US20140083155A1 - Compliant Layer for Matched Tool Molding of Uneven Composite Preforms - Google Patents

Compliant Layer for Matched Tool Molding of Uneven Composite Preforms Download PDF

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Publication number
US20140083155A1
US20140083155A1 US13/625,598 US201213625598A US2014083155A1 US 20140083155 A1 US20140083155 A1 US 20140083155A1 US 201213625598 A US201213625598 A US 201213625598A US 2014083155 A1 US2014083155 A1 US 2014083155A1
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Prior art keywords
metal alloy
alloy sheet
matched
preform
recited
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Abandoned
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US13/625,598
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English (en)
Inventor
Marc R. Matsen
Erika L. Carter
Panagiotis E. George
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Boeing Co
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Boeing Co
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Filing date
Publication date
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Priority to US13/625,598 priority Critical patent/US20140083155A1/en
Assigned to THE BOEING COMPANY reassignment THE BOEING COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: CARTER, ERIKA L., GEORGE, PANAGIOTIS E., MATSEN, MARC R.
Priority to PCT/US2013/051873 priority patent/WO2014046781A1/en
Priority to CA2885632A priority patent/CA2885632A1/en
Priority to EP13745756.0A priority patent/EP2909012B1/en
Priority to ES13745756.0T priority patent/ES2670837T3/es
Priority to JP2015533055A priority patent/JP2015533695A/ja
Priority to KR1020157007638A priority patent/KR20150081423A/ko
Publication of US20140083155A1 publication Critical patent/US20140083155A1/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
    • B29C70/04—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
    • 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
    • B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
    • B29C35/02—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould
    • B29C35/08—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation
    • B29C35/0805—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation using electromagnetic radiation
    • B29C2035/0811—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation using electromagnetic radiation using induction

Definitions

  • This disclosure generally relates to fabrication of parts made of composite material. More specifically, this disclosure relates to apparatus and methods for consolidating and forming a pre-form made of fiber-reinforced plastic material (also referred to herein as a composite preform) to reduce voids and/or porosity.
  • a pre-form made of fiber-reinforced plastic material also referred to herein as a composite preform
  • Fiber-reinforced organic resin matrix composites have a high strength-to-weight ratio or a high stiffness-to-weight ratio and desirable fatigue characteristics that make them increasingly popular as a replacement for metal in aerospace applications.
  • Organic resin composites may comprise thermoplastics or thermosetting plastics.
  • Prepregs combine continuous, woven, or chopped reinforcing fibers with an uncured, matrix resin, and usually comprise fiber sheets with a thin film of the matrix. Sheets of prepreg generally are placed (laid-up) by hand or with fiber placement machines directly upon a tool or die having a forming surface contoured to the desired shape of the completed part or are laid-up in a flat sheet which is then draped and formed over the tool or die to the contour of the tool.
  • the resin in the prepreg layup is consolidated (i.e., pressed to remove any air, gas, or vapor) and cured (i.e., chemically converted to its final form usually through chain-extension) in a vacuum bag process in an autoclave (i.e., a pressure oven) to complete the part.
  • a vacuum bag process i.e., a pressure oven
  • the prepreg is laid-up, bagged (if necessary) and placed between matched metal tools that include forming surfaces that define the internal, external, or both mold lines of the completed part.
  • the tools and composite preform are placed within a press and then the tools and preform are heated under pressure to produce a consolidated, net-shaped part.
  • Induction heating is a process in which an electrically conducting object (usually a metal) is heated by electromagnetic induction. During such heating, eddy currents are generated within the metal and the electrical resistance of the metal leads to Joule heating thereof.
  • An induction heater typically comprises an electromagnet through which a high-frequency alternating current is passed.
  • Most organic matrix composites require a susceptor in or adjacent to the composite material preform to achieve the necessary heating for consolidation or forming. The susceptor is heated inductively and transfers its heat principally through conduction to the preform sandwiched between opposing susceptor facesheets. During heating under pressure, the number of voids and/or the porosity of a composite preform can be reduced.
  • Recycled graphite fibers can be used in the fabrication of composite aircraft parts, such as lightweight seat back components.
  • a matte product is fabricated using recycled graphite fibers and virgin thermoplastic fibers; then the matte product is consolidated and formed in matched tooling comprising opposing susceptor facesheets.
  • These matte products produced with recycled graphite fibers can exhibit a rather matted and tangled fiber architecture. These products can also have undesirable unevenness and thickness/density variations.
  • the graphite fibers are tangled, they do not facilitate the flow of the thermoplastic material. These characteristics lead to the formation of voids and/or porosity in the final composite product due to the fact that thickness and density distribution are not uniform across the matte product.
  • voids and/or porosity is further aided by the fact that the fibers are entangled and flow is limited and unable to “heal” porosity very effectively. Even prepreg has some variation in thickness and density distribution, which could lead to the formation of voids and/or porosity during matched tool molding of prepreg composites.
  • the subject matter disclosed herein is directed to a method for reducing the number of voids and/or porosity during the consolidation and formation of a composite preform having uneven thickness and/or density distribution, such as a matte product comprising recycled graphite fibers and virgin thermoplastic fibers.
  • This method is carried out using an apparatus that comprises matched molding tools.
  • the apparatus further comprises a compliant layer that is situated between the composite preform and one of the matched molding tools for the purpose of providing a more even pressure over the entire area of the preform during the consolidation process.
  • the compliant layer should have an offset tensile yield point (0.2% of the strain) in a range of 25-300 psi at the temperature of consolidation of the preform at strain rates of about 1% to 10% strain per minute.
  • a sheet of magnesium base alloy is used to act as the compliant layer or shim to compensate for uneven thickness or density over the area of a composite preform, for example, a matte product comprising recycled graphite fibers and virgin thermoplastic fibers.
  • a composite preform for example, a matte product comprising recycled graphite fibers and virgin thermoplastic fibers.
  • Magnesium base alloy makes an excellent candidate for a compliant layer for high-performance thermoplastic resins due to the fact that some magnesium alloys become very soft at temperatures useful for assisting the consolidation and molding of thermoplastic composites (i.e., 600-750° F.) and do not melt until above 1000° F.
  • the magnesium alloy sheet softens and forms into the areas of relatively lower pressure.
  • the magnesium alloy sheet can be reused due to the soft nature of the material.
  • alloys can be used instead of a magnesium base alloy provided that the alloy has an offset tensile yield point (0.2% of the strain) in a range of 25-300 psi at the temperature of consolidation of the preform at strain rates of about 1% to 10% strain per minute
  • a method for consolidating a preform made of composite material with reduced number of voids and/or porosity.
  • the preform and a compliant metal alloy sheet are placed between less compliant matched confronting forming/molding surfaces with the preform being sandwiched between the metal alloy sheet and one of the matched confronting surfaces.
  • the matched confronting surfaces are inductively heated (which heats the compliant metal alloy sheet by conduction) until the preform reaches at least a consolidation temperature of the composite material.
  • force is applied so that the matched confronting surfaces exert sufficient compressive force on the preform and metal alloy sheet to cause the composite material to consolidate at the consolidation temperature.
  • the compliant metal alloy sheet has a tensile yield point in a range of 25-300 psi at the consolidation temperature at a strain rate of about 1% to 10% strain per minute.
  • Another aspect of the disclosed subject matter is an apparatus for consolidating a preform made of composite material at a consolidation temperature, comprising: first and second tool assemblies having matched confronting surfaces; a metal alloy sheet disposed between said matched confronting surfaces, wherein said metal alloy sheet has a tensile yield point in a range of 25-300 psi at the consolidation temperature at a strain rate of about 10% strain per minute; means for heating at least the matched confronting surfaces of the first and second tool assemblies; and means for applying force to one or both of the first and second tool assemblies so that the matched confronting surfaces are capable of exerting compressive force on the preform and metal alloy sheet.
  • a further aspect is a method for consolidating a composite preform made of recycled graphite fibers and organic resin fibers, comprising: placing the composite preform and a metal alloy sheet between matched confronting surfaces of first and second tool assemblies, the matched confronting surfaces being less compliant than the metal alloy sheet; heating the matched confronting surfaces of the first and second tool assemblies and the metal alloy sheet during a heating cycle; and applying force to one or both of the first and second tool assemblies so that the matched confronting surfaces exert sufficient compressive force on the composite preform and metal alloy sheet to cause thermal coupling of one matched surface to one side of the composite preform, the other side of the composite preform to the metal alloy sheet, and the metal alloy sheet to the other matched confronting surface.
  • the force is applied during at least a portion of the heating cycle.
  • the metal alloy sheet has a tensile yield point in a range of 25-300 psi at a consolidation temperature at a strain rate of about 1% to 10% strain per minute.
  • FIG. 1 is a diagram showing a sectional view of portions of a known apparatus, the apparatus comprising upper and lower tool assemblies with matched surfaces designed to consolidate and form a composite preform.
  • the tool assemblies are shown in their retracted positions and the preform is shown in an uncompressed state.
  • FIG. 2 is a diagram showing a sectional view of the apparatus depicted in FIG. 1 , except that the tool assemblies are in their extended positions with the preform compressed therebetween.
  • FIG. 3 is a diagram showing an end view of a portion of a lower tooling die in accordance with one embodiment.
  • FIG. 4 is a diagram showing a sectional view of a portion of the lower tooling partially depicted in FIG. 3 , the section being taken along line 4 - 4 seen in FIG. 3 .
  • FIG. 5 is a diagram showing the placement of an unconsolidated matte product between a pair of opposing susceptors in their retracted positions, the matte product comprising recycled graphite fibers and virgin thermoplastic fibers.
  • FIG. 6 is a diagram showing a consolidated matte product between a pair of susceptors in their extended positions.
  • FIG. 8 is a graph showing the effect of temperature on the tensile properties of a magnesium base alloy having a chemical composition of 2.5-3.5% aluminum; 0.7-1.3% zinc; 0.20-1.0% manganese; balance magnesium.
  • the 0.2% proof stress curve has been extrapolated to the right of the vertical axis labeled “ ELONGATION ” to show the anticipated effect of temperatures in excess of 300° C. on the 0.2% proof stress.
  • FIG. 9 is a block diagram showing components of a system comprising upper and lower tool assemblies with matched surfaces and a compliant metal alloy sheet disposed therebetween for use in consolidating composite preforms.
  • the following detailed disclosure describes a method and an apparatus for consolidating and molding/forming a composite preform having an uneven thickness and/or density distribution.
  • a compliant layer is placed between the composite preform and one heated consolidation tool.
  • the compliant layer is designed to distribute the molding pressure more evenly over the entire area of the uneven preform during the consolidation process.
  • FIGS. 1 and 2 One known apparatus for matched tool consolidation of composite preforms is partly depicted in FIGS. 1 and 2 .
  • FIG. 1 shows the apparatus in a pre-consolidation stage
  • FIG. 2 shows the apparatus while consolidation is under way.
  • the apparatus comprises a lower die frame 2 , a lower tooling die 4 supported by the lower die frame 2 and having a first contoured die surface 6 , an upper die frame 8 , and an upper tooling die 10 supported by the upper die frame 8 and having a second contoured die surface 12 which is complementary to the first contoured die surface 6 .
  • the contoured die surfaces 6 and 12 may define a complex shape different than what is depicted in FIGS. 1 and 2 .
  • the novel means disclosed herein also have application when the die surfaces are planar.
  • the die frames 2 and 8 may be coupled to hydraulic actuators (not shown in FIGS. 1 and 2 ), which move the dies toward and away from each other.
  • one or more induction coils may extend through each of the tooling dies 4 and 10 to form an induction heater for raising the temperature of the resin in a composite preform to at least its consolidation temperature.
  • a thermal control system (not shown) may be connected to the induction coils.
  • the apparatus further comprises a lower susceptor 18 and an upper susceptor 20 made of electrically and thermally conductive material.
  • the susceptors and the induction coils are positioned so that the susceptors can be heated by electromagnetic induction.
  • the lower susceptor 18 may generally conform to the first contoured die surface 6 and the upper susceptor 20 may generally conform to the second contoured die surface 12 .
  • it is preferred that the temperature at which a composite preform is consolidated should not exceed a certain temperature.
  • susceptors 18 and 20 are preferably so-called “smart susceptors”.
  • a smart susceptor is constructed of a material, or materials, that generate heat efficiently until reaching a threshold (i.e., Curie) temperature.
  • a threshold i.e., Curie
  • the magnetic permeability of those portions falls to unity (i.e., the susceptor becomes paramagnetic) at the Curie temperature.
  • This drop in magnetic permeability has two effects: it limits the generation of heat by those portions at the Curie temperature, and it shifts the magnetic flux to the lower temperature portions, causing those portions below the Curie temperature to more quickly heat up to the Curie temperature. Accordingly, thermal uniformity of the heated preform during the forming process can be achieved irrespective of the input power fed to the induction coils by judiciously selecting the material for the susceptor.
  • each susceptor is a layer or sheet of magnetically permeable material.
  • Preferred magnetically permeable materials for constructing the susceptors include ferromagnetic materials that have an approximately 10-fold decrease in magnetic permeability when heated to a temperature higher than the Curie temperature. Such a large drop in permeability at the critical temperature promotes temperature control of the susceptor and, as a result, temperature control of the part being manufactured.
  • Ferromagnetic materials include iron, cobalt, nickel, gadolinium and dysprosium, and alloys thereof.
  • the consolidation/molding apparatus shown in FIGS. 1 and 2 further comprises a cooling system 14 comprising respective sets of cooling conduits 16 distributed in the tooling dies 4 and 10 .
  • Each set of coolant conduits 16 is coupled via respective manifolds to a source of cooling medium, which may liquid, gas or a gas/liquid mixture such as mist or aerosol.
  • the composite preform 22 is initially positioned between the upper and lower tooling dies of the stacked tooling apparatus, as shown in FIG. 1 . Then the tooling dies 4 and 10 are moved toward each other, as shown in FIG. 2 , as the induction coils heat the susceptors 18 and 20 . Therefore, as the tooling dies close toward each other, the susceptors rapidly heat the composite preform 22 . During this process, the composite preform will be molded by the opposing contoured (or planar) surfaces of the susceptors 18 and 20 .
  • the cooling system 14 will be operated to apply a cooling medium to the tooling dies 4 and 10 , thereby also cooling the susceptors 18 and 20 and the composite preform 22 therebetween.
  • the composite preform 22 remains sandwiched between the susceptors for a predetermined period of time until complete cooling of the composite preform has occurred. This allows the molded and consolidated composite preform 22 to retain the structural shape which is defined by the contoured surfaces of the susceptors 18 and 20 .
  • the tooling dies are then opened and the composite preform can be removed.
  • the formed and cooled composite preform is removed from the stacked tooling apparatus without loss of dimensional accuracy when it is cooled at an appropriate property-enhancing rate.
  • FIG. 3 is an end view of a portion of a lower tooling die 4 in accordance with one embodiment.
  • the upper tooling die may have a similar construction.
  • Each tooling die comprises a multiplicity of cavities 32 , which may be mutually parallel.
  • FIG. 3 shows only two such cavities 32 , the upper portion of each cavity 32 having a portion of a respective turn of an induction coil 34 which passes through the uppermost portion of the cavity.
  • FIG. 4 The sectional view shown in FIG. 4 is taken along line 4 - 4 seen in FIG. 3 and passes through a cavity 32 , but not through the portion of inductive coil 34 therein.
  • One or more coils can be used. As the parts requiring fabrication get bigger, it may be necessary to break the coil into multiple coils connected in parallel in order to limit the voltage required by each coil. Without the smart susceptors, control of the current (and resulting temperature) to each parallel coil could become problematic.
  • FIGS. 3 and 4 show a portion of a lower tooling die for which the corresponding portion of the attached susceptor is horizontal rather than angled.
  • the lower tooling die may comprise a lamination of alternating metal (e.g., stainless steel) plates 28 and dielectric spacers 30 which are trimmed to appropriate dimensions to form a plurality of parallel longitudinal cavities 32 in which the turns of one or more induction coils 34 reside.
  • Each metal plate 28 may have a thickness in the range of about 0.0625 to about 0.5 inch.
  • Air gaps 36 may be provided between the upper portions of metal plates 28 to facilitate cooling of the susceptors.
  • the stacked metal plates 28 may be attached to each other using clamps (not shown), fasteners (not shown) and/or other suitable means known to persons skilled in the art.
  • the stacked metal plates 28 may be selected based on their electrical and thermal properties and may be transparent to the electromagnetic field produced by the induction coils.
  • the smart susceptor 18 is attached directly to the metal plates 28 of the lower tooling die.
  • the smart susceptor 20 seen in FIG. 1 is likewise attached directly to the metal plates of the upper tooling die.
  • the metal plates 28 are made of austenitic (non-magnetic) stainless steel and each plate is 0.185 inch thick, which is suitable when the induction heater is operated at a frequency of 1 to 3 kHz and with smart susceptors having thicknesses of 0.125 inch. These lamination plates can be thicker than 0.185 inch for lower induction heater frequencies and would need to be thinner when using higher frequencies.
  • These laminations can (and should) have a space 36 between them to allow the quenching fluid (gas or liquid) to have direct impingement against the surface of the heated susceptor 18 .
  • This spacing is dictated by the thickness and strength of the smart susceptor surface shell and the consolidation pressures used.
  • the susceptors do not require an electrical connection to one another.
  • the metal plates 28 are interleaved with dielectric spacers 30 except near the susceptor and in places that are needed to allow the quenching medium to flow to the susceptor. The same considerations apply to the upper tooling die and the susceptor attached thereto.
  • each induction coil 34 is fabricated from copper tubing which is lightly drawn.
  • a lightly drawn condition of the tubing enables precision bending by numerically controlled bending machines.
  • Numerically controlled bending of the tubes allows accurate placement of the tubing relative to the changing contours of the susceptors, thereby improving the degree to which the each susceptor is uniformly inductively coupled to the induction heater across the length and width of the susceptor.
  • the compliant layer disclosed hereinafter can be employed also in cases wherein the susceptors are planar rather than concave/convex.
  • the coils 34 also remove thermal energy by serving as a conduit for a coolant fluid, such as water.
  • the coils After being bent and installed, the coils include straight tubing sections connected by flexible tubing sections.
  • the flexible tubing sections connect the straight tubing sections and also allow the dies to be separated.
  • the accurate placement of the tubing of the induction coils 34 promotes uniformity in the amount of heat generated by the magnetic flux field and the amount of heat removed by flow of the coolant fluid.
  • the induction coils 34 can be connected to a temperature control system that includes a power supply, a controlling element, a sensor and a fluid coolant supply preferably containing water (not shown).
  • the power supply supplies an alternating current to the induction coils 34 which causes the coils to generate the electromagnetic flux field.
  • the fluid coolant supply supplies water to the induction coils 34 for circulation through the coils and the removal of thermal energy from the dies.
  • the sensor is capable of measuring the power supplied by the power supply. Alternatively, or in addition to measuring the power supply, the sensor may include a voltmeter that can measure the voltage drop across the induction coils 34 .
  • the controlling element receives the sensor output and uses the measurements in a feedback loop to adjust the power being supplied by the power supply.
  • the controlling element can include hardware, software, firmware, or a combination thereof that is capable of using feedback to adjust the voltage output by the power supply.
  • the system described with reference to FIGS. 1-4 can be enhanced to facilitate the processing of composite preforms having uneven thickness and/or density across the extent of the preform by adding a compliant layer between the composite preform and one susceptor.
  • a compliant layer between the composite preform and one susceptor.
  • FIG. 5 shows the placement of such a matte product 40 (in an unconsolidated state) between a pair of opposing susceptors 18 and 20 in their retracted positions.
  • the matte product 40 can have a matted and tangled fiber architecture and undesirable unevenness and thickness/density variations.
  • the graphite fibers are tangled, they do not facilitate the flow of the thermoplastic material. As seen in FIG.
  • the consolidation apparatus further comprises a compliant layer that is situated between the composite preform and one of the matched molding tools for the purpose of providing a more even pressure over the entire area of the preform during the consolidation process.
  • the compliant layer should have an offset tensile yield point (0.2% of the strain) in a range of 25-300 psi at the temperature of consolidation of the preform at strain rates of about 1% to 10% strain per minute.
  • a sheet 44 of magnesium base alloy approximately 0.125 inch thick is used to act as the compliant layer or shim to compensate for uneven thickness or density over the area of a matte product 40 comprising recycled graphite fibers and virgin thermoplastic fibers.
  • the matte product 40 and the magnesium alloy sheet 44 are shown sandwiched between a pair of susceptors 18 and 20 in their extended position, i.e., the molding apparatus is closed.
  • a magnesium base alloy is selected which becomes very soft at temperatures useful for assisting the consolidation and molding of thermoplastic composites (i.e., 600-750° F.) and does not melt until above 1000° F.
  • the magnesium alloy sheet 44 softens and forms into the areas of relatively lower pressure.
  • the magnesium alloy sheet 44 can be reused due to the soft nature of the material.
  • a suitable magnesium alloy sheet material is Elektron AZ31B Sheet, which is commercially available from Magnesium Elektron UK in Manchester, England.
  • AZ31B is a wrought magnesium base alloy, is non-magnetic, has high electrical and thermal conductivity, and has a melting range of 1050-1170° F. Superplastic forming of AZ31B can occur during the preform consolidation process.
  • the chemical composition of AZ31B magnesium base alloy is: 2.5-3.5% aluminum; 0.7-1.3% zinc; 0.20-1.0% manganese; balance magnesium.
  • FIG. 8 is a graph showing the effect of temperature on the tensile properties of this particular magnesium base alloy. The 0.2% proof stress curve has been extrapolated to the right of the vertical axis labeled “ ELONGATION ” to show the anticipated effect of temperatures in excess of 300° C. on the 0.2% proof stress.
  • magnesium base alloys can be used instead of AZ31B provided that the alloy has an offset tensile yield point (0.2% of the strain) in a range of 25-300 psi at the temperature of consolidation of the preform at strain rates of about 1% to 10% strain per minute.
  • metal alloys having a base element different than magnesium, such as aluminum, can be used provided that they have the aforementioned tensile yield property.
  • FIG. 9 A system incorporating a compliant layer 44 the type described above is shown in FIG. 9 .
  • the compliant layer 44 is attached to the upper tool die 10 by means of clamps, fasteners or other known means (not shown in FIG. 9 ), with an upper susceptor 20 disposed between the compliant layer 44 and the upper tool die 10 .
  • the compliant layer could be attached to the lower tool die 4 with the lower susceptor 18 disposed therebetween.
  • the upper and lower tool dies are moved toward each other by hydraulic actuators 46 , which tool closing motion is indicated by arrows in FIG. 9 .
  • Electrical power is supplied to the induction coils (not shown) by a power supply 48 in the manner previously described.
  • the hydraulic actuators 46 move the tool dies apart to allow removal of the consolidated product from the mold.
  • the compliant layer can be reused.
  • a compliant layer of the type described above also has application in the consolidation and forming/molding of composite preforms other than the matte product described herein.
  • the compliant layer can be used in the consolidation of composite preforms that comprise reinforcing fibers embedded in a matrix made of either thermoplastic or thermosetting plastic material.
  • a compliant layer can be used with heated consolidation tools that lack susceptors.
  • the compliant layer can be placed between one of those heated matched surfaces and the composite preform.
US13/625,598 2012-09-24 2012-09-24 Compliant Layer for Matched Tool Molding of Uneven Composite Preforms Abandoned US20140083155A1 (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
US13/625,598 US20140083155A1 (en) 2012-09-24 2012-09-24 Compliant Layer for Matched Tool Molding of Uneven Composite Preforms
PCT/US2013/051873 WO2014046781A1 (en) 2012-09-24 2013-07-24 Compliant layer for matched tool molding of uneven composite preforms
CA2885632A CA2885632A1 (en) 2012-09-24 2013-07-24 Compliant layer for matched tool molding of uneven composite preforms
EP13745756.0A EP2909012B1 (en) 2012-09-24 2013-07-24 Compliant layer for matched tool molding of uneven composite preforms
ES13745756.0T ES2670837T3 (es) 2012-09-24 2013-07-24 Capa flexible para el moldeo con herramientas combinadas de preformas irregulares de material compuesto
JP2015533055A JP2015533695A (ja) 2012-09-24 2013-07-24 不均一な複合プリフォームの整合されたツール成形用コンプライアント層
KR1020157007638A KR20150081423A (ko) 2012-09-24 2013-07-24 불균일 복합재 예비 성형체의 매칭된 툴 몰딩을 위한 순응층

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US13/625,598 US20140083155A1 (en) 2012-09-24 2012-09-24 Compliant Layer for Matched Tool Molding of Uneven Composite Preforms

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EP (1) EP2909012B1 (ko)
JP (1) JP2015533695A (ko)
KR (1) KR20150081423A (ko)
CA (1) CA2885632A1 (ko)
ES (1) ES2670837T3 (ko)
WO (1) WO2014046781A1 (ko)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140069162A1 (en) * 2011-05-23 2014-03-13 Nippon Steel & Sumitomo Metal Corporation Hot press molding method and hot press molding die
KR20150143892A (ko) * 2014-05-21 2015-12-23 필립모리스 프로덕츠 에스.에이. 에어로졸 형성 기재 및 에어로졸 전달 시스템
CN111941806A (zh) * 2019-05-17 2020-11-17 波音公司 使用镁叶片制造复合结构的方法与系统
US20210346932A1 (en) * 2018-10-19 2021-11-11 Arizona Board of Regents on Behalf of the Univerity of Arizona Method and system for using induction heating to shape objects

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9993946B2 (en) * 2015-08-05 2018-06-12 The Boeing Company Method and apparatus for forming tooling and associated materials therefrom
US10814526B2 (en) * 2017-09-22 2020-10-27 The Boeing Company Induction forming and curing of thermoset composite charges

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4657717A (en) * 1984-03-16 1987-04-14 Alcan International Limited Forming fibre-plastics composites
US20070160822A1 (en) * 2005-12-21 2007-07-12 Bristow Paul A Process for improving cycle time in making molded thermoplastic composite sheets

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5009687A (en) * 1989-10-02 1991-04-23 United Technologies Corporation Method of molding a composite article using softened glass as a pressure transmitting medium
US5380480A (en) * 1993-08-04 1995-01-10 E. I. Du Pont De Nemours And Company Process of making a consolidated part
US5520532A (en) * 1994-08-01 1996-05-28 United Technologies Corporation Molding assembly for forming airfoil structures

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4657717A (en) * 1984-03-16 1987-04-14 Alcan International Limited Forming fibre-plastics composites
US20070160822A1 (en) * 2005-12-21 2007-07-12 Bristow Paul A Process for improving cycle time in making molded thermoplastic composite sheets

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140069162A1 (en) * 2011-05-23 2014-03-13 Nippon Steel & Sumitomo Metal Corporation Hot press molding method and hot press molding die
US9433989B2 (en) * 2011-05-23 2016-09-06 Nippon Steel & Sumitomo Metal Corporation Hot press molding method and hot press molding die
KR20150143892A (ko) * 2014-05-21 2015-12-23 필립모리스 프로덕츠 에스.에이. 에어로졸 형성 기재 및 에어로졸 전달 시스템
KR101656639B1 (ko) 2014-05-21 2016-09-22 필립모리스 프로덕츠 에스.에이. 에어로졸 형성 기재 및 에어로졸 전달 시스템
US20210346932A1 (en) * 2018-10-19 2021-11-11 Arizona Board of Regents on Behalf of the Univerity of Arizona Method and system for using induction heating to shape objects
CN111941806A (zh) * 2019-05-17 2020-11-17 波音公司 使用镁叶片制造复合结构的方法与系统

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ES2670837T3 (es) 2018-06-01
WO2014046781A1 (en) 2014-03-27

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