GB2348163A - A fibre-reinforced composite - Google Patents
A fibre-reinforced composite Download PDFInfo
- Publication number
- GB2348163A GB2348163A GB9906750A GB9906750A GB2348163A GB 2348163 A GB2348163 A GB 2348163A GB 9906750 A GB9906750 A GB 9906750A GB 9906750 A GB9906750 A GB 9906750A GB 2348163 A GB2348163 A GB 2348163A
- Authority
- GB
- United Kingdom
- Prior art keywords
- reinforcement layer
- fibre reinforcement
- matrix
- fibre
- matrix material
- 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.)
- Withdrawn
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 38
- 239000011159 matrix material Substances 0.000 claims abstract description 69
- 239000000835 fiber Substances 0.000 claims abstract description 61
- 230000002787 reinforcement Effects 0.000 claims abstract description 50
- 238000000034 method Methods 0.000 claims abstract description 38
- 238000004519 manufacturing process Methods 0.000 claims abstract description 16
- 239000004634 thermosetting polymer Substances 0.000 claims abstract description 11
- 229920001169 thermoplastic Polymers 0.000 claims abstract description 6
- 239000004416 thermosoftening plastic Substances 0.000 claims abstract description 6
- 229920001187 thermosetting polymer Polymers 0.000 claims abstract description 4
- 239000000945 filler Substances 0.000 claims abstract description 3
- 238000010438 heat treatment Methods 0.000 claims description 6
- 238000001816 cooling Methods 0.000 claims description 4
- 229920000728 polyester Polymers 0.000 claims description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 2
- 239000004698 Polyethylene Substances 0.000 claims description 2
- 229920003235 aromatic polyamide Polymers 0.000 claims description 2
- 229910052799 carbon Inorganic materials 0.000 claims description 2
- 239000011521 glass Substances 0.000 claims description 2
- 239000000155 melt Substances 0.000 claims description 2
- -1 polyethylene Polymers 0.000 claims description 2
- 229920000573 polyethylene Polymers 0.000 claims description 2
- 239000004760 aramid Substances 0.000 claims 1
- 238000002347 injection Methods 0.000 abstract description 13
- 239000007924 injection Substances 0.000 abstract description 13
- 239000011347 resin Substances 0.000 description 18
- 229920005989 resin Polymers 0.000 description 18
- 238000001802 infusion Methods 0.000 description 11
- 239000000463 material Substances 0.000 description 5
- 230000008901 benefit Effects 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 238000009745 resin transfer moulding Methods 0.000 description 3
- 239000012855 volatile organic compound Substances 0.000 description 3
- 238000009787 hand lay-up Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 239000004593 Epoxy Substances 0.000 description 1
- 229920006397 acrylic thermoplastic Polymers 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000003190 augmentative effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000006482 condensation reaction Methods 0.000 description 1
- 239000002537 cosmetic Substances 0.000 description 1
- 125000003700 epoxy group Chemical group 0.000 description 1
- 230000009970 fire resistant effect Effects 0.000 description 1
- 239000003063 flame retardant Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 229920003192 poly(bis maleimide) Polymers 0.000 description 1
- 229920003229 poly(methyl methacrylate) Polymers 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 235000013824 polyphenols Nutrition 0.000 description 1
- 239000011208 reinforced composite material Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- ISXSCDLOGDJUNJ-UHFFFAOYSA-N tert-butyl prop-2-enoate Chemical compound CC(C)(C)OC(=O)C=C ISXSCDLOGDJUNJ-UHFFFAOYSA-N 0.000 description 1
- 239000012815 thermoplastic material Substances 0.000 description 1
- 229920001567 vinyl ester resin Polymers 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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/542—Placing or positioning the reinforcement in a covering or packaging element before or during moulding, e.g. drawing in a sleeve
-
- 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
- B29C70/06—Fibrous reinforcements only
- B29C70/08—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers
-
- 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
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Reinforced Plastic Materials (AREA)
- Laminated Bodies (AREA)
Abstract
A method of manufacturing a fibre reinforced composite comprises the steps of providing a fibre reinforcement layer and a first matrix adjacent to a first surface of the fibre reinforcement layer, enclosing it in an envelope and injecting a second matrix material into the envelope, the second matrix material being a thermoset resin matrix which infuses into the second surface of the reinforcement layer. The first matrix material may be a thermoplastic or a thermoset. Depending on the matrix materials used, the fibre and matrix may be heated and cooled during the production of the composite. The first matrix may comprise a filler. A distribution means may be positioned between the fibre reinforcement and the envelope. The envelope may be subject to a vacuum and/or an external pressure during or after injection. The fibre reinforcement layer may comprise a plurality of dry plies. A fibre reinforced composite manufactured in accordance with the method described is also claimed.
Description
Method of Manufacture of Composite Materials
This invention relates to a method of manufacture of composite materials and composite materials manufactured by this method.
Conventionally, there are a number of ways to manufacture composite materials. The method used will depend on the quality of product required and the number of parts to be manufactured. The cheapest way to manufacture composites is to use hand lay-up. The are a number of problems associated with this technique including reproducibility and exposure of the laminator to emissions from the resin system used. A more reproducible method of manufacturing composites is to inject the resin into a dry fibre preform which is enclosed in a mould. This can be done either by creating a vacuum around the fibre preform to draw the resin through the layers of fibre as in a liquid resin infusion technique or, by injecting the resin into the fibres under pressure as used in resin transfer moulding (RTM). Both of these techniques allow for the production of near net shape parts and control the emissions of volatile organic compounds (VOC's). The cost of processing for both the liquid resin infusion technique and RTM processes is more than for hand lay-up, with RTM being the more expensive as the pressure used is higher.
Another technique that can be used is resin film infusion where a film or a slab of uncured resin in placed in communication with a preform. The application of heat and pressure melts the resin, which then infuses into the preform and subsequently cures.
For some applications, it would be desirable to have a composite with properties that varied throughout its thickness. For example, one of the surfaces may need to be fire or chemical resistant whilst the whole composite would have to meet certain structural requirements. The use of chemical or fire resistant resins and additives tends to be expensive and can result in a reduction of other desirable properties. If these expensive materials are only present in the composite where they are required, the cost of producing such composites is reduced.
Currently, the only way of manufacturing such composites is in number of steps which reduces any cost benefit as it increases the time of manufacture.
It is an object of the present invention to provide a method of manufacture of composite parts which can have variable properties through the thickness of the composite. The method utilises the advantages of closed mould techniques, namely the production of near net shape parts with controlled emissions of VOC's, without the disadvantages of conventional routes used to manufacture composites with variable properties through its thickness.
According to a first aspect of this invention, a method of manufacture of fibre reinforced composite materials comprises the steps of providing a fibre reinforcement layer, providing a first matrix adjacent to a first surface of the fibre reinforcement layer, enclosing the fibre reinforcement layer and first matrix in an envelope and injecting a second matrix material into the envelope, the second matrix material being a thermoset resin matrix, whereby the second matrix infuses into the second surface of the fibre reinforcement layer.
The second matrix material, is preferably a liquid of low viscosity to enable injection and infusion throughout the dry portion of the fibre reinforcement layer prior to the curing of the material. Suitable thermoset materials include polyesters, epoxies, phenolics, vinyl-esters, acrylics, bismaleimides. Whichever suitable material is chosen would depend on the properties required in the final composite.
Preferably, the first matrix material is a thermoplastic and the method includes the additional step of heating the first matrix material prior to injection of the second matrix material. The temperature and duration of the heating would be determined by the thermoplastic material used and the degree of infusion of the thermoplastic through the fibre reinforcement layer from the first surface that is required.
Preferably, the fibre reinforcement layer is cooled prior to the injection of the second matrix material. This allows for better control of the degree of infusion by the first matrix.
Preferably the first matrix material is a thermoset resin which is preferably in a solid or highly viscous form at ambient to enable correct placing of the matrix material with respect to the fibre reinforcement layer and enclosure of them under the envelope.
Preferably, the first matrix material is a high temperature cure thermoset resin. In order to cure the resin, the fibre reinforcement layer and first matrix material are preferably heated.
The temperature chosen will depend on the resin system used and the required degree of cure.
Preferably, the fibre reinforcement layer and first matrix material are cooled after the required degree of cure of the first matrix material has been achieved. This would allow the first and second resin matrices to chemically react and so produce a strong bond between the different layers.
Preferably, the fibre reinforcement layer is heated to a suitable temperature either prior to or during injection of the subsequent matrix material. The temperature being maintained until the resin has reached the desired degree of cure. This step would occur after the cooling step.
In order to produce a composite material with a variation in properties though its thickness, the second matrix material is preferably different to the first matrix material. When selecting the different matrix materials and processing conditions, a person skilled in the art will appreciate that care would be required in order to produce a high quality composite. One problem that could be encountered is the presence of residual stresses in the composite as a result of a difference in shrinkage percentages and rates of the matrix materials.
The properties required in the composite may be inherent in the matrix material itself or, may be imparted or augmented by the use of a suitable filler material.
In order to ensure full infusion of the subsequent matrix material into the dry portion of the fibre reinforcement layer, a distribution means may be positioned between the fibre reinforcement layer and envelope. This is particularly useful if the shape of the composite is complex. A distribution means between the envelope and the fibre reinforcement layer enables fast distribution of the matrix material to all parts of the dry reinforcement layer.
Another advantage of utilising a distribution means is that the infusion time of the subsequent matrix material is reduced, thus allowing it to be cured more quickly so reducing the time to manufacture each part.
Preferably, the envelope is subject to a vacuum prior to injection of the second matrix material. This would allow any gases produced to be removed from the envelope for example if the curing of a thermoset resin results in a condensation reaction. The use of a vacuum would also allow for faster distribution of the matrix material through the fibre reinforcement. If the second matrix material is subject to a vacuum during injection, the envelope is preferably flexible. An alternative to subjecting the envelope to a vacuum would be to inject the second matrix material under pressure. If the second matrix material is subject to a pressure during injection, the envelope is preferably rigid.
In a preferred embodiment, the envelope is subject to additional pressure during the injection of the subsequent matrix material. This pressure may be maintained until the subsequent matrix material has cured. This enables more accurate control of the thickness and the volume fraction of fibre of the composite being manufactured. This is especially useful when a large number of components are being manufactured and reproducibility is important. The additional pressure may also assist in the infusion of the subsequent matrix material into the dry portion of the fibre reinforcement layer.
Preferably, the fibre reinforcement layer comprises a plurality of dry plies. These plies may be stitched. The type of reinforcement, its orientation and the volume fraction desired in the final composite will be a function of the property requirements of the composite when in use.
For some applications it may be desirable to have a mixture of types of fibres. Suitable fibre types include glass, aramids, polyester, polyethylene and carbon.
In a second aspect of this invention, a fibre reinforced composite comprising a fibre reinforcement layer having a first matrix located from a first surface of the fibre reinforcement layer to a depth only partially through the fibre reinforcement layer and a thermoset resin matrix located from a second surface of the fibre reinforcement layer only partially through the fibre reinforcement layer. The first matrix material may be a thermoplastic or a thermoset. The two resin matrices may fully wet the fibre reinforcement layer. However further matrix materials may also be present in the final composite. These may be incorporated in an infusion or an injection process. If the further matrix materials are to be infused, they may be positioned where desired within the fibre reinforcement layer, prior to the infusion step. Alternatively, they may be infused in a separate process. If the further matrix materials are to be injected, they may be injected either prior to the injection of the second matrix material or after it, depending on the properties required in the final composite material. This enables the final composite to not only have a difference in properties between the first surface and the second surface but, also a difference at the first surface and a desirable point between the first surface and the second surface. An example of this, is when the first layer of matrix material at the first surface is cosmetic, the second layer comprises a fire retardant, and the subsequent layer imparts structural support.
When the first and second matrices are both thermoset resins, the matrices may be the same.
The variation of properties through the thickness of the composite would be achieved by a difference in the curing cycle of the resin used in each stage. For example, if the resin were high temperature cure and the first matrix material were heated in order to facilitate curing, by cooling prior to the injection of the second matrix then, heating the fibre and resin on injection, the first matrix would be post cured, resulting in a difference in properties between the first and second matrices.
Claims (20)
- Claims 1 A method of manufacturing a fibre reinforced composite comprising the steps of : (i) providing a fibre reinforcement layer; (ii) providing a first matrix adjacent to a first surface of the fibre reinforcement layer; (iii) enclosing the fibre reinforcement layer and first matrix in an envelope; and (iv) injecting a second matrix material into the envelope, the second matrix material being a thermoset resin matrix, whereby the second matrix infuses into the second surface of the fibre reinforcement layer.
- 2 A method as claimed in claim 1 wherein the first matrix material is a thermoplastic and the method includes the additional step of heating the first matrix after step (iii) whereby the first matrix melts and infuses into the first surface of the fibre reinforcement layer and only partially through the fibre reinforcement layer.
- 3 A method as claimed in claim 2 wherein the method further comprises the step of cooling the fibre reinforcement layer prior to step (iv).
- 4 A method as claimed in claim 1 wherein the first matrix material is a thermoset resin.
- 5 A method as claimed in claim 4 wherein the first matrix material is a high temperature cure thermoset resin.
- 6 A method as claimed in claim 5 wherein the method further comprises the step of heating the fibre reinforcement layer after step (iii).
- 7 A method as claimed in claim 6 wherein the method further comprises the step of cooling the fibre reinforcement layer prior to step (iv).
- 8 A method as claimed in any preceding claim wherein the method further comprises the step of heating the fibre reinforcement layer prior to or during step (iv).
- 9 A method as claimed in any preceding claim wherein the matrices are different.
- 10 A method as claimed in any preceding claim wherein the first matrix comprises a filler.
- I I A method as claimed in any preceding claim wherein a distribution means is positioned between the fibre reinforcement and the envelope.
- 12 A method as claimed in any preceding claim wherein the envelope is subject to a vacuum.
- 13 A method as claimed in any preceding claim wherein the envelope is subjected to an external pressure during or after step (iv).
- 14 A method as claimed in any preceding claim wherein the fibre reinforcement layer comprises a plurality of dry plies.
- 15 A method according to any preceding claim wherein the fibre reinforcement layer comprises at least one of glass, aramid, polyester, polyethylene or carbon.
- 16 A fibre reinforced composite manufactured in accordance with a method as claimed in any preceding claim.
- 17 A fibre reinforced composite comprising a fibre reinforcement layer having a first matrix located from a first surface of the fibre reinforcement layer to a depth only partially through the fibre reinforcement layer; and a thermoset resin matrix located from a second surface of the fibre reinforcement layer only partially through the fibre reinforcement layer.
- 18 A composite as claimed in claim 17 wherein the first matrix material is a thermoplastic or a thermoset.
- 19 A composite as claimed in claim 17 wherein the first and second matrices are the same.
- 20 A composite as claimed in claims 17 to 19 wherein the fibre reinforcement layer is fully wetted.
Priority Applications (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9906750A GB2348163A (en) | 1999-03-24 | 1999-03-24 | A fibre-reinforced composite |
| GB0120501A GB2363616B (en) | 1999-03-24 | 2000-02-01 | Composite materials and method of manufacturing the same |
| AU21220/00A AU2122000A (en) | 1999-03-24 | 2000-02-01 | Composite materials and method of manufacturing the same |
| PCT/GB2000/000287 WO2000056524A1 (en) | 1999-03-24 | 2000-02-01 | Composite materials and method of manufacturing the same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9906750A GB2348163A (en) | 1999-03-24 | 1999-03-24 | A fibre-reinforced composite |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB9906750D0 GB9906750D0 (en) | 1999-05-19 |
| GB2348163A true GB2348163A (en) | 2000-09-27 |
Family
ID=10850244
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB9906750A Withdrawn GB2348163A (en) | 1999-03-24 | 1999-03-24 | A fibre-reinforced composite |
| GB0120501A Expired - Fee Related GB2363616B (en) | 1999-03-24 | 2000-02-01 | Composite materials and method of manufacturing the same |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB0120501A Expired - Fee Related GB2363616B (en) | 1999-03-24 | 2000-02-01 | Composite materials and method of manufacturing the same |
Country Status (3)
| Country | Link |
|---|---|
| AU (1) | AU2122000A (en) |
| GB (2) | GB2348163A (en) |
| WO (1) | WO2000056524A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102501389A (en) * | 2011-11-15 | 2012-06-20 | 中国航空工业集团公司北京航空材料研究院 | Method for preparing composite material lamination structure through interlamination heat slip |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10354106B4 (en) * | 2003-11-19 | 2013-09-26 | Bayerische Motoren Werke Aktiengesellschaft | Method for producing a fiber composite structure |
| WO2005105416A1 (en) * | 2004-04-29 | 2005-11-10 | Cook Composites & Polymers Company | In-mold coating by a multiple step infusion process |
| CA2499849C (en) * | 2005-03-09 | 2010-02-02 | Zcl Composites Inc. | Composite laminated sheet material for containment sumps |
| GB2447964B (en) | 2007-03-29 | 2012-07-18 | Gurit Uk Ltd | Moulding material |
| DE102008047564A1 (en) * | 2008-09-16 | 2010-03-25 | Kraussmaffei Technologies Gmbh | Method and device for producing plastic products with integrated reinforcement structure |
| CN102107535A (en) * | 2010-12-22 | 2011-06-29 | 成都飞机工业（集团）有限责任公司 | Method for manufacturing carbon fiber reinforced resin matrix composite structure |
| DE102011108289A1 (en) * | 2011-07-21 | 2012-08-16 | Daimler Ag | Fiber reinforced plastic (FRP) motor vehicle component has fiber layer and differently colored matrix materials that together form component areas, so that visible side of components areas are provided with different colored surfaces |
| DE102011109724A1 (en) * | 2011-08-06 | 2013-02-07 | Daimler Ag | Fiber reinforced plastic composite component for motor car, has fibers in component regions in composite with matrix material, where component is formed as electrical conductive component imparting electric conductivity with one of regions |
| CN105034407B (en) * | 2015-09-17 | 2017-04-12 | 哈尔滨工业大学 | Preparation method for bicontinuous resin-based cenosphere composite foamed material |
| DE102019110462A1 (en) * | 2019-04-23 | 2020-10-29 | Leibniz-Institut Für Polymerforschung Dresden E.V. | METHOD FOR PRODUCING A MOLDED PART FROM A FIBER-PLASTIC COMPOSITE |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB651192A (en) * | 1946-03-15 | 1951-03-14 | Ernst Altman | Improvements in and relating to recessed articles made from reinforced thermoplasticor thermo-setting type resin |
| GB2066144A (en) * | 1979-12-20 | 1981-07-08 | Nava Pier Luigi | Method and apparatus to mould reinforced resin articles |
| EP0242891A2 (en) * | 1986-02-27 | 1987-10-28 | Dsm Resins B.V. | Sheet moulding compound and an upper layer for it |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4622091A (en) * | 1984-11-29 | 1986-11-11 | The Boeing Company | Resin film infusion process and apparatus |
| US4957801A (en) * | 1989-05-17 | 1990-09-18 | American Cyanamid Company | Advance composites with thermoplastic particles at the interface between layers |
| US4992228A (en) * | 1989-09-28 | 1991-02-12 | The Dow Chemical Company | Method for preparing preforms for molding processes |
| US5496602A (en) * | 1994-11-22 | 1996-03-05 | Dow-United Technologies Composite Products, Inc. | Low resin content unidirectional fiber tape |
| US6139942A (en) * | 1997-02-06 | 2000-10-31 | Cytec Technology, Inc. | Resin composition, a fiber reinforced material having a partially impregnated resin and composites made therefrom |
-
1999
- 1999-03-24 GB GB9906750A patent/GB2348163A/en not_active Withdrawn
-
2000
- 2000-02-01 AU AU21220/00A patent/AU2122000A/en not_active Abandoned
- 2000-02-01 GB GB0120501A patent/GB2363616B/en not_active Expired - Fee Related
- 2000-02-01 WO PCT/GB2000/000287 patent/WO2000056524A1/en not_active Ceased
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB651192A (en) * | 1946-03-15 | 1951-03-14 | Ernst Altman | Improvements in and relating to recessed articles made from reinforced thermoplasticor thermo-setting type resin |
| GB2066144A (en) * | 1979-12-20 | 1981-07-08 | Nava Pier Luigi | Method and apparatus to mould reinforced resin articles |
| EP0242891A2 (en) * | 1986-02-27 | 1987-10-28 | Dsm Resins B.V. | Sheet moulding compound and an upper layer for it |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102501389A (en) * | 2011-11-15 | 2012-06-20 | 中国航空工业集团公司北京航空材料研究院 | Method for preparing composite material lamination structure through interlamination heat slip |
| CN102501389B (en) * | 2011-11-15 | 2014-05-14 | 中国航空工业集团公司北京航空材料研究院 | Method for preparing composite material lamination structure through interlamination heat slip |
Also Published As
| Publication number | Publication date |
|---|---|
| AU2122000A (en) | 2000-10-09 |
| GB2363616B (en) | 2003-06-11 |
| WO2000056524A1 (en) | 2000-09-28 |
| GB2363616A (en) | 2002-01-02 |
| GB0120501D0 (en) | 2001-10-17 |
| GB9906750D0 (en) | 1999-05-19 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |