CN105690791A - Barrel-shaped composite structural member overall molding method capable of achieving easy demolding - Google Patents
Barrel-shaped composite structural member overall molding method capable of achieving easy demolding Download PDFInfo
- Publication number
- CN105690791A CN105690791A CN201610040526.1A CN201610040526A CN105690791A CN 105690791 A CN105690791 A CN 105690791A CN 201610040526 A CN201610040526 A CN 201610040526A CN 105690791 A CN105690791 A CN 105690791A
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- China
- Prior art keywords
- structural member
- composite material
- barrel
- tubular composite
- material structural
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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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention belongs to the technical field of composite molding, and provides a barrel-shaped composite structural member overall molding method capable of achieving easy demolding. The method comprises the following steps that a sealed airbag made of a high temperature and pressure resisting material is manufactured according to the dimension of a barrel-shaped composite structural member to be molded; the sealed airbag is sealed after being full of compressed air to serve as a mold of the barrel-shaped composite structural member; the surface of the sealed airbag is coated with a demolding agent, or demolding cloth is paved and pasted on the surface of the sealed airbag; a winding molding method is adopted for completing fiber laying of the barrel-shaped composite structural member; the barrel-shaped composite structural member obtained after fiber laying is completed is cured through an autoclave-vacuum bag method; and the sealed airbag is deflated for pressure reducing, the barrel-shaped composite structural member is made to be separated from the airbag, the demolding process is completed, and the overall barrel-shaped composite structural member is obtained. The method is simple in process, overall molding of various complex barrel-shaped composite structural members can be achieved, demolding is convenient, and cost can be obviously reduced.
Description
Technical field
The invention belongs to technical field of composite material molding, particularly relate to the tubular composite material structural member integral forming method of a kind of easy demoulding。
Background technology
The production of the tubular composite material structural member of prior art, widely used metal solid member is that core is processed, it is tightly combined with core after products solidifying molding, when causing product stripping, core is difficult to take out, need the compulsory measure demoulding such as to knock, this method not only wastes time and energy, it is also possible to causing deformation of products, breakage is even scrapped。And one of development trend of composite maximizes exactly, integration, thus reducing amount of parts, improve the overall performance of product, this result also in a large amount of appearance of many curved surfaces big-size complicated shape tubular composite material structural member, so the processing technique adopting metal solid member to be core is increasingly difficult to meet actual production demand。
The another kind of production method of tubular composite material structural member is silicon rubber thermal expansion molding molding。This process is with the bigger elastomeric material such as silicone rubber of thermal coefficient of expansion for core, and with the relatively low rigid material such as steel of thermal coefficient of expansion for former, material prepreg is plated between core and former by precalculating thickness, when mould heats, because silicone rubber is bigger than steel volumetric expansion, then silicone rubber can be subject to material prepreg and the restriction of steel former, thus composite for molding is produced radial pressure, it is achieved the heat-pressure curing molding of composite。The maximum feature of this technique is to expand, by core, the pressure provided needed for product molding, and the outer wall of goods is controlled by the interior profile of rigidity former, and inwall is controlled by the expansion of core。But the orientation of silicone rubber kind used, the state of prepreg, fiber and Lay up design thereof will affect the swelliong power of core, and the bulbs of pressure of core change with temperature, it is difficult to accurately control, therefore, inner wall size precision controlling is poor, and the problem that steel former there is also demoulding difficulty。
Summary of the invention
In order to solve problem above, the present invention provides the tubular composite material structural member integral forming method of a kind of easy demoulding。The inventive method adopts high temperature high-pressure resistant material fiber painting silica gel cloth to prepare pressure bladder, seal after pressure bladder is full of compression gas, as the mould of tubular composite material structural member, to replace metal core die, adopt autoclave-vacuum bag molding to be solidified by tubular composite material structural member simultaneously。The inventive method technique is simple, can not only realize the global formation of various complex cylindrical composite material structural member, make composite material structural member overall performance significantly improve, and be convenient in demoulding, it is possible to be significantly reduced to this。
Technical scheme:
A kind of tubular composite material structural member integral forming method of the easy demoulding, step is as follows:
The pressure bladder of high temperature resistant/cryogenic high pressure material is prepared according to the size of tubular composite material structural member to be formed, described pressure bladder is the closing space with air inlet, and the outer mold surface size of pressure bladder is equal to the interior molding surface size of tubular composite material structural member；Seal after pressure bladder is full of compression gas, as the mould of tubular composite material structural member；At pressure bladder surface coating release agent or paving release cloth；Adopting winding, molding method to complete the fiber placement of tubular composite material structural member, pressure bladder is full of pressure that compression gas the reaches pressure more than fiber placement process；The tubular composite material structural member completed by fiber placement adopts autoclave-vacuum bag molding to solidify；By pressure bladder venting decompression, make tubular composite material structural member depart from air bag, complete knockout course, it is thus achieved that overall tubular composite material structural member, one end open is closed in described tubular composite material structural member one end。
The material of described pressure bladder is that fiber is coated with silica gel cloth。
Beneficial effects of the present invention:
1) suitability is strong, it is possible to realize the global formation of various complex cylindrical composite material structural member, makes composite material structural member overall performance significantly improve, and connects the series of problems such as the stress concentration brought again after avoiding tradition piecemeal molding simultaneously。
2) air bag deflation is reduced pressure, the demoulding can be realized, be convenient in demoulding。
3) technique is simple, it is possible to be significantly reduced to this。
Accompanying drawing explanation
Accompanying drawing is the tubular composite material structural member global formation schematic diagram of the easy demoulding of the present invention。
In figure: 1 pressure bladder；2 releasing agents or release cloth；3 tubular composite material structural members；4 sealing devices。
Detailed description of the invention
Below in conjunction with accompanying drawing and technical scheme, further illustrate the specific embodiment of the present invention。
Embodiment
As shown in drawings, the tubular composite material structural member global formation of the easy demoulding includes pressure bladder 1, sealing device 4, the releasing agent on pressure bladder surface or release cloth 2 and the tubular composite material structural member 3 of one end open is closed in one end。
The concrete technology step of the tubular composite material structural member global formation of the easy demoulding of the present invention is as follows:
Preparing fiber according to the size of tubular composite material structural member 3 and be coated with the pressure bladder 1 of silica gel cloth material, described pressure bladder 1 is the closing space with air inlet, and the outer mold surface size of pressure bladder 1 is equal to the interior molding surface size of tubular composite material structural member 3；Seal with sealing device 4 after pressure bladder 1 is full of compression gas, as the mould of tubular composite material structural member 3；At pressure bladder 1 surface coating release agent or paving release cloth 2；Adopting winding, molding method to complete the fiber placement of tubular composite material structural member 3, the pressure that the full compression gas of pressure bladder 1 reaches is more than the pressure of fiber placement process；The tubular composite material structural member 3 completed by fiber placement adopts autoclave-vacuum bag molding to solidify；Pressure bladder 1 is exitted decompression, make tubular composite material structural member 3 and pressure bladder 1 depart from, complete knockout course, it is thus achieved that tubular composite material casing。
The present invention is not limited to the concrete structure of above-described embodiment, all any amendment, equivalent replacement and improvement etc. made within the spirit and principles in the present invention, should be included within protection scope of the present invention。
Claims (2)
1. the tubular composite material structural member integral forming method of an easy demoulding, it is characterized in that, step is as follows: prepare the pressure bladder of high temperature resistant/cryogenic high pressure material according to the size of tubular composite material structural member to be formed, described pressure bladder is the closing space with air inlet, and the outer mold surface size of pressure bladder is equal to the interior molding surface size of tubular composite material structural member；Seal after pressure bladder is full of compression gas, as the mould of tubular composite material structural member；At pressure bladder surface coating release agent or paving release cloth；Adopting winding, molding method to complete the fiber placement of tubular composite material structural member, pressure bladder is full of pressure that compression gas the reaches pressure more than fiber placement process；The tubular composite material structural member completed by fiber placement adopts autoclave-vacuum bag molding to solidify；By pressure bladder venting decompression, make tubular composite material structural member depart from air bag, complete knockout course, it is thus achieved that overall tubular composite material structural member。
2. the tubular composite material structural member integral forming method of a kind of easy demoulding according to claim 1, it is characterised in that the material of described pressure bladder is that fiber is coated with silica gel cloth。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610040526.1A CN105690791A (en) | 2016-01-21 | 2016-01-21 | Barrel-shaped composite structural member overall molding method capable of achieving easy demolding |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610040526.1A CN105690791A (en) | 2016-01-21 | 2016-01-21 | Barrel-shaped composite structural member overall molding method capable of achieving easy demolding |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105690791A true CN105690791A (en) | 2016-06-22 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610040526.1A Pending CN105690791A (en) | 2016-01-21 | 2016-01-21 | Barrel-shaped composite structural member overall molding method capable of achieving easy demolding |
Country Status (1)
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| CN (1) | CN105690791A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106863836A (en) * | 2016-12-27 | 2017-06-20 | 航天神舟飞行器有限公司 | Composite overall structure fuel tank and its manufacture method |
| CN107662354A (en) * | 2016-07-27 | 2018-02-06 | 中国航发商用航空发动机有限责任公司 | Make the anti-process for creping of composite cylinder and device of high microsteping content |
| CN108274780A (en) * | 2018-04-02 | 2018-07-13 | 天津工业大学 | A kind of forming method of hollow composite |
| CN108284622A (en) * | 2017-12-13 | 2018-07-17 | 江南工业集团有限公司 | The moulding process of Filament Wound Composite tubular member |
| CN111688237A (en) * | 2020-06-23 | 2020-09-22 | 中国航空制造技术研究院 | Forming method of tubular composite material part with two closed ends |
| CN112265300A (en) * | 2020-10-15 | 2021-01-26 | 滕州深水湾复合材料科技有限公司 | Method for manufacturing composite material pipeline |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2124789A1 (en) * | 1971-05-19 | 1972-12-07 | Deutsche Forsch Luft Raumfahrt | Elastomer moulding bladder - reinforced with fibres, to produce reinforced plastic containers of the required size |
| DE19803909A1 (en) * | 1998-02-02 | 1999-08-05 | Ver Foerderung Inst Kunststoff | Resin injection process for production of continuous fiber reinforced hollow products, e.g. turbine blades, pressure tanks or structural components |
| CN101716824A (en) * | 2009-11-13 | 2010-06-02 | 程显军 | Manufacturing technology of oil pipeline made of carbon fibre composite |
-
2016
- 2016-01-21 CN CN201610040526.1A patent/CN105690791A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2124789A1 (en) * | 1971-05-19 | 1972-12-07 | Deutsche Forsch Luft Raumfahrt | Elastomer moulding bladder - reinforced with fibres, to produce reinforced plastic containers of the required size |
| DE19803909A1 (en) * | 1998-02-02 | 1999-08-05 | Ver Foerderung Inst Kunststoff | Resin injection process for production of continuous fiber reinforced hollow products, e.g. turbine blades, pressure tanks or structural components |
| CN101716824A (en) * | 2009-11-13 | 2010-06-02 | 程显军 | Manufacturing technology of oil pipeline made of carbon fibre composite |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107662354A (en) * | 2016-07-27 | 2018-02-06 | 中国航发商用航空发动机有限责任公司 | Make the anti-process for creping of composite cylinder and device of high microsteping content |
| CN107662354B (en) * | 2016-07-27 | 2020-01-07 | 中国航发商用航空发动机有限责任公司 | Method and apparatus for making high fiber content composite material cylinder anti-wrinkling |
| CN106863836A (en) * | 2016-12-27 | 2017-06-20 | 航天神舟飞行器有限公司 | Composite overall structure fuel tank and its manufacture method |
| CN108284622A (en) * | 2017-12-13 | 2018-07-17 | 江南工业集团有限公司 | The moulding process of Filament Wound Composite tubular member |
| CN108274780A (en) * | 2018-04-02 | 2018-07-13 | 天津工业大学 | A kind of forming method of hollow composite |
| CN111688237A (en) * | 2020-06-23 | 2020-09-22 | 中国航空制造技术研究院 | Forming method of tubular composite material part with two closed ends |
| CN112265300A (en) * | 2020-10-15 | 2021-01-26 | 滕州深水湾复合材料科技有限公司 | Method for manufacturing composite material pipeline |
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Application publication date: 20160622 |
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