US20170320289A1 - Composite Core and Method of Making Same - Google Patents
Composite Core and Method of Making Same Download PDFInfo
- Publication number
- US20170320289A1 US20170320289A1 US15/659,427 US201715659427A US2017320289A1 US 20170320289 A1 US20170320289 A1 US 20170320289A1 US 201715659427 A US201715659427 A US 201715659427A US 2017320289 A1 US2017320289 A1 US 2017320289A1
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- United States
- Prior art keywords
- fibers
- tubes
- core
- mandrel
- present application
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- Abandoned
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- 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
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Definitions
- the present application relates in general to the field of composite structures.
- Composite structures such as composite sandwich structures, are often used because of their high strength-to-weight ratio. Such structures are frequently used in the manufacture of aircraft, such as airplanes, helicopters, and the like.
- Composite sandwich structures typically include an upper skin, a lower skin, and a core adhesively bonded between the upper skin and the lower skin.
- the upper and lower skins are made of a composite material, such as carbon, graphite, glass fibers, or the like disposed in a polymeric matrix, such as epoxy, polyetheretherketone, or the like.
- the core often comprises a honeycomb structure made from resin-infused paper.
- honeycomb core utilizes a plurality of composite webs or ribbons extending across the core, such that each of the webs defines one-half of a row of cells of the core.
- Such an approach doubles the wall thickness of adjacent cell nodes effectively increasing the weight of the core by approximately 30% without a comparable increase in load carrying capability.
- One drawback with a stacked ribbon block is the doubling of some walls where the ribbons contact each other resulting in different stiffness and strength in the ribbon direction and in the perpendicular direction to the ribbons.
- the core is also difficult to tailor in the ribbon direction.
- FIG. 1 is a perspective view of an illustrative embodiment of a composite core according to the present application
- FIG. 2 is an enlarged, cross-sectional view of a portion of the composite core of FIG. 1 taken along the line 2 - 2 of FIG. 1 ;
- FIGS. 3-8B are stylized, top, plan views of illustrative fiber configurations of a portion of the core of FIG. 1 ;
- FIGS. 8C and 9 are enlarged, cross-sectional views of certain embodiments of a portion of the core of FIG. 1 , as indicated in FIG. 2 ;
- FIG. 10 is a cross-sectional view of an illustrative embodiment, alternative to that of FIG. 2 , of a composite core according to the present application;
- FIG. 11 is a stylized, side, elevational view of a sleeve of the present application being braided, illustrating one particular embodiment of a method according to the present application for making the sleeve;
- FIG. 12 is a stylized, side, elevational view of the sleeve of FIG. 11 being placed on a mandrel, further illustrating the method of FIG. 11 of making the sleeve;
- FIG. 13 is a stylized, side, elevational view of a sleeve of the present application being braided onto a mandrel, illustrating one particular embodiment of a method, according to the present application, for making the sleeve;
- FIG. 14 is a stylized, top, plan view of an illustrative embodiment of a composite core tube of the present application being made using a filament winding process, illustrating one particular method, according to the present application, for making the composite core tube;
- FIG. 15 is a stylized, top, plan view of an illustrative embodiment of a composite core tube of the present application being made using a fiber placement process, illustrating one particular embodiment of a method, of the present application, for making the composite core tube;
- FIG. 16 is a stylized, perspective view of an alternate method, according to the present application, for making a composite core tube of the present application;
- FIG. 17 is a stylized, exploded, cross-sectional view of a plurality of mandrels and composite core tubes as assembled for processing the plurality of composite core tubes into a composite core of the present application;
- FIG. 18 is a stylized, cross-sectional view illustrating one particular embodiment of a method for processing a plurality of composite core tubes into a composite core of the present application
- FIG. 19 is a stylized, exploded, cross-sectional view of a plurality of expandable mandrels and composite core tubes as assembled for processing the plurality of composite core tubes into a composite core of the present application;
- FIG. 20 is a stylized, cross-sectional view illustrating one particular embodiment of a method for processing a plurality of composite core tubes in expandable mandrels, into a composite core of the present application;
- FIG. 21 is a stylized, side, elevational view of an illustrative embodiment of a composite sandwich structure according to the present application.
- FIG. 22 is a stylized, top, plan view of the composite sandwich structure of FIG. 21 ;
- FIG. 23 is a cross-sectional view of the composite sandwich structure of FIG. 21 , taken along the line 23 - 23 in FIG. 22 ;
- FIGS. 24 is a stylized, top, plan view of illustrative fiber configuration of a portion of the core of FIG. 1 .
- a composite core which includes a plurality of tubes, each of the plurality of tubes comprising a single tow or split tow of fibers wound in a single candy stripe pattern. Adjacent tubes of the plurality of tubes are placed adjacent to one another along sides of the adjacent tubes. A resin is introduced into the preform by a number of means, including vacuum assisted resin transfer molding, resin film infusion, or towpreg.
- Another object of the present application allows for the winding angle to be varied in order to provide for the optimum core shear and compression strength.
- the winding angle can be spaced apart to reduce the amount of material used and provide for a porous core wall with a plurality of small holes.
- a composite core which includes a plurality of tubes, each the plurality of tubes comprising a plurality of fibers disposed in a polymeric matrix. Adjacent tubes of the plurality of tubes are adhesively bonded, or infused, to one another along sides of the adjacent tubes.
- a method of making a composite core includes the steps of providing a plurality of tubes, each of the plurality of tubes including a plurality of fibers disposed in a polymeric matrix, or subsequently infusing with a polymeric matrix, and adhesively bonding adjacent tubes of the plurality of tubes along sides of the adjacent tubes.
- a composite sandwich structure in yet another aspect of the present application, includes a first skin, a core, and a first adhesive layer adhesively bonded, infused, or otherwise attached to the first skin and a first face of the core.
- the core includes a plurality of tubes, each the plurality of tubes comprising a plurality of fibers disposed in a polymeric matrix, such that adjacent tubes of the plurality of tubes are adhesively bonded, or otherwise attached to one another along sides of the adjacent tubes.
- the present application represents a composite, open-celled core and a method of making the composite core.
- the core includes a plurality of tubes (i.e., hollow, cylindrical structures) arranged in a two-dimensional array, such that adjacent tubes are adhesively bonded to one another.
- Each of the tubes comprises a plurality of reinforcing fibers disposed in a polymeric matrix.
- at least one of the tubes comprises a plurality of braided fibers disposed in the polymeric matrix.
- at least one of the tubes comprises a plurality of fibers formed generally in a helical shape disposed in a polymeric matrix.
- the tubes may take on many different cross-sectional configurations, such as triangular, square, rectangular, pentagonal, hexagonal, heptagonal, octagonal, or the like.
- the core may include a combination of tube shapes.
- the core may include a combination of octagon shaped tubes and square shaped tubes in a geometric pattern.
- FIG. 1 depicts a first illustrative embodiment of a composite, open-celled core 101 according to the present application.
- Core 101 comprises a plurality of tubes 103 arranged in a two-dimensional array. Note that only two tubes 103 are labeled in.
- Each of tubes 103 defines a passageway or “cell” 105 extending therethrough.
- Core 101 may comprise any suitable number, size, cross-sectional shape, and construction of tubes 103 , as will be discussed in greater detail below.
- FIG. 2 depicts a cross-sectional view of a portion of core 101 taken along a line 2 - 2 in FIG. 1 .
- Each of tubes 103 comprises a plurality of reinforcement fibers disposed in a polymeric matrix.
- tubes 103 may comprise fibers comprising one or more of carbon, graphite, glass, an aromatic polyamide (i.e., “aramid”) material, a variant of an aromatic polyamide material (e.g., a polyparaphenylene terephthalamide material, such as Kevlar® by E. I. du Pont de Nemours and Company of Richmond, Virginia), or the like.
- aromatic polyamide i.e., “aramid”
- a variant of an aromatic polyamide material e.g., a polyparaphenylene terephthalamide material, such as Kevlar® by E. I. du Pont de Nemours and Company of Richmond, Virginia
- the scope of the present application encompasses fibers comprising any suitable material or combination of materials.
- the polymeric matrix may comprise any suitable thermoplastic or thermosetting resin.
- resins include epoxy, polyimide, polyamide, bismaleimide, polyester, vinyl ester, phenolic, polyetheretherketone (PEEK), polyetherketone (PEK), polyphenylene sulfide (PPS), and the like.
- the fibers of tubes 103 may be oriented in one or more directions and may be woven or unwoven. Exemplary embodiments of fiber arrangements of tubes 103 are shown in FIGS. 3-8B .
- FIG. 3 depicts one illustrative embodiment of a portion of tube 103 indicated in FIG. 1 .
- tube 103 comprises a plurality of fibers 301 (only one labeled for clarity) extending in a first direction and a plurality of fibers 303 (only one labeled for clarity) extending in a second direction.
- tube 103 may alternatively only include fibers 301 arranged in a single direction, such as a uniaxial or helical fiber configurations.
- fibers 301 and 303 are depicted as fiber centerlines. Fibers 301 and 303 are oriented in a biaxial fiber configuration. Fibers 301 overlap fibers 303 . In one embodiment, fibers 301 are woven about fibers 303 . In another embodiment, fibers 301 are woven about fibers 303 and fibers 303 are woven about fibers 301 . In yet another embodiment, a first ply comprises fibers 301 and a second ply comprises fibers 303 , such that the second ply is laid-up over the first ply.
- the first ply comprises one or more of fibers 301 and fibers 303
- the second ply comprises fibers 301 and fibers 303 not present in the first ply.
- the scope of the present application contemplates two or more of fibers 301 to be parts of a single fiber or two or more of fibers 303 to be parts of a single fiber.
- FIG. 4 depicts an alternative, illustrative embodiment of the portion of tube 103 indicated in FIG. 1 .
- tube 103 exhibits a triaxial fiber configuration, comprising a plurality of fibers 401 (only one labeled for clarity) extending in a third direction in addition to fibers 301 and fibers 303 .
- fibers 301 , fibers 303 , and fibers 401 are depicted as fiber centerlines. Fibers 401 overlap fibers 301 and fibers 303 .
- fibers 301 are woven about fibers 303 and fibers 401 .
- fibers 301 and fibers 303 are woven about fibers 401 .
- fibers 301 are woven about fibers 303 and fibers 401
- fibers 303 are woven about fibers 301 and fibers 401 .
- a first ply comprises fibers 301
- a second ply comprises fibers 401
- a third ply comprises fibers 303 , such that the second ply is disposed between the first ply and the third ply.
- the scope of the present application encompasses any suitable arrangement of first, second, and third plies.
- the scope of the present application encompasses the first, second, and third plies comprising any suitable combination of fibers 301 , fibers 303 , and fibers 401 .
- the scope of the present application contemplates two or more of fibers 301 to be parts of a single fiber or two or more of fibers 303 to be parts of a single fiber.
- FIG. 5 depicts one particular illustrative configuration of the portion of tube 103 indicated in FIG. 1 .
- a plurality of fibers 501 (only one labeled for clarity) extending in a first direction and a plurality of fibers 503 (only one labeled for clarity) extending in a second direction are woven about one another such that only small gaps (e.g., a gap 505 ) exist between adjacent fibers of fibers 501 and between adjacent fibers of fibers 503 .
- the polymeric matrix substantially fills these gaps. Accordingly, fluids are inhibited from passing through the gaps.
- fibers may be spaced apart so that the polymeric matrix does not fill gaps between the fibers.
- tube 103 comprises a plurality of fibers 601 (only one labeled for clarity) extending in a first direction and a plurality of fibers 603 (only one labeled for clarity) extending in a second direction, such that gaps (e.g., a gap 605 ) larger than the gaps of FIG. 5 exist between adjacent fibers of fibers 601 and between adjacent fibers of fibers 603 . Even after tube 103 is cured, the polymeric matrix does not completely fill the gaps. Accordingly, fluids may pass through the gaps.
- certain fibers of tube 103 may differ in size or material than other fibers of tube 103 . Moreover, certain fibers may be woven about only certain other fibers or may be woven about groups of two or more fibers.
- the portion of tube 103 indicated in FIG. 1 comprises a plurality of fibers 701 (only one labeled for clarity) extending in a first direction, a plurality of fibers 703 (only one labeled for clarity) extending in the first direction, and a plurality of fibers 705 (only one labeled for clarity) extending in a second direction. Note that fibers 703 are smaller than fibers 701 or fibers 705 .
- fibers 703 comprise a different material than the material of fibers 701 and fibers 705 . It should be noted that the scope of the present application encompasses a combination of any number of fiber materials in tube 103 . It should also be noted that, in some embodiments, not all of the fibers of tube 103 are individually woven about one another.
- tubes 103 may comprise woven material, such as illustrated in FIGS. 5-8B , in the form of woven broadgoods, braided sleeves, flat braids, or braided broadgoods. Moreover, any of the embodiments of FIGS. 5-8B may exhibit a triaxial configuration.
- FIGS. 8A and 8B depict one particular illustrative configuration of the portion of tube 103 indicated in FIG. 1 .
- a plurality of fibers 801 (only one labeled for clarity) extending in a first direction and a second direction are woven with one or more removable bands 803 , about one another.
- Removable bands 803 are configured to be removed in a post cure operation, thus producing gaps 805 .
- removable bands 803 may include a soluble material such that a flushing exposure to water would dissolve and remove bands 803 , thereby producing gaps 805 (as shown in FIG. 8B ).
- Removable bands 803 may be introduced in a variety of configurations and quantities, thereby producing selected weave pattern.
- the configurations of removable bands 803 with plurality of fibers 801 can be selectively chosen to produce gaps 805 and configured for a selected flow rate between and among cells 105 of core 101 .
- FIGS. 8C and 9 depict enlarged views of a portion, indicated in FIG. 2 , of core 101 .
- adhesive bonds between tubes 103 are formed by polymeric matrices of adjacent tubes 103 .
- the polymeric matrix of one tube 103 bonds directly to the polymeric matrix of an adjacent tube 103 .
- Fibers in one tube 103 are crosslinked with fibers of adjacent tube 103 , which is further described in regard to FIG. 24 .
- adhesive bonds between tubes 103 are provided by an adhesive layer 901 disposed between tubes 103 .
- tubes 103 exhibit any desired cross-sectional height H.
- core 101 may include tubes 103 having a height H of about six millimeters or may include tubes 103 that have the height H of about 50 millimeters.
- the scope of the present application is not limited by these exemplary heights H. Rather, core 101 may comprise tubes 103 having any desired size, e.g., height H.
- core 101 may comprise different sized tubes 103 .
- core 101 may comprise one or more tubes 103 having sizes that are different from one or more other tubes 103 .
- core 101 may comprise tubes 103 having different heights H.
- Tubes 103 of the embodiment illustrated in FIGS. 1 and 2 exhibit hexagonal cross-sectional shapes.
- the scope of the present application is not so limited. Rather, a core of the present application may comprise tubes having any shape suitable for the implementation of the core.
- a core 1001 comprises a plurality of rectangular tubes 1003 . Note that only two tubes 1003 are labeled in FIG. 10 for clarity. As in the previous embodiment, adjacent tubes 1003 are adhesively bonded, or otherwise attached, to one another. Other aspects of tubes 1003 generally correspond to the aspects of tubes 103 discussed above and shown in FIGS. 1-9 .
- the core of the present application such as core 101 (shown in FIGS. 1 and 2 ) and core 1001 (shown in FIG. 10 ), may be produced using any suitable method. It should be noted that, while the particular manufacturing embodiments discussed below and illustrated in the drawings are directed to the manufacture of core 101 , the embodiments apply equally to the manufacture of core 1001 or any other core encompassed within the scope of the present application.
- tube 103 (shown in FIGS. 1 and 2 ) is made by braiding a sleeve 1101 of fibers 1103 (only one labeled for clarity) using a braiding machine 1105 .
- Sleeve 1101 may comprise, for example, a biaxial arrangement of fibers 1103 or a triaxial arrangement of fibers 1103 , as discussed above.
- Fibers 1103 may comprise dry fibers or resin-coated fibers, such as fibers coated with a thermoplastic resin.
- sleeve 1101 is place over a mandrel 1201 after sleeve has been braided.
- mandrel 1201 exhibits a size and shape corresponding to cell 105 (see FIG. 1 or 2 ).
- Mandrel 1201 and sleeve 1101 are subsequently assembled with other mandrels and sleeves, as will be discussed in greater detail below, to form core 101 (shown in FIG. 1 ).
- sleeve 1101 may be braided directly onto mandrel 1201 .
- fibers 1103 are secured to mandrel 1201 , if only frictionally, prior to braiding sleeve 1101 .
- Braiding machine 1105 may be advanced along mandrel 1201 , as indicated by an arrow 1301 , as sleeve 1101 is braided.
- Mandrel 1201 may be advanced with respect to braiding machine 1105 , as indicated by an arrow 1303 , instead of or in addition to braiding machine 1105 being advanced along mandrel 1201 .
- tube 103 (shown in FIGS. 1 and 2 ) is made using a filament winding process.
- a continuous, resin-impregnated fiber 1401 extending from a filament winding machine 1403 , is wound about a mandrel 1405 .
- the resin can be either a thermosetting or thermoplastic resin and becomes the polymeric matrix of tube 103 upon curing tube 103 .
- the material placement process may be conducted in a variety of processes; however, it is preferred that the mandrel 1405 moves axially while a spool of fiber 1401 rotates around the mandrel 1405 , as indicated by an arrow 1407 .
- a spool or a plurality of spools of material could rotate around the mandrel. Relative motion of the material dispensing mechanism to the mandrel is inferred.
- a helical shaped pattern is formed.
- One or more plies 1409 of fiber 1401 are wound onto mandrel 1405 to form tube 103 .
- the angle of which fiber 1401 is wound about mandrel 1405 may vary along the length of the mandrel 1405 in order to customize the strength of the core.
- the angle of the fiber 1401 may be dynamically changed during the material placement process in order to customize a compressive strength of the core.
- mandrel 1405 exhibits a size and shape corresponding to cell 105 (see FIG. 1 or 2 ). It should be further noted, however, that the present application is not limited to the particular illustrated configurations of filament winding machine 1403 or mandrel 1405 .
- Mandrel 1405 and the one or more plies 1409 that have been filament wound onto mandrel 1405 are subsequently assembled with other mandrels and plies, as will be discussed in greater detail below, to form core 101 (shown in FIG. 1 ).
- the material may have a tendency to un-wind.
- a band of material potentially adhesive or fiberous, may be used to keep fiber 1401 from unraveling upon cutting of the plies 1409 and the mandrel 1405 .
- An adhesive material with unidirectional fibers could be used to band the fiber 1401 on mandrel 1405 and remain compatible with the base material.
- tube 103 (shown in FIGS. 1 and 2 ) is made using a fiber placement process.
- a continuous, resin-impregnated tow 1501 (only one labeled for clarity) of approximately 1000 fibers is applied to a mandrel 1503 by a fiber placement machine 1505 .
- tow 1501 may also be portions of a full tow; for example, tow 1501 may be a half tow of 500 fibers.
- a tape of fibers, cut to a prescribed width may be used.
- a pre-cut tape of fibers may be referred to as a “slit-tape.”
- a slit-tape allows the user to more closely control the width dimension, as compared to a tow of fibers.
- Exemplary prescribed widths of slit-tape include 1 ⁇ 8′′ and 1 ⁇ 4′′, to name a few.
- the resin can be either a thermosetting or thermoplastic resin and becomes the polymeric matrix of tube 103 upon curing tube 103 .
- mandrel 1503 moves axially while tow 1501 rotates around the mandrel 1503 , as indicated by an arrow 1507 .
- tow 1501 is applied to mandrel 1503 by fiber placement machine 1505 , a helical shaped pattern is formed.
- One or more plies 1509 of tow 1501 are wound onto mandrel 1503 to form tube 103 . It should be appreciated that more than one tow 1501 of different materials may be used. Note that, in the illustrated embodiment, mandrel 1503 exhibits a size and shape corresponding to cell 105 (see FIG. 1 or 2 ). It should be further noted, however, that the present application is not limited to the particular illustrated configurations of fiber placement machine 1505 or mandrel 1503 .
- Mandrel 1503 and the one or more plies 1509 that have been fiber placed onto mandrel 1503 are subsequently assembled with other mandrels and plies, as will be discussed in greater detail below, to form core 101 (shown in FIG. 1 ).
- adjacent tubes 103 are located so that fibers in a first tube 103 crosslink with fibers in an adjacent tube 103 where adjacent tubes 103 contact each other, as shown in FIG. 8C .
- fibers 2401 are represented as dashed lines in order to clarify that fibers 2401 are from a tube 103 adjacent to another fibers 2403 of another tube 103 , as shown in FIG. 1 .
- fibers 2401 and 2403 may be actual individual fibers, or centerlines for a plurality of fibers, such as fibers in tow 1501 . In the example shown in FIG.
- tubes 103 are created by winding fibers about a mandrel at an angle (such as mandrels 1405 and 1503 ) as shown in FIGS. 14 and 15 .
- Fibers 2401 and 2403 are each wound about a different mandrel, but in a similar orientation. However, when mandrels are placed together in a mold, as shown in FIG. 18 , fibers 2401 and 2403 are oriented to each other in a crosslinking pattern. For example, when fibers 2401 and 2403 are each wound about a mandrel at a same direction and a same 45 degree angle, then fibers 2401 and 2403 , of adjacent tubes 103 , actually have a 90 degree crosslinking orientation to each other.
- crosslinked fibers 2401 and 2403 provide strength to core 101 .
- fibers 2401 and 2403 of adjacent tubes 103 can be wound about a mandrel in a variety of orientations; for example, fibers 2401 and 2403 may be wound about a mandrel at 30 degree orientations such that fibers 2401 and 2403 are crosslinked at 120 degree orientations to each other.
- fibers 2401 and 2403 may be braided, instead of being wound, onto mandrels in a variety of patterns; nevertheless, fibers 2401 and 2403 of adjacent tubes 103 become further crosslinked during processing.
- An exemplary method of processing multiple adjacent tubes 103 to form core 101 is described in relation to FIGS. 17-20 .
- tube 103 may be made using manual, hand-layup methods.
- one or more plies 1601 having desired fiber orientations are applied onto a mandrel 1603 to form tube 103 .
- the one or more plies 1601 may comprise woven dry fibers, unwoven dry fibers, resin-impregnated woven fibers, or resin-impregnated unwoven fibers.
- mandrel 1603 exhibits a size and shape corresponding to cell 105 (see FIG. 1 or 2 ).
- the present application is not limited to the particular illustrated configurations of the one or more plies 1601 or mandrel 1603 .
- Mandrel 1603 and the one or more plies 1601 that have been applied onto mandrel 1603 are subsequently assembled with other mandrels and plies, as will be discussed in greater detail below, to form core 101 (shown in FIG. 1 ).
- a plurality of mandrels 1701 (corresponding to mandrels 1201 , 1405 , 1503 , 1603 , or the like) and tubes 103 are assembled together to form the basis for core 101 (shown in FIG. 1 ).
- the plurality of mandrels 1701 and tubes 103 may include any suitable number of mandrels 1701 and tubes 103 in any suitable configuration to form core 101 .
- the plurality of mandrels 1701 and tubes 103 are assembled together in a mold 1801 .
- mold 1801 is not limited to the configuration depicted in FIG. 18 but may take on any suitable configuration.
- An inner surface 1803 of mold 1801 has the form of an exterior surface 107 (see FIG. 1 ) of core 101 .
- tubes 103 comprise a thermosetting polymeric matrix that is cured prior to assembling mandrels 1701 and tubes 103 into mold 1801 .
- adhesive layer 901 (shown in FIG. 9 ) is applied between adjacent tubes 103 prior to assembling mandrels 1701 and tubes 103 into mold 1801 .
- tubes 103 comprise a thermoplastic polymeric matrix or comprise a thermosetting polymeric matrix that is not cured prior to assembling mandrels 1701 and tubes 103 into mold 1801 .
- adhesive layer 901 may be applied between adjacent tubes 103 prior to assembling mandrels 1701 and tubes 103 into mold 1801 , but is not required.
- tubes 103 If fibers pre-impregnated with polymeric resin are used in tubes 103 , heat and, in some embodiments, pressure is applied to tubes 103 after mandrels 1701 and tubes 103 have been assembled into mold 1801 . If tubes 103 are not cured prior to assembly into mold 1801 , the applied heat cures tubes 103 . If adhesive layers 901 are used to adhesively bond adjacent tubes 103 , the applied heat melts and cures adhesive layers 901 .
- a thermoplastic or thermosetting polymeric resin is introduced about the dry fibers via one or more ports 1805 , 1807 .
- the polymeric resin becomes the polymeric matrix of tubes 103 .
- Processes such as resin transfer molding, vacuum-assisted resin transfer molding, or the like can be used to accomplish the introduction of the polymeric resin about the dry fibers. Heat and, in some embodiments, pressure is applied to tubes 103 to cure the polymeric resin.
- mandrels 1701 are removed from tubes 103 .
- mandrels 1701 are merely withdrawn from tubes 103 .
- mandrels 1701 are dissolved, for example, by heat or a solvent.
- mandrels 1701 are water soluble and, thus, water is used to dissolve mandrels 1701 .
- the mandrel may remain the core to aid in stabilizing the core during machining of the core.
- the mandrel may also remain inside the core after machining and during the processing and curing of the core to the skins in order to stabilize the core during the processing and curing. Next, the mandrel could be dissolved with water, or removed through a similar means. It should be appreciated that the mandrels can also be comprised of several layers, including an outside soluble material that remains with the core, and an inside metal material that is removed after the core is processed.
- FIGS. 19 and 20 represent another illustrative embodiment a mandrel 1901 used to create core 101 .
- An expandable mandrel 1901 may be used such that tubes 103 are formed on expandable mandrels 1901 for formation of core 101 .
- Expandable mandrel 1901 is preferably constructed of a material that expands in volume when subjected to heat, or any other catalyst that would tripper volumetric expansion. Expandable mandrels 1901 , with tubes 103 , are then stacked and arranged in a selected pattern while in their pre-expanded state, as shown in FIG. 19 .
- Expandable mandrels 1901 are preferably confined in a mold 1801 such that volumetric expansion of expandable mandrels 1901 forces tubes 103 to formed to a specified shape and pattern.
- the pattern shown in FIGS. 19 and 20 is merely exemplary of a variety of shapes and patterns to which expandable mandrels 1901 can be arranged.
- mandrels 1901 can be stacked directly adjacent, above, and below so as to form tubes 103 into a square shape.
- One exemplary advantage of expandable mandrels 1901 is that a variety of core 101 shapes can be manufactured from a single sized mandrel. In addition, it is simpler to wind fibers onto a round mandrel versus a multi-faceted mandrel.
- FIGS. 21 and 22 illustrate a side, elevational view and a top, plan view, respectively, of a composite sandwich structure 2101 according to the present application.
- FIG. 23 which is a cross-sectional view of a portion of composite sandwich structure 2101
- composite sandwich structure 2101 comprises a core 2301 disposed between an upper skin 2303 and a lower skin 2305 .
- Upper skin 2303 is adhesively bonded to an upper face 2307 of core 2301 by a first adhesive layer 2309 .
- Lower skin 2305 is adhesively bonded to a lower face 2311 by a second adhesive layer 2313 . It should be noted that, in various embodiments, one of upper skin 2303 and lower skin 2305 may be omitted.
- adhesive layers 2309 , 2313 extend substantially only between core 2301 and skins 2303 , 2305 , respectively. In other words, adhesive layers 2309 , 2313 are omitted over open cells 2315 of core 2301 . This configuration is accomplished, in one embodiment, by concentrating adhesive on the edge surfaces of the core through a reticulation process.
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Abstract
Description
- The present application relates in general to the field of composite structures.
- Composite structures, such as composite sandwich structures, are often used because of their high strength-to-weight ratio. Such structures are frequently used in the manufacture of aircraft, such as airplanes, helicopters, and the like. Composite sandwich structures typically include an upper skin, a lower skin, and a core adhesively bonded between the upper skin and the lower skin. The upper and lower skins are made of a composite material, such as carbon, graphite, glass fibers, or the like disposed in a polymeric matrix, such as epoxy, polyetheretherketone, or the like. The core often comprises a honeycomb structure made from resin-infused paper.
- The use of conventional sandwich structures, however, is limited in some applications because the core of the sandwich structure fails to provide substantive mechanical strength in some implementations. In other words, the strength of such a conventional sandwich structure is limited by the strength of the core.
- Efforts have been made to manufacture core that provides better specific mechanical strength at a reduced cost. One particular honeycomb core utilizes a plurality of composite webs or ribbons extending across the core, such that each of the webs defines one-half of a row of cells of the core. Such an approach doubles the wall thickness of adjacent cell nodes effectively increasing the weight of the core by approximately 30% without a comparable increase in load carrying capability. One drawback with a stacked ribbon block is the doubling of some walls where the ribbons contact each other resulting in different stiffness and strength in the ribbon direction and in the perpendicular direction to the ribbons. The core is also difficult to tailor in the ribbon direction. In addition, if a load concentration exists in the core, it is difficult to manufacture a core block that has thicker cell walls only in the region local to the concentration. Furthermore, there is a potential weakness in the joint where the ribbons intersect, especially in core block comprising a plurality of procured ribbons bonded in a secondary operation. If an unbalanced or unsymmetrical layup is used in each ribbon, the ribbon will distort or twist after cure, thereby making a stacking procedure of a block of ribbons more difficult and also trapping residual stresses.
- There are many cores well known in the art for use in composite sandwich structures; however, considerable room for improvement remains.
- The novel features believed characteristic of the embodiments of the present application are set forth in the appended claims. However, the embodiments themselves, as well as a preferred mode of use, and further objectives and advantages thereof, will best be understood by reference to the following detailed description when read in conjunction with the accompanying drawings, wherein:
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FIG. 1 is a perspective view of an illustrative embodiment of a composite core according to the present application; -
FIG. 2 is an enlarged, cross-sectional view of a portion of the composite core ofFIG. 1 taken along the line 2-2 ofFIG. 1 ; -
FIGS. 3-8B are stylized, top, plan views of illustrative fiber configurations of a portion of the core ofFIG. 1 ; -
FIGS. 8C and 9 are enlarged, cross-sectional views of certain embodiments of a portion of the core ofFIG. 1 , as indicated inFIG. 2 ; -
FIG. 10 is a cross-sectional view of an illustrative embodiment, alternative to that ofFIG. 2 , of a composite core according to the present application; -
FIG. 11 is a stylized, side, elevational view of a sleeve of the present application being braided, illustrating one particular embodiment of a method according to the present application for making the sleeve; -
FIG. 12 is a stylized, side, elevational view of the sleeve ofFIG. 11 being placed on a mandrel, further illustrating the method ofFIG. 11 of making the sleeve; -
FIG. 13 is a stylized, side, elevational view of a sleeve of the present application being braided onto a mandrel, illustrating one particular embodiment of a method, according to the present application, for making the sleeve; -
FIG. 14 is a stylized, top, plan view of an illustrative embodiment of a composite core tube of the present application being made using a filament winding process, illustrating one particular method, according to the present application, for making the composite core tube; -
FIG. 15 is a stylized, top, plan view of an illustrative embodiment of a composite core tube of the present application being made using a fiber placement process, illustrating one particular embodiment of a method, of the present application, for making the composite core tube; -
FIG. 16 is a stylized, perspective view of an alternate method, according to the present application, for making a composite core tube of the present application; -
FIG. 17 is a stylized, exploded, cross-sectional view of a plurality of mandrels and composite core tubes as assembled for processing the plurality of composite core tubes into a composite core of the present application; -
FIG. 18 is a stylized, cross-sectional view illustrating one particular embodiment of a method for processing a plurality of composite core tubes into a composite core of the present application; -
FIG. 19 is a stylized, exploded, cross-sectional view of a plurality of expandable mandrels and composite core tubes as assembled for processing the plurality of composite core tubes into a composite core of the present application; -
FIG. 20 is a stylized, cross-sectional view illustrating one particular embodiment of a method for processing a plurality of composite core tubes in expandable mandrels, into a composite core of the present application; -
FIG. 21 is a stylized, side, elevational view of an illustrative embodiment of a composite sandwich structure according to the present application; -
FIG. 22 is a stylized, top, plan view of the composite sandwich structure ofFIG. 21 ; -
FIG. 23 is a cross-sectional view of the composite sandwich structure ofFIG. 21 , taken along the line 23-23 inFIG. 22 ; and -
FIGS. 24 is a stylized, top, plan view of illustrative fiber configuration of a portion of the core ofFIG. 1 . - While the system and method of the present application are susceptible to various modifications and alternative forms, specific embodiments thereof have been shown by way of example in the drawings and are herein described in detail. It should be understood, however, that the description herein of specific embodiments is not intended to limit the invention to the particular embodiment disclosed, but on the contrary, the intention is to cover all modifications, equivalents, and alternatives falling within the spirit and scope of the process of the present application as defined by the appended claims.
- Illustrative embodiments of the application are described below. In the interest of clarity, not all features of an actual implementation are described in this specification. It will of course be appreciated that in the development of any such actual embodiment, numerous implementation-specific decisions must be made to achieve the developer's specific goals, such as compliance with system-related and business-related constraints, which will vary from one implementation to another. Moreover, it will be appreciated that such a development effort might be complex and time-consuming but would nevertheless be a routine undertaking for those of ordinary skill in the art having the benefit of this disclosure.
- In the specification, reference may be made to the spatial relationships between various components and to the spatial orientation of various aspects of components as the devices are depicted in the attached drawings. However, as will be recognized by those skilled in the art after a complete reading of the present application, the devices, members, apparatuses, etc. described herein may be positioned in any desired orientation. Thus, the use of terms such as “above,” “below,” “upper,” “lower,” or other like terms to describe a spatial relationship between various components or to describe the spatial orientation of aspects of such components should be understood to describe a relative relationship between the components or a spatial orientation of aspects of such components, respectively, as the device described herein may be oriented in any desired direction.
- There is a need for an improved core for use in composite sandwich structures.
- Therefore, it is an object of the present application to provide an improved core for use in composite sandwich structures.
- This and other objects are achieved by a composite core, which includes a plurality of tubes, each of the plurality of tubes comprising a single tow or split tow of fibers wound in a single candy stripe pattern. Adjacent tubes of the plurality of tubes are placed adjacent to one another along sides of the adjacent tubes. A resin is introduced into the preform by a number of means, including vacuum assisted resin transfer molding, resin film infusion, or towpreg.
- Another object of the present application allows for the winding angle to be varied in order to provide for the optimum core shear and compression strength. The winding angle can be spaced apart to reduce the amount of material used and provide for a porous core wall with a plurality of small holes.
- This and other objects are achieved by a composite core, which includes a plurality of tubes, each the plurality of tubes comprising a plurality of fibers disposed in a polymeric matrix. Adjacent tubes of the plurality of tubes are adhesively bonded, or infused, to one another along sides of the adjacent tubes.
- In another aspect of the present application, a method of making a composite core is provided. The method includes the steps of providing a plurality of tubes, each of the plurality of tubes including a plurality of fibers disposed in a polymeric matrix, or subsequently infusing with a polymeric matrix, and adhesively bonding adjacent tubes of the plurality of tubes along sides of the adjacent tubes.
- In yet another aspect of the present application, a composite sandwich structure is provided. The composite sandwich structure includes a first skin, a core, and a first adhesive layer adhesively bonded, infused, or otherwise attached to the first skin and a first face of the core. The core includes a plurality of tubes, each the plurality of tubes comprising a plurality of fibers disposed in a polymeric matrix, such that adjacent tubes of the plurality of tubes are adhesively bonded, or otherwise attached to one another along sides of the adjacent tubes.
- The present application represents a composite, open-celled core and a method of making the composite core. The core includes a plurality of tubes (i.e., hollow, cylindrical structures) arranged in a two-dimensional array, such that adjacent tubes are adhesively bonded to one another. Each of the tubes comprises a plurality of reinforcing fibers disposed in a polymeric matrix. In one embodiment, at least one of the tubes comprises a plurality of braided fibers disposed in the polymeric matrix. In another embodiment, at least one of the tubes comprises a plurality of fibers formed generally in a helical shape disposed in a polymeric matrix. The tubes may take on many different cross-sectional configurations, such as triangular, square, rectangular, pentagonal, hexagonal, heptagonal, octagonal, or the like. Furthermore, the core may include a combination of tube shapes. For example, the core may include a combination of octagon shaped tubes and square shaped tubes in a geometric pattern.
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FIG. 1 depicts a first illustrative embodiment of a composite, open-celled core 101 according to the present application.Core 101 comprises a plurality oftubes 103 arranged in a two-dimensional array. Note that only twotubes 103 are labeled in. -
FIG. 1 for clarity. Each oftubes 103 defines a passageway or “cell” 105 extending therethrough.Core 101 may comprise any suitable number, size, cross-sectional shape, and construction oftubes 103, as will be discussed in greater detail below. -
FIG. 2 depicts a cross-sectional view of a portion ofcore 101 taken along a line 2-2 inFIG. 1 . Each oftubes 103 comprises a plurality of reinforcement fibers disposed in a polymeric matrix. For example,tubes 103 may comprise fibers comprising one or more of carbon, graphite, glass, an aromatic polyamide (i.e., “aramid”) material, a variant of an aromatic polyamide material (e.g., a polyparaphenylene terephthalamide material, such as Kevlar® by E. I. du Pont de Nemours and Company of Richmond, Virginia), or the like. The scope of the present application, however, encompasses fibers comprising any suitable material or combination of materials. The polymeric matrix may comprise any suitable thermoplastic or thermosetting resin. Exemplary resins include epoxy, polyimide, polyamide, bismaleimide, polyester, vinyl ester, phenolic, polyetheretherketone (PEEK), polyetherketone (PEK), polyphenylene sulfide (PPS), and the like. - The fibers of
tubes 103 may be oriented in one or more directions and may be woven or unwoven. Exemplary embodiments of fiber arrangements oftubes 103 are shown inFIGS. 3-8B .FIG. 3 depicts one illustrative embodiment of a portion oftube 103 indicated inFIG. 1 . In the illustrated embodiment,tube 103 comprises a plurality of fibers 301 (only one labeled for clarity) extending in a first direction and a plurality of fibers 303 (only one labeled for clarity) extending in a second direction. It should be appreciated thattube 103 may alternatively only includefibers 301 arranged in a single direction, such as a uniaxial or helical fiber configurations. It should be noted thatfibers Fibers Fibers 301overlap fibers 303. In one embodiment,fibers 301 are woven aboutfibers 303. In another embodiment,fibers 301 are woven aboutfibers 303 andfibers 303 are woven aboutfibers 301. In yet another embodiment, a first ply comprisesfibers 301 and a second ply comprisesfibers 303, such that the second ply is laid-up over the first ply. Alternatively, the first ply comprises one or more offibers 301 andfibers 303, while the second ply comprisesfibers 301 andfibers 303 not present in the first ply. Moreover, the scope of the present application contemplates two or more offibers 301 to be parts of a single fiber or two or more offibers 303 to be parts of a single fiber. -
FIG. 4 depicts an alternative, illustrative embodiment of the portion oftube 103 indicated inFIG. 1 . In the illustrated embodiment,tube 103 exhibits a triaxial fiber configuration, comprising a plurality of fibers 401 (only one labeled for clarity) extending in a third direction in addition tofibers 301 andfibers 303. Note thatfibers 301,fibers 303, andfibers 401 are depicted as fiber centerlines.Fibers 401overlap fibers 301 andfibers 303. In one embodiment,fibers 301 are woven aboutfibers 303 andfibers 401. In another embodiment,fibers 301 andfibers 303 are woven aboutfibers 401. In one embodiment,fibers 301 are woven aboutfibers 303 andfibers 401, whilefibers 303 are woven aboutfibers 301 andfibers 401. - Alternatively, in another embodiment, a first ply comprises
fibers 301, a second ply comprisesfibers 401, and a third ply comprisesfibers 303, such that the second ply is disposed between the first ply and the third ply. It should be noted, however, that the scope of the present application encompasses any suitable arrangement of first, second, and third plies. Moreover, the scope of the present application encompasses the first, second, and third plies comprising any suitable combination offibers 301,fibers 303, andfibers 401. Furthermore, as in the embodiment ofFIG. 3 , the scope of the present application contemplates two or more offibers 301 to be parts of a single fiber or two or more offibers 303 to be parts of a single fiber. -
FIG. 5 depicts one particular illustrative configuration of the portion oftube 103 indicated inFIG. 1 . In this embodiment, a plurality of fibers 501 (only one labeled for clarity) extending in a first direction and a plurality of fibers 503 (only one labeled for clarity) extending in a second direction are woven about one another such that only small gaps (e.g., a gap 505) exist between adjacent fibers offibers 501 and between adjacent fibers offibers 503. Oncetube 103 is cured (i.e., the polymeric matrix has either hardened or crosslinked), the polymeric matrix substantially fills these gaps. Accordingly, fluids are inhibited from passing through the gaps. - In an alternative embodiment, shown in
FIG. 6 , fibers may be spaced apart so that the polymeric matrix does not fill gaps between the fibers. In the illustrated embodiment,tube 103 comprises a plurality of fibers 601 (only one labeled for clarity) extending in a first direction and a plurality of fibers 603 (only one labeled for clarity) extending in a second direction, such that gaps (e.g., a gap 605) larger than the gaps ofFIG. 5 exist between adjacent fibers offibers 601 and between adjacent fibers offibers 603. Even aftertube 103 is cured, the polymeric matrix does not completely fill the gaps. Accordingly, fluids may pass through the gaps. - It should be noted that certain fibers of
tube 103 may differ in size or material than other fibers oftube 103. Moreover, certain fibers may be woven about only certain other fibers or may be woven about groups of two or more fibers. For example, in the embodiment ofFIG. 7 , the portion oftube 103 indicated inFIG. 1 comprises a plurality of fibers 701 (only one labeled for clarity) extending in a first direction, a plurality of fibers 703 (only one labeled for clarity) extending in the first direction, and a plurality of fibers 705 (only one labeled for clarity) extending in a second direction. Note thatfibers 703 are smaller thanfibers 701 orfibers 705. In one implementation,fibers 703 comprise a different material than the material offibers 701 andfibers 705. It should be noted that the scope of the present application encompasses a combination of any number of fiber materials intube 103. It should also be noted that, in some embodiments, not all of the fibers oftube 103 are individually woven about one another. - It should be noted that the embodiment of
FIG. 6 may also be modified to have the configuration ofFIG. 7 , in that larger gaps exist between adjacent fibers. It should also be noted that one or more oftubes 103 may comprise woven material, such as illustrated inFIGS. 5-8B , in the form of woven broadgoods, braided sleeves, flat braids, or braided broadgoods. Moreover, any of the embodiments ofFIGS. 5-8B may exhibit a triaxial configuration. -
FIGS. 8A and 8B depict one particular illustrative configuration of the portion oftube 103 indicated inFIG. 1 . In this embodiment, a plurality of fibers 801 (only one labeled for clarity) extending in a first direction and a second direction are woven with one or moreremovable bands 803, about one another.Removable bands 803 are configured to be removed in a post cure operation, thus producinggaps 805. For example,removable bands 803 may include a soluble material such that a flushing exposure to water would dissolve and removebands 803, thereby producing gaps 805 (as shown inFIG. 8B ).Removable bands 803 may be introduced in a variety of configurations and quantities, thereby producing selected weave pattern. The configurations ofremovable bands 803 with plurality offibers 801 can be selectively chosen to producegaps 805 and configured for a selected flow rate between and amongcells 105 ofcore 101. - As shown in
FIG. 2 , adjacent sides oftubes 103 are adhesively bonded, or otherwise attached, to one another toform core 101.FIGS. 8C and 9 depict enlarged views of a portion, indicated inFIG. 2 , ofcore 101. In the embodiment ofFIG. 8C , adhesive bonds betweentubes 103 are formed by polymeric matrices ofadjacent tubes 103. In other words, the polymeric matrix of onetube 103 bonds directly to the polymeric matrix of anadjacent tube 103. Fibers in onetube 103 are crosslinked with fibers ofadjacent tube 103, which is further described in regard toFIG. 24 . Alternatively, as depicted inFIG. 9 , adhesive bonds betweentubes 103 are provided by anadhesive layer 901 disposed betweentubes 103. - Returning to
FIG. 2 ,tubes 103 exhibit any desired cross-sectional height H. For example,core 101 may includetubes 103 having a height H of about six millimeters or may includetubes 103 that have the height H of about 50 millimeters. The scope of the present application, however, is not limited by these exemplary heights H. Rather,core 101 may comprisetubes 103 having any desired size, e.g., height H. Moreover,core 101 may comprise differentsized tubes 103. In other words,core 101 may comprise one ormore tubes 103 having sizes that are different from one or moreother tubes 103. For example,core 101 may comprisetubes 103 having different heights H. -
Tubes 103 of the embodiment illustrated inFIGS. 1 and 2 exhibit hexagonal cross-sectional shapes. The scope of the present application, however, is not so limited. Rather, a core of the present application may comprise tubes having any shape suitable for the implementation of the core. For example, as shown inFIG. 10 , acore 1001 comprises a plurality ofrectangular tubes 1003. Note that only twotubes 1003 are labeled inFIG. 10 for clarity. As in the previous embodiment,adjacent tubes 1003 are adhesively bonded, or otherwise attached, to one another. Other aspects oftubes 1003 generally correspond to the aspects oftubes 103 discussed above and shown inFIGS. 1-9 . - The core of the present application, such as core 101 (shown in
FIGS. 1 and 2 ) and core 1001 (shown inFIG. 10 ), may be produced using any suitable method. It should be noted that, while the particular manufacturing embodiments discussed below and illustrated in the drawings are directed to the manufacture ofcore 101, the embodiments apply equally to the manufacture ofcore 1001 or any other core encompassed within the scope of the present application. - In one embodiment, shown in
FIG. 11 , tube 103 (shown inFIGS. 1 and 2 ) is made by braiding asleeve 1101 of fibers 1103 (only one labeled for clarity) using abraiding machine 1105.Sleeve 1101 may comprise, for example, a biaxial arrangement offibers 1103 or a triaxial arrangement offibers 1103, as discussed above.Fibers 1103 may comprise dry fibers or resin-coated fibers, such as fibers coated with a thermoplastic resin. As shown inFIG. 12 ,sleeve 1101 is place over amandrel 1201 after sleeve has been braided. Note that, in the illustrated embodiment,mandrel 1201 exhibits a size and shape corresponding to cell 105 (seeFIG. 1 or 2 ).Mandrel 1201 andsleeve 1101 are subsequently assembled with other mandrels and sleeves, as will be discussed in greater detail below, to form core 101 (shown inFIG. 1 ). - It should be noted that, as shown in
FIG. 13 ,sleeve 1101 may be braided directly ontomandrel 1201. In such an embodiment,fibers 1103 are secured tomandrel 1201, if only frictionally, prior tobraiding sleeve 1101.Braiding machine 1105 may be advanced alongmandrel 1201, as indicated by anarrow 1301, assleeve 1101 is braided.Mandrel 1201 may be advanced with respect tobraiding machine 1105, as indicated by anarrow 1303, instead of or in addition tobraiding machine 1105 being advanced alongmandrel 1201. - In another embodiment, shown in
FIG. 14 , tube 103 (shown inFIGS. 1 and 2 ) is made using a filament winding process. A continuous, resin-impregnatedfiber 1401, extending from afilament winding machine 1403, is wound about amandrel 1405. The resin can be either a thermosetting or thermoplastic resin and becomes the polymeric matrix oftube 103 upon curingtube 103. The material placement process may be conducted in a variety of processes; however, it is preferred that themandrel 1405 moves axially while a spool offiber 1401 rotates around themandrel 1405, as indicated by anarrow 1407. Alternatively, a spool or a plurality of spools of material could rotate around the mandrel. Relative motion of the material dispensing mechanism to the mandrel is inferred. Asfiber 1401 is wound ontomandrel 1405 byfilament winding machine 1403, a helical shaped pattern is formed. One ormore plies 1409 offiber 1401, in desired orientations with respect tomandrel 1405, are wound ontomandrel 1405 to formtube 103. The angle of whichfiber 1401 is wound aboutmandrel 1405 may vary along the length of themandrel 1405 in order to customize the strength of the core. For example, the angle of thefiber 1401 may be dynamically changed during the material placement process in order to customize a compressive strength of the core. Note that, in the illustrated embodiment,mandrel 1405 exhibits a size and shape corresponding to cell 105 (seeFIG. 1 or 2 ). It should be further noted, however, that the present application is not limited to the particular illustrated configurations offilament winding machine 1403 ormandrel 1405.Mandrel 1405 and the one ormore plies 1409 that have been filament wound ontomandrel 1405 are subsequently assembled with other mandrels and plies, as will be discussed in greater detail below, to form core 101 (shown inFIG. 1 ). It should further be appreciated that upon cutting ofplies 1409 and themandrel 1405, the material may have a tendency to un-wind. A band of material, potentially adhesive or fiberous, may be used to keepfiber 1401 from unraveling upon cutting of theplies 1409 and themandrel 1405. An adhesive material with unidirectional fibers could be used to band thefiber 1401 onmandrel 1405 and remain compatible with the base material. - In yet another embodiment, shown in
FIG. 15 , tube 103 (shown inFIGS. 1 and 2 ) is made using a fiber placement process. A continuous, resin-impregnated tow 1501 (only one labeled for clarity) of approximately 1000 fibers is applied to amandrel 1503 by afiber placement machine 1505. It should be appreciated thattow 1501 may also be portions of a full tow; for example,tow 1501 may be a half tow of 500 fibers. In lieu of atow 1501, a tape of fibers, cut to a prescribed width, may be used. A pre-cut tape of fibers may be referred to as a “slit-tape.” A slit-tape allows the user to more closely control the width dimension, as compared to a tow of fibers. Exemplary prescribed widths of slit-tape include ⅛″ and ¼″, to name a few. The resin can be either a thermosetting or thermoplastic resin and becomes the polymeric matrix oftube 103 upon curingtube 103. During the fiber placement process,mandrel 1503 moves axially whiletow 1501 rotates around themandrel 1503, as indicated by anarrow 1507. Astow 1501 is applied tomandrel 1503 byfiber placement machine 1505, a helical shaped pattern is formed. One ormore plies 1509 oftow 1501, in desired orientations with respect tomandrel 1503, are wound ontomandrel 1503 to formtube 103. It should be appreciated that more than onetow 1501 of different materials may be used. Note that, in the illustrated embodiment,mandrel 1503 exhibits a size and shape corresponding to cell 105 (seeFIG. 1 or 2 ). It should be further noted, however, that the present application is not limited to the particular illustrated configurations offiber placement machine 1505 ormandrel 1503.Mandrel 1503 and the one ormore plies 1509 that have been fiber placed ontomandrel 1503 are subsequently assembled with other mandrels and plies, as will be discussed in greater detail below, to form core 101 (shown inFIG. 1 ). - It is important to note that
adjacent tubes 103, as best shown inFIG. 1 , are located so that fibers in afirst tube 103 crosslink with fibers in anadjacent tube 103 whereadjacent tubes 103 contact each other, as shown inFIG. 8C . Referring toFIG. 24 as an illustrative embodiment,fibers 2401 are represented as dashed lines in order to clarify thatfibers 2401 are from atube 103 adjacent to anotherfibers 2403 of anothertube 103, as shown inFIG. 1 . It should be appreciated thatfibers tow 1501. In the example shown inFIG. 24 ,tubes 103 are created by winding fibers about a mandrel at an angle (such asmandrels 1405 and 1503) as shown inFIGS. 14 and 15 .Fibers FIG. 18 ,fibers fibers fibers adjacent tubes 103, actually have a 90 degree crosslinking orientation to each other. It should be appreciated that multiple mandrels having similarly oriented wound fibers are assembled adjacently, without changing the orientation of the mandrels, so as to produce crosslinking of fibers inadjacent tubes 103. After curing,crosslinked fibers core 101. It should be appreciated thatfibers adjacent tubes 103 can be wound about a mandrel in a variety of orientations; for example,fibers fibers fibers fibers adjacent tubes 103 become further crosslinked during processing. An exemplary method of processing multipleadjacent tubes 103 to formcore 101 is described in relation toFIGS. 17-20 . - Alternatively, tube 103 (shown in
FIGS. 1 and 2 ) may be made using manual, hand-layup methods. For example, as shown inFIG. 16 , one ormore plies 1601 having desired fiber orientations are applied onto amandrel 1603 to formtube 103. The one ormore plies 1601 may comprise woven dry fibers, unwoven dry fibers, resin-impregnated woven fibers, or resin-impregnated unwoven fibers. Note that, in the illustrated embodiment,mandrel 1603 exhibits a size and shape corresponding to cell 105 (seeFIG. 1 or 2 ). It should be further noted, however, that the present application is not limited to the particular illustrated configurations of the one ormore plies 1601 ormandrel 1603.Mandrel 1603 and the one ormore plies 1601 that have been applied ontomandrel 1603 are subsequently assembled with other mandrels and plies, as will be discussed in greater detail below, to form core 101 (shown inFIG. 1 ). - As shown in
FIG. 17 , a plurality of mandrels 1701 (corresponding tomandrels tubes 103 are assembled together to form the basis for core 101 (shown inFIG. 1 ). Note that the plurality ofmandrels 1701 andtubes 103 may include any suitable number ofmandrels 1701 andtubes 103 in any suitable configuration to formcore 101. In one embodiment, shown inFIG. 18 , the plurality ofmandrels 1701 andtubes 103 are assembled together in amold 1801. Note thatmold 1801 is not limited to the configuration depicted inFIG. 18 but may take on any suitable configuration. Aninner surface 1803 ofmold 1801 has the form of an exterior surface 107 (seeFIG. 1 ) ofcore 101. - In one embodiment,
tubes 103 comprise a thermosetting polymeric matrix that is cured prior to assemblingmandrels 1701 andtubes 103 intomold 1801. In such an embodiment, adhesive layer 901 (shown inFIG. 9 ) is applied betweenadjacent tubes 103 prior to assemblingmandrels 1701 andtubes 103 intomold 1801. In another embodiment,tubes 103 comprise a thermoplastic polymeric matrix or comprise a thermosetting polymeric matrix that is not cured prior to assemblingmandrels 1701 andtubes 103 intomold 1801. In such an embodiment,adhesive layer 901 may be applied betweenadjacent tubes 103 prior to assemblingmandrels 1701 andtubes 103 intomold 1801, but is not required. - If fibers pre-impregnated with polymeric resin are used in
tubes 103, heat and, in some embodiments, pressure is applied totubes 103 aftermandrels 1701 andtubes 103 have been assembled intomold 1801. Iftubes 103 are not cured prior to assembly intomold 1801, the appliedheat cures tubes 103. Ifadhesive layers 901 are used to adhesively bondadjacent tubes 103, the applied heat melts and curesadhesive layers 901. - If dry fibers are used in
tubes 103, in one embodiment, a thermoplastic or thermosetting polymeric resin is introduced about the dry fibers via one ormore ports tubes 103. Processes such as resin transfer molding, vacuum-assisted resin transfer molding, or the like can be used to accomplish the introduction of the polymeric resin about the dry fibers. Heat and, in some embodiments, pressure is applied totubes 103 to cure the polymeric resin. - After the
adjacent tubes 103 are adhesively bonded to one another toform core 101,mandrels 1701 are removed fromtubes 103. In one embodiment,mandrels 1701 are merely withdrawn fromtubes 103. In other embodiments, however,mandrels 1701 are dissolved, for example, by heat or a solvent. In one embodiment,mandrels 1701 are water soluble and, thus, water is used to dissolvemandrels 1701. In the embodiment wherein the mandrel is dissolvable, the mandrel may remain the core to aid in stabilizing the core during machining of the core. The mandrel may also remain inside the core after machining and during the processing and curing of the core to the skins in order to stabilize the core during the processing and curing. Next, the mandrel could be dissolved with water, or removed through a similar means. It should be appreciated that the mandrels can also be comprised of several layers, including an outside soluble material that remains with the core, and an inside metal material that is removed after the core is processed. -
FIGS. 19 and 20 represent another illustrative embodiment amandrel 1901 used to createcore 101. Anexpandable mandrel 1901 may be used such thattubes 103 are formed onexpandable mandrels 1901 for formation ofcore 101.Expandable mandrel 1901 is preferably constructed of a material that expands in volume when subjected to heat, or any other catalyst that would tripper volumetric expansion.Expandable mandrels 1901, withtubes 103, are then stacked and arranged in a selected pattern while in their pre-expanded state, as shown inFIG. 19 .Expandable mandrels 1901 are preferably confined in amold 1801 such that volumetric expansion ofexpandable mandrels 1901forces tubes 103 to formed to a specified shape and pattern. The pattern shown inFIGS. 19 and 20 is merely exemplary of a variety of shapes and patterns to whichexpandable mandrels 1901 can be arranged. For example,mandrels 1901 can be stacked directly adjacent, above, and below so as to formtubes 103 into a square shape. One exemplary advantage ofexpandable mandrels 1901 is that a variety ofcore 101 shapes can be manufactured from a single sized mandrel. In addition, it is simpler to wind fibers onto a round mandrel versus a multi-faceted mandrel. - The scope of the present application encompasses a composite sandwich structure comprising a core of the present application. For example,
FIGS. 21 and 22 illustrate a side, elevational view and a top, plan view, respectively, of acomposite sandwich structure 2101 according to the present application. As shown inFIG. 23 , which is a cross-sectional view of a portion ofcomposite sandwich structure 2101,composite sandwich structure 2101 comprises acore 2301 disposed between anupper skin 2303 and alower skin 2305.Upper skin 2303 is adhesively bonded to anupper face 2307 ofcore 2301 by afirst adhesive layer 2309.Lower skin 2305 is adhesively bonded to alower face 2311 by asecond adhesive layer 2313. It should be noted that, in various embodiments, one ofupper skin 2303 andlower skin 2305 may be omitted. - In one embodiment,
adhesive layers core 2301 andskins adhesive layers open cells 2315 ofcore 2301. This configuration is accomplished, in one embodiment, by concentrating adhesive on the edge surfaces of the core through a reticulation process. - The particular embodiments disclosed above are illustrative only, as the application may be modified and practiced in different but equivalent manners apparent to those skilled in the art having the benefit of the teachings herein. Furthermore, no limitations are intended to the details of construction or design herein shown, other than as described in the claims below. It is therefore evident that the particular embodiments disclosed above may be altered or modified and all such variations are considered within the scope and spirit of the application. Accordingly, the protection sought herein is as set forth in the claims below. It is apparent that an application with significant advantages has been described and illustrated. Although the present application is shown in a limited number of forms, it is not limited to just these forms, but is amenable to various changes and modifications without departing from the spirit thereof.
Claims (6)
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Families Citing this family (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9845600B2 (en) * | 2011-07-01 | 2017-12-19 | Embry-Riddle Aeronautical University, Inc. | Highly vented truss wall honeycomb structures |
US10669021B2 (en) | 2012-09-14 | 2020-06-02 | Textron Innovations Inc. | Method of optimizing and customizing rotor blade structural properties by tailoring large cell composite core and a rotor blade incorporating the same |
US9120246B2 (en) * | 2013-03-01 | 2015-09-01 | Bell Helicopter Textron Inc. | Pressure tunable expandable mandrel for manufacturing a composite structure |
US9302869B2 (en) * | 2013-03-01 | 2016-04-05 | Bell Helicopter Textron Inc. | System and method of manufacturing composite core |
US10131108B2 (en) * | 2013-03-01 | 2018-11-20 | Bell Helicopter Textron Inc. | System and method of manufacturing composite core |
US9145277B2 (en) * | 2013-03-01 | 2015-09-29 | Bell Helicopter Textron Inc. | System and method of manufacturing composite core |
US9120255B2 (en) * | 2013-03-15 | 2015-09-01 | Bell Helicopter Textron Inc. | Composite core and method of making same |
US9211618B2 (en) | 2013-12-20 | 2015-12-15 | Bell Helicopter Textron Inc. | Method of securing composite core during a manufacturing process |
US9156239B2 (en) | 2013-12-20 | 2015-10-13 | Bell Helicopter Textron Inc. | Method of manufacturing net edge core and a method of bonding net edge core to a substructure |
US9090026B2 (en) * | 2013-12-20 | 2015-07-28 | Bell Helicopter Textron Inc. | Method of splicing composite core |
US9895840B2 (en) * | 2014-05-15 | 2018-02-20 | The Boeing Company | Thermoformed cascades for jet engine thrust reversers |
US10456994B2 (en) * | 2015-10-26 | 2019-10-29 | Samtech Corporation | Composite container |
CN105459474A (en) * | 2015-12-09 | 2016-04-06 | 上海复合材料科技有限公司 | Low-density and high-performance composite sandwich structure and preparation method thereof |
US10513324B2 (en) | 2016-02-08 | 2019-12-24 | Bell Helicopter Textron Inc. | Composite rib assembly |
US10639854B2 (en) | 2016-02-08 | 2020-05-05 | Bell Helicopter Textron Inc. | Composite wing structure and methods of manufacture |
US11142297B2 (en) | 2016-02-08 | 2021-10-12 | Bell Helicopter Textron Inc. | Heating tool |
CN106003851B (en) * | 2016-06-21 | 2017-10-27 | 赵坤 | A kind of honeycomb structure and honeycomb boards |
US10550499B2 (en) | 2017-01-19 | 2020-02-04 | Bell Helicopter Textron Inc. | Fabricating composite core with woven composite fibers |
GB2559807B (en) * | 2017-02-21 | 2019-05-22 | Pembroke Bow Ltd | Helmet |
US10823112B2 (en) | 2017-05-25 | 2020-11-03 | The Boeing Company | Method for manufacturing and assembly of a thrust reverser cascade |
JP6766756B2 (en) * | 2017-06-08 | 2020-10-14 | 豊田合成株式会社 | Pressure-resistant container |
US11167836B2 (en) | 2018-06-21 | 2021-11-09 | Sierra Nevada Corporation | Devices and methods to attach composite core to a surrounding structure |
CN108908950A (en) * | 2018-07-23 | 2018-11-30 | 上海复合材料科技有限公司 | A kind of carbon fiber pipe battle array structure and preparation method thereof |
US11491686B2 (en) | 2019-07-22 | 2022-11-08 | The Boeing Company | Compression molded cascades with two piece mold |
CN113496957A (en) * | 2020-03-19 | 2021-10-12 | 深圳市柔宇科技有限公司 | Elastic substrate, electronic device, electronic assembly and manufacturing method thereof |
CN118046597A (en) * | 2024-04-15 | 2024-05-17 | 上海复合材料科技有限公司 | Composite material sandwich structure and forming method thereof |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5128192A (en) * | 1990-02-02 | 1992-07-07 | Northrop Corporation | Braided preform process for thermoplastic honeycomb cores |
US5944935A (en) * | 1996-07-24 | 1999-08-31 | Zukas; Florian J. | Preparation of adhesively bonded sandwich structures |
US20010042593A1 (en) * | 2000-05-18 | 2001-11-22 | Ligui Zhou | Self-adhesive prepreg face sheet for sandwich panels |
JP2006247867A (en) * | 2005-03-08 | 2006-09-21 | Murata Mach Ltd | Frp honeycomb structure and its manufacturing method |
US20100080941A1 (en) * | 2008-10-01 | 2010-04-01 | The Boeing Company | Composite truss panel having fluted core and method for making the same |
Family Cites Families (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3058125A (en) * | 1960-02-23 | 1962-10-16 | Louis J Zerbee | Ventilating and shock absorbing cushion |
DE1959976A1 (en) | 1969-11-29 | 1971-06-16 | Hamburger Flugzeugbau Gmbh | Lightweight component made from plastic tubes |
US3879243A (en) * | 1973-01-05 | 1975-04-22 | Jonas Medney | Porous filament wound pipe and method for making same |
US4025675A (en) * | 1973-12-19 | 1977-05-24 | Messerschmitt-Bolkow-Blohm Gmbh | Reinforced laminates |
US4600619A (en) * | 1984-12-31 | 1986-07-15 | The Boeing Company | Continuously wound filament structure for use in noise attenuation element |
EP0244120A3 (en) * | 1986-04-16 | 1989-07-12 | Courtaulds Plc | Composite element |
JPH02122923A (en) * | 1988-11-01 | 1990-05-10 | Fuji Heavy Ind Ltd | Composite panel and manufacture thereof |
DE4030529A1 (en) * | 1990-09-27 | 1992-04-02 | Dornier Gmbh | METHOD FOR PRODUCING SANDWICH STRUCTURES FROM FIBER REINFORCED CERAMICS |
US5217769A (en) * | 1990-11-08 | 1993-06-08 | Milliken Research Corporation | Tubular woven fabric comprising PVA warp yarns |
US5567500A (en) | 1991-08-07 | 1996-10-22 | Speciality Cellular Products Company | Composite honeycomb core structure comprising cell walls constructed of at least three unidirectional fiber layers or at least two unidirectional fiber layers and a random fiber layer |
DE69434917T2 (en) | 1993-05-04 | 2007-11-08 | Foster-Miller, Inc., Waltham | GRID-BASED PLATE WITH FOAM CORE |
US5888608A (en) | 1995-08-15 | 1999-03-30 | The Board Of Trustees Of The Leland Stanford Junior University | Composite grid/frame structures |
US5651850A (en) | 1996-01-11 | 1997-07-29 | The Boeing Company | Method of fabricating hybrid composite structures |
US5789060A (en) | 1996-07-29 | 1998-08-04 | Specialty Cellular Products Company | Heat conduction honeycomb core |
CA2287561C (en) * | 1998-10-26 | 2007-08-28 | Faroex Ltd. | Structural panel for bridging between spaced support |
BE1013181A5 (en) | 1999-12-17 | 2001-10-02 | Sonaca Sa | Joint compound for assembly of at least one body outside on a sandwich panel and panel incorporating at least one such connection. |
US6655633B1 (en) * | 2000-01-21 | 2003-12-02 | W. Cullen Chapman, Jr. | Tubular members integrated to form a structure |
US6503596B1 (en) | 2000-11-30 | 2003-01-07 | Michael L. Fellman | Composite firewall structure |
US7243879B2 (en) * | 2001-12-06 | 2007-07-17 | Kazak Composites, Incorporated | Lattice fin for missiles or other fluid-born bodies and method for producing same |
JP2004358806A (en) | 2003-06-04 | 2004-12-24 | Mitsubishi Rayon Co Ltd | Manufacturing method for honeycomb structure |
-
2011
- 2011-02-04 WO PCT/US2011/023681 patent/WO2011097433A1/en active Application Filing
- 2011-02-04 US US13/260,690 patent/US9713913B2/en active Active
- 2011-02-04 CN CN201180008434.0A patent/CN102741045B/en active Active
- 2011-02-04 EP EP11740388.1A patent/EP2507051B1/en active Active
- 2011-02-04 CA CA2786737A patent/CA2786737C/en active Active
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2017
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Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5128192A (en) * | 1990-02-02 | 1992-07-07 | Northrop Corporation | Braided preform process for thermoplastic honeycomb cores |
US5944935A (en) * | 1996-07-24 | 1999-08-31 | Zukas; Florian J. | Preparation of adhesively bonded sandwich structures |
US20010042593A1 (en) * | 2000-05-18 | 2001-11-22 | Ligui Zhou | Self-adhesive prepreg face sheet for sandwich panels |
JP2006247867A (en) * | 2005-03-08 | 2006-09-21 | Murata Mach Ltd | Frp honeycomb structure and its manufacturing method |
US20100080941A1 (en) * | 2008-10-01 | 2010-04-01 | The Boeing Company | Composite truss panel having fluted core and method for making the same |
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EP2507051B1 (en) | 2015-01-14 |
WO2011097433A1 (en) | 2011-08-11 |
EP2507051A1 (en) | 2012-10-10 |
CA2786737A1 (en) | 2011-08-11 |
CA2786737C (en) | 2016-04-19 |
US9713913B2 (en) | 2017-07-25 |
US20120021165A1 (en) | 2012-01-26 |
EP2507051A4 (en) | 2012-12-05 |
CN102741045B (en) | 2015-12-02 |
CN102741045A (en) | 2012-10-17 |
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