CN110239112A - A kind of processing method of composite material shape for hat Material Stiffened Panel - Google Patents
A kind of processing method of composite material shape for hat Material Stiffened Panel Download PDFInfo
- Publication number
- CN110239112A CN110239112A CN201910416214.XA CN201910416214A CN110239112A CN 110239112 A CN110239112 A CN 110239112A CN 201910416214 A CN201910416214 A CN 201910416214A CN 110239112 A CN110239112 A CN 110239112A
- Authority
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- China
- Prior art keywords
- shape
- hat
- prefabricated
- hat stringer
- core model
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000000463 material Substances 0.000 title claims abstract description 40
- 239000002131 composite material Substances 0.000 title claims abstract description 22
- 238000003672 processing method Methods 0.000 title claims abstract description 10
- 238000000465 moulding Methods 0.000 claims abstract description 19
- 239000000835 fiber Substances 0.000 claims abstract description 16
- 239000011347 resin Substances 0.000 claims description 10
- 229920005989 resin Polymers 0.000 claims description 10
- 229920001971 elastomer Polymers 0.000 claims description 8
- 239000005060 rubber Substances 0.000 claims description 8
- 238000007711 solidification Methods 0.000 claims description 6
- 230000008023 solidification Effects 0.000 claims description 6
- 229920001721 polyimide Polymers 0.000 claims description 4
- 239000009719 polyimide resin Substances 0.000 claims description 4
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 claims description 3
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 229920006231 aramid fiber Polymers 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- 239000003795 chemical substances by application Substances 0.000 claims description 3
- 239000011248 coating agent Substances 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 239000000945 filler Substances 0.000 claims description 3
- 239000003365 glass fiber Substances 0.000 claims description 3
- 239000007769 metal material Substances 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical group C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- 229920001568 phenolic resin Polymers 0.000 claims description 3
- 239000005011 phenolic resin Substances 0.000 claims description 3
- 239000004033 plastic Substances 0.000 claims description 3
- 229920003023 plastic Polymers 0.000 claims description 3
- 150000001875 compounds Chemical class 0.000 claims description 2
- 238000005538 encapsulation Methods 0.000 claims description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims 1
- 229910052760 oxygen Inorganic materials 0.000 claims 1
- 239000001301 oxygen Substances 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 8
- 239000003822 epoxy resin Substances 0.000 description 3
- 229920000647 polyepoxide Polymers 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 239000011521 glass Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- JEIPFZHSYJVQDO-UHFFFAOYSA-N iron(III) oxide Inorganic materials O=[Fe]O[Fe]=O JEIPFZHSYJVQDO-UHFFFAOYSA-N 0.000 description 1
- 208000020442 loss of weight Diseases 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- -1 phenolic aldehyde Chemical class 0.000 description 1
- 239000002023 wood Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
- B29D99/0014—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
-
- 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
- B29C70/32—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 on a rotating mould, former or core
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses a kind of processing methods of composite material shape for hat Material Stiffened Panel, feature is using shape for hat stringer mold as former, and cut prefabricated covering, then by multi-layer fiber prepreg laying on shape for hat stringer mold, obtain prefabricated shape for hat stringer, the core model of annular is placed into prefabricated shape for hat stringer again, and air bag is put into core model makes core model strut and be bonded completely with prefabricated shape for hat stringer, prefabricated covering is covered in prefabricated shape for hat stringer and core model, die for cover plate is pressed on prefabricated covering again, finally assembled mold is put into autoclave and carries out curing molding, keep shape for hat stringer and covering integral, obtain composite material shape for hat Material Stiffened Panel；Advantage is this method using shape for hat stringer mold as former, and cross section is used to be put into air bag for the core model of annular and in core model to support prefabricated shape for hat stringer, so that prefabricated covering and prefabricated shape for hat stringer are pressurized uniformly when processing, forming quality of products is reliable and stable, and core model easily takes out after processing is completed.
Description
Technical field
The present invention relates to composite molding processing more particularly to a kind of processing sides of composite material shape for hat Material Stiffened Panel
Method.
Background technique
With the development of aero-manufacturing technology, the dosage of composite material is more than 50% on airliner of new generation, composite wood
Material is transitioned into large-scale whole main load-bearing part from traditional non-bearing part, secondary bearing member.And shape for hat Material Stiffened Panel due to its compared with
High rigidity, axial load transmission efficiency and loss of weight efficiency, are widely used on the positions such as airframe, wing.But cap
Type Material Stiffened Panel has larger difference, difficulty with the integral forming method of traditional structure due to the hollow structure of its shape for hat stringer
It is larger.
Current shape for hat Material Stiffened Panel generally uses rubber core modulus method to form, and rubber core modulus method is to utilize solid rubber core model
As the support core mold of shape for hat stringer, solid rubber core model is extracted after solidification.But solid rubber core model at the time of molding by
High temperature and pressure are also easy to produce moderate finite deformation, so that the molding surface size of shape for hat Material Stiffened Panel is poor, core model is not easily taken out, and due to reality
The pressure transmission effect of heart core model is bad, and the skin areas compression effect of shape for hat Material Stiffened Panel is poor, and product quality is bad, is unable to satisfy pair
The requirement of composite material low cost and reliability manufacture.
Summary of the invention
Technical problem to be solved by the invention is to provide a kind of forming quality of products is reliable and stable, and core model is picked and placed and is easy
Composite material shape for hat Material Stiffened Panel processing method.
The technical scheme of the invention to solve the technical problem is: a kind of composite material shape for hat Material Stiffened Panel adds
Work method, comprising the following specific steps
(1), shape for hat stringer mold, and conduct are gone out according to the dimensioned of the shape for hat stringer in the shape for hat Material Stiffened Panel of required processing
Former；
(2), in advance by multi-layer fiber prepreg on plate laying, and cut by the size of the covering in shape for hat Material Stiffened Panel,
Obtain prefabricated covering；
(3), by multi-layer fiber prepreg laying on shape for hat stringer mold, and by the ruler of the shape for hat stringer in shape for hat Material Stiffened Panel
It is very little to cut, obtain prefabricated shape for hat stringer；
(4), in cross section it is the core model outer surface coating release agent of annular, and is placed into prefabricated shape for hat stringer, then
It is put into air bag in core model, so that core model is strutted and is bonded completely with prefabricated shape for hat stringer air bag inflation；
(5), crack band, and the gap between the two sides of core model upper end and prefabricated shape for hat stringer are pasted in the upper part of core model
Place's filling filler；
(6), prefabricated covering is covered in prefabricated shape for hat stringer and core model, then die for cover plate is pressed on prefabricated covering, and
It is sealed encapsulation；
(7), vacuum bag is fixed on shape for hat stringer mold, and to bag vacuum, die for cover plate is made to be pressurized；
(8), above-mentioned assembled mold is put into autoclave and carries out curing molding, keep shape for hat stringer and covering integral；
(9), die for cover plate and shape for hat stringer mold are removed after the completion of solidification, and core model is extracted out from shape for hat stringer, is obtained compound
Material shape for hat Material Stiffened Panel.
Further, the fiber prepreg material is fiber-reinforced resin base prepreg, in which: fiber is carbon fiber, glass
Glass fiber or aramid fiber, resin are epoxy resin, bimaleimide resin, polyimide resin or phenolic resin.
Further, the material of the core model is rubber, plastics, metal or composite material.
Further, at least one in both the prefabricated covering and the prefabricated shape for hat stringer is uncured shape
State.
Further, the molding mode of the solidification of hot-press tank is co-curing molding, is glued molding or second bonding altogether
Molding.
Compared with prior art, it is an advantage of the invention that this method is in processing, using shape for hat stringer mold as former, and
Cross section is used to be put into air bag for the core model of annular and in core model to support prefabricated shape for hat stringer, so that prefabricated covering when processing
It is pressurized uniformly with prefabricated shape for hat stringer, forming quality of products is reliable and stable, and core model easily takes out after processing is completed.
Detailed description of the invention
Fig. 1 is the schematic perspective view of composite material shape for hat Material Stiffened Panel；
Fig. 2 is machining sketch chart of the invention.
Specific embodiment
The present invention will be described in further detail below with reference to the embodiments of the drawings.
As shown, a kind of processing method of composite material shape for hat Material Stiffened Panel, comprising the following specific steps
(1), shape for hat stringer mold 2 is gone out according to the dimensioned of the shape for hat stringer 11 in the shape for hat Material Stiffened Panel 1 of required processing, and
As former；
(2), in advance by multi-layer fiber prepreg on plate laying, and cut out by the size of the covering 12 in shape for hat Material Stiffened Panel 1
It cuts, obtains prefabricated covering 3；
(3), by multi-layer fiber prepreg laying on shape for hat stringer mold 2, and by the shape for hat stringer 11 in shape for hat Material Stiffened Panel 1
Size cut, obtain prefabricated shape for hat stringer 4；
(4), in cross section it is 5 outer surface of the core model coating release agent of annular thin-walled, and is placed into prefabricated shape for hat stringer 4
In, it is then put into air bag 6 in core model 5, so that core model 5 is strutted and is bonded completely with prefabricated shape for hat stringer 4 inflation of air bag 6；
(5), crack band 7 is pasted in the upper part of core model 5, and between the two sides of 5 upper end of core model and prefabricated shape for hat stringer 4
Fill filler 8 in gap；
(6), prefabricated covering 3 is covered in prefabricated shape for hat stringer 4 and core model 5, die for cover plate 9 is then pressed in prefabricated covering 3
On, and carry out hermetically sealed；
(7), vacuum bag 10 being fixed on shape for hat stringer mold 2, and vacuum bag 10 being vacuumized, die for cover plate 9 is made to be pressurized；
(8), above-mentioned assembled mold is put into autoclave and carries out curing molding, keep shape for hat stringer 11 whole at one with covering 12
Body；
(9), die for cover plate 9 and shape for hat stringer mold 2 are removed after the completion of solidification, and core model 5 is extracted out from shape for hat stringer 11, is obtained
Composite material shape for hat Material Stiffened Panel 1.
In above-described embodiment, fiber prepreg material be fiber-reinforced resin base prepreg, in which: fiber can for carbon fiber,
Glass fibre or aramid fiber, resin can be epoxy resin, bimaleimide resin, polyimide resin or phenolic aldehyde tree
Rouge, therefore, fiber prepreg material can be carbon-fibre reinforced epoxy resin prepreg, fibre reinforced polyimide resin prepreg
Or glass fibre-reinforced phenolic resin prepreg etc.；The material of core model 5 can be rubber, plastics, metal or composite material；It is prefabricated
At least one in covering 3 and prefabricated 4 the two of shape for hat stringer is uncured state；The molding mode of solidification of hot-press tank can be used altogether
Curing molding is glued molding or second bonding molding altogether.
Claims (5)
1. a kind of processing method of composite material shape for hat Material Stiffened Panel, it is characterised in that comprising the following specific steps
(1), shape for hat stringer mold, and conduct are gone out according to the dimensioned of the shape for hat stringer in the shape for hat Material Stiffened Panel of required processing
Former；
(2), in advance by multi-layer fiber prepreg on plate laying, and cut by the size of the covering in shape for hat Material Stiffened Panel,
Obtain prefabricated covering；
(3), by multi-layer fiber prepreg laying on shape for hat stringer mold, and by the ruler of the shape for hat stringer in shape for hat Material Stiffened Panel
It is very little to cut, obtain prefabricated shape for hat stringer；
(4), in cross section it is the core model outer surface coating release agent of annular, and is placed into prefabricated shape for hat stringer, then
It is put into air bag in core model, so that core model is strutted and is bonded completely with prefabricated shape for hat stringer air bag inflation；
(5), crack band, and the gap between the two sides of core model upper end and prefabricated shape for hat stringer are pasted in the upper part of core model
Place's filling filler；
(6), prefabricated covering is covered in prefabricated shape for hat stringer and core model, then die for cover plate is pressed on prefabricated covering, and
It is sealed encapsulation；
(7), vacuum bag is fixed on shape for hat stringer mold, and to bag vacuum, die for cover plate is made to be pressurized；
(8), above-mentioned assembled mold is put into autoclave and carries out curing molding, keep shape for hat stringer and covering integral；
(9), die for cover plate and shape for hat stringer mold are removed after the completion of solidification, and core model is extracted out from shape for hat stringer, is obtained compound
Material shape for hat Material Stiffened Panel.
2. a kind of processing method of composite material shape for hat Material Stiffened Panel as described in claim 1, it is characterised in that: the fibre
Dimension prepreg is fiber-reinforced resin base prepreg, in which: fiber is carbon fiber, glass fibre or aramid fiber, and resin is ring
Oxygen resin, bimaleimide resin, polyimide resin or phenolic resin.
3. a kind of processing method of composite material shape for hat Material Stiffened Panel as described in claim 1, it is characterised in that: the core
The material of mould is rubber, plastics, metal or composite material.
4. a kind of processing method of composite material shape for hat Material Stiffened Panel as described in claim 1, it is characterised in that: described is pre-
At least one in both covering processed and the prefabricated shape for hat stringer is uncured state.
5. a kind of processing method of composite material shape for hat Material Stiffened Panel as described in claim 1, it is characterised in that: the heat
The mode of tank curing molding is pressed to be co-curing molding, be glued molding or second bonding molding altogether.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910416214.XA CN110239112A (en) | 2019-05-20 | 2019-05-20 | A kind of processing method of composite material shape for hat Material Stiffened Panel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910416214.XA CN110239112A (en) | 2019-05-20 | 2019-05-20 | A kind of processing method of composite material shape for hat Material Stiffened Panel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110239112A true CN110239112A (en) | 2019-09-17 |
Family
ID=67884299
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910416214.XA Pending CN110239112A (en) | 2019-05-20 | 2019-05-20 | A kind of processing method of composite material shape for hat Material Stiffened Panel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110239112A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111157172A (en) * | 2020-01-03 | 2020-05-15 | 中南大学 | Real-time monitoring method for local pressure during structural member forming |
| 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 |
| CN111391362A (en) * | 2020-06-04 | 2020-07-10 | 沈阳西子航空产业有限公司 | Thermal expansion and pressure forming method for flat tail silicone rubber of unmanned aerial vehicle composite material |
| CN111942518A (en) * | 2020-08-24 | 2020-11-17 | 中国人民解放军海军工程大学 | Novel cap-shaped rib structure made of functional composite material |
| CN112372931A (en) * | 2020-10-23 | 2021-02-19 | 大连理工大学 | Injection molding process machining method of large composite material reinforced thin-wall support structure |
| CN113021938A (en) * | 2019-12-09 | 2021-06-25 | 上海飞机制造有限公司 | Forming device and forming process for hat-shaped stringer stiffened wallboard made of composite material |
| CN113524722A (en) * | 2021-07-27 | 2021-10-22 | 中航西安飞机工业集团股份有限公司 | Composite material hat-shaped reinforced wall plate VARI forming resin flow infiltration device and method |
| CN113771389A (en) * | 2020-06-09 | 2021-12-10 | 上海飞机制造有限公司 | Hollow core mould suitable for manufacturing hat type stringer wallboard component and processing 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 |
| CN117698169A (en) * | 2024-02-02 | 2024-03-15 | 哈尔滨远驰航空装备有限公司 | Resin matrix composite aviation suspension girder, forming method and die |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113021938A (en) * | 2019-12-09 | 2021-06-25 | 上海飞机制造有限公司 | Forming device and forming process for hat-shaped stringer stiffened wallboard made of composite material |
| CN113021938B (en) * | 2019-12-09 | 2023-02-21 | 上海飞机制造有限公司 | Forming device and forming process for hat-shaped stringer stiffened wallboard made of composite material |
| 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 |
| CN111157172A (en) * | 2020-01-03 | 2020-05-15 | 中南大学 | Real-time monitoring method for local pressure during structural member forming |
| CN111391362A (en) * | 2020-06-04 | 2020-07-10 | 沈阳西子航空产业有限公司 | Thermal expansion and pressure forming method for flat tail silicone rubber of unmanned aerial vehicle composite material |
| CN113771389A (en) * | 2020-06-09 | 2021-12-10 | 上海飞机制造有限公司 | Hollow core mould suitable for manufacturing hat type stringer wallboard component and processing method |
| CN113771389B (en) * | 2020-06-09 | 2023-04-21 | 上海飞机制造有限公司 | Hollow core mold suitable for manufacturing cap-shaped stringer wallboard member and processing method |
| CN111942518A (en) * | 2020-08-24 | 2020-11-17 | 中国人民解放军海军工程大学 | Novel cap-shaped rib structure made of functional composite material |
| CN112372931A (en) * | 2020-10-23 | 2021-02-19 | 大连理工大学 | Injection molding process machining method of large composite material reinforced thin-wall support structure |
| 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 |
| CN114506095B (en) * | 2020-11-16 | 2024-01-26 | 中国商用飞机有限责任公司 | Core mould for manufacturing cap-shaped reinforcing member |
| CN113524722A (en) * | 2021-07-27 | 2021-10-22 | 中航西安飞机工业集团股份有限公司 | Composite material hat-shaped reinforced wall plate VARI forming resin flow infiltration device and method |
| CN117698169A (en) * | 2024-02-02 | 2024-03-15 | 哈尔滨远驰航空装备有限公司 | Resin matrix composite aviation suspension girder, forming method and die |
| CN117698169B (en) * | 2024-02-02 | 2024-04-30 | 哈尔滨远驰航空装备有限公司 | Resin matrix composite aviation suspension girder, forming method and die |
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Application publication date: 20190917 |
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