US20110151232A1 - Modified Resin Systems for Liquid Resin Infusion Applications & Process Methods Related Thereto - Google Patents

Modified Resin Systems for Liquid Resin Infusion Applications & Process Methods Related Thereto Download PDF

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US20110151232A1
US20110151232A1 US12/963,823 US96382310A US2011151232A1 US 20110151232 A1 US20110151232 A1 US 20110151232A1 US 96382310 A US96382310 A US 96382310A US 2011151232 A1 US2011151232 A1 US 2011151232A1
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resin
particles
modified resin
formulation
thermoplastic material
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Jonathan Edward Meegan
Robert Blackburn
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Cytec Technology Corp
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Cytec Technology Corp
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Assigned to CYTEC TECHNOLOGY CORP. reassignment CYTEC TECHNOLOGY CORP. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BLACKBURN, ROBERT, MEEGAN, JONATHAN EDWARD
Publication of US20110151232A1 publication Critical patent/US20110151232A1/en
Priority to US15/653,098 priority Critical patent/US10836118B2/en
Abandoned legal-status Critical Current

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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
    • B29C70/02—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements, e.g. non-specified reinforcements, fibrous reinforcing inserts and fillers, e.g. particulate fillers, incorporated in matrix material, forming one or more layers and with or without non-reinforced or non-filled layers
    • B29C70/021—Combinations of fibrous reinforcement and non-fibrous material
    • B29C70/025—Combinations of fibrous reinforcement and non-fibrous material with particular filler
    • 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
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
    • B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—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
    • B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
    • B29C70/48—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08F—MACROMOLECULAR COMPOUNDS OBTAINED BY REACTIONS ONLY INVOLVING CARBON-TO-CARBON UNSATURATED BONDS
    • C08F279/00—Macromolecular compounds obtained by polymerising monomers on to polymers of monomers having two or more carbon-to-carbon double bonds as defined in group C08F36/00
    • C08F279/02—Macromolecular compounds obtained by polymerising monomers on to polymers of monomers having two or more carbon-to-carbon double bonds as defined in group C08F36/00 on to polymers of conjugated dienes
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08G—MACROMOLECULAR COMPOUNDS OBTAINED OTHERWISE THAN BY REACTIONS ONLY INVOLVING UNSATURATED CARBON-TO-CARBON BONDS
    • C08G59/00—Polycondensates containing more than one epoxy group per molecule; Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups
    • C08G59/18—Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups ; e.g. general methods of curing
    • C08G59/20—Macromolecules obtained by polymerising compounds containing more than one epoxy group per molecule using curing agents or catalysts which react with the epoxy groups ; e.g. general methods of curing characterised by the epoxy compounds used
    • C08G59/32—Epoxy compounds containing three or more epoxy groups
    • C08G59/38—Epoxy compounds containing three or more epoxy groups together with di-epoxy compounds
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
    • C08K5/00—Use of organic ingredients
    • C08K5/16—Nitrogen-containing compounds
    • C08K5/17—Amines; Quaternary ammonium compounds
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
    • C08L55/00—Compositions of homopolymers or copolymers, obtained by polymerisation reactions only involving carbon-to-carbon unsaturated bonds, not provided for in groups C08L23/00 - C08L53/00
    • C08L55/04—Polyadducts obtained by the diene synthesis
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
    • C08L63/00—Compositions of epoxy resins; Compositions of derivatives of epoxy resins
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2063/00—Use of EP, i.e. epoxy resins or derivatives thereof, as moulding material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
    • B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
    • B29K2105/16—Fillers
    • B29K2105/165—Hollow fillers, e.g. microballoons or expanded particles
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
    • C08L2205/00—Polymer mixtures characterised by other features
    • C08L2205/02—Polymer mixtures characterised by other features containing two or more polymers of the same C08L -group
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08L—COMPOSITIONS OF MACROMOLECULAR COMPOUNDS
    • C08L2207/00—Properties characterising the ingredient of the composition
    • C08L2207/53—Core-shell polymer
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/249921—Web or sheet containing structurally defined element or component

Definitions

  • Modified resin systems for liquid resin infusion applications prepreg autoclave applications and hybrids thereof.
  • Liquid resin infusion is a process used to manufacture fiber-reinforced composite structures and components for use in a range of different industries including the aerospace, transport, electronics, and building and leisure industries.
  • the general concept in LRI technology involves infusing resins into a fiber reinforcement, fabric or a pre-shaped fibrous reinforcement (“preform”) by placing the material or preform into a mold (two-component mold or single-sided mold) and then injecting resin under high pressure (or ambient pressure) into the mold cavity or vacuum bag sealed single-sided mold.
  • the resin infuses into the material or preform resulting in a fiber-reinforced composite structure.
  • LRI technology is especially useful in manufacturing complex-shaped structures which are otherwise difficult to manufacture using conventional technologies.
  • Variation of liquid resin infusion processes include, but are not limited to, Resin Infusion with Flexible Tooling (RIFT), Constant Pressure Infusion (CPI), Bulk Resin Infusion (BRI), Controlled Atmospheric Pressure Resin Infusion (CAPRI), Resin Transfer Molding (RTM), Seemann Composites Resin Infusion Molding Process (SCRIMP), Vacuum-assisted Resin Infusion (VARA) and Vacuum-assisted Resin Transfer Molding (VARTM).
  • RIFT Resin Infusion with Flexible Tooling
  • CPI Constant Pressure Infusion
  • BRI Bulk Resin Infusion
  • CAPRI Controlled Atmospheric Pressure Resin Infusion
  • RTM Resin Transfer Molding
  • SCRIMP Seemann Composites Resin Infusion Molding Process
  • VARA Vacuum-assisted Resin Infusion
  • VARTM Vacuum-assisted Resin Transfer Molding
  • One technology to toughen fiber-reinforced composite structures manufactured by LRI technologies is to integrate the toughener into the preform itself.
  • a soluble toughening fiber may be directly woven into the preform thereby eliminating the need to add toughener into the resin which otherwise would increase the viscosity of the resin (rendering it unsuitable for resin infusion).
  • Another example is the use of soluble or insoluble veils comprising of toughener used as an interleaf with the reinforcement of the preform.
  • the manufacturing process may be more complicated and costly, in addition to increasing the risk of hot/wet performance knock-downs and solvent sensitivity with a polymer based insoluble interleaf.
  • Another technology is the addition of particles to the resin. The amount of particles required to reach a suitable toughness threshold, however, is often high resulting in a viscous resin requiring a very narrow process window that is generally unfavorable for LRI.
  • the particles may be one of chemically functionalized or chemically non-functionalized core-shell rubber particles or hollow particles.
  • a material comprising the core may be one of polybutadiene-styrene, polybutadiene or a combination thereof, and a material comprising the shell may be one of silica, polymerized monomers of acrylic acid derivatives containing the acryl group including acrylic and poly(methyl methacrylate) or a combination thereof.
  • the particles In a cured condition, the particles may be substantially uniformly dispersed throughout the modified resin system.
  • the thermoplastic material may be one of phenoxy-based polymers, poly(ether sulfone) polymers, poly(ether ether sulfones), poly(methyl methacrylate) polymers, carboxylterminated butadiene acrylonitrile polymers, copolymers thereof, or combinations thereof.
  • the formulation wherein the amount of thermoplastic material is below approximately 30% net weight, preferably below 7%, of the modified resin system.
  • at least the thermoplastic material phase may separate from the base resin. More particularly, the thermoplastic material phase may separate into aggregate domains from the base resin, each aggregate domain having an island-like morphology.
  • the morphology in a cured article may evolve: (i) during the later stages of a ramp to dwell temperature; or (ii) after a ramp to dwell has been completed during the cure cycle.
  • the amount of particles and the amount of thermoplastic material may be combined in a 1 to 0.56 ratio.
  • the threshold average viscosity may be less than 5 Poise at a temperature of less than 180° C., more narrowly between 80° C. and 130° C.
  • a composite article comprising: a structure having a predetermined shape, the structure having a plurality of layers of a fiber-based fabric, the structure having a targeted composite toughness within a predetermined range, wherein the toughness is at least partially imparted by a modified resin system during a process, the modified resin system including: (i) at least one base resin; (ii) an amount of particles within a predetermined range in a carrier resin; and (iii) an amount of thermoplastic material within a predetermined range wherein the base resin, the particles and the thermoplastic material are combined to form the modified resin system, the modified resin having a average viscosity below a threshold average viscosity within a predetermined temperature range is herein disclosed.
  • the modified resin system may further include a curing agent, the curing agent comprising an aniline-based amine compound.
  • the base resin may be one of epoxy, bismaleimide, cyanate ester or a combination thereof.
  • the base resin may include a combination of epoxies including at least one di-, tri- or tetra-epoxy.
  • the particles may be one of core-shell rubber (CSR) particles or hollow particles wherein, when the particles are CSR particles, a material comprising the core is one of polybutadiene-styrene, polybutadiene or a combination thereof, and a material comprising the shell is one of silica, polymerized monomers of acrylic acid derivatives containing the acryl group including acrylic and poly(methyl methacrylate) or a combination thereof. In a cured condition, the particles may be substantially uniformly dispersed throughout the modified resin system.
  • CSR core-shell rubber
  • a formulation comprising: (i) a base resin comprising at least one epoxy; (ii) a curing agent; (iii) an amount of thermoplastic material; and (iv) an amount of core-shell particles wherein the base resin, the curing agent, the thermoplastic material and the particles are combined to form the modified resin system, the modified resin having an amount of thermoplastic material of less 30% net weight, preferably less than 7% net weight, of the total weight of the modified resin system is herein disclosed.
  • a manufacturing process comprising: (i) preparing a preform; (ii) laying the preform within a mold; (iii) heating the mold to a predetermined temperature; and (iv) injecting a resin wherein the resin is a modified resin, the modified resin system comprising a combination of (i) at least one base resin; (ii) a curing agent; (iii) an amount of particles within a predetermined range in a carrier resin; and (iv) an amount of thermoplastic material within a predetermined range wherein the amount of thermoplastic material of the modified resin is less than 30% net weight, preferably less than 7% net weight, of the total weight of the modified resin system is herein disclosed.
  • the predetermined temperature of the mold may be 110° C.
  • the manufacturing process may further comprise ramping a temperature of the mold to 180° C. at a rate of less than 10° C. per minute, more narrowly, less than 5° C. per minute.
  • the manufacturing process wherein, when the mold reaches 180° C., the temperature is held for between 90 minutes and 150 minutes.
  • the preform may be sealed within the mold by at least a vacuum bag.
  • An average viscosity of the modified resin system may be less than 5 Poise at a temperature range of less than 180° C., more narrowly between 80° C. and 130° C.
  • the preform may be comprised of plurality of layers of fiber-based fabric.
  • the fiber-based fabric may have a structure comprising one of woven fabrics, multi-warp knitted fabrics, non-crimp fabrics, unidirectional fabrics, braided socks and fabrics, narrow fabrics and tapes or fully-fashioned knit fabrics.
  • the fiber-based fabric may be comprised of reinforcing fibers of a material such as organic polymer, inorganic polymer, carbon, glass, inorganic oxide, carbide, ceramic, metal or a combination thereof.
  • FIG. 1 is a schematic illustrating conventional toughened resin systems and the modified resin system according to an embodiment of the invention.
  • FIG. 2 is a chart showing the relationship between viscosity and toughness for a thermoplastic material in a base resin, core-shell particles a base resin, and a combination of thermoplastic material and core-shell particles in a base resin according to an embodiment of the invention.
  • FIG. 3A is an optical micrograph of thermally-evolved thermoplastic domains and core-shell rubber particle regions at increasing concentration, but at a constant ratio of core-shell particles:thermoplastic toughener in a modified resin system according to an embodiment of the invention.
  • FIG. 3B is an optical microscopy evaluation of the thermally evolved thermoplastic domains and CSR particle regions in the proposed invention demonstrating the influence of CSR concentration on the dimensions of the witnessed morphology.
  • FIG. 4 is a scanning electron microscopy (SEM) image of the island like morphology and core shell particles witnessed in a cured and modified resin system with respect to damage resistance mechanisms according to an embodiment of the invention.
  • SEM scanning electron microscopy
  • FIG. 5 is a graph comparing the fracture toughness of a modified resin system according to embodiments of the invention to the fracture toughness of other resin systems.
  • FIG. 6 Describes the evolution of the morphology as represented by an embodiment of the current invention as a function of temperature or vitrfication onset in the base resin comprising the proposed invention.
  • FIGS. 7A and 7B are Transmission electron Microscopy images of the island like morphology and core shell particles witnessed in a cured and modified resin system with respect to damage resistance mechanisms according to an embodiment of the invention.
  • FIG. 8 Is an expanded SEM image detailing the growth rings in the thermoplastic domains present in the proposed invention.
  • FIG. 9 illustrates a schematic of the generalized morphology of a modified resin system according to embodiments of the invention
  • FIG. 10 Illustrates a representative LRI system having a fabric perform thereon.
  • FIG. 11 is a chart comparing CSAI values of the modified resin system according to embodiments of the invention to the CSAI values for other resin systems.
  • Embodiments of the invention are directed to modified resin systems for use in resin infusion (RI) processes, variations of LRI processes and other suitable processes such as prepreg processes.
  • the modified resin system includes a novel combination of at least one base resin, an amount of particles within a predetermined range and an amount of thermoplastic material within a predetermined range wherein, when combined, the modified resin system has an average viscosity below a threshold average viscosity within a specific temperature range and a high level of toughness.
  • the modified resin system may additionally include a curing agent and other suitable components.
  • the modified resin system has been experimentally shown to exhibit a unique, controllable and constant morphology which is substantially or completely responsible for imparting a required toughness and damage resistance to a finished composite article without adversely impacting resin properties such as viscosity, potlife, cure temperature, glass transition temperature or tensile modulus of the modified resin system.
  • a combination of at least one base resin, an amount of particles within a predetermined range and an amount of thermoplastic material within a predetermined range, in addition to other components may be combined in a “one pot” formulation to generate a modified resin system which can be used in RI/LRI processes or prepreg processes.
  • the modified resin system as formulated according to embodiments of the invention was discovered to have an unexpectedly low viscosity, low reactivity, a high level of toughness (G 1C ), among other characteristics, when subjected to numerous experimental tests.
  • modified resin may also be used in variations of liquid resin infusion processes including, but not limited to, Resin Infusion with Flexible Tooling (RIFT), Constant Pressure Infusion (CPI), Bulk Resin Infusion (BRI), Controlled Atmospheric Pressure Resin Infusion (CAPRI), Resin Transfer Molding (RTM), Seemann Composites Resin infusion Molding Process (SCRIMP), Vacuum-assisted Resin Infusion (VARI), Resin Transfer Injection (RTI) and Vacuum-assisted Resin Transfer Molding (VARTM) as well as other processes used to manufacture composite articles.
  • RIFT Resin Infusion with Flexible Tooling
  • CPI Constant Pressure Infusion
  • BRI Bulk Resin Infusion
  • CAPRI Controlled Atmospheric Pressure Resin Infusion
  • RTM Resin Transfer Molding
  • SCRIMP Seemann Composites Resin infusion Molding Process
  • VARI Vacuum-assisted Resin Infusion
  • RTI Vacuum-assisted Resin Transfer Molding
  • FIG. 1 is a schematic illustrating conventional resin systems and the modified resin system according to an embodiment of the invention.
  • Numerical reference 102 represents an unmodified neat epoxy which may be used in composite manufacturing processes. An unmodified epoxy resin system is generally known to be unsuitable in the manufacture of high toughness composite articles without resorting to the use of a secondary, insoluble toughening article such as a hot-melt adhesive web, e.g., SPUNFAB® veil.
  • Numerical reference 104 represents a modified epoxy system having core-shell rubber (CSR) particles therein to impart a toughening characteristic. Typically, modified epoxy systems of this type are known to exhibit high toughness values which often do not translate into equivalent composite performance.
  • Numerical reference 106 represents another modified epoxy system having a thermoplastic therein. This modified epoxy system is known to have an average viscosity which is outside of acceptable processing windows for LRI applications.
  • Numerical reference 108 represents a modified resin system according to embodiments of the invention which is characterized by having a suitable average viscosity for LRI (e.g., less than 5 Poise) without sacrificing performance in the resin or composite, specifically related to toughness properties.
  • Modified resin system 108 includes at least one base resin, an amount of particles within a predetermined range and an amount of thermoplastic material within a predetermined range in a novel combination which makes it suitable for LRI processes, prepreg processes and other like processes.
  • the base resin is an epoxy resin or combination of epoxy resins; however, embodiments of the invention are not limited to epoxy resins.
  • a “resin” is a synthetic polymer compound which begins in a viscous state and hardens with treatment. Resins are used as a structural matrix material in the manufacture of adhesives and composites and are often reinforced with fibers (e.g., glass, Kevlar, Boron and Carbon).
  • the base resin may be any one of epoxy, bismaleimide, benzoxazine, cyanate ester, vinyl ester, polyisocyanurates, bismalimide, cyanate ester, phenolic resin or any combination thereof in addition to other suitable resins.
  • the base resin is an epoxy resin or a combination of epoxy resins.
  • the epoxy resin may be a tetra-, tri-, di-epoxy or combinations of tetra-, tri- and/or di-epoxies.
  • Exemplary tri-epoxies include triglycidyl p-aminophenol (MY-0510 available from Huntsman Advanced Materials, Inc.) and ARALDITE® (MY-0600 available from Huntsman Advanced Materials, Inc.).
  • An exemplary tetra-epoxy is tetraglycidyl diaminodiphenyl methane (MY-721 available from Huntsman Advanced Materials, Inc.).
  • Other suitable epoxy resins include bisphenol F epoxy (PY-306 available from Ciba Geigy).
  • a “particle” is a polymer-based material having a core-shell or hollow morphology.
  • Core-shell rubber (CSR) particles have the characteristic of having a core comprising of a rubbery material surrounded by an outer shell of glassy material.
  • CSR particles are used as toughening agents when combined with polymeric matrices, e.g., epoxy resins.
  • the particles may be any commercially available chemically functionalized or chemically non functionalized CSR particles having a core material of polybutadiene-styrene or polybutadiene and having a shell material of silica or polymerized monomers of acrylic acid derivatives containing the acryl group including acrylic and poly(methyl methacrylate).
  • the CSR particles may be supplied in a carrier resin such as tetraglycidyl diaminodiphenyl methane (i.e., MY-721) and may have a diameter of between about fifty (50) nanometers (nm) and about eight hundred (800) nm, in one embodiment, about one-hundred (100) nm.
  • a carrier resin such as tetraglycidyl diaminodiphenyl methane (i.e., MY-721) and may have a diameter of between about fifty (50) nanometers (nm) and about eight hundred (800) nm, in one embodiment, about one-hundred (100) nm.
  • CSR particles examples include, but are not limited to, the Paraloid series of materials (available from Rohm and Haas), MX411 (polybutadiene-styrene/acrylic) and MX416 (polybutadiene/acrylic) (both are dispersions in Huntsman MY721 epoxy resin and are available from Kaneka Corp.); however, any particle exhibiting the CSR or hollow structure as described above may be used in the modified resin systems according to embodiments of the invention.
  • Paraloid series of materials available from Rohm and Haas
  • MX411 polybutadiene-styrene/acrylic
  • MX416 polybutadiene/acrylic
  • Core-shell particles have been evidenced to toughen LRI systems via a cavitation mechanism in addition to crack pinning or “tear out” mechanisms.
  • a cavitation mechanism the rubbery cores of the CSR particles yield under the stress concentrations at a crack tip, resulting in dissipation of energy from the crack front and the formation of voids in the core material.
  • thermoplastic is a polymer that is elastic and flexible above a glass transition temperature (T g ).
  • the thermoplastic Material comprises one of phenoxy-based polymers, poly(ether sulfone) (PES) polymers, poly(ether ether sulfones), polymerized monomers of acrylic acid derivatives containing the acryl group including acrylic and poly(methyl methacrylate) (PMMA) polymers, carboxyl terminated butadiene acrylonitrile (CTBN) polymers, copolymers thereof; or combinations thereof.
  • PES poly(ether sulfone)
  • PMMA poly(methyl methacrylate)
  • CBN carboxyl terminated butadiene acrylonitrile
  • copolymers thereof copolymers thereof.
  • Representative thermoplastics include, but are not limited to, KM180 (available from Cytec Industries.
  • thermoplastic or other suitable material e.g., Nanostrength X, available from Arkema, Inc.
  • a base resin more particularly, exhibiting aggregate domains, or an “island-like” morphology (explained in more detail below)
  • any thermoplastic or other suitable material e.g., Nanostrength X, available from Arkema, Inc.
  • exhibiting a thermally driven phase separation from a base resin more particularly, exhibiting aggregate domains, or an “island-like” morphology (explained in more detail below, may be used in the modified resin systems according to embodiments of the invention.
  • thermoplastic toughening of composite or resin matrices is crack pinning.
  • Indications of crack pinning mechanisms include tailing behind thermoplastic domains or apparent plastic deformation around such thermoplastic zones originating from a divergent crack front around a thermoplastic rich region and subsequent convergence of the split crack fronts.
  • Another example of a typical toughening mechanism is that of ductile tearing which can be described as a localized plastic deformation upon application of a stress to the material.
  • a “curing agent” is a substance or mixture of substances added to a polymer composition (e.g., resin) to promote or control the curing reaction. Addition of curing agent functions to toughen and harden a polymer material by cross-linking of polymer chains.
  • curing agents include, but are not limited to, methylenebis (3-chloro-2,6 diethylaniline) (MCDEA), 3,3′-diaminodiphenyl sulfone (3,3′-DDS), 4,4′-diaminodiphenyl sulfone (4,4′-DDS), dicyandiamide (DICY), N-methyl-diethanolamine (MDEA) and 4,4′-methylene-bis-(2-isopropyl-6-methyl-aniline) (MMIPA).
  • MCDEA methylenebis (3-chloro-2,6 diethylaniline)
  • 3,3′-DDS 3,3′-diaminodiphenyl sulfone
  • 4,4′-diaminodiphenyl sulfone 4,4′-diaminodiphenyl sulfone
  • dicyandiamide DICY
  • MDEA N-methyl-diethanolamine
  • MMIPA 4,4
  • the modified resin system may include a thermoplastic which is 7% or less net weight of the modified resin system combined with an amount of CSR particles in a 1 to 0.56 ratio of thermoplastic to CSR particles.
  • the base resin may be a combination of di-, tetra- and tri-epoxies such as PY-306, MY-0500 and/or MY-0600).
  • the thermoplastic material may be 5003P and the CSR particles may be MX411 (in MY-721) or MX416 (in MY-721) one-hundred (100) nm particles.
  • a curing agent, such as MCDEA may be added to the “one pot” resin system to make the resin system curable when heat and/or pressure is/are applied thereto.
  • the formulation of the present invention comprises at least one base resin; an amount of particles within a predetermined range in a carrier resin; and an amount of thermoplastic material within a predetermined range wherein the base resin, the particles and the thermoplastic material are combined to form a modified resin system, the modified resin having an average viscosity below a threshold average viscosity within a predetermined temperature range.
  • the threshold average viscosity of the formulation is less than 5 Poise at a temperature of less than 180° C. and preferably at a temperature of between 80° C. and 130° C.
  • thermoplastic material When the formulation is in a cured condition, at least the thermoplastic material is phase separated from the base resin and preferably phase separates into aggregate domains from the base resin, each aggregate domain having an island-like morphology.
  • the cure morphology evolves (i) during the later stages of a ramp to dwell temperature or (ii) after a ramp to dwell has been completed during the cure cycle.
  • the amount of thermoplastic material in the formulation is below approximately 30% net weight of the modified resin system and preferably below approximately 7% net weight of the modified resin system.
  • the formulation may include an amount of particles and the amount of thermoplastic material combined in a 1 to 0.56 ratio.
  • the thermoplastic material is phase separated from the base resin and preferably, the thermoplastic material phase separates into aggregate domains from the base resin, each aggregate domain having an island-like morphology.
  • the above manufacturing process may further modified wherein the predetermined temperature of the mold is between 90° C. and 120° C. or more preferably the predetermined temperature of the mold is 110° C.
  • the manufacturing process may be practiced by ramping a temperature of the mold to 180° C. at a rate of up to 5° C. per minute or more preferably at a rate of 2° C. per minute.
  • the temperature may be held about 120 minutes.
  • the manufacturing process may be practiced wherein the preform is a plurality of layers of fiber-based fabric.
  • the fiber-based fabric may have a structure comprising one of woven fabrics, multi-warp knitted fabrics, non-crimp fabrics, unidirectional fabrics, braided socks and fabrics, narrow fabrics and tapes or fully-fashioned knit fabrics.
  • the fiber-based fabric may utilize reinforcing fibers of a material selected from the group consisting of organic polymer, inorganic polymer, carbon, glass, inorganic oxide, carbide, ceramic, metal or a combination thereof.
  • the manufacturing process is preferably practiced where the preform is sealed within the mold by at least a vacuum bag.
  • a base resin having di-, tri- and tetra-epoxies, a quantity of amine curing agent and quantities of 5003P thermoplastic and CSR particles i.e. MX411
  • the combination (100 grams) was transferred into steel molds which were then placed in a fan oven preheated to 100° C. (ramp to 180° C. at 1° C. per minute, dwell for 2 hrs ramp to 25° C. at 2° C. per minute).
  • Samples (prepared from the cured modified resin plaque) were prepared according to the relevant ASTM standard for the desired test.
  • thermoplastic i.e., 5003P
  • core-shell particles i.e. MX4111
  • core-shell particles i.e., core-shell particles
  • the viscosity ( ⁇ ) in the base resin system was observed to increase as the percentage loading of thermoplastic was increased, but to be independent of CSR concentration.
  • the toughness (G 1C ) of the systems was found to increase with both increasing thermoplastic and CSR concentration.
  • the modified resin systems were targeted to remain within a threshold limit of an average viscosity within a temperature range while maintaining a high level of toughness (G 1C ). It was discovered that formulations according to embodiments of the invention complied with a threshold average viscosity of less than five (5) P with a net weight of thermoplastic material of less than 30%, more narrowly less than 7%, combined with an amount of CSR particles in a 1 to 0.56 ratio of thermoplastic to CSR particles, which resultant combined characteristics rendered the modified resin system suitable for LRI applications.
  • the viscosity of less than (5) P was discovered to be achievable at a temperature of less than 180° C., more narrowly between 80° C. and 130° C.
  • the thermoplastic material is between about 0.1% and 7% net weight of the modified resin system and the amount CSR particles is between about 0.1% and 10% net weight of the modified resin system while maintaining a 1 to 0.56 ratio of thermoplastic to CSR particles.
  • the thermoplastic material is about 3.4% net weight of the modified resin system and the amount CSR particles is about 1.9% net weight of the modified resin system while maintaining a 1 to 0.56 ratio of thermoplastic to CSR particles. It was discovered that the main contribution to achieving the threshold viscosity was, among other factors, attributable to the thermoplastic.
  • Microcrack resistance is the ability of a material to resist formation of small, numerous cracks upon induced stress and strain in the material which instigates localized damage events that eventually weaken and compromise the composite article. Microcrack resistance is typically evaluated using multiple, simulated strain cycles. Samples are withdrawn for microscopic analysis during the cycle phase and cracks are readily identifiable after penetrative staining. During experiments, cured modified resin samples showed no microcracks after 400 thermal cycles ( ⁇ 53° C. to 90° C.) in one experiment and no microcracks after 2000 thermal cycles in another experiment.
  • Modified resin systems and unmodified or partially modified resin systems were prepared and compared to study crack pinning, ductile tearing and cavitation behavior of the systems expressed in fracture toughness (K 1C ) values.
  • the following systems were prepared: (i) a modified resin system having thermoplastic and CSR particles (Formulation 4); (ii) a partially modified resin system having thermoplastic material (Formulation 5); (iii) a partially modified resin system having CSR particles (Formulation 6); and (iv) an unmodified resin system (Formulation 7).
  • Examination of the fracture surface of Formulation 4 illustrated multiple fracture toughness mechanisms at work.
  • thermoplastic domains i.e., 5003P
  • CSR particle domains i.e., MX411
  • FIG. 4 examination of the fracture surface of the other Formulations 5, 6, 7 exhibited none or only partial similar damage resistance as that found with respect to Formulation 4. Additionally the combination of a low concentration of thermoplastic appeared to facilitate a more homogenous dispersion of CSR particles than in Formulation 6.
  • the morphology of the modified resin system was determined to generally consist of a phase separation, more particularly, an “island-like” morphology, of the thermoplastic and/or CSR particles from the base resin.
  • the “island-like” morphology is generally a result of a thermally driven phase separation of the thermoplastic from the base resin into discrete domains of thermoplastic-rich material identified by a clearly defined border with the cured or partially cured base resin when the modified resin system is in a cured or partially cured condition.
  • thermoplastic domains began to evolve followed by development of these seeds.
  • thermoplastic domains began to evolve.
  • the morphology of the thermoplastic domains was seen to be substantially or completely evolved (see FIG.
  • This unique processing factor i.e., the controlled and constant morphology evolution developed during a time period and at a critical temperature (in this case, at about 180° C.), advantageously avoids flow and filtration issues which would otherwise arise from having additive particles of the same size as the CSR particles in conventional formulations.
  • a critical temperature in this case, at about 180° C.
  • the morphology of the cured modified resin system was determined to be generally dependent upon the relative concentrations of CSR particles and thermoplastic and, therefore, directly controllable.
  • thermoplastic domains form via a phase separation of thermoplastic from the base resin during the cure of the resin while the CSR particles remain located within the base resin and are not drawn into the thermoplastic domains (see FIGS. 3A , 3 B, 4 ).
  • SEM scanned electron microscope
  • TEM transmission electron microscopy
  • the TEM evidence is supported by SEM evidence indicating the presence of growth rings within the thermoplastic morphology (see FIGS. 7A , 8 , 9 ) and also a combined optical microscopy/differential scanning calorimetry (DSC) study demonstrating the onset of morphology growth at the point where the resin begins to vitrify (see FIG. 6 ).
  • FIG. 3A illustrates a schematic of the generalized morphology of the modified resin system according to embodiments of the invention as discovered by the inventors.
  • addition of thermoplastic within a predetermined range (as well as CSR particles within a predetermined range) to a base resin (having one or more resins) resulted in a thermally-induced phase separation of the thermoplastic material from the base resin during the cure cycle of the modified resin system.
  • the CSR particles were observed to partially, substantially or completely remain within the base resin and were not therefore experimentally determined to be incorporated into the thermoplastic material domains.
  • the morphology of the modified resin system discovered by the inventors is believed to contribute to the combination of high Compressive After Impact Strength (CSAI), K 1C toughness (G 1C ), and microcrack resistance required for composite articles exposed to damage caused by environmental conditions and/or events while simultaneously allowing for a wide processing window during the fabrication process. It is anticipated that any thermoplastic exhibiting phase separation morphology, more particularly, an “island-like” morphology, combined with a suitable nanoscale particle (i.e., CSR or hollow particle) would be appropriate for formulating modified resin systems according to embodiments of the invention.
  • FIG. 10 illustrates a representative LRI approach (e.g., Resin Infusion in Flexible Tooling (RIFT)) having a fabric preform thereon.
  • the system includes a single-sided tool (i.e., mold) 1002 with a fiber preform 1004 laid thereon.
  • a peel-ply layer 1006 may be applied to a surface of preform 1004 .
  • a vacuum bag 1008 having a breather 1010 therein seals preform 1004 therein creating a “cavity”, or area in which preform 1004 resides.
  • a release agent or gel coat 1012 may be applied to a surface of tool 1002 and/or to a surface of vacuum bag 1008 .
  • the “cavity” is connected to a resin inlet 1014 via a resin transfer line (not shown). At another end, or at the same end, the “cavity” is connected to a vacuum system (not shown) via a vacuum evacuation line 1016 .
  • a liquid resin 1018 may be infused into the “cavity” at ambient pressure, a predetermined pressure or a gradient pressure. Liquid resin 1018 may be infused at ambient temperature, a predetermined temperature or a temperature gradient.
  • modified resin systems may be applied to preforms constructed from one or more layers of engineered textiles to manufacture composite articles using LRI processing techniques and tools (such as that represented in FIG. 10 ).
  • the engineered textiles may include, but are not limited to, woven fabrics, multi-warp knitted fabrics, non-crimp fabrics, unidirectional fabrics, braided socks and fabrics, narrow fabrics and tapes and fully-fashioned knit fabrics. These fabric materials are typically formed of fiber glass, carbon fiber, aramid fibers, polyethylene fibers or mixtures thereof.
  • NCF non-crimped fiber
  • Laminate test samples were also prepared using a closed mold RTM press set at 25 cm 3 /minute flow rate and an eight (8) millimeter (mm) inlet.
  • the resin pot was held constant at 100° C. and the tool was held constant at 110° C. for infiltration of the resin prior to commencing a 2° C. per minute ramp towards 180° C., dwelling for two (2) hours before ramping down at 2° C. per minute to room temperature.
  • the tool may be heated to a temperature of between 130° C. and 180° C. at a rate of less than 10° C. per minute.
  • T g glass transition temperature
  • DMTA Dynamic Mechanical Thermal Analysis
  • In-plane shear modulus was measured for laminate test samples according to known methods. In-plane shear modulus was determined to be between 3.5 GPa and 4.5 GPa (dry/RT) and between 3.0 GPa and 4.0 GPa (hot/wet).
  • Damage resistance is the ability of the composite article to resist damage after a force event which may cause delamination and weakening of the composite article and is a critical parameter for in-service behavior in high performance applications. Damage resistance can be measured through dent depth analysis or C-scan damage area analysis of impacted composite samples. Damage tolerance can be measured by a Compressive Strength After Impact (CSAI) test.
  • CSAI Compressive Strength After Impact
  • Laminate test samples prepared using modified resin systems according to embodiments of the invention exhibited reduced dent depths when compared to prior art laminates.
  • laminate test samples were found to have an average dent depth of between 0.6 mm and 0.8 mm following an impact event. These values represent about a 10% decrease in dent depth when compared to prior art laminates.
  • laminate test samples were found to have CSAI values between about 220 and 270 Mega-Pascals (MPa) in a plain weave textile (see FIG. 11 ) and between about 200 and 225 MPa in a non-crimp fiber textile which indicate a high tolerance to damage after an impact event.
  • OHC values were experimentally determined to be between 280 MPa to 320 MPa (dry) and between 220 MPa and 260 MPa (hot/wet).
  • modified resin systems with a suitable toughness renders it suitable for the manufacture of complex structures in a range of different industries including the aerospace, transport, electronics, building and leisure industries.
  • the modified resin systems may be used to construct components including, but not limited to, frame and stringer-type components for twin aisle derivatives and single aisle replacement programs, fuselage shell components, integrated flight control components for replacement programs, wing box structures and rotorblade systems for rotorcraft. Additionally, the modified resin systems may be used in the manufacture of composite for complex textile systems.

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