Patent Grant
11819743
The present disclosure relates generally to a golf club head with a mixed material construction.
In an ideal club design, for a constant total swing weight, the amount of structural mass would be minimized (without sacrificing resiliency) to provide a designer with additional discretionary mass to specifically place in an effort to customize club performance. In general, the total of all club head mass is the sum of the total amount of structural mass and the total amount of discretionary mass. Structural mass generally refers to the mass of the materials that are required to provide the club head with the structural resilience needed to withstand repeated impacts. Structural mass is highly design-dependent, and provides a designer with a relatively low amount of control over specific mass distribution. Conversely, discretionary mass is any additional mass (beyond the minimum structural requirements) that may be added to the club head design for the sole purpose of customizing the performance and/or forgiveness of the club. There is a need in the art for alternative designs to all metal golf club heads to provide a means for maximizing discretionary weight to maximize club head moment of inertia (MOI) and lower/back center of gravity (COG).
While this provided background description attempts to clearly explain certain club-related terminology, it is meant to be illustrative and not limiting. Custom within the industry, rules set by golf organizations such as the United States Golf Association (USGA) or The R&A, and naming convention may augment this description of terminology without departing from the scope of the present application.
The present disclosure provides various embodiments of golf club head designs that incorporate polymeric composite structures into the overall club head construction. In some of the embodiments described below, at least a portion of the club head may be formed from a thermoplastic composite, such as, for example, a fabric reinforced thermoplastic composite or a fiber-filled thermoplastic composite. In some embodiments, one or more layers of a fabric-reinforced thermoplastic composite may be joined with one or more layers of a molded, fiber-filled thermoplastic composite. For the purpose of easily differentiating within this disclosure, a “fabric reinforced composite” is intended to refer to a composite material having a reinforcing fabric embedded within a thermoplastic matrix. The fabric may be formed from a plurality of uni- or multi-directional constituent fibers that are aligned, layered, or woven into a fabric-like pattern. Conversely, a “fiber-filled thermoplastic composite” (or “filled thermoplastic” (FT) for short) is one where discontinuous chopped fibers are mixed with a liquid/flowable polymer prior to being injected into a mold for final part creation.
During the molding of a filled thermoplastic, a thermoplastic resin is heated to a temperature above the melting point of the polymer, where it is freely flowable. To facilitate the flowable characteristic despite having a dispersed filler material embedded within the resin, the filler materials generally include discrete particulate having a maximum dimension of less than about 25 mm, or more commonly less than about 12 mm. For example, the filler materials may include discrete particulate having a maximum dimension of 4 mm, 5 mm, 6 mm, 7 mm, 8 mm, 9 mm, or 10 mm, or having an average maximum dimension of between about 5 mm and about 25 mm (recognizing that breakage may occur during the molding process). Filler materials useful for the present designs may include, for example, glass beads or discontinuous reinforcing fibers formed from carbon, glass, or an aramid polymer.
In contrast to the discrete nature of the fibers/filler in a filled thermoplastic, the fibers in a fabric-reinforced composite (FRC) may be substantially larger/longer, and may have sufficient size and characteristics such that they may be provided as a continuous fabric separate from the polymer. When integrated with the thermoplastic resin, even if the polymer is freely flowable when melted, the included continuous fibers are generally not.
FRC materials are generally formed by arranging the fiber into a desired arrangement, and then impregnating the fiber material with a sufficient amount of a polymeric material to provide rigidity. In this manner, while FT materials may have a resin content of greater than about 45% by volume or more preferably greater than about 55% by volume, FRC materials desirably have a resin content of less than about 45% by volume, or more preferably less than about 35% by volume. FRC materials traditionally use two-part thermoset epoxies as the polymeric matrix, however, the present designs generally use thermoplastic polymers, instead, as the matrix. In many instances, FRC materials are pre-prepared prior to final manufacturing, and such intermediate material is often referred to as a prepreg. When a thermoset polymer is used, the prepreg is partially cured in intermediate form, and final curing occurs once the prepreg is formed into the final shape. When a thermoplastic polymer is used, the prepreg may include a cooled thermoplastic matrix that may subsequently be heated and molded into final shape.
As discussed below, fabric reinforced composites are best suited for portions of the design where strength is desired across a continuous surface, whereas filled thermoplastics may be best suited where more complex and/or variable geometries are desired, or at junctures where walls or features come together at angles. Likewise, each has a different dynamic response during an impact, which may further dictate placement within the design.
In the present designs, one or both of the front body 14 and the rear body 16 may be substantially formed from a thermoplastic composite material that includes at least one of a fabric reinforced composite or a filled thermoplastic. In some embodiments, the strike face 30 and/or front body 14 may comprise a metal (e.g. titanium alloy, steel alloy). In other embodiments, however, the strike face 30 and/or front body 14 may comprise a thermoplastic polymer and/or may be formed entirely from a thermoplastic composite material. Likewise, in some configurations, portions the rear body 16 may be comprised of a fabric-reinforced composite resilient layer and a filled thermoplastic structural layer. Furthermore, one or more portions of the rear body 16 may comprise or may be substantially formed form a metal.
In configurations where both the front and rear bodies 14, 16 include a thermoplastic composite, the front body 14 may comprise a thermoplastic composite that is the same as, or different than a thermoplastic composite of the rear body 16. If compatible/miscible thermoplastic resins are used in both the front body 14 and rear body 16, then in some configurations, the front body 14 may be affixed and/or coupled to at least a portion of the rear body 16 without the need for intermediate adhesives or fasteners. Instead the polymers of the adjoining bodies may be thermally fused/welded together.
Furthermore, in embodiments including directly abutting FRC and FT layers/portions, the use of miscible thermoplastic resins in these respective layers provides a unique ability to co-mold the layers together. This provides a club head design of unique geometries for weight savings via the filled thermoplastic layers, but also manufacturing capability of merging layers of rigid strength via the composite resilient layer.
Finally, in some embodiments, the use of certain thermoplastic resins may provide acoustic advantages that are not possible with other materials. Use of the thermoplastic polymers of the present construction may enable the assembled golf club head to acoustically respond closer to that of an all-metal design.
“A,” “an,” “the,” “at least one,” and “one or more” are used interchangeably to indicate that at least one of the item is present; a plurality of such items may be present unless the context clearly indicates otherwise. All numerical values of parameters (e.g., of quantities or conditions) in this specification, including the appended claims, are to be understood as being modified in all instances by the term “about” whether or not “about” actually appears before the numerical value. “About” indicates that the stated numerical value allows some slight imprecision (with some approach to exactness in the value; about or reasonably close to the value; nearly). If the imprecision provided by “about” is not otherwise understood in the art with this ordinary meaning, then “about” as used herein indicates at least variations that may arise from ordinary methods of measuring and using such parameters. In addition, disclosure of ranges includes disclosure of all values and further divided ranges within the entire range. Each value within a range and the endpoints of a range are hereby all disclosed as separate embodiment. The terms “comprises,” “comprising,” “including,” and “having,” are inclusive and therefore specify the presence of stated items, but do not preclude the presence of other items. As used in this specification, the term “or” includes any and all combinations of one or more of the listed items. When the terms first, second, third, etc. are used to differentiate various items from each other, these designations are merely for convenience and do not limit the items.
The terms “loft” or “loft angle” of a golf club, as described herein, refers to the angle formed between the club face and the shaft, as measured by any suitable loft and lie machine.
The terms “first,” “second,” “third,” “fourth,” and the like in the description and in the claims, if any, are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the terms so used are interchangeable under appropriate circumstances such that the embodiments described herein are, for example, capable of operation in sequences other than those illustrated or otherwise described herein. Furthermore, the terms “include,” and “have,” and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, device, or apparatus that comprises a list of elements is not necessarily limited to those elements, but may include other elements not expressly listed or inherent to such process, method, system, article, device, or apparatus.
The terms “left,” “right,” “front,” “back,” “top,” “bottom,” “over,” “under,” and the like in the description and in the claims, if any, are used for descriptive purposes with general reference to a golf club held at address on a horizontal ground plane and at predefined loft and lie angles, though are not necessarily intended to describe permanent relative positions. It is to be understood that the terms so used are interchangeable under appropriate circumstances such that the embodiments of the apparatus, methods, and/or articles of manufacture described herein are, for example, capable of operation in other orientations than those illustrated or otherwise described herein.
The terms “couple,” “coupled,” “couples,” “coupling,” and the like should be broadly understood and refer to connecting two or more elements, mechanically or otherwise. Coupling (whether mechanical or otherwise) may be for any length of time, e.g., permanent or semi-permanent or only for an instant.
Other features and aspects will become apparent by consideration of the following detailed description and accompanying drawings. Before any embodiments of the disclosure are explained in detail, it should be understood that the disclosure is not limited in its application to the details or construction and the arrangement of components as set forth in the following description or as illustrated in the drawings. The disclosure is capable of supporting other embodiments and of being practiced or of being carried out in various ways. It should be understood that the description of specific embodiments is not intended to limit the disclosure from covering all modifications, equivalents and alternatives falling within the spirit and scope of the disclosure. Also, it is to be understood that the phraseology and terminology used herein is for the purpose of description and should not be regarded as limiting.
Referring to the drawings, wherein like reference numerals are used to identify like or identical components in the various views,
The golf club head 10 includes a front body portion 14 (“front body 14”) and a rear body portion 16 (“rear body 16”) that are secured together to define a substantially closed/hollow interior volume. As is conventional with wood-style heads, the golf club head 10 includes a crown 18 and a sole 20, and may be generally divided into a heel portion 22, a toe portion 24, and a central portion 26 that is located between the heel portion 22 and toe portion 24.
The front body 14 generally includes a strike face 30 intended to impact a golf ball, a frame 32 that surrounds and extends rearward from a perimeter 34 of the strike face 30 to provide the front body 14 with a cup-shaped appearance, and a hosel 36 for receiving a golf club shaft or shaft adapter.
To reduce the structural mass of the club head beyond what is possible with traditional metal forming techniques, some or all of the front body 14 and/or the rear body 16 may be substantially formed from one or more thermoplastic composite materials such as fabric reinforced composites and/or filled thermoplastics. The structural weight savings accomplished through these designs may be used to either reduce the entire weight of the club head 10 (which may provide faster club head speeds and/or longer hitting distances) or to increase the amount of discretionary mass that is available for placement on the club head 10 (i.e., for a constant club head weight). In a preferred embodiment, the additional discretionary mass is re-included in the final club head design via one or more metallic weights 40 (such as shown in
Referring to
With continued reference to
In the embodiment illustrated in
With respect to both the polymeric construction of the crown member 50 and the sole member 52, any filled thermoplastics or fabric reinforced thermoplastic composites should preferably incorporate one or more engineering polymers that have sufficiently high material strengths and/or strength/weight ratio properties to withstand typical use while providing a weight savings benefit to the design. Specifically, it is important for the design and materials to efficiently withstand the stresses imparted during an impact between the strike face 30 and a golf ball, while not contributing substantially to the total weight of the golf club head 10. In general, preferred polymers may be characterized by a tensile strength at yield of greater than about 60 MPa (neat), and, when filled, may have a tensile strength at yield of greater than about 110 MPa, or more preferably greater than about 180 MPa, and even more preferably greater than about 220 MPa. In some embodiments, suitable filled thermoplastic polymers may have a tensile strength at yield of from about 60 MPa to about 350 MPa. In some embodiments, these polymers may have a density in the range of from about 1.15 to about 2.02 in either a filled or unfilled state, and may preferably have a melting temperature of greater than about 210° C. or more preferably greater than about 250° C.
PPS and PEEK are two exemplary thermoplastic polymers that meet the strength and weight requirements of the present design. Unlike many other polymers, however, the use of PPS or PEEK is further advantageous due to their unique acoustic properties. Specifically, in many circumstances, PPS and PEEK emit a generally metallic-sounding acoustic response when impacted. As such, by using a PPS or PEEK polymer, the present design may leverage the strength/weight benefits of the polymer, while not compromising the desirable metallic club head sound at impact.
With continued reference to
As such, to maximize the strength of the present design at the lowest possible structural weight, the design provided in
As shown in
With reference to
While affixing the one or more weights 40 to the structural layer 56 at a rear portion of the club head 10 desirably shifts the center of gravity of the club head 10 rearward and lower while also increasing the club head's moment of inertia, it also may create a cantilevered point mass spaced apart from the more structural metallic front body 14. As such, in some embodiments, the one or more structural members 68 may span between the weighted portion 72 and the forward portion 60 to provide a reinforced load path between the one or more weights 40 and the metallic front body 14. In this manner, the one or more stiffening members 68 may be operative to aid in transferring a dynamic load between the weighted portion 72 and the front body 14 during an impact between the strike face 30 and a golf ball. At the same time, these same rib-like stiffening members 68 may be operative to reinforce the resilient layer 54 and increase the modal frequencies of the club head at impact such that the natural frequency is greater than about 3,500 Hz at impact, and exists without substantial dampening by the polymer. When this surface reinforcement is combined with the desirable metallic-like acoustic impact properties of polymers such as PPS or PEEK, a user may find the club head 10 to be audibly similar from an all-metal club head while the design provides significantly improved mass properties (CG location and/or moments of inertia).
In a preferred embodiment, the resilient layer 54 and the structural layer 56 may be integrally bonded to each other without the use of an intermediate adhesive. Such a construction may simplify manufacturing, reduce concerns about component tolerance, and provide a superior bond between the constituent layers than could be accomplished via an adhesive or other joining methods. To accomplish the integral bond, each of the resilient layer 54 and structural layer 56 may include a compatible thermoplastic polymer that may be thermally bonded to the polymer of the mating layer.
Once the composite shell portion is in a proper shape, a filled thermoplastic supporting structure may then be injection molded into direct contact with the shell at step 84. Such a process is generally referred to as insert-molding. In this process, the shell is directly placed within a heated mold having a gated cavity exposed to a portion of the shell. Molten polymer is forcibly injected into the cavity, and thereafter either directly mixes with molten polymer of the heated composite shell, or locally bonds with the softened shell. As the mold is cooled, the polymer of the composite shell and supporting structure harden together in a fused relationship. The bonding is enhanced if the polymer of the shell portion and the polymer of the supporting structure are compatible, and is even further enhanced if the two components include a common or otherwise miscible thermoplastic resin component. While insert-molding is a preferred technique for forming the structure, other molding techniques, such as compression molding, may also be used.
With continued reference to
Referring again to
In some embodiments, the resilient layer 54 may have a substantially uniform thickness that may be in the range of from about 0.5 mm to about 0.7 mm, from about 0.5 mm to about 1.0 mm, or from about 0.6 mm to about 0.9 mm, or from about 0.7 mm to about 0.8 mm. In some embodiments, the resilient layer 54 may have a substantially uniform thickness of 0.5 mm, 0.55 mm, 0.60 mm, 0.65 mm, or 0.70 mm. In areas of the structural layer 56 that directly abut the resilient layer 54 (i.e., areas where the resilient layer 54 is located exterior to the structural layer 56), some embodiments of the structural layer 56 may have a substantially uniform thickness of from about 0.5 mm to about 0.7 mm, from about 0.5 mm to about 1.0 mm, or from about 0.6 mm to about 0.9 mm, or from about 0.7 mm to about 0.8 mm. In some embodiments, the structural layer 56 may have a substantially uniform thickness of 0.5 mm, 0.55 mm, 0.60 mm, 0.65 mm, or 0.70 mm. A substantially uniform construction of both the resilient layer 54 and the structural layer 56 is generally illustrated in
Referring again to
While the method 80 illustrated in
Specific to construction of a mixed-material crown member 50, and similar to that described above with respect to the sole member 52, the formation may begin by thermoforming a fiber reinforced thermoplastic composite into an external shell portion of the club head 10. The thermoforming process may involve, for example, pre-heating a thermoplastic prepreg to a molding temperature at least above the glass transition temperature of the thermoplastic polymer, molding the prepreg into the shape of the shell portion, and then trimming the molded part to size.
Once the composite shell portion is in a proper shape, a filled thermoplasticic supporting structure (i.e., one or both of the inner structural layer 112 and outer structural layer 114) may then be injection molded into direct contact with the shell (e.g., via insert-molding, as described above).
While
As further shown, the filled thermoplastic outer layer 202 may have a variable thickness 210 that extends between the fabric reinforced composite layer 206 and the ball striking surface. In embodiments where the fabric reinforced composite layer 206 has a substantially uniform thickness, the filled thermoplastic outer layer 202 may primarily contribute to a variable thickness 212 of the strike face 30 as a whole.
As shown in
With reference to
In the illustrated embodiment of
In the illustrated embodiment, the channel 232 allows the strike face 30 to absorb 0.9% more impact energy that is transferrable to a golf ball to increase ball speed and travel distance. In many embodiments, the channel 232 allows the strike face 30 to absorb 0.75% to 1.5% more impact energy that may be transferred to a golf ball to increase ball speed and travel distance.
In an embodiment where a filled thermoplastic outer layer 202 is disposed outward of a fabric reinforced composite layer 206, such as shown in
Because filled thermoplastics may have anisotropic structural qualities that are dependent on the typical or average orientation of the embedded, discontinuous fibers, special attention may need to be paid to the formation of the filled thermoplastic (FT) layer 202, 222 to ensure that it has sufficient strength to withstand repeated impacts. More specifically, a filled polymeric component will generally have greater strength against loads that are aligned with the longitudinal axis of the embedded fibers, and comparatively less strength to loads applied laterally. Because fiber orientation within a filled polymer is highly dependent on mold flow during the initial part formation, embodiments of a polymeric front body 14 may utilize mold and part designs that aid in orienting the embedded fiber along the most likely force/stress propagation paths.
As is understood, during a molding process, such as injection molding, embedded fibers tend to align with a direction of the flowing polymer. With some fibers (i.e., particularly with short fiber reinforced thermoplastics) and resins, the alignment tends to occur more completely close to the walls of the mold or edge of the part. These layers are referred to as shear layers or skin layers. Conversely, within a central core layer, the fibers may sometimes be more randomized and/or perpendicular to the flowing polymer. The thickness of the core layer may generally be altered by various molding parameters including molding speed (i.e., slower molding speed may yield a thinner core layer) and mold design. With the present designs, it is desirable to minimize the thickness of any randomized core layer to enable better control over fiber orientation.
During an impact, stresses tend to radiate outward from the impact location while propagating toward the rear of the club head 10. Additionally, bending moments are imparted about the shaft, which induces material stresses between the impact location and the hosel 36, and along the hosel 36/parallel to a hosel axis 240 (as shown in
Because the discontinuous fibers are mixed within the flowable polymer prior to forming the part, it is impossible to guarantee perfect alignment. With that said, however, the design of the front body 14 and manner of injection molding (e.g., fill rate, gating/venting, and temperature) may be controlled to align as many of the embedded fibers with these axes as possible. For example, within the hosel, it is preferable if greater than about 50% of the fibers are aligned within 30 degrees of the hosel axis 240. Between the center of the face and the hosel 36, it is preferable if greater than about 50% of the fibers are aligned within 30 degrees of the horizontal face axis 242, and/or within the frame 32, it is preferable if greater than about 50% of the fibers are aligned within 30 degrees of the fore-rear axis 244. In another embodiment, greater than about 60% of the fibers within the hosel 36 are aligned within 25 degrees of the hosel axis 240, greater than about 60% of the fibers between the center of the face and the hosel 36 are aligned within 25 degrees of the horizontal face axis 242, and/or greater than about 60% of the fibers within the frame 32 are aligned within 25 degrees of the fore-rear axis 244. In still another embodiment, greater than about 70% of the fibers within the hosel 36 are aligned within 20 degrees of the hosel axis 240, greater than about 70% of the fibers between the center of the face and the hosel 36 are aligned within 20 degrees of the horizontal face axis 242, and/or greater than about 70% of the fibers within the frame 32 are aligned within 20 degrees of the fore-rear axis 244.
To encourage the polymer to fill the hosel 36 from bottom to top, it may be desirable to fill the face from a location near the toe 24 and that is at or preferably above the horizontal centerline 254 of the face 30 (i.e., between the crown 18 and a line drawn through the center of the face 256 and parallel to a ground plane when the club is held at address). This may encourage the flow 258 and corresponding fiber alignment to follow a generally downward slant from above the horizontal centerline 254 at the toe 24 toward the center of the face 256 while between the toe and the center 256. Following this, at the center 256, the flow 260 and corresponding fiber alignment may generally be parallel to the horizontal centerline 254 at or immediately surrounding the center of the face 256. Finally, the flow 262 may arc upward and fill the hosel 36 largely from the bottom toward the neck. While
As shown in
As further shown in
While
Once the composite shell portion is in a proper shape, it is placed within a mold at 284, after which a filled thermoplastic is then injection molded into direct contact with the FRC at step 286. As previously mentioned, such a process is generally referred to as insert-molding. In this process, the pre-formed shell is directly placed within a heated mold having a gated cavity/void that is directly abuts an exposed portion of the shell. Molten polymer is forcibly injected into the cavity, and thereafter it either directly mixes with molten polymer of the heated composite shell, or locally bonds with the softened shell. As the mold is cooled, the polymer of the composite shell and supporting structure harden together in a fused relationship. The bonding is enhanced if the polymer of the shell portion and the polymer of the supporting structure are compatible, and is even further enhanced if the two components include a common or otherwise miscible thermoplastic resin component. While insert-molding is a preferred technique for forming the structure, other molding techniques, such as compression molding, may also be used (e.g., where the FT layer is produced as a distinct, independent layer, and then fused with other layers via compression molding)
In further designs, a plurality of inserts are provided into the mold prior to injecting the filled thermoplastic. For example, a first insert may form the outer surface of the front body 14, a second insert may then form a reinforced back surface, and the filled thermoplastic may be injected in between. In another embodiment, one or more reinforcing meshes, including metallic meshes or screens, may be embedded within the FT layer to provide additional reinforcement and strength. In such an embodiment, to facilitate solid integration between the mesh and the FT layer, the mesh may include a plurality of apertures within which the thermoplastic resin may flow during creation of the FT layer.
While the disclosure above generally explains the use of thermoplastic composites that have at least one fabric-reinforced composite layer and at least one filled thermoplastic layer, it should be understood that the present techniques are not limited to simply two layers in a given component. In many embodiments, the thermoplastic composites may comprise a laminate that has two or more, three or more, four or more, five or more, six or more, seven or more, eight or more, nine or more, ten or more layers of mixed material. By forming each layer with a thermoplastic base resin, there is almost no limit to the number of times that any one or more layers may be reformed if the design so requires. This very nature may then enable the creation of intricate and/or complex three-dimensional material structures by pre-forming layers with different grain patterns, internal fiber orientations, and/or aperture size, shape, and/or spacing. This technology then enables the strength to weight ratio to be optimized by engineering the structure of the material, itself.
In some embodiments, one or more of the strike face 30, crown 18, or sole 20 may comprise a plurality of distinct layers of thermoplastic composite, each fused to at least one directly adjacent/abutting thermoplastic composite layer without the use of an intermediate adhesive. Each layer may consist of a fabric reinforced thermoplastic composite, a filled thermoplastic (preferably filled with a long and/or short fiber fill), or an unfilled thermoplastic. The base thermoplastic resin of each layer may be identical or otherwise miscible with the base thermoplastic resin of one or more of the directly abutting layers. In this manner, in one configuration, at least a plurality of the layers may be separately formed and then collectively fused together through the application of heat and pressure, such as with a compression molding process.
Further expanding on the concept of engineered material structures,
While
In a similar manner as illustrated with the crown/sole in
As mentioned above, different mixed materials or compounds/elements may form each of these lamina layers within the crown 18, sole 20, and/or strike face 30. The different lamina layers may share a common matrix polymer (i.e., the same thermoplastic polymer in each lamina layer), and either the same or different reinforcement elements or compounds per lamina layer. The different lamina layers may share a common derivative matrix polymer that is not chemically the same, but is miscible to each other. For example, one lamina layer could be a thermoplastic polymer that is one chemical compound, and the next lamina layer is another thermoplastic compound that is a different chemical formula from the thermoplastic compound of the lamina layer above, but shares enough chemical structure, 3D shape, and chemical properties to be miscible with the thermoplastic layer above. Each of the reinforcement element or compound can be the same or different in these “miscible” thermoplastic lamina layers. The different lamina layer may also share a thermoplastic resin that is common with each layer, but each lamina layer may have the same or different matrix polymer and/or reinforcement element/compound.
The combination of the matrix polymer and reinforcement element (fabric or fiber fill) allows for the end product to comprise advantages of both the matrix polymer and the reinforcement element. Also, the matrix polymer having reinforcement elements shrink less than unfilled resins/polymers when subjected to any form of heat molding, thereby improving the dimensional control of molded parts and reduce the cost of composites. In many embodiments, the matrix polymer of the crown/sole member's 24/26 may be polycarbonate (PC), polyphenylene sulfide (PPS), polypropylene (PP), Nylon-6 (PA6), Nylon 6-6 (PA66), Nylon-12 (PA12), Polymethylpentene (TPX), polyvinylidene fluoride (PVDF), polymethylmacylate (PMMA), poly ether ketone (PEEK), polyetherimide (PEI), or polyether ketone (PEK).
The materials of, for example, the matrix polymer of the crown 18, sole 20, and/or strike face 30 each may be selected and/or formed to achieve one or more material properties such as tensile strength, tensile modulus, and density. The matrix polymer of the crown, sole, and/or strike face may comprise a tensile strength ranging from 30 MPa to 3000 MPa. In some embodiments, the tensile strength of the matrix polymer may range from 30 MPa to 500 MPa, 500 MPa to 1000 MPa, 1000 MPa to 1500 MPa, 1500 Pa to 2000 MPa, 2000 MPa to 2500 MPa, 2500 MPa to 3000 MPa, 30 MPa to 1500 MPa, 1500 MPa to 3000 MPa, 500 MPa to 2500 MPa, 30 MPa to 1000 MPa, 1000 MPa to 2000 MPa, or 2000 MPa to 3000 MPa. In some embodiments, the tensile strength of the crown, sole, and/or strike face's matrix polymer may be 30 MPa, 200 MPa, 400 MPa, 800 MPa, 1200 MPa, 1600 MPa, 2000 MPa, 2400 MPa, 2800 MPa, or 3000 MPa.
The matrix polymer of the crown, sole, and/or strike face may comprise a tensile modulus ranging from 1.5 GPa to 12 GPa. In some embodiment, the tensile modulus may range from 1.5 GPa to 6 GPa, 6 GPa to 12 GPa, 1.5 GPa to 3 GPa, 3 GPa to 6 GPa, 6 GPa to 9 GPa, or 9 GPa to 12 GPa. In some embodiments, the matrix polymer of the crown, sole, and/or strike face may have a tensile modulus of 1.5 GPa, 2 GPa, 3 GPa, 4 GPa, 5 GPa, 6 GPa, 7 GPa, 8 GPa, 9 GPa, 10 GPa, 11 GPa, or 12 GPa.
The matrix polymer of the crown, sole, and/or strike face may comprise a density ranging from 0.80 g/cm3 to 1.80 g/cm3. In some embodiments, the density may range from 0.80 g/cm3 to 1.3 g/cm3, 1.3 g/cm3 to 1.8 g/cm3, 1.0 g/cm3 to 1.6 g/cm3, 0.8 g/cm3 to 1.1 g/cm3, 1.1 g/cm3 to 1.5 g/cm3, 1.5 g/cm3 to 1.8 g/cm3, 0.8 g/cm3 to 1.0 g/cm3, 1.0 g/cm3 to 1.2 g/cm3, 1.2 g/cm3 to 1.4 g/cm3, 1.4 g/cm3 to 1.6 g/cm3, or 1.6 g/cm3 to 1.8 g/cm3. In some embodiments, the matric polymer of the crown/sole may have a density of 0.8 g/cm3, 0.9 g/cm3, 1.0 g/cm3, 1.1 g/cm3, 1.2 g/cm3, 1.3 g/cm3, 1.4 g/cm3, 1.5 g/cm3, 1.6 g/cm3, 1.7 g/cm3, or 1.8 g/cm3.
The reinforcement fabrics/fibers embedded within one or more of the crown, sole, and/or strike face may be carbon fiber, aramid fibers (e.g., Nomex, Vectran, Kevlar, Twaron), bamboo fiber, natural fiber (e.g., cotton, hemp, flax), glass fibers, glass beads, metal fibers (e.g., Ti, Al), ceramic fibers (e.g., TiO2), and granite, SiC). The materials of such reinforcement fabrics/fibers within the crown, sole, and/or strike face comprises material properties such as tensile strength, tensile modulus and density. In some embodiments, the tensile strength of the crown, sole, and/or strike face's reinforcement elements range from 300 MPa to 7000 MPa. In some embodiments, the tensile strength of the reinforcement elements may range from 300 MPa to 4000 MPa, 4000 MPa to 7000 MPa, 2000 MPa to 5500 MPa, 300 MPa to 2000 MPa, 2000 MPa to 3500 MPa, 3500 MPa to 5000 MPa, 5000 MPa to 7000 MPa, 300 MPa to 1500 MPa, 1500 MPa to 2500 MPa, 2500 MPa to 3500 MPa, 3500 MPa to 4500 MPa, 4500 MPa to 5500 MPa, or 5500 MPa to 7000 MPa. In some embodiments, the reinforcement elements of the crown, sole, and/or strike face may have a tensile strength of 300 MPa, 1000 MPa, 1500 MPa, 2000 MPa, 2500 MPa, 3000 MPa, 3500 MPa, 4000 MPa, 4500 MPa, 5000 MPa, 5500 MPa, 6000 MPa, 6500 MPa, or 7000 MPa.
In some embodiments, the tensile modulus of the crown, sole, and/or strike face's reinforcement elements range from 30 GPa to 700 GPa. In some embodiments, the tensile modulus of the reinforcement elements may range from 30 GPa to 400 GPa, 400 GPa to 700 GPa, 200 GPa to 550 GPa, 30 GPa to 200 GPa, 200 GPa to 350 GPa, 350 GPa to 500 GPa, 500 GPa to 700 GPa, 30 GPa to 150 GPa, 150 GPa to 250 GPa, 250 GPa to 350 GPa, 350 GPa to 450 GPa, 450 GPa to 550 GPa, or 550 GPa to 700 GPa. In some embodiments, the reinforcement elements of the crown, sole, and/or strike face may have a tensile Modulus of 30 GPa, 100 GPa, 150 GPa, 200 GPa, 250 GPa, 300 GPa, 350 GPa, 400 GPa, 450 GPa, 500 GPa, 550 GPa, 600 GPa, 650 GPa, or 700 GPa.
In some embodiments, the density of the reinforcement elements of the crown, sole, and/or strike face range from 0.75 g/cm3 to 10 g/cm3. In some embodiments, the density of the reinforcement elements may range from 1 g/cm3 to 5 g/cm3. In some embodiments, the reinforcement elements of the crown, sole, and/or strike face may be 1.8 kg/mm2, 200 kg/mm2, 400 kg/mm2, 600 kg/mm2, 800 kg/mm2, 1000 kg/mm2, 1200 kg/mm2, 1400 kg/mm2, 1600 kg/mm2, 1800 kg/mm2, 2000 kg/mm2, or 2200 kg/mm2.
The rear body 16 may generally be formed from a fabric reinforced thermoplastic composite crown member 500 forming at least a portion of the crown 18, a fabric reinforced thermoplastic composite sole member 502 forming at least a portion of the sole 20, and a filled or unfilled thermoplastic supporting structure 504 that supports one or both of the FRC crown member 500 or FRC sole member 502. In some embodiments, the thermoplastic supporting structure 504 may include a plurality of discontinuous reinforcing fibers and/or a metallic fill (e.g., a powder) embedded within a thermoplastic resin. In a preferred embodiment, the thermoplastic resin of the supporting structure 504 is the same or otherwise miscible with the thermoplastic resin used to form both the FRC crown member 500 and the FRC sole member 502. In this manner, the crown and sole members 500, 502 may be joined to the supporting structure 504 using direct bonding and without the need for intermediate adhesives.
In embodiments where the front body 14 and rear body 16 are formed primarily using thermoplastic composite materials, it has been found that the club head moments of inertia and total mass both drop rather substantially. More specifically, switching to this particular thermoplastic construction provides a design that is about 60 to about 100 grams lighter than conventional driver heads, which generally weigh between about 200 grams and about 210 grams. In order to maintain a constant swing weight with improved moments of inertia (i.e., resistance to club head twisting during off-center impacts), it is desirable to incorporate this mass back into the club head in the form of discretionary, placed mass.
In some embodiments, it may be desirable to locate at least a portion of the discretionary mass toward a forward portion of the club head. In some embodiments, it has been found that the use of a forwardly located mass provides a more stable and balanced club head. More particularly, it has been discovered that if the center of gravity is pushed rearward beyond approximately the geometric center where the club head, the club head may become unstable, particularly during the deceleration phase of the swing near impact. This concern has not arisen with traditional metal constructions due to the structural mass maintained in the forward regions of the club head. With the low density of polymers, and the increase in discretionary mass, however, it is a concern that must be accounted for in the design or placement of discretionary mass.
It has been found that in some designs, the face thickness and density may provide sufficient forward weighting to avoid the need for additional forward metallic weights. In one embodiment, the forward weighting was found to not be required if the maximum thickness of the variable thickness strikeface was from about 5.0 mm to about 9.0 mm, or from about 6.0 mm to about 8.0 mm, with the perimeter thickness of from about 3.0 mm to about 5.0 mm, or from about 3.5 mm to about 4.5 mm. In one embodiment, forward metallic weights were not required when the maximum face thickness was about 7.25 mm and the surrounding perimeter face thickness was about 4.45 mm.
In one embodiment that utilizes no added forward metallic mass, all of the discretionary mass may be added to the club head in the form of a tungsten or other dense metal weight that is provided, for example, in a rear weighted portion 72 of the sole 20. Such a design would aid in moving the center of gravity down and back, which improves the launch characteristics of an impacted ball. Unfortunately, in some circumstances a concentrated load of this nature may require a strengthened support structure between the weight and the strike face that may withstand the impact loading without catastrophically buckling. The further back, heavier, and more concentrated the mass becomes, the more structure and/or stiffer material would then be required to resist bucking of the intermediate portion of the club head.
In another embodiment, the skeleton 552 may be a thermoplastic composite that incorporates a metallic filler into a thermoplastic resin for at least one of the lower cage 554 and the perimeter band 556. This hybrid thermoplastic skeleton may then be bonded/fused to abutting thermoplastic structure 504, for example, on an inward-facing surface 558 of the structure 504. In such an embodiment, the metal filler may be from about 30% to about 90% by volume of the filled portion of the skeleton 552, alternatively, it may be from about 60% to about 80% by volume, or even about 65% to about 75% by volume of the filled portion of the skeleton 552. In some embodiments, the filled portion of the skeleton 552 may have a specific gravity of greater than about 8, or greater than about 9, or greater than about 10. In one particular embodiment the filled portion of the skeleton 552 may comprise a 70% tungsten filler in a 30% thermoplastic resin (by volume), and may have a specific gravity in the range of about 12.5 to about 14.0.
During manufacturing the skeleton 552 may be compression molded in contact with the structure 504, whereby each respective structure is heated to a temperature above the glass transition temperature of its respective resin. Upon cooling, the abutting parts may then be fused together.
In yet another embodiment, the supporting structure 504, itself, may include a metallic filler that is operative to reintroduce a portion of the available discretionary weight. In such an embodiment, at least a portion of the structure 504 may have specific gravity of greater than about 8, or greater than about 9, or greater than about 10, or in the range of about 12.5 to about 14.0.
Common to each of the presently disclosed designs is a desire to provide a golf club head that maximizes the total amount of discretionary mass, which may be employed to locate the center of gravity as close to the sole and rear of the club as is possible within stability constraints, while maximizing the moment of inertia toward the maximum limits allowable under U.S.G.A. regulations. To accomplish this desire, one or both of a forward body 14 or rear body 16 of the club head 10 is formed from a reinforced thermoplastic composite that has a lower specific gravity than typically used metals. It has been found, however, that accomplishing adequate durability with polymers that are less strong than metals requires an increase in the volume of material required thus offsetting at least a portion of the weight savings. The presently described embodiments utilize a design-based approach to reinforcing the polymeric structure in a way that attempts to minimize the amount of additional material that must be added. These designs incorporate selective reinforcement to guard against buckling within primary load paths, utilize aligned reinforcing fibers embedded within the thermoplastic to tune the anisotropic strengths of the thermoplastic composites to the dynamics of the structure, and/or utilize a mixed material thermoplastic laminate structure to leverage the design and material advantages of both filled thermoplastics and fabric reinforced composites in the same structure.
The present designs have realized net weight savings of up to about 60 to 100 grams. Absent any reintroduction of this weight, the club head would realize a dramatic reduction in both swing weight and moment of inertia. Reintroduction of the weight, however, posed separate challenges in how specifically to attach the weight to the structure, how to distribute the weight to avoid impact dynamics that may damage intermediate structure, and how to locate the weight to maximize moments of inertia while pushing the center of gravity as far down and back as possible. The presently described embodiments for re-weighting the club head each attempt to balance these objectives, for example, by placing weight forward to minimize impact stresses and maintaining a center of gravity forward of a critical point that could result in instability, by distributing the weight in a structural manner, such as using a skeleton or metal-doped reinforcing structure or by incorporating the weight into weighted and/or doped lamina layers within the outer shell of the club head. Incorporation of the weight into the structure, itself, is a design that is made possible largely through the use of thermoplastic resins, which may be used to form discrete layers having specific design properties, and then subsequently reforming the collection of layers into a collective laminate stack-up.
As discussed below, the designs described herein have proved to be successful in achieving the design objectives of a high moment of inertia club head with a center of gravity that is pushed down and back while still maintaining stability and durability.
General Mass Properties
As generally illustrated in
The club head 10 further comprises a head center of gravity (CG) 812 and a head depth plane 814 extending through the geometric center 800 of the strikeface 30, perpendicular to the loft plane 802, in a direction from the heel 22 to the toe 24 of the club head 10. In many embodiments, the head CG 812 is located at a head CG depth 816 from the loft plane 802, measured in a direction perpendicular to the loft plane 802. The head CG 812 is further located at a head CG height 818 from the head depth plane 814, measured in a direction perpendicular to the head depth plane 814. In many embodiments, the head CG height 818 is positive when the head CG 812 is located above the head depth plane 814 (i.e. between the head depth plane 814 and the crown 18), and the head CG height 818 is negative with the head CG 812 is located below the head depth plane 814 (i.e. between the head depth plane 814 and the sole 20).
In many embodiments, the head CG height 818 may be less than 0.08 inches, less than 0.07 inches, less than 0.06 inches, less than 0.05 inches, less than 0.04 inches, less than 0.03 inches, less than 0.02 inches, less than 0.01 inches, or less than 0 inches (i.e. the head CG height may have a negative value, such that it is located below the head depth plane). Further, in many embodiments, the head CG height 818 may have an absolute value less than approximately 0.08 inches, less than approximately 0.07 inches, less than approximately 0.06 inches, less than approximately 0.05 inches, or less than approximately 0.04 inches. Further still, in many embodiments, the head CG depth 816 may be greater than approximately 1.7 inches, greater than approximately 1.8 inches, greater than approximately 1.9 inches, greater than approximately 2.0 inches, greater than approximately 2.1 inches, greater than approximately 2.2 inches, or greater than approximately 2.3 inches.
In many embodiments of the present designs, the head CG depth 816 and the head CG height 818 may be related by Relation 1 and/or Relation 2 below:
For the purpose of determining club head moments of inertia, a coordinate system may be defined at the CG 812 via mutually orthogonal axes (i.e., an x-axis 820, a y-axis 822, and a z-axis 824). The y-axis 822 extends through the head CG 812 from the crown 18 to the sole 22, perpendicular to a ground plane when the club head is at an address position. The x-axis 820 extends through the head CG 812 from the heel 22 to the toe 24 and perpendicular to the y-axis 822. The z-axis 824 extends through the head CG 812 from the front end 830 to the back end 832 and perpendicular to the x-axis 820 and the y-axis 822.
Moments of inertia then exist about the x-axis Ixx (i e crown-to-sole moment of inertia) and about the y-axis Iyy (i.e. heel-to-toe moment of inertia). In many embodiments, the crown-to-sole moment of inertia Ixx may be greater than approximately 3000 g·cm2, greater than approximately 3250 g·cm2, greater than approximately 3500 g·cm2, greater than approximately 3750 g·cm2, greater than approximately 4000 g·cm2, greater than approximately 4250 g·cm2, greater than approximately 4500 g·cm2, greater than approximately 4750 g·cm2, greater than approximately 5000 g·cm2, greater than approximately 5250 g·cm2, greater than approximately 5500 g·cm2, greater than approximately 5750 g·cm2, greater than approximately 6000 g·cm2, greater than approximately 6250 g·cm2, greater than approximately 6500 g·cm2, greater than approximately 6750 g·cm2, or greater than approximately 7000 g·cm2. Further, in many embodiments, the heel-to-toe moment of inertia Iyy may be greater than approximately 5000 g·cm2, greater than approximately 5250 g·cm2, greater than approximately 5500 g·cm2, greater than approximately 5750 g·cm2, greater than approximately 6000 g·cm2, greater than approximately 6250 g·cm2, greater than approximately 6500 g·cm2, greater than approximately 6750 g·cm2, or greater than approximately 7000 g·cm2.
In many embodiments, the club head comprises a combined moment of inertia (i.e. the sum of the crown-to-sole moment of inertia Ixx and the heel-to-toe moment of inertia Iyy) greater than 8000 g·cm2, greater than 8500 g·cm2, greater than 8750 g·cm2, greater than 9000 g·cm2, greater than 9250 g·cm2, greater than 9500 g·cm2, greater than 9750 g·cm2, greater than 10000 g·cm2, greater than 10250 g·cm2, greater than 10500 g·cm2, greater than 10750 g·cm2, greater than 11000 g·cm2, greater than 11250 g·cm2, greater than 11500 g·cm2, greater than 11750 g·cm2, or greater than 12000 g·cm2, greater than 12500 g·cm2, greater than 13000 g·cm2, greater than 13500 g·cm2, or greater than 14000 g·cm2.
Table 1, below numerically illustrates the mass parameters for eight different club heads. Specifically, the table shows the CG depth 816, CG height 818, moment of inertia Ixx about the horizontal x-axis 820, and moment of inertia Iyy about the y-axis 822.
Metal clubs 1-3 are all commercially available drivers having an all metal structural design (i.e., at least the crown, sole, and face). Metal 1 is a metal driver head with a full titanium structure, a volume of less than about 445 cm3, and a rear backweight. Metal 2 is metal driver head with a full titanium structure, a volume of greater than or equal to 460 cm3, and a rear backweight. Metal 3 is a metal driver head with a full titanium structure, a volume of in the range of about 450-457 cm3, and a movable weighting system.
“Metal Face; Polymer Body” is a driver head of similar construction as is shown in
Finally, “All Polymer 1” is a polymeric composite driver head that includes a polymeric front body 14, such as shown in
As shown by
Angling the sole extension 1020 relative to the strike face 30 may offset the CG 812 of the golf club head 1000 towards either the heel end 22 or the toe end 24. For example, the center of gravity may be offset towards the heel end 22 0.010 inch, 0.020 inch, 0.030 inch, 0.040 inch, 0.050 inch, 0.060 inch, 0.070 inch, 0.080 inch, 0.090 inch, 0.100 inch, 0.110 inch, 0.120 inch, 0.130 inch, 0.140 inch, or 0.150 inch. In a similar fashion, the toe-ward angle may decrease while the heel-ward angle increases. For example, the combination of toe-ward angle 1050 and heel-ward angle may be 80 degrees and 100 degrees, 70 degrees and 110 degrees, 60 degrees and 120 degrees, 50 degrees and 130 degrees, or 45 degrees and 135 degrees. For example, the center of gravity may be offset towards the toe end 24 by 0.010 inch, 0.020 inch, 0.030 inch, 0.040 inch, 0.050 inch, 0.060 inch, 0.070 inch, 0.080 inch, 0.090 inch, 0.100 inch, 0.110 inch, 0.120 inch, 0.130 inch, 0.140 inch, or 0.150 inch. This angular offset may be desirable to place a rear mass more toward the rear, heel-ward portion or rear toe-ward portion to position a club head center of gravity in that direction to influence ball flight characteristics. Other angular offsets in different embodiments may differently combine the first component sole portion rear extension toe-ward angle 1050 and the first component sole portion rear extension heel-ward angle 1055, which may produce different club head center of gravity positions and different ball flight characteristics.
In some embodiments, the sole extension 1020 may have a varying width. In these embodiments, the toe-ward angle 1050 and the heel-ward angle 1055 may not be supplementary angles (may not sum to 180 degrees). In some embodiments, both the toe-ward and the heel-ward angles (1050 and 1055) of the sole extension 1020 may be acute angles, reducing the weight of the first component 1014 and allowing greater perimeter weighting in the club head 1000. In other embodiments, both the toe-ward and the heel-ward angles (1050 and 1055) may be obtuse angles, increasing the durability of the sole and simplifying manufacturing assembly of the golf club head 1000.
In some embodiments, both the toe-ward and heel-ward angles (1050 and 1055) are obtuse angles, such that the width of the sole extension 1020 decreases in a front-to-rear direction. This configuration is desirable in embodiments wherein the non-metallic portion 1016 is a unitary piece. In such embodiments, the non-metallic portion 1016 is generally slid onto the first component 1014 in a front-to-rear direction. Accordingly, in such embodiments, the sole extension 1020 must be narrowest at the rear edge of the sole extension 1020 to allow the non-metallic portion 1016 to slide smoothly and fit properly along the first component 1014. Additional embodiments of this design are described in U.S. Pat. No. 10,596,427 as well as U.S. Patent Application Publication Nos. 2020/0298072 and 2020/0179774, which are all incorporated by reference in their entirety.
The sole extension 1020 may serve to structurally couple a sole portion 1022 of the frame 32 with a weight assembly 1072 at or near the rear of the clubhead. The weight assembly 1072 extends upward from the sole 1022 and forms a middle portion of the rear of the club head 1000. The weight assembly 1072 forms only a lower portion of the rear, it does not extend above a perimeter edge 1104 of the golf club head 1000. Further, the weight assembly 1072 does not form a cup shape of any kind. The transition between the sole extension 1020 and the weight assembly 1072 is a generally distinct and angled transition. The transition between the sole extension 1020 and the weight assembly 1072 is not a gradual transition and the interior of weight assembly 1072 does not comprise smooth, concave surfaces forming a cup.
In many embodiments, the weight assembly 1072 may be configured to receive a detachable weight member 1090 that has a greater specific gravity than the metal used to form the sole extension 1020 or forward portion 1018. In some embodiments, the detachable weight member 1090 may include one or more threaded inserts that are operative to secure the detachable weight member 1090 to the first component 1014.
As shown in
In some embodiments, the weight assembly 1072 may comprise a weight channel 1074 configured to receive the detachable weight member 1090. The weight channel 1074 may be recessed within the weight assembly 1072 such that a large portion of the detachable weight member 1090 sits within the recessed channel 1074 and does not extend past the perimeter of the golf club head 1000. Rather than a curvilinear channel that follows the curvature of the club head body, the weight channel 1074 comprises a plurality of straight sections that are angled with respect to one another. Thus, the weight assembly 1072 does not comprise continuous concave or convex surfaces when viewed from either the interior or the exterior of the golf club head 1000 but instead forms a plurality of disjointed, flat surfaces. The transitions between these disjointed, flat surfaces are sharp angles that distinctly define where each section begins and ends. In some embodiments, the weight channel 1074 may comprise three of such sections, one corresponding to each of the threaded receivers. In one embodiment, the detachable weight member 1090 may be configured in the weight assembly 1072 of the golf club head 1000 to set up in a neutral position to hit a straight golf shot. The weight member 1090 couples to a central threaded receiver 1081b of the weight assembly 1072. The central positioning of the weight member 1090 within the weight assembly 1072 leads to a generally straight ball flight, as the center of gravity or CG 812 of the entire golf club head 1000 is extremely balanced.
In another embodiment, the detachable weight member 1090 may be configured in the weight assembly 1072 of the golf club head 1000 to set up a heel-ward position, to hit a fade type golf shot. The weight member 1090 couples to a heel-side threaded receiver 1081a of the weight assembly 1072. The heel-ward positioning of the weight member 1090 within the weight assembly 1072 leads to a generally left to right ball flight (for lefthanded golfers a right to left ball flight), as the entire golf club head CG 812 is off center towards the heel portion 22 of the golf club head 1000. In another embodiment, the detachable weight member 1090 may be configured in the weight assembly 1072 of the golf club head 1000 to set up a toe-ward position, to hit a draw type golf shot. The weight member 1090 couples to a toe-side threaded receiver 1081c of the weight assembly 1072. The toe-ward positioning of the weight member 1090 within the weight assembly 1072 leads to a generally right to left ball flight (for righthanded golfers a left to right ball flight), as the entire golf club head CG 812 is off center towards the toe portion 24 of the golf club head 1000.
In many embodiments, the mass of the weight member 1090 ranges between 1 g and 40 g. In some embodiments, the mass of the weight member 1090 ranges from 1 g-5 g, 5 g-10 g, 10 g-15 g, 15 g-20 g, 20 g-25 g, 25 g-30 g, 30 g-35 g, or 35 g-40 g.
The combination of a weight assembly 1072 in the rear portion with relatively small distances between weight positions and a single, heavy weight member 1090 leads to improvements in CG movement and MOI preservation. The small maximum separation between weight positions provides a smaller displacement of the weight member 1090 towards the heel 22 or toe 24 of the golf club head 1000, but the heavier weight member 1090 counterbalances the smaller displacement of the weight member 1090, allowing the user to shape golf ball flight by using a comparatively smaller weight member displacement while also preserving more of the total MOI and forgiveness of the golf club head 1000.
Table 1 below displays the positioning of the center of gravity (CG) 812 of an exemplary golf club head 1000 with a similar weight assembly, as the detachable weight 1090 is reconfigured within the weight assembly 1072. The golf club head CG 812 is displaced in terms of movement parallel to the x-axis 820, the y-axis 822, and the z-axis 824. The CG 812 differential movement in inches parallel to the X-axis is the CGx. The differential movement in inches parallel to the Y-axis is the CGy. The differential movement in inches relative to the Z-axis is the CGz. The results below were compiled from a 35 gram tungsten weight, a 199 g golf club head weight, and with 0.6 inches of reconfiguration (a 0.6 inch distance 1083 between threaded receivers) within the weight assembly 1072 relative to the central threaded receiver 1081b when the detachable weight 1090 is moved to either the heel-side threaded receiver 1081a or the toe-side threaded receiver 1081c.
Referring to Table 1, above, the movement of CGx is approximately 0.04 inch towards the heel 22 or 0.09 inch towards the toe 24 from the starting center position when the weight member 1090 is placed in either the heel-side threaded receiver 1081a or the toe-side threaded receiver 1081c. However, the movements of CGy and CGz are significantly smaller (less than 0.01 inch and 0.04 inch respectively).
In the exemplary golf club head 1000, each 0.01 inch of CGx shift towards either the heel 22 or toe 24 resulted in a ball flight bias of approximately 1 yard. For example, with the weight member 1090 in the heel-ward position, the approximately 0.09 inch CGx shift towards the heel produced a ball flight biased to fade from left-to-right (for a right handed golf club) approximately 9 yards more than the same golf club head 1000 with the weight member 1090 in the center position. Similarly, with the weight member 1090 in the toe-ward position, the approximately 0.04 inch CGx shift towards the toe 24 produced a ball flight biased to draw from right-to-left (for a right handed golf club) approximately 4 yards more than the same golf club head 1000 with the weight member 1090 in the center position.
The recessed channel 1074 of the weight assembly 1072 displaces a small amount of mass from the rear of the golf club head 1000. Many prior art golf club heads comprise weight channels disposed over a large surface area of the heel, rear, and toe that displace large amounts of mass from the rear of said prior art golf club heads, undesirably pushing the center of gravity of said prior art club heads far forward towards the face and decreasing forgiveness. Due to the compact design of the weight assembly 1072 of the present club head 1000, the amount of mass removed from the rear is negligible with respect to its effect on the club head CGz.
In one example, the CGz of the golf club head 1000 with the weight member 1090 detached was measured and compared to the center of gravity position of a similar golf club head devoid of a weight channel. The CGz of the club head with no weight channel was −1.632 inches (measured rearward of the strike face). The CGz of the club head comprising a weight channel 1074 but no weight member 1090 was −1.520 inches. Further, when the weight member 1090 was reintroduced into the exemplary golf club head 1000, the CGz position shifted all the way back to −2.041 inches. Introducing a compact weight channel 1074 by itself does bring the CG forward, however, this effect is negligible compared to the rearward CG shift achieved by introducing the heavy weight member 1090. The heavy weight member 1090 offsets the forward CGz shift of including the weight channel 1074 and positions the CG at a desirable depth to produce the desired ball flight while still providing a high level of forgiveness.
Further, the total moment of inertia or MOI decrease of the golf club head 1000 is minimized. Referring to Table 2, above, the change of total MOI for the same golf club head 1000 is a very small 3.4% decrease when the weight member 1090 is shifted to the heel-side threaded receiver 1081a, and the total golf club head MOI actually increases by 1.7% when the weight member 1090 is shifted to the toe-side threaded receiver 1091c. Thus, as the CG 812 of the golf club head 1000 is moved in a heelward or toeward direction, the forgiveness of the golf club head 1000 is largely preserved.
Referring to Table 3, above, a comparison of a similar, prior art golf club head has an 11.0% decrease in total golf club head MOI when the weight assembly is configured in a most heelward position, and 3.4% decrease when the weight assembly is configured in a most toeward position.
Further, the compact design of the overall structure of the weight assembly 1072 provides weight savings compared to the larger weight assemblies of prior art golf club heads. These weight savings allow the golf club head 1000 to comprise a greater overall volume without making the club head 1000 too heavy. Increasing the overall volume of the golf club head 1000 in this way increases MOI and provides a more forgiving golf club head 1000. Further, enabling a short weight channel 1072 that does not wrap around a significant portion of the heel and toe peripheries of the club head 1000 allows a greater portion of the club head 1000 to be formed by the non-metallic portion 1016. This creates even greater weight savings that can be reintroduced throughout the club head 1000 to further maximize MOI.
In one example, MOI values of an exemplary golf club head 1000 with a volume of 462 cubic centimeters and a compact weight assembly 1072 with a channel length 1076 of 1.84 inches were compared to a similar golf club head with a volume of 457 cubic centimeters and a weight assembly with a channel length of 4.65 inches. The exemplary golf club head 1000 with the higher overall volume and compact weight channel 1074 comprised a heel-to-toe moment of interia (Iyy) of 5655 g*cm2 and a crown-to-sole moment of inertia (Ixx) of 4272 g*cm2 while golf club head with the lower overall volume and the longer weight channel comprised a heel-to-toe moment of interia (Iyy) of only 5184 g*cm2 and a crown-to-sole moment of inertia (Ixx) of only 3503 g*cm2.
In some configurations, this “T” shaped design may further include one or more crown braces 1030 that extend between the weighted portion 1072 and a crown portion 1024 of the frame 32. The crown braces 1030 may serve to buttress the weighted portion 1072 against vertical motion throughout the dynamics of the swing and impact, while also stiffening the crown against different vibration modes. In some designs, the crown brace 1030 may further aid in manufacturing the first component (e.g., maintaining dimensional tolerances during a casting process).
With continued reference to
In one particular configuration, each panel 1100, 1102 may wrap around an outer peripheral edge 1104 (best shown in
In some embodiments, a first panel 1100 may be a heel-side body panel 1100 while a second panel 1102 may be a toe-side body panel 1102. The heel-side body panel 1100 may extend from a heel-side of the crown brace 1030 to a heel-side of the sole extension 1020 across the outer peripheral edge 1104. Likewise, the toe-side body panel 1102 may extend from a toe-side of the crown brace 1030 to a toe-side of the sole extension 1020 across the outer peripheral edge 1104.
As further shown in
As with many of the designs shown and discussed above, the structural layer 1056 of the design in
The polymeric panels 1100, 1102 may be secured to the first component, for example, by adhering the panel to a recessed feature, such as a flange or crown brace 1030. This technique is best shown in
Instead of using a metal crown brace 1030, some embodiments may alternatively use a polymeric crown brace to secure the adjacent panels 1100, 1102 together and stiffen the crown structure. In such an embodiment, the structural layer of one of the two panels may include a thickened portion that extends beyond the FRC resilient layer. When assembled, the adjacent panel may overlap this ledge much in the same way it is shown to overlap the metal crown brace 1030. The two panels may be secured to each other, for example, through the use of an adhesive, or alternatively by welding/fusing the thermoplastic from the adjacent parts to each other. Examples of suitable fusing techniques may include, for example, ultrasonic welding, spin welding, laser welding, or the like.
While the present disclosure primarily discusses the fabric reinforced composite resilient layer 1054 and the filled thermoplastic structural layer 1056 as being formed, in part, using a thermoplastic resin, in other embodiments, it may be possible to form similar designs with the use of a thermosetting resin (e.g., via a molding process such as compression molding of one or more prepregs or resin pre-forms, or through an injection molding process that is specifically tailored to thermosetting resins) or a cross-linked thermoplastic resin.
Furthermore, in some alternate embodiments, the composite body panels 1200, 1220 may be formed with only a reinforced composite resilient layer 1054 and without a filled thermoplastic structural layer 1056. For instance, the composite body panels 1200, 1220 may be formed from only compression-molded prepregs without a cooperating structural support layer 1056. In yet other embodiments, the composite body panels 1200, 1220 may be formed with only a filled thermoplastic layer, which may be manufactured through injection molding.
As shown in
Referring again to
In one configuration, the boundary lip 1314 may form a portion of the strikeface 30. For example, instead of simply providing a joint surface against which the lower peripheral edge of the first component strikeface may be secured, the boundary lip 1314 may instead extend upward and form a portion of the strikeface 30. In doing so, this boundary lip 1314 may operatively reinforce the polymeric face portion 1308. In some embodiments, the boundary lip 1314 may extend across at least 25% of the strikeface 30, or at least 50% of the strikeface 30, or at least 60% of the strikeface 30, or at least 70% of the strikeface 30, or at least 80% of the strikeface 30, or at least 90% of the strikeface, or across the entire strikeface 30. This metallic strikeface backing (i.e., formed by the boundary lip 1314) may have a thickness that is substantially thinner than the thickness of a conventional metal-only strikeface. In some embodiments, the metal strikeface backing may have an average thickness of between about 0.4 mm and about 1.2 mm or between about 0.4 mm and about 0.8 mm and may be bonded to the first component, for example, using an adhesive or an interlocking surface texture/overmolding interface.
As noted above, the first component 1302 may generally have a polymeric composite structure. This structure maybe similar to one or more of the designs discussed above and may include a fabric reinforced composite layer 1320 and/or one or more filled thermoplastic layers 1322. In one configuration, the first component 1302 may include a fabric reinforced layer 1320 that forms the outer surface 1324 of both the crown 18 and strikeface 30 (i.e., when the club head 1300 is fully assembled). To provide enhanced strength, particularly at the bend where the strikeface 30 meets the crown 18, the fabric reinforced layer 1320 may include a plurality of constituent fibers that extend continuously from a rear edge 1326 of the crown 18 to a bottom edge 1328 of the strikeface 30.
In some embodiments, the fabric reinforced layer 1320 (in this or any of the prior-mentioned embodiments) may comprise a plurality of discrete layers (i.e., plies) of unidirectional fabric that are stacked on each other to form a total thickness of the layer. Each unidirectional fabric ply may have an orientation that is expressed as the average longitudinal fiber direction/orientation of the fibers within that ply. In this construction, some of the plies should have an orientation that is nonparallel to plies that are directly adjacent (i.e., in a transverse/surface normal direction) layers. In the example shown in
In some embodiments, some or all of the first component 1302 may comprise a filled thermoplastic material that is formed through injection molding. For example, an injection molding process, such as generally illustrated in
As generally shown in
The fabric reinforced composite layers 1406 may each generally be formed by spreading (at 1408) a plurality of individual fibers such that they are all approximately parallel and co-planar. The spread fibers are then bound together in a resin matrix (at 1410) that is solidified or partially cured to form stock material. This stock material may then be die cut (at 1412) into a blank that is suitable to form or approximate the final component layer and optionally pre-molded (at 1414) into a shape that approximates the final contours of the component.
In one configuration, the filled thermoplastic layers 1406 may be formed by first injection molding a substantially uniform blank (at 1416) that has a regular shape and is designed to maximize the uniformity of discontinuous fiber orientation within the thermoplastic polymer resin. An example shape may be a bar where the mold is gated at a first longitudinal end and is vented at an opposite longitudinal end. From this stock, a component blank may be cut (at 1418) and optionally pre-molded (at 1420) into a shape that approximates the final contours of the component.
In general, the pre-molding steps 1414, 1420 may comprise, for example, vacuum forming, compression molding, and the like. In the case of thermoplastic resins, it may further require heating the component layer to a temperature above the glass transition temperature of the polymer prior to forming it on a mold.
With either component type (filled or fabric reinforced), the component may be cut from the stock such that the fiber direction is at a prescribed orientation relative to the component. In this manner, each constituent layer within the final structure may have an engineered primary strength dimension.
In still another configuration, instead of being injection molded into a stock material with uniform fiber orientation (i.e., and then cut from the stock material) the layer may be injection molded into a final or substantially final shape/geometry in a first instance (at 1422). In such a configuration, placement of gates, vents, flow leaders, and wells within the mold design may direct flow in such a manner to control fiber orientation in more complex ways (e.g., such as shown in
Following the creation of the individual constituent layers, one or more of the layers may be pre-heated (at 1424) prior to the layers being stacked (at 1426) and placed in a mold (at 1428). The preheating step may be more applicable when using a thermoplastic resin to bring the temperature of the polymer up closer to the glass transition temperature. Such pre-heating may be accomplished, for example, using radiant and/or convective heating. With some thermosetting resins, the pre-heating step may be omitted as it may prematurely initiate cross-linking of the polymer.
Once in the mold, the plurality of layers may be fused together through the application of heat and pressure (at 1430) to create a unitary laminate structure. In some embodiments, the laminate structure may comprise one, two, three, four, five, six, seven, eight, nine, ten, eleven, twelve, thirteen, fourteen, fifteen, sixteen, seventeen, eighteen, nineteen, or twenty composite layers/sheets/plies. In other embodiments, the composite structure may contain between 20 and 40, or between 40 and 60 layers/sheets/plies.
In some embodiments, one or more layers may have a non-uniform thickness, or may extend across only a portion of the created component. For example, in the component illustrated in
In one embodiment, the reinforcing fibers in the fiber reinforced composite may specifically comprise a pitch-based carbon fiber, which has a higher modulus of elasticity than more commonly used polyacrylonitrile (PAN) carbon fibers. Further, in some embodiments, each pre compression molded layer of fabric reinforced composite may have a fiber areal weight (FAW) of less than about 15 g/m2, or less than about 10 g/m2 or less than about 7 g/m2, or between about 5 g/m2 and about 20 g/m2, or between about 7 g/m2 and about 15 g/m2, or between about 5 g/m2 and about 10 g/m2, or about 7 g/m2. A prepreg with this FAW may typically involve a fabric having an average thickness that is approximately equal to between 1.0 and about 2.5 times the diameter of a single fiber. Such a prepreg is different than conventional fabric reinforced prepregs that have a FAW of between about 75 g/m2 and about 150 g/m2, which may have a thickness that is at least 5-15 times the diameter of a single fiber. By using thinner prepregs, greater control of dimensional strength properties may be achieved while at the same time minimizing the ability for transverse cracks to propagate through the structure. In doing so, the desired design strength may be achieved via lighter and thinner overall structures. For example, in one embodiment, a pitch-based carbon fiber fabric reinforced crown portion, having a FAW of about 7 g/m2 per layer, may achieve suitable design strength at an average thickness of about 0.007 inch (about 0.177 mm).
With general reference to any of the embodiments described above that include a fabric reinforced composite resilient layer, it should be appreciated that any of these layers may be constructed using the techniques described in
As noted above, while the present designs may be formed using thermosetting polymeric resins, thermoplastic resins provide several distinct advantages. For example, thermoplastics provide easier and longer-term storage options for intermediate layers and stock inventory. Conversely, thermosetting prepregs have a finite shelf life due to tendency for the polymer chains to gradually cross-link. Also precured/partially cured thermosets tend to be mildly tacky, which may require more care when storing. Finally, thermoplastic resins may be more easily recycled, both in terms of manufacturing waste (e.g., defect parts, molding scrap, off cuts), and in terms of post-consumer waste.
Replacement of one or more claimed elements constitutes reconstruction and not repair. Additionally, benefits, other advantages, and solutions to problems have been described with regard to specific embodiments. The benefits, advantages, solutions to problems, and any element or elements that may cause any benefit, advantage, or solution to occur or become more pronounced, however, are not to be construed as critical, required, or essential features or elements of any or all of the claims, unless such benefits, advantages, solutions, or elements are expressly stated in such claims.
As the rules to golf may change from time to time (e.g., new regulations may be adopted or old rules may be eliminated or modified by golf standard organizations and/or governing bodies such as the United States Golf Association (USGA), the Royal and Ancient Golf Club of St. Andrews (R&A), etc.), golf equipment related to the apparatus, methods, and articles of manufacture described herein may be conforming or non-conforming to the rules of golf at any particular time. Accordingly, golf equipment related to the apparatus, methods, and articles of manufacture described herein may be advertised, offered for sale, and/or sold as conforming or non-conforming golf equipment. The apparatus, methods, and articles of manufacture described herein are not limited in this regard.
While the above examples may be described in connection with an iron-type golf club, the apparatus, methods, and articles of manufacture described herein may be applicable to other types of golf club such as a driver wood-type golf club, a fairway wood-type golf club, a hybrid-type golf club, an iron-type golf club, a wedge-type golf club, or a putter-type golf club.
Moreover, embodiments and limitations disclosed herein are not dedicated to the public under the doctrine of dedication if the embodiments and/or limitations: (1) are not expressly claimed in the claims; and (2) are or are potentially equivalents of express elements and/or limitations in the claims under the doctrine of equivalents.
This builds upon the disclosure provided in U.S. patent application Ser. No. 17/094,722, filed on Nov. 10, 2020, which is a continuation of U.S. patent application Ser. No. 16/252,349, filed on Jan. 18, 2019, now U.S. Pat. No. 10,828,543, issued Nov. 10, 2020, which claims the benefit of priority from U.S. Provisional Patent Application Nos. 62/619,631 filed 19 Jan. 2018; 62/644,319 filed 16 Mar. 2018; 62/702,996 filed 25 Jul. 2018; 62/703,305 filed 25 Jul. 2018; 62/718,857 filed 14 Aug. 2018; 62/770,000 filed 20 Nov. 2018; 62/781,509 filed 18 Dec. 2018; and 62/781,513 filed 18 Dec. 2018. U.S. patent application Ser. No. 16/252,349 is a continuation-in-part of U.S. patent application Ser. No. 15/901,081, filed on Feb. 21, 2018, now U.S. Pat. No. 10,300,354, issued May 28, 2019, which is a continuation of U.S. patent application Ser. No. 15/607,166, filed on May 26, 2017, now U.S. Pat. No. 9,925,432, issued Mar. 27, 2018, which claims the benefit of priority from U.S. Provisional Patent No. 62/324,741, filed May 27, 2016. This application is also a continuation-in-part of U.S. patent application Ser. No. 17/105,459, filed Nov. 25, 2020, which is a continuation-in-part of PCT Application No. PCT/US2020/043483, filed Jul. 24, 2020, which claims the benefit of priority from U.S. Provisional Patent Appl. No. 62/8878,263, filed Jul. 24, 2019. PCT Application No. PCT/US2020/043483 is a continuation-in-part of U.S. patent application Ser. No. 16/789,261, filed Feb. 12, 2020, which is a continuation of U.S. patent application Ser. No. 16/215,474, filed on Dec. 10, 2018, now U.S. Pat. No. 10,596,427, issued Mar. 24, 2020, which claims the benefit of priority from U.S. Provisional Patent No. 62/596,677, filed on Dec. 8, 2017. U.S. patent application Ser. No. 17/105,459 is also a continuation-in-part of PCT Application No. PCT/US2020/047702, filed on Aug. 24, 2020, which claims the benefit of priority from U.S. Provisional Patent No. 62/891,158, filed on Aug. 23, 2019. U.S. patent application Ser. No. 17/105,459 also claims the benefit of priority from U.S. Provisional Application Nos. 62/940,799, filed Nov. 26, 2019; 62/976,229, filed Feb. 13, 2020; and 63/015,398, filed Apr. 24, 2020. This application is also a continuation-in-part of U.S. patent application Ser. No. 16/724,176, filed on Dec. 20, 2019, which claims the benefit of priority from U.S. Provisional Patent Appl. Nos. 62/878,263, filed Jul. 24, 2019; 62/855,751, filed May 31, 2019; 62/784,190, Dec. 21, 2018; and 62/784,265, filed Dec. 21, 2018 U.S. patent application Ser. No. 16/724,176 is also a continuation-in-part of U.S. patent application Ser. No. 16/215,474, filed on Dec. 10, 2018, now U.S. Pat. No. 10,596,427, issued Mar. 24, 2020, which claims the benefit of priority from U.S. Provisional Patent No. 62/596,677, filed on Dec. 8, 2017. This application also claims the benefit of priority from U.S. Provisional Patent Nos. 62/976,992, filed Feb. 14, 2020 and 63/050,692, filed Jul. 10, 2020. The disclosure of each of the above-referenced applications is incorporated by reference in its entirety.
| Number | Name | Date | Kind |
|---|---|---|---|
| 1538312 | William | May 1925 | A |
| 4581190 | Nagamoto et al. | Apr 1986 | A |
| 4664383 | Aizawa | May 1987 | A |
| 4867458 | Sumikawa | Sep 1989 | A |
| 5080366 | Okumoto et al. | Jan 1992 | A |
| 5193811 | Okumoto et al. | Mar 1993 | A |
| 5328176 | Lo | Jul 1994 | A |
| 5586949 | Aizawa | Dec 1996 | A |
| 5614143 | Hager | Mar 1997 | A |
| 5624331 | Lo et al. | Apr 1997 | A |
| 5669827 | Nagamoto | Sep 1997 | A |
| 6354962 | Galloway et al. | Mar 2002 | B1 |
| 6354963 | Kodama et al. | Mar 2002 | B1 |
| 6368234 | Galloway | Apr 2002 | B1 |
| 6381828 | Boyce et al. | May 2002 | B1 |
| 6390933 | Galloway et al. | May 2002 | B1 |
| 6435977 | Helmstetter et al. | Aug 2002 | B1 |
| 6440011 | Hocknell et al. | Aug 2002 | B1 |
| 6471604 | Hocknell et al. | Oct 2002 | B2 |
| 6491592 | Cackett et al. | Dec 2002 | B2 |
| 6565452 | Helmstetter et al. | May 2003 | B2 |
| 6575845 | Galloway et al. | Jun 2003 | B2 |
| 6582323 | Soracco et al. | Jun 2003 | B2 |
| 6602149 | Jacobson | Aug 2003 | B1 |
| 6605007 | Bissonnette et al. | Aug 2003 | B1 |
| 6648772 | Vincent | Nov 2003 | B2 |
| 6648774 | Lee | Nov 2003 | B1 |
| 6663504 | Hocknell et al. | Dec 2003 | B2 |
| 6739982 | Murphy et al. | May 2004 | B2 |
| 6739983 | Helmstetter et al. | May 2004 | B2 |
| 6743118 | Soracco | Jun 2004 | B1 |
| 6758763 | Murphy et al. | Jul 2004 | B2 |
| 6783466 | Seki et al. | Aug 2004 | B2 |
| 6860823 | Lee | Mar 2005 | B2 |
| 6860824 | Evans | Mar 2005 | B2 |
| 6872152 | Beach | Mar 2005 | B2 |
| 6926619 | Helmstetter et al. | Aug 2005 | B2 |
| 6929565 | Nakahara et al. | Aug 2005 | B2 |
| 6945876 | Nakahara et al. | Sep 2005 | B2 |
| 6994637 | Murphy et al. | Feb 2006 | B2 |
| 7025692 | Erickson et al. | Apr 2006 | B2 |
| 7029403 | Rice et al. | Apr 2006 | B2 |
| 7056228 | Beach | Jun 2006 | B2 |
| 7059973 | Erickson et al. | Jun 2006 | B2 |
| 7066835 | Evans | Jun 2006 | B2 |
| 7101289 | Gibbs et al. | Sep 2006 | B2 |
| 7108614 | Lo | Sep 2006 | B2 |
| 7115047 | Stevens et al. | Oct 2006 | B2 |
| 7118493 | Galloway | Oct 2006 | B2 |
| 7121955 | Stevens et al. | Oct 2006 | B2 |
| 7121957 | Hocknell et al. | Oct 2006 | B2 |
| 7125344 | Hocknell et al. | Oct 2006 | B2 |
| 7128661 | Soracco et al. | Oct 2006 | B2 |
| 7128664 | Dnoda et al. | Oct 2006 | B2 |
| 7137907 | Gibbs | Nov 2006 | B2 |
| 7144333 | Murphy et al. | Dec 2006 | B2 |
| 7147576 | Imamoto et al. | Dec 2006 | B2 |
| 7163468 | Gibbs et al. | Jan 2007 | B2 |
| 7163470 | Galloway et al. | Jan 2007 | B2 |
| 7166038 | Williams et al. | Jan 2007 | B2 |
| 7166041 | Evans | Jan 2007 | B2 |
| 7169060 | Stevens et al. | Jan 2007 | B2 |
| 7175541 | Lo | Feb 2007 | B2 |
| 7214142 | Meyer et al. | May 2007 | B2 |
| 7252599 | Hasegawa et al. | Aug 2007 | B2 |
| 7252600 | Murphy et al. | Aug 2007 | B2 |
| 7255654 | Murphy et al. | Aug 2007 | B2 |
| 7258624 | Kobayashi | Aug 2007 | B2 |
| 7258625 | Kawaguchi et al. | Aug 2007 | B2 |
| 7261645 | Oyama | Aug 2007 | B2 |
| 7278927 | Gibbs et al. | Oct 2007 | B2 |
| 7297072 | Meyer et al. | Nov 2007 | B2 |
| 7303487 | Kumamoto | Dec 2007 | B2 |
| 7311613 | Stevens et al. | Dec 2007 | B2 |
| 7318782 | Imamoto et al. | Jan 2008 | B2 |
| 7320646 | Galloway | Jan 2008 | B2 |
| 7338390 | Lindsay | Mar 2008 | B2 |
| 7344452 | Imamoto et al. | Mar 2008 | B2 |
| 7367900 | Kumamoto | May 2008 | B2 |
| 7377860 | Breier et al. | May 2008 | B2 |
| 7387577 | Murphy et al. | Jun 2008 | B2 |
| 7402112 | Galloway | Jul 2008 | B2 |
| 7407448 | Stevens et al. | Aug 2008 | B2 |
| 7438647 | Hocknell | Oct 2008 | B1 |
| 7438649 | Ezaki et al. | Oct 2008 | B2 |
| 7448964 | Schweigert et al. | Nov 2008 | B2 |
| 7455600 | Imamoto et al. | Nov 2008 | B2 |
| 7468005 | Kouno | Dec 2008 | B2 |
| 7470201 | Nakahara et al. | Dec 2008 | B2 |
| 7488261 | Cackett et al. | Feb 2009 | B2 |
| 7491134 | Murphy et al. | Feb 2009 | B2 |
| 7494424 | Williams et al. | Feb 2009 | B2 |
| 7497788 | Imamoto et al. | Mar 2009 | B2 |
| 7497789 | Burnett et al. | Mar 2009 | B2 |
| 7510485 | Yamamoto | Mar 2009 | B2 |
| 7520822 | Yamagishi et al. | Apr 2009 | B2 |
| 7524249 | Breier et al. | Apr 2009 | B2 |
| 7530901 | Imamoto et al. | May 2009 | B2 |
| 7530903 | Imamoto et al. | May 2009 | B2 |
| 7540812 | Imamoto et al. | Jun 2009 | B2 |
| 7549933 | Kumamoto | Jun 2009 | B2 |
| 7549935 | Foster et al. | Jun 2009 | B2 |
| 7559851 | Cackett et al. | Jul 2009 | B2 |
| 7568982 | Cackett et al. | Aug 2009 | B2 |
| 7582248 | Reyes et al. | Sep 2009 | B2 |
| 7591737 | Gibbs et al. | Sep 2009 | B2 |
| 7601078 | Mergy et al. | Oct 2009 | B2 |
| 7607992 | Nishio | Oct 2009 | B2 |
| 7611424 | Nagai | Nov 2009 | B2 |
| 7632193 | Thielen | Dec 2009 | B2 |
| 7632195 | Jorgensen | Dec 2009 | B2 |
| 7658686 | Soracco | Feb 2010 | B2 |
| 7674187 | Cackett et al. | Mar 2010 | B2 |
| 7691008 | Oyama | Apr 2010 | B2 |
| 7708652 | Cackett et al. | May 2010 | B2 |
| 7749096 | Gibbs et al. | Jul 2010 | B2 |
| 7749103 | Nakano | Jul 2010 | B2 |
| 7775903 | Kawaguchi et al. | Aug 2010 | B2 |
| 7785212 | Lukasiewicz et al. | Aug 2010 | B2 |
| 7803065 | Breier et al. | Sep 2010 | B2 |
| 7854364 | DeShiell et al. | Dec 2010 | B2 |
| 7922604 | Roach et al. | Apr 2011 | B2 |
| 7931546 | Bennett et al. | Apr 2011 | B2 |
| 7938740 | Breier et al. | May 2011 | B2 |
| 7938742 | Galloway et al. | May 2011 | B2 |
| 7946929 | Wahlin et al. | May 2011 | B2 |
| 7959522 | North, III | Jun 2011 | B2 |
| 7959523 | Rae et al. | Jun 2011 | B2 |
| 7967591 | Reyes et al. | Jun 2011 | B2 |
| 7993216 | Lee | Aug 2011 | B2 |
| 8007371 | Breier et al. | Aug 2011 | B2 |
| 8025591 | Cruz et al. | Sep 2011 | B2 |
| 8197357 | Rice et al. | Jun 2012 | B1 |
| 8197358 | Watson et al. | Jun 2012 | B1 |
| 8221261 | Curtis et al. | Jul 2012 | B2 |
| 8267808 | De La Cruz et al. | Sep 2012 | B2 |
| 8303433 | Roach et al. | Nov 2012 | B2 |
| 8308582 | Tanimoto | Nov 2012 | B2 |
| 8376876 | Gibbs et al. | Feb 2013 | B2 |
| 8388464 | Gilbert et al. | Mar 2013 | B2 |
| 8414422 | Peralta et al. | Apr 2013 | B2 |
| 8419569 | Bennett et al. | Apr 2013 | B2 |
| 8425827 | Lee | Apr 2013 | B2 |
| 8435137 | Hirano | May 2013 | B2 |
| 8444506 | Watson et al. | May 2013 | B2 |
| 8460123 | DeMille et al. | Jun 2013 | B1 |
| 8491416 | DeMille et al. | Jul 2013 | B1 |
| 8506421 | Stites et al. | Aug 2013 | B2 |
| 8517859 | Golden et al. | Aug 2013 | B2 |
| 8523705 | Breier et al. | Sep 2013 | B2 |
| 8540588 | Rice et al. | Sep 2013 | B2 |
| 8556746 | DeMille et al. | Oct 2013 | B1 |
| 8585514 | Boyd | Nov 2013 | B2 |
| 8608591 | Chao | Dec 2013 | B2 |
| 8632419 | Tang et al. | Jan 2014 | B2 |
| 8632420 | Kawaguchi et al. | Jan 2014 | B2 |
| 8696489 | Gibbs et al. | Apr 2014 | B2 |
| 8702534 | DeMille et al. | Apr 2014 | B2 |
| 8715109 | Bennett et al. | May 2014 | B2 |
| 8727911 | Demille et al. | May 2014 | B2 |
| 8747253 | Stites | Jun 2014 | B2 |
| 8753219 | Gilbert et al. | Jun 2014 | B2 |
| 8753226 | Rice et al. | Jun 2014 | B2 |
| 8790196 | Solheim et al. | Jul 2014 | B2 |
| 8814723 | Tavares et al. | Aug 2014 | B2 |
| 8858362 | Leposky et al. | Oct 2014 | B1 |
| 8870680 | Yamamoto | Oct 2014 | B2 |
| 8870683 | Hettinger et al. | Oct 2014 | B2 |
| 8876629 | Deshmukh et al. | Nov 2014 | B2 |
| 8926450 | Takahashi et al. | Jan 2015 | B2 |
| 8938871 | Roach et al. | Jan 2015 | B2 |
| 8939848 | Soracco et al. | Jan 2015 | B2 |
| 8979671 | DeMille et al. | Mar 2015 | B1 |
| 9174098 | Hayase | Mar 2015 | B2 |
| 9033818 | Myrhum et al. | May 2015 | B2 |
| 9033822 | DeMille et al. | May 2015 | B1 |
| 9079368 | Tavares et al. | Jul 2015 | B2 |
| 9168435 | Boggs et al. | Oct 2015 | B1 |
| 9192826 | Golden et al. | Nov 2015 | B2 |
| 9199137 | Deshmukh et al. | Dec 2015 | B2 |
| 9320949 | Golden et al. | Apr 2016 | B2 |
| 9352198 | Roach et al. | May 2016 | B2 |
| 9393465 | Stokke et al. | Jul 2016 | B2 |
| 9399157 | Greensmith | Jul 2016 | B2 |
| 9427631 | Larson et al. | Aug 2016 | B1 |
| 9457245 | Lee | Oct 2016 | B2 |
| 9504883 | DeMille et al. | Nov 2016 | B2 |
| 9526955 | DeMille et al. | Dec 2016 | B2 |
| 9533200 | Dolezel et al. | Jan 2017 | B2 |
| 9545548 | Petersen et al. | Jan 2017 | B2 |
| 9579548 | Boyd et al. | Feb 2017 | B2 |
| 9586104 | Roach et al. | Mar 2017 | B2 |
| 9682291 | Chao | Jun 2017 | B2 |
| 9682299 | Tang et al. | Jun 2017 | B2 |
| 9694256 | Myers | Jul 2017 | B2 |
| 9717960 | Deshmukh et al. | Aug 2017 | B2 |
| 9724573 | Kawaguchi et al. | Aug 2017 | B2 |
| 9833666 | Boggs et al. | Dec 2017 | B2 |
| 9849347 | Sander | Dec 2017 | B2 |
| 9861866 | DeMille et al. | Jan 2018 | B2 |
| 9908014 | Wester | Mar 2018 | B1 |
| 9925432 | Morales | Mar 2018 | B2 |
| 10004958 | Tang | Jun 2018 | B2 |
| 10046212 | Sargent et al. | Aug 2018 | B2 |
| 10137335 | Hope et al. | Nov 2018 | B2 |
| 10143898 | Cornelius et al. | Dec 2018 | B2 |
| 10155144 | Lee | Dec 2018 | B2 |
| 10300354 | Morales et al. | May 2019 | B2 |
| 10357901 | Deshmukh et al. | Jul 2019 | B2 |
| 10369437 | Cleghorn | Aug 2019 | B1 |
| 10463928 | Stokke | Nov 2019 | B2 |
| 10596427 | Jertson | Mar 2020 | B2 |
| 10639524 | Penney | May 2020 | B2 |
| 10675514 | Spackman | Jun 2020 | B2 |
| 10765922 | Morales | Sep 2020 | B2 |
| 10806977 | Spackman | Oct 2020 | B2 |
| 10828543 | Morales | Nov 2020 | B2 |
| 10940373 | Milleman | Mar 2021 | B2 |
| 10940374 | Milleman | Mar 2021 | B2 |
| 10953294 | Jertson | Mar 2021 | B2 |
| 10974109 | Stokke | Apr 2021 | B2 |
| 10987551 | Morales | Apr 2021 | B2 |
| 11110325 | Spackman | Sep 2021 | B2 |
| 11235210 | Spackman | Feb 2022 | B2 |
| 11278775 | Morales | Mar 2022 | B2 |
| 20010049310 | Cheng | Dec 2001 | A1 |
| 20030186760 | Lee | Oct 2003 | A1 |
| 20040005936 | Imamoto | Jan 2004 | A1 |
| 20040033844 | Chen | Feb 2004 | A1 |
| 20040116207 | Shiell et al. | Jun 2004 | A1 |
| 20040176177 | Mahaffey | Sep 2004 | A1 |
| 20050026719 | Yang | Feb 2005 | A1 |
| 20050043115 | Lin | Feb 2005 | A1 |
| 20050143189 | Lai et al. | Jun 2005 | A1 |
| 20050159239 | Imamoto et al. | Jul 2005 | A1 |
| 20050233831 | Ezaki et al. | Oct 2005 | A1 |
| 20060052181 | Serrano et al. | Mar 2006 | A1 |
| 20060089206 | Lo | Apr 2006 | A1 |
| 20070155533 | Solheim et al. | Jul 2007 | A1 |
| 20070293344 | Davis | Dec 2007 | A1 |
| 20080139339 | Cheng | Jun 2008 | A1 |
| 20080293512 | Chen | Nov 2008 | A1 |
| 20090062032 | Boyd | Mar 2009 | A1 |
| 20110070964 | Stites | Mar 2011 | A1 |
| 20110070970 | Wan | Mar 2011 | A1 |
| 20120021848 | Watson | Jan 2012 | A1 |
| 20120064991 | Evans | Mar 2012 | A1 |
| 20120083359 | Stites | Apr 2012 | A1 |
| 20130040755 | Stites | Feb 2013 | A1 |
| 20150297960 | Goudarzi | Oct 2015 | A1 |
| 20150306473 | Breier | Oct 2015 | A1 |
| 20160332040 | Lafortune et al. | Nov 2016 | A1 |
| 20170128797 | Nivanh | May 2017 | A1 |
| 20170340932 | Morales | Nov 2017 | A1 |
| 20180140916 | Sillies | May 2018 | A1 |
| 20190134472 | Stokke | May 2019 | A1 |
| 20210001191 | Bamber | Jan 2021 | A1 |
| Number | Date | Country |
|---|---|---|
| 2004024734 | Jan 2004 | JP |
| 2006271770 | Oct 2006 | JP |
| 2013009713 | Jan 2013 | JP |
| 2007076304 | Jul 2007 | WO |
| 2017205699 | May 2016 | WO |
| Entry |
|---|
| E9 Face Technology With Dual Roll—Multi-material Construction, Cobra Golf, accessed Oct. 19, 2017; https:/lwww.cobragolf.com/pumagolf/tech—overview. |
| Taylormade M1 Driver, Multi-material Construction, accessed Jun. 7, 2016; http://www.intheholegolf.com/TM15-M1D/TaylorMade-M1-Driver.html. |
| Adams Men's Golf Speedline Super XTD Fairway Wood; Amazon, accessed Oct. 19, 2017; https://www.amazon.com/Adams-Golf-Speedline-SUPER-Fairway/dp/B007LI2S04. |
| Callaway Womens Great Big Bertha Driver, Amazon, accessed Oct. 19, 2017; https://www.amazon.com/Callaway-Womens-Great-Bertha-Driver/dp/B013SYR0VQ. |
| Nike Vapor Flex 440 Driver Adjustable Loft Golf Club Left Hand, accessed Jun. 7, 2016; http://www.globalgolf.com/golf-clubs/1034365-nike-vapor-flex-440-driver-left-hand/. |
| International Search Report and Written Opinion of the International Searching Authority from PCT Application No. PCT/US19/14321, dated May 9, 2019. |
| International Search Report and Written Opinion of the International Searching Authority from PCT Application No. PCT/US19/14326, dated May 23, 2019. |
| International Search Report and Written Opinion of the International Searching Authority from PCT Application No. PCT/US17/34807, dated May 27, 2016. |
| Number | Date | Country | |
|---|---|---|---|
| 20210162280 A1 | Jun 2021 | US |
| Number | Date | Country | |
|---|---|---|---|
| 62976992 | Feb 2020 | US | |
| 63050692 | Jul 2020 | US | |
| 62342741 | May 2016 | US | |
| 62619631 | Jan 2018 | US | |
| 62644319 | Mar 2018 | US | |
| 62702996 | Jul 2018 | US | |
| 62703305 | Jul 2018 | US | |
| 62718857 | Aug 2018 | US | |
| 62770000 | Nov 2018 | US | |
| 62781509 | Dec 2018 | US | |
| 62781513 | Dec 2018 | US | |
| 62596677 | Dec 2017 | US | |
| 62878263 | Jul 2019 | US | |
| 62940799 | Nov 2019 | US | |
| 62976229 | Feb 2020 | US | |
| 63015398 | Apr 2020 | US | |
| 62891158 | Aug 2019 | US | |
| 62855751 | May 2019 | US | |
| 62784190 | Dec 2018 | US | |
| 62784265 | Dec 2018 | US |
| Number | Date | Country | |
|---|---|---|---|
| Parent | 16252349 | Jan 2019 | US |
| Child | 17094722 | US | |
| Parent | 15607166 | May 2017 | US |
| Child | 15901081 | US | |
| Parent | 17176107 | US | |
| Child | 15901081 | US | |
| Parent | 16215474 | Dec 2018 | US |
| Child | 16789261 | US |
| Number | Date | Country | |
|---|---|---|---|
| Parent | 17094722 | Nov 2020 | US |
| Child | 17176107 | US | |
| Parent | 15901081 | Feb 2018 | US |
| Child | 16252349 | US | |
| Parent | 17105459 | Nov 2020 | US |
| Child | 17176107 | US | |
| Parent | PCT/US2020/043483 | Jul 2020 | US |
| Child | 17105459 | US | |
| Parent | 16789261 | Feb 2020 | US |
| Child | PCT/US2020/043483 | US | |
| Parent | PCT/US2020/047702 | Aug 2020 | US |
| Child | 16215474 | US | |
| Parent | PCT/US2020/047702 | Aug 2020 | US |
| Child | 17105459 | US | |
| Parent | 17176107 | US | |
| Child | 17105459 | US | |
| Parent | 16724176 | Dec 2019 | US |
| Child | 17176107 | US | |
| Parent | 16215474 | Dec 2018 | US |
| Child | 16724176 | US |
