IMPROVED PROCESS FOR RESIN TRANSFER MOLDING

Abstract: An improved process for preparing a matrix resin composite comprising the steps of: (1) preparing a preform containing multiple layer of reinforcing material and a crosslinkable tackifier by (a) applying the tackifier onto the reinforcing material, (b) compressing the layers of reinforcing material and partially crosslinking the tackifier under a pressure sufficient to compact the tackified, reinforcing layers to a volume which is less than their volume in the finished composite part and in a manner such that at least one surface of each of the reinforcing layers is or will be, during partially crosslinking, in direct contact with the tackifier, and (2) contacting the preform with a matrix resin.

Description: IMPROVED PROCESS FOR RESIN TRANSFER MOLDING The present invention relates to a process for preparing resin matrix composites by resin transfer molding and to preforms useful in such processes. One method for preparing a resin matrix composite of a continuous resin phase reinforced with fibers such as woven fabric, chopped fiber, is known as resin transfer molding ("RTM"). In a conventional resin transfer molding process, layers of a reinforcing material are loaded into a mold, a thermosetting, matrix resin is injected into the mold and the resin cured to provide a finished composite. It is difficult and t. Tie consuming to load the layers of the reinforcing material into the mold. In addition, it was often necessary to stitch the reinforcing layers together in order to provide net-shaped preforms. By "net-shaped", it is meant that preform generally conforms to the final shape of the composite article. In an improved resin transfer molding process, individual layers of a reinforcing material are sprinkled with a solid, tackifying powder which, when heated, will fuse onto the surface of the reinforcing material and then solidify upon cooling. The layers of the reinforcing materials with the tackifier can be stacked together, the tackifier heated, fusing the plies together under an appropriate pressure, and then cooled to form what has been called a net- shaped preform. This multilayered preform is placed into a mold, the matrix resin added, and the composite formed using ordinary resin transfer molding processes. The tackifier used in known resin transfer molding may not be sufficiently soluble in the matrix resin to completely dissolve prior to curing it. As such, when the curable matrix resin is pumped into one end of the mold, it transports the undissolved tackifier to the other end of the mold. The resulting composite product contains a matrix resin whose chemical composition varies with location within the composite. Those areas having high concentrations of tackifier frequently have poorer physical or mechanical properties than the area containing lower proportions of tackifier. Moreover, extensive heating during the preforming process increases the molecular weight of the tackifier which causes a loss in adhesion between the tackifier and the reinforcing layers. In addition, the tack if ied preforms are normally larger than the shape of the final composite because of the natural loft of the reinforcing fiber or fabric. In the preparation of the final resin matrix composite, the preforms are then compressed while the matrix resin is cured. Unfortunately, this often shifts or moves the preform or individual layers in the preform; thereby rendering the final composite part less uniform. In view of the deficiencies of the prior art processes, it is desirable to provide an RTM process which provides greater uniformity in the final product. In one aspect, the present invention is a process for preparing a matrix resin composite comprising the steps of: (1) preparing a preform comprising a tackifier of a curable resin and two or more layers of a reinforcing material by: (a) applying the tackifier to at least one layer of reinforcing material, (b) compressing two or more layers of the reinforcing material and partially crosslinking the tackifier under a pressure above atmospheric pressure and sufficient to compact the reinforcing layers to a volume which is less than their volume in the finished matrix resin composite part and in a manner such that at least one surface of the reinforcing layers is or will be, during partially crosslinking, in direct contact with the tackifier, and (2) contacting the preform with a matri. resin which is a curable resin the same as or different than the tackifier under conditions such that the tackifier and matrix resins are cured, thereby forming the matrix resin composite. In a preferred embodiment, the method for preparing the matrix resin composite comprises subjecting the layers of tack if ied, reinforced material to a temperature sufficient to partially crosslink the tackifier and at conditions such that at least one surface of each of the reinforcing layers is or will be, during partial crosslinking, in direct contact with the tackifier and to a pressure cycle of: (i) a first pressure greater than atmospheric pressure, (ii) a second pressure which is substantially higher than the first pressure and sufficient to compact the preform to a volume which is less than their volume in the finished matrix resin composite part, (c) reducing the pressure to a third pressure which is lower than the second pressure while cooling the partially crosslinked, tackified, reinforcing material to a temperature sufficient to solidify the tackifier. By the method of the present invention, final composite articles can be effectively prepared from preforms without crimping. These preforms, as well as the composites prepared therefrom, exhibit excellent uniformity. In a second aspect, the present invention is a preform which comprises two or more layers of reinforcing material and a tackifier of a curable resin prepared by the described method. The process and preforms of the present invention can be used to make reinforced matrix composites. The composites are useful as structural materials. The preforms of the present invention are prepared from a tackifier and a reinforcing material. The preforms are then prepared into the resin matrix composites using a matrix resin which forms a continuous phase with the reinforcing material forming a discontinuous phase. The reinforcing material can be essentially any fibrous material which reinforces the composite such as woven or non-woven fibers, random fibers, monof ilaments and chopped fiber. They may be in the form of woven or non-woven fibrous materials, or in the form of random short fibers, and may be unidirectional or multidirectional. Materials which can be employed for reinforcing the matrix include quartz, aramid, boron, glass, carbon, polybenzazole, polybenzothiazole, and polyethylene. In general, the reinforcing material is preferably a quartz, aramid, boron, glass, carbon, or gel-spun polyethylene fiber. Preferably, the reinforcing material is in the form of woven fabrics, most preferably woven graphite fabric. The tackifier is applied to the reinforcing material. The tackifier is preferably either: (1) a self-crosslinkable material (that is, a material which is capable of at least partially crosslinking, optionally in the presence of crosslink -litiators or promoters) with itself; or (2) a mixture of crosslinkable material and a crosslinking agent which is capable of at least partially curing the crosslinkable material. Examples of suitable self-crosslinkable materials include polyimide, particularly bismaleimide; polycyanate ester; vinyl ester (with suitable initiators and promoters); and benzocyclobutene. The preferable self-crosslinkable material is a polyimide. The most preferred self-crosslinkable material is bismaleimide. An example of such a preferred self- crosslinkable material is 5250-4RTM BMI sold by BASF NARMCO. Mixtures of crosslinkable material and crosslinking agent, that is, crosslinkable systems, are preferably mixtures of a thermosetting resin and a curing agent, often referred to as a hardener. Representative examples of such systems include: (a) an epoxy resin (such as TACTIX ® 123 epoxy resin or PR 500 τ " from 3M) and a curing agent which can cure an epoxy resin (such as MELAMINE'" 5260 curing agent); (b) a polyisocyanate and polyol which reacts with the isocyanate to form a polyurethane (such as SPECTRIM* MM310); and (c) an epoxy resin and cyanate ester resin (such as E-905L resin from BP Chemicals). When a crosslinkable system is employed, it is preferably an epoxy resin used in conjunction with a suitable curing agent and optionally a curing catalyst. In the preferred system, the epoxy resin is preferably the glycidyl ether of a polyhydric phenol, such as biphenol, bisphenol A, tetrabromobisphenol A, a novolac resin or bis-(hydroxyphenyl)f luorene resin. It may be either a liquid or a solid epoxy resin and preferably has an epoxy equivalent weight (EEW) of between 150 and 700. In the preferred system, the curing agent is preferably an amine, amide, sulfimide, sulfamide, polymercaptan, polyphenol, substituted imidazole, polyacid, polyanhydride, urea, thiourea or sulfonamide. It is more preferably an amine or amide compound, such as dicyanamide. In order to assist in partial curing it may be desirable to use a multistage curing agent, that is, a curing agent which reacts with the epoxy resin to cure at different temperatures or at different rates at the same temperature. The multistage curing agent may be a single compound such as sulfanilamide or cyanoguanidine or a mixture of compounds that contain two or more reactive moieties that react with the epoxy resin to cure at different temperatures or at different rates at the same temperature. The equivalent ratio of curing agent to epoxy resin is preferably between 0.5: 1 and 1.5: 1, and more preferably between 0.8: 1 and 1.2: 1 , although a stoichiometric or 1 : 1 equivalent ratio is often most preferred. Examples of suitable catalysts include primary aliphatic polyamines such as diethylenetriamine, triethylenetetramine and tetraethylenepentamine, tertiary amines such as triethyleneamine, tripropyleneamine and tributylamine, phosphonium salts such as ethyltriphenylphosphonium chloride, butyltriphenylphosphonium bromide, tetra-n- butylphosphonium acetate and ethyltriphenylphosp h onium acetate, and substituted imidazoles such as 2-methylimidazole. Preferably, the catalyst is phosphonium salt such as tetra-n- butylphosphonium acetate and ethyltriphenylphosphonium acetate. If employed, the catalysts is preferably employed in a concentration of from 0.01 to 2 parts catalyst per 100 parts resin, by weight (phr), more preferably from 0.05 to 0.5 phr, and most preferably from 0.08 and to 0.2 phr. In preparing the preform, the tackifier can be applied in any manner such that at least one surface of each of the reinforcing layers will be in contact with the tackifier during partially curing of the tackier. In general, the tackifier is applied to at least one side of each layer of the reinforcing material employed in preparing the preform in a manner and quantity sufficient to maintain net-shape, but small enough to leave the resulting preform porous to la er allow the matrix resin to infuse throughout the reinforcing material. The tackifier is preferably employed in an amount of at least about 0.25, more preferably at least about 1 , and most preferably at least about 3, weight percent of the reinforcing material. The tackifier is preferably used in an amount of no more than about 15, more preferably no more than about 8, and most preferably no more that about 5, weight percent of the reinforcing material. The tackifier may be applied by known methods, such as spraying or dipping for liquid tackifiers, or sprinkling by hand, by using a flour sifter-type apparatus or by electrostatic application for tackifiers in the form of powders. It is preferably applied substantially evenly across the reinforcing material. The layers of the reinforcing material are stacked and compressed together at a temperature sufficient to partially crosslink the tackifier after the tackifier is applied. For instance, the multiple layers of the reinforcing material can be compressed under a pressure above atmospheric pressure and sufficient to compress the tackif ied, reinforcing layers to a volume which is less than the volume of the finished resin matrix composite even after release of the compression pressure, and at a temperature sufficient to partially crosslink the tackifier. Typically, when the compression pressure is released, the preform expands or springs back and the compression pressure and temperature used in the practice of this invention is such to prevent the preform from expanding to a volume larger than its net-shape after release of compression. The compression pressure is preferably from 10 psia (that is, 25 psig) (172 kPa) to 300 psia (2067 kPa), more preferably from 20 psia (138 kPa) to 200 psia (1378 kPa), most preferably from 30 psia (207 kPa) to 160 psia (1102 kPa). The tackifier should be sufficiently crosslinked during compression to maintain the net-shape and to prevent substantial springback upon release of the compression pressure and the time and temperature used in preparing the preform are chosen such that the tackifier is partially crosslinked while the preform is formed. Partially crosslinking the tackifier prevents substantial migration of the tackifier while a matrix resin is injected. To fuse or stick the tackifier to the reir *orcing material, this preforming temperature is preferably higher than the glass transition temperature of the tackifier. The o glass transition temperature of the tackifier can be conveniently measured by differential scanning calorimetry ("DSC"). The preforming temperature most advantageously employed will vary depending on a variety of factors including the resin and curing agent selected, and the desired properties of the preforming step and resulting product and can readily be determined by persons of ordinary skill in the art. In general, the temperature at which 5 preforming is conducted is from 80°F (27°C) to 400°F (204°C), more preferably from 150°F (66°C) to 350°F (177°C). The preforming step is preferably conducted in a time from 5 to 180 minutes, more preferably from 10 to 120 minutes, most preferably from 30 to 90 minutes. The amount to which the tackifier is crosslinked (that is, the degree of crosslinking) can be controlled by a variety of different methods. In one method, a resin 0 composition that contains both resin and a curing agent may contain less than a stoichiometric amount of curing agent, so that only an incomplete cure is possible. The precise quantities of resin and curing agent can vary depending upon the resin and curing agent selected, but can readily be determined by persons of ordinary skill in the art. For instance, when the resin is a dif unctional epoxy resin and the curing agent is a diamine, then the ratio of epoxy equivalents 5 to amine equivalents is preferably between 0.5: 1 and 0.85: 1 or between 1.25: 1 and 2: 1. In a second method, when resin composition contains both resin and a curing agent, the curing agent may be a multistage curing agent. In such case, the resin and curing agent can be cured at a first temperature and time that will only partially cure the resins and subsequently to a second, but different conditions, to complete cure. 0 Even when the tackifier is self-crosslinkable or contains stoichiometric ratios of resin and hardener, the time and temperature of the partial cure may be selected to provide the desired level of curing. Again, the optimal time and temperature will vary depending upon the tackifier and the presence or absence of any catalyst within the tackifier. For instance, when the tackifier contains bismaleimide, it is preferably reacted for between 5 and 120 5 minutes at a temperature between 120°C and 150 C C to partially cure the bismaleimide in forming the net-shape preform. Some partially cured tackifiers may continue to cure slowly at room temperature. Therefore, the preform is preferably prepared into a resin composite matrix before the tackifier has sufficiently cured to render the preform usable in preparing the resin matrix composite. The preform is preferably shelf-stable (that is, will not render the preform unusable) for at least about two weeks, more preferably for at least about a month, and most preferably for at least about three months. The pressure may be applied by any conventional means such as by a press, for example, a hydraulic press, air press, air-oil press, mechanical press such as screw-driven press, a vacuum bag with or without a pressure vessel and weights. The means for imparting the compressk n pressure preferably comprises a heating device so that the tackif ier/reinforcing material combination can be exposed to the desired temperature sufficient to partially cure the tackifier during the compression step. Examples of heating devices include an electric heater, steam lines, appropriate heat medium lines which can be incorporated in a compression fixture, or surrounding the compression fixture such as environmental chamber, constant temperature oven or autoclave. The press is preferably controlled such that the desired compression pressure and temperature can be applied. The press is preferably a hydraulic press with such a control system and an environmental chamber surrounding the compression fixture, a vacuum bag placed in pressured or unpressured autoclave or a combination of a hydraulic press and a vacuum bag. In a preferred embodiment, the layers of reinforcing material are compressed together under a "pulse" cycle which comprises: (•) a "first pressure above atmospheric pressure, (ii) a second pressure which is substantially higher than the first pressure and sufficient to compact the preform to a volume which is less than their volume in the finished matrix resin composite part, (c) reducing the pressure to a third pressure which is lower than the second pressure while cooling the partially crosslinked, tackif ied, reinforcing material to a temperature sufficient to solidify the tackifier. The first pressure is substantially lower than the second pressure. The first pressure is preferably from 5 to 50 (from 35 to 345), more preferably from 10 to 30 (from 69 to 207), most preferably from 12 to 16 (from 83 to 110), psi (kPa). The first pressure is preferably applied until the temperature of the preform rises sufficiently high enough to fuse or stick the tackifier to the reinforcing material. This depends on the tackifier employed and desired temperature but is generally from 1 to 60 minutes, preferably is 5 to 15 minutes. The second pressure is higher than the first pressure and sufficient to compact the preform to a volume which is less than the volume of the desired molding. The pressure is preferably from 25 to 500 (from 172 to 3445), more preferably from 40 to 300 (from 276 to 2067), most preferably from 50 to 200 (from 345 to 1378), psi (kPa). During this period, the temperature is maintained at the preforming temperatures described hereinbefore. The preform is exposed to the second pressure for preferably 1 to 60 minutes, more preferably 3 to 30 minutes, most preferably 5 to 10 minutes. After applying the second pressure, the partially crosslinked, tackif ied, reinforcing material is cooled to a temperature sufficient to solidify the tackifier under the 5 third pressure which is lower than the second pressure. The third pressure is preferably from 5 to 50 (from 35 to 345), more preferably from 10 to 30 (from 69 to 207), most preferably from 12 to 16 (from 83 to 110), psia (kPa). The third pressure is preferably initially applied before the preform begins to cool, and preferably until the pre 'orm reaches sufficiently low temperature to solidify the tackifier. The preform is exposed to the third pressure for preferably more than 1 o 5 minutes, more pre erably more than 15 minutes, most preferably more than 30 minutes, and preferably no more than 120 minutes, more preferably no more than 90 minutes, most preferably no more than 45 minutes. The third pressure may be the same or different with the first pressure, but is preferably same as the first pressure. The temperature to solidify the tackifier is any temperature lower than a glass transition temperature of the tackifier and is 15 preferably at ambient temperature (for example, 20 to 25°C). In this preferred embodiment, the pressure is applied by using a press with a control system or a combination of a press and a vacuum bag placed in pressured or unpressured environmental chamber. By applying this pressure, a temperature rising and cooling step can be conducted under lower pressure, and preform can be prepared without 20 applying high pressure during entire process. After its preparation, the preform is contacted with a matrix resin that contains a second curable resin which may or may not be the same or different than the tackifier. The matrix resin is preferably substantially the same as the tackifier, such that at least 50 percent of the backbone unit of the tackifier and the matrix resin are the same, more preferably at least 25 80 percent are the same, most preferably the tackifier and the matrix resin are made of the same material. The matrix resins should be completely cured without a crosslinking agent, or with at least a stoichiometric quantity of curing agent. The matrix resin is advantageously employed in an amount sufficient to hold the fibers together, to maintain fiber alignment and, preferably, to transfer loads around broken 30 fibers. However, it is usually preferable to minimize the quantity of matrix resin in the composite. After curing, the matrix resin and tackifier usually make up at least 25 volume percent of the composite and most often make up at least about 35 volume percent. The matrix resin and tackifier preferably make up no more than about 80, more preferably no more than about 50, and most preferably no more than about 40 volume percent of the composite. 35 The matrix resin is preferably applied under sufficient pressure to force it throughout the preform, so that the preform is impregnated with resin and voids (that is, those areas without resin) within the cured composite are minimized. The matrix resin is preferably applied under a vacuum or at a pressure of up to 600 psia (4134 kPa), more preferably from 50 to 400 psia (345 to 2756 kPa). There is frequently a pressure drop across the mold, so that pressure at the inlet may be as high as about 400 psia (2756 kPa) while pressure at the outlet is 50 psia (345 kPa) or lower. The matrix resin and tackifier are then subjected to a temperature and other 5 conditions suitable to fully cure them. The curing temperature and time most advantageous used will vary depending upon a variety of factors including the matrix resin and tackifier used, but generally the curing temperature is preferably from 30 to 350°C, and the curing time is preferably from 15 to 300 minutes. When the matrix -esin and tackifier are epoxy resins such as glycidyl ether of a polyhydric phenol, a novolac resin or bis-(hydroxyphenyl)f luorene resin, then 10 the final curing step is preferably conducted for a time from 30 to 120 minutes at a temperature from 90°C to 180°C. However, for some epoxy resins the best curing temperature may be as high as 250°C or more. When the matrix resin and tackifier are bismaleimide resins, then the final curing step is conducted for a time from 60 to 240 minutes at a temperature from 150°C to 210 G C, followed by a post-curing step of from 60 to 240 minutes at a temperature from 15 175°C to 230°C. The final curing step is preferably completed in a mold that can provide a composite of the desired shape. The resulting cured composite can be cooled, finished such as removing a flash and being applied a paint, and used in the ordinary manner for matrix composites. The following examples are illustrative of the invention only and they should not 20 be taken as limiting its scope. Unless otherwise stated all parts and percentages are by weight. The following materials are used in the examples: Epoxy Resin A - is brominated diglycidyl ether of bisphenol A having a viscosity of 170 cP to 210 cP at 150°C, an epoxy equivalent weight of 440 to 470 and is commercially available from The Dow Chemical Company as Quatlex* 6410. 25 Epoxy Resin B - is diglycidyl ether of bisphenol A having a melting point of 138°F (59°C) (by DSC), an epoxy equivalent weight of 675 to 750 and is commercially available from The Dow Chemical Company as D.E.R. ® 662EH. Epoxy Resin C - is a brominated diglycidyl ether of bisphenol A having an epoxy equivalent weight of 305 to 355, and is commercially available from The Dow Chemical 30 Company as D.E.R. ® 542. Epoxy Resin D - is diglycidyl ether of bisphenol A having a viscosity of 9000 cP to 10500 cP at 25°C, an epoxy equivalent weight of 176 to 183 and is commercially available from The Dow Chemical Company as D.E.R. ® 383. Epoxy Resin E - is a f luorene-containing epoxy resin. It is crosslinkable resin 35 without crosslinking agent. It is commercially available from 3M Corp. as AMD-0036. Bis-A - is epoxy resin grade bisphenol A with an equivalent weight of 114.1 and is commercially available from The Dow Chemical Company. TBBA - is tetrabromobisphenol A (2,2-bis-(3,5-dibromo-4- hydroxyphenyl)propane) with an equivalent weight of 271.9 and is available from Schenectady Chemicals, Inc. BMI Resin - is a bismaleimide resin blend having a viscosity of 50 cps at 130°C, that is commercially available from BASF NARMCO as 5250-4RTM. Catalyst A - is a 70 weight percent solution of ethyltriphenylphosphonium acetate: acetic acid complex and commercially available from Morton Thiokol. Catalyst B - is the amide of sulfanillic a id (sulfanilamide) with a melting point of 165°C to 167°C and is commercially available rom Aldrich Chemical. Example 1 - Compaction Test Using Advanced BMI Resin Synthesis of Advanced BMI Resin BMI Resin (1000 grams) was weighed into a 2-liter resin kettle. The resin kettle was placed in a hot air circulation oven at 110°C (230°F) for approximately one hour in order to lower the viscosity of the resin. The kettle was heated using infrared lamps with stirring, according to the time and temperature set out in Table I. Table I Viscosity of Resin at 150°C (cps) < 10 30 50 78 242 546 1021 1621 2173 The preferred viscosity of the final cooled tackifier product was 2000 cps when tested at 150°C. Compaction Test On Preforms With Advanced BMI Resin Using MTS Testing Machine A sixteen-ply preform was formed using the thus formed advanced BMI resin. A test sample was stamped out into a 1.128 inch diameter circular wafer from sixteen plies of 6K- 4HS graphite woven fabric which is arranged so that fibers of the reinforcing material are running in four directions, 0, 90, ± 45 degrees and the wafer substantially has uniformity in all directions, that is, quasi-isotropic configuration, using a steel rule die held in a 2.5 ton hydraulic press made by Carver laboratory. The advanced BMI resin powder is sprinkled on each ply in an even coat at a concentration of about 4.8 percent by \. -eight. The nominal thickness of the test sample is 0.24 inches. The sample was loaded into a physical testing machine made by Mechanical Test System (hereinafter MTS testing machine) with pressure control via hydraulic press which can maintain a constant pressure on the sample during contraction or expansion of the sample. The test fixture which contained the sample was placed in an environmental chamber. The temperature of the test sample was maintained at 200°F (93°C) ± 1°C. The weight load was adj usted to press the sample for 50 psia (345 kPa) of pressure. The sample was heated for 10 minutes to bring it up to the desired temperature. The thickness of the sample was recorded, and the test started. At the end of the time period, the sample was cooled to 100°F (38°C) and the thickness was recorded again. The springback was calculated as the difference between the two thickness measurements. The result is shown in Table II. Comparative Example A The method of Example 1 was repeated except that the weight load was adjusted to 50 psia (345 kPa) and immediately released. The springback was calculated with the results shown in Table II. Example 2 Example 1 was repeated except that the temperature of the test sample was maintained at 300°F (149°C) ± 1°C in the environmental chamber. Again, the springback was calculated with the results shown in Table II. Comparative Example B The method of Example 2 was repeated except that the test sample is maintained at 300°F (149 c C) ± 1°C in the environmental chamber. The springback was calculated with the results shown in Table II. Compaction temperature m (°F) 200 (93) 200 (93) 300 (149) 300 (149) These Examples show the use of a self-crosslinkable tackifier for making preforms. And these Comparative Examples show the preforms were not allowed to partially crosslink the tackifier under the pressure sufficient to compact the preforms to a volume which was less than the volume of net-shape. Comparing with Comparative Examples A and B, the preforms by Examples 1 and 2 show lower springback. Examples 3-10 A sixteen-ply preform as prepared in Example 1 was loaded into a creep testing machine made by Advanced Test Systems Incorporation (hereinafter ATS creep testing machine) in which pressure supplied is via steel weight instead of hydraulic means. Some of the samples were subjected to a pulse pressure cycle of 10 minutes under pressure of 15 psia (103 kPa) while heating to an elevated temperature as set forth in Table III, 5 minutes under a pressure as recorded in Table III and about 30 minutes under 15 psia (103 kPa) while being cooled to 100°F (38°C). Other samples were subjected to a single pressure for a period of 15 minutes under a full pressure as set forth in Table III while heating to the desired temperature, then cooling to 100°F (38°C). The springback for each sample was recorded and these results are recorded in Table III. These examples show the use of a self-crosslinkable tackifier for making preforms using a compressing step. The preforms showed low springback. In addition, preforms made using a pulse process showed surprisingly better results, that is, lower springback. Moreover, the preforms by pulse process can be prepared without applying high pressure during the temperature rising and cooling steps. It may improve process capability by eliminating a use of means for applying high pressure such as a hydraulic press during entire process and using a means for applying only lower pressure such as a vacuum bag during the temperature rising and cooling step. Example 1 1 - Compaction Test With Fluorene-Containing Epoxy Resin E A preform was made as described in Example 1 except that the compression temperature was 250 C F (121°C), the compression pressure was 45 psi (310 kPa) and Epoxy Resin E was used as the tackifier. The results of the springback measurements are shown in Table IV. Comparative Example C A preform was made as described in Comparative Example A except that the compression temperature was 250 o F,(121 c C) the compression pressure was 45 psi (310 Pa) and Epoxy Resin E was used as the tackifier. The results of the springback measurements are shown in Table IV. r C«o m m«pa_c«t-i«o«n t C o o m mp F e a r c a t t i l1 o,n. β Example No. Time temperature (minute) (° J F J ) ϋcl- 11 60 250 (121) C 250 (121) I This Example shows the use of a crosslinkable tackifier for making preforms, and this Comparative Example shows the preform was not allowed to partially crosslink the tackifier under the pressure sufficient to compact the preforms to a volume which was less than the volume of net-shape. Comparing with Comparative Example C, the preform by Example 11 showed lower springback. Example 12 A preform was fabricated from seven plies of 6K-4HS IM7 woven graphite fabric, arranged in a quasi-isotropic configuration. The dimt isions of the preform were 12 inches by 30 inches. The woven fabric had a nominal thickness of 0.1 inches, and a net thickness of 0.058 inches was desired. The test sample was placed in a steel mandrel, vacuum bagged to the surface and loaded into an autoclave. The autoclave was pressurized to 60 psi (413 kPa). The temperature was raised to 190°F (88°C) to 200°F (93°C) for 10 minutes, and maintained to ± 5°C via the autoclave heating system for 20 minutes. The preform was then cooled to 100°F (38 C C) under the pressure about 30 minutes. The thickness of the preform without pressure was 0.058 inches. Example 13 A preform was formed as described in Example 13 except that the pressurization cycle was different in that the pressure of the autoclave is initially atmospheric pressure and a compression pressure to the preform was 15 psi until the temperature was raised to 190°F (88°C) to 200°F (93°C) for 10 minutes, and then the pressure of the autoclave was raised to 60 psi (413 kPa) and the temperature was maintained at 190°F (88°C) to 200°F (93°C) for 20 minutes, afterward, the pressure of the autoclave was reduced to atmospheric pressure and the temperature of the autoclave was decreased to 100°F (38°C) for 30 minutes. The thickness of the preform was 0.058 inches. Example 12 and 13 show the use of curable tackifier with crosslinking agent. The preforms show low springback. Furthermore, the preform made by the pulse process in Example 13 had almost equivalent springback to that made in the single process shown in Example 12, although high pressure was applied for a shorter time. It may improve process capability by eliminating the use of means for applying high pressure such as a hydraulic press during entire process and using a means for applying only lower pressure such as a vacuum bag during the temperature rising and cooling step. Comparative Example D - Compaction Test On Preforms With An Advanced Epoxy Resin Synthesis Of An Advanced Epoxy Resin An advanced bromine-containing epoxy resin was made. Epoxy Resin D (356 grams) and Bis-A (132 grams) were heated under nitrogen atmosphere from ambient temperature to 60°C without stirring. At 60°C, the viscosity of the reaction mixture was low enough to allow heating from 60°C to 80°C with stirring. Catalyst A (0.62 grams, 1 100 ppm) was added dropwise to the stirred reaction mixture. Over 45 minutes, the reaction temperature was increased from 80°C to 150°C. An exotherm occurred around 150°C, and heating was reduced so that the reaction temperature did not exceed 200°C. Stirring was continued at about 190 C C for an additional 45 minutes. The hot reaction product was poured onto a cool, non-stick surface as a layer approximately 1 /4" thick (6.4 mm). After the advanced resin cools and solidifies, it was broken into flake form. The flaked advanced epoxy resin was ground into a fine powder using a Bantam Mill (Mikro-Pul Corporation) fitted with a 0.013" (0.33 mm) herring one slit screen. The grinding chamber was cooled to ambient temperature with liquid nitrogen to prevent melting of the resinous compound during the grinding. A preform was made as described in Example 1 except the advanced epoxy resin is used as tackifier. The result is shown in Table V. Comparative Example E The method of Comparative Example D was repeated except that the weight load was adjusted to 50 psia (345 kPa) and immediately released. The springback was calculated with the results shown in Table V. Comparative Example F Comparative Example D was repeated except that the temperature of the test sample was maintained at 300°F (149°C) ± 1°C in the environmental chamber. Again, the springback was calculated with the results shown in Table V. Comparative Example G The method of Example E was repeated except that the test sample was maintained at 300°F (149°C) ± 1°C in the environmental chamber. The springback was calculated with the results shown in Table V. Example No. D I These Comparative Examples show the use of uncrosslinkable tackifier. The preforms show extremely high springback tendency comparing with the above described Examples using crosslinkable tackifier.

Claims: 1. A process for preparing a matrix resin composite comprising the steps of: (1) preparing a preform comprising a tackifier of a curable resin and two or more layers of reinforcing material by: (a) applying tackifier to at least one layer of the reinforcing material, (b) compressing the layers of reinforcing material and partially crosslinking the tackifier under a pressure above atmospheric pressure sufficient to compact the tackif ied, reinforcing layers to a volume which is less than their volume in the matrix resin composite and in a manner such that at least one surface of each of the reinforcing L yers is or will be, during partially crosslinking, in direct contact with the tackif ier, and o (2) contacting the preform with a matrix resin which is a curable resin the same as or different than the tackifier under conditions such that the tackifier and matrix resins are cured, thereby forming the matrix resin composite. 2. The process of Claim 1 wherein the preform, after compression step 1(b) and return to atmospheric pressure, has an equal or smaller volume than its volume in the matrix resin composite. 3. The process of Claim 1 wherein the matrix resin and the tackifier resin are substantially the same. 4. The process of Claim 1 wherein the tackifier comprises a bismaleimide resin. 5. The process of Claim 1 wherein the tackifier comprises an epoxy resin and a 0 suitable curing agent. 6. The process of Claim 1 wherein the step (b) is: (b) subjecting the layers of tackif ied, reinforced material to a temperature sufficient to melt and partially crosslink the tackifier and at conditions such that at least one surface of each of the reinforcing layers is or will be, during partial crosslinking, in direct contact with the tackifier and to a pressure cycle of: (i) a first pressure greater than atmospheric pressure, (ii) a second pressure which is substantially higher than the first pressure and sufficient to compact the preform to a volume which is less than their volume in the matrix resin composite, 0 and further comprising a step (c): (c) reducing the pressure to a third pressure which is lower than the second pressure while cooling the partially crosslinked, tackif ied, reinforcing material to a temperature sufficient to solidify the tackifier; between the step (b)(ii) and (2). 5 7. The process of Claim 6 wherein the preform, after compression step 1 (b) and return to atmospheric pressure, has an equal or smaller volume than its volume in the matrix resin composite. 8. The process of Claim 6 or wherein the matrix resin and the tackifier resin are substantially the same. 9. The process of Claim 6 wherein the tackifier comprises a bismaleimide resin. 10. The process of Claim 6 wherein the tackifier comprises an epoxy resin and a suitable curing agent. 11. A preform comprising a tackifier of a curable resin and two or more layers of reinforcing material prepared by: (a) applying tackifier to at least one layer of the reinfi. cing material, (b) compressing the layers of reinforcing material and partially crosslinking the tackifier under a pressure above atmospheric pressure sufficient to compact the tackif ied, reinforcing layers to a volume which is less than their volume in the matrix resin composite and in a manner such that at least one surface of each of the reinforcing layers is or will be, during partially crosslinking, in direct contact with the tackifier. 12. The preform prepared by the method of Claim 1 1 wherein the preform, after compression step (b) and return to atmospheric pressure, has an equal or smaller volume than its volume in the matrix resin composite. 13. The preform prepared by the method of Claim 11 wherein the tackifier comprises a bismaleimide resin. 14. The preform prepared by the method of Claim 11 wherein the tackifier comprises an epoxy resin and a suitable curing agent. 15. A preform comprising a tackifier of a curable resin and two or more layers of reinforcing material prepared by: (a) applying tackifier to at least one layer of the reinforcing material, (b) subjecting the layers of tackified, reinforced material to a temperature sufficient to melt and partially crosslink the tackifier and at conditions such that at least one surface of each of the reinforcing layers is or will be, during partial crosslinking, in direct contact with the tackifier and to a pressure cycle of: (i) a first pressure greater than atmospheric pressure, (ii) a second pressure which is substantially higher than the first pressure and sufficient to compact the preform to a volume which is less than their volume in the matrix resin composite, and (c) reducing the pressure to a third pressure which is lower than the second pressure while cooling the partially crosslinked, tackified, reinforcing material to a temperature sufficient to solidify the tackifier. 16. The preform prepared by the method of Claim 15 wherein the preform, after compression step (b) and return to atmospheric pressure, has an equal or smaller volume than its volume in the matrix resin composite. 17. The preform prepared by the method of Claim 15 wherein the tackifier comprises a bismaleimide resin. 18. The preform prepared by the method of Claim 15 wherein the tackifier comprises an epoxy resin and a suitable curing agent.

Inventors: BARRON JAMES H, GENDREAU JOHNNY P, WHITE WARREN D, BARRON, JAMES, H., GENDREAU, JOHNNY, P., WHITE, WARREN, D.
Applicants: DOW CHEMICAL CO, THE DOW CHEMICAL COMPANY
Application year: 1995
Main classification: B29B11
IPC codes: B29B11, B29C70, B29K101, B29K105, C08J5