for manufacturing cap-shaped reinforcing member |
| WO2022099707A1 (en) * | 2020-11-16 | 2022-05-19 | 中国商用飞机有限责任公司 | Core mold for producing hat-shaped reinforcement member |
| CN114536785B (en) * | 2022-03-30 | 2024-04-23 | 连云港中复连众复合材料集团有限公司 | Forming process of cap-shaped stringer reinforced wallboard without twisting strips |
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| CN103640231A (en) * | 2013-12-17 | 2014-03-19 | 沈阳飞机工业（集团）有限公司 | External locating device of combined type vacuum bag and locating method thereof |
| US20170136687A1 (en) * | 2015-11-17 | 2017-05-18 | The Boeing Company | Heat Shrinkable Film Tube and Method for Manufacturing Hollow Composite Parts |
| CN106799851A (en) * | 2016-12-27 | 2017-06-06 | 中国商用飞机有限责任公司 | Method for forming and manufacturing composite material hat-shaped reinforced wall plate based on filament laying technology |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103640231A (en) * | 2013-12-17 | 2014-03-19 | 沈阳飞机工业（集团）有限公司 | External locating device of combined type vacuum bag and locating method thereof |
| US20170136687A1 (en) * | 2015-11-17 | 2017-05-18 | The Boeing Company | Heat Shrinkable Film Tube and Method for Manufacturing Hollow Composite Parts |
| CN106799851A (en) * | 2016-12-27 | 2017-06-06 | 中国商用飞机有限责任公司 | Method for forming and manufacturing composite material hat-shaped reinforced wall plate based on filament laying technology |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109573332A (en) * | 2018-12-25 | 2019-04-05 | 重庆具码科技有限公司 | A kind of engine packing box |
| CN111152482A (en) * | 2019-12-17 | 2020-05-15 | 中国航空制造技术研究院 | Preparation method of cap-shaped reinforced wall plate preform suitable for RFI (radio frequency interference) process |
| CN112571815A (en) * | 2020-10-29 | 2021-03-30 | 成都飞机工业（集团）有限责任公司 | Rib positioning method of reinforced wall plate |
| CN112571815B (en) * | 2020-10-29 | 2022-06-14 | 成都飞机工业（集团）有限责任公司 | Rib positioning method of reinforced wall plate |
| CN114506095A (en) * | 2020-11-16 | 2022-05-17 | 中国商用飞机有限责任公司 | Core mould for manufacturing cap-shaped reinforcing member |
| WO2022099707A1 (en) * | 2020-11-16 | 2022-05-19 | 中国商用飞机有限责任公司 | Core mold for producing hat-shaped reinforcement member |
| CN114506095B (en) * | 2020-11-16 | 2024-01-26 | 中国商用飞机有限责任公司 | A core mold for making hat-shaped reinforced components |
| CN112659418A (en) * | 2020-11-23 | 2021-04-16 | 航天特种材料及工艺技术研究所 | Integrated forming die and manufacturing method for composite material curved surface reinforced wall plate |
| CN114147994A (en) * | 2021-11-24 | 2022-03-08 | 航天特种材料及工艺技术研究所 | A kind of composite material cabin structure integral molding method |
| CN114147994B (en) * | 2021-11-24 | 2023-05-05 | 航天特种材料及工艺技术研究所 | Integral forming method for composite cabin structure |
| CN114536785B (en) * | 2022-03-30 | 2024-04-23 | 连云港中复连众复合材料集团有限公司 | Forming process of cap-shaped stringer reinforced wallboard without twisting strips |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108407335B (en) | 2020-10-20 |
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