US20100075074A1 - Collapsible Mandrel Tools and Associated Methods for Fabrication of Wound Composite Articles - Google Patents
Collapsible Mandrel Tools and Associated Methods for Fabrication of Wound Composite Articles Download PDFInfo
- Publication number
- US20100075074A1 US20100075074A1 US12/542,613 US54261309A US2010075074A1 US 20100075074 A1 US20100075074 A1 US 20100075074A1 US 54261309 A US54261309 A US 54261309A US 2010075074 A1 US2010075074 A1 US 2010075074A1
- Authority
- US
- United States
- Prior art keywords
- mandrel
- grooves
- collapsible mandrel
- enclosure
- collapsible
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
- B29C53/56—Winding and joining, e.g. winding spirally
- B29C53/58—Winding and joining, e.g. winding spirally helically
- B29C53/583—Winding and joining, e.g. winding spirally helically for making tubular articles with particular features
- B29C53/587—Winding and joining, e.g. winding spirally helically for making tubular articles with particular features having a non-uniform wall-structure, e.g. with inserts, perforations, locally concentrated reinforcements
-
- E—FIXED CONSTRUCTIONS
- E04—BUILDING
- E04C—STRUCTURAL ELEMENTS; BUILDING MATERIALS
- E04C3/00—Structural elongated elements designed for load-supporting
- E04C3/02—Joists; Girders, trusses, or trusslike structures, e.g. prefabricated; Lintels; Transoms; Braces
- E04C3/28—Joists; Girders, trusses, or trusslike structures, e.g. prefabricated; Lintels; Transoms; Braces of materials not covered by groups E04C3/04 - E04C3/20
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/42—Moulds or cores; Details thereof or accessories therefor characterised by the shape of the moulding surface, e.g. ribs or grooves
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/44—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles
- B29C33/48—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling
- B29C33/485—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles with means for collapsing or disassembling cores or mandrels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
- B29C53/80—Component parts, details or accessories; Auxiliary operations
- B29C53/82—Cores or mandrels
- B29C53/821—Mandrels especially adapted for winding and joining
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/20—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres
- B29C70/205—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in a single direction, e.g. roofing or other parallel fibres the structure being shaped to form a three-dimensional configuration
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B1/00—Layered products having a general shape other than plane
- B32B1/08—Tubular products
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
- B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
- B32B3/28—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by a layer comprising a deformed thin sheet, i.e. the layer having its entire thickness deformed out of the plane, e.g. corrugated, crumpled
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
- B32B37/1018—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure using only vacuum
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
- B32B5/12—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer characterised by the relative arrangement of fibres or filaments of different layers, e.g. the fibres or filaments being parallel or perpendicular to each other
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
- B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
-
- E—FIXED CONSTRUCTIONS
- E04—BUILDING
- E04B—GENERAL BUILDING CONSTRUCTIONS; WALLS, e.g. PARTITIONS; ROOFS; FLOORS; CEILINGS; INSULATION OR OTHER PROTECTION OF BUILDINGS
- E04B1/00—Constructions in general; Structures which are not restricted either to walls, e.g. partitions, or floors or ceilings or roofs
- E04B1/18—Structures comprising elongated load-supporting parts, e.g. columns, girders, skeletons
- E04B1/19—Three-dimensional framework structures
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/13—Hollow or container type article [e.g., tube, vase, etc.]
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/13—Hollow or container type article [e.g., tube, vase, etc.]
- Y10T428/131—Glass, ceramic, or sintered, fused, fired, or calcined metal oxide or metal carbide containing [e.g., porcelain, brick, cement, etc.]
- Y10T428/1314—Contains fabric, fiber particle, or filament made of glass, ceramic, or sintered, fused, fired, or calcined metal oxide, or metal carbide or other inorganic compound [e.g., fiber glass, mineral fiber, sand, etc.]
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/13—Hollow or container type article [e.g., tube, vase, etc.]
- Y10T428/1352—Polymer or resin containing [i.e., natural or synthetic]
- Y10T428/1362—Textile, fabric, cloth, or pile containing [e.g., web, net, woven, knitted, mesh, nonwoven, matted, etc.]
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
- Y10T428/24058—Structurally defined web or sheet [e.g., overall dimension, etc.] including grain, strips, or filamentary elements in respective layers or components in angular relation
- Y10T428/24124—Fibers
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
- Y10T428/24628—Nonplanar uniform thickness material
- Y10T428/24636—Embodying mechanically interengaged strand[s], strand-portion[s] or strand-like strip[s] [e.g., weave, knit, etc.]
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T442/00—Fabric [woven, knitted, or nonwoven textile or cloth, etc.]
- Y10T442/10—Scrim [e.g., open net or mesh, gauze, loose or open weave or knit, etc.]
Definitions
- the present invention relates to collapsible mandrel devices and their use in methods for fabrication of wound composite articles. Accordingly, the present invention involves the fields of chemistry, materials science, and engineering technology.
- Mandrels have been used for years in a variety of industries for performing many different tasks, such as lathing. Many other tasks are aided by the use of an elongated cylinder which turns about a longitudinal axis. On example of mandrel use is in shaping metal pipes or glass. Mandrels have also been used in making jewelry such as a rings or bracelets. In addition, mandrels have been used in the formation of fiber composite articles where the fibers are wound around the mandrel to create a tube and then further cured or processed into a finished article.
- a collapsible mandrel in accordance with the present invention may include a plurality of discrete segments coupled about a longitudinal axis and collectively forming an enclosure with a substantially continuous exterior working surface.
- the working surface can have a network of intersecting grooves formed therein which cooperatively establish a substantially continuous interconnected lattice corresponding to the three dimensional geometric configuration to be imparted to a composite article formed using the mandrel.
- the mandrel may further include a removable core assembly occupying an interior volume of the enclosure and coupling the segments together to form the enclosure.
- the interior volume can have a size sufficient to permit entry of a segment into a hollow portion thereof in order to allow the mandrel to collapse and be removed from the formed composite article.
- the present invention encompasses methods of shaping a fiber-based composite material to be consolidated into a three dimensional structure.
- a method may include: 1) providing a mandrel as disclosed herein; 2) filling the grooves of the working surface of the mandrel with a composite material; 3) consolidating the composite material in the grooves into a three dimensional structure substantially corresponding to the geometric configuration cooperatively established by the grooves; 4) collapsing the mandrel into pieces inside of the three dimensional consolidated structure; and 5) removing the mandrel pieces from within the consolidated structure.
- the present invention encompasses shaped fiber-based composite material assemblies.
- such an assembly may include: 1) a collapsible mandrel as recited herein; and 2) a fiber-based composite material preform filling the grooves of the interconnected lattice of the working surface of the enclosure on the mandrel.
- FIG. 1 is a longitudinal cross-sectional view of a collapsible mandrel in accordance with an embodiment of the present invention.
- FIG. 2 a - h is show schematic views of various groove intersection configurations in accordance with various embodiments of the present invention.
- FIG. 3 a - h shows various geometric configurations for the cross-section shape of the grooves in accordance with various embodiments of the present invention.
- FIG. 4 is a side perspective view of discrete segments to be assembled and collectively form an enclosure with a working surface for the mandrel in accordance with an embodiment of the present invention.
- FIG. 5 is a longitudinal perspective view of a mandrel in accordance with an embodiment of the present invention.
- FIG. 6 is a perspective view of a collapsible mandrel engaged with a finished composite article with one or more segments in a collapsed position for removal of the mandrel from the composite article in accordance with an embodiment of the present invention.
- fiber-based composite material refers to a material comprised of carbon or other fiber (e.g., a carbon or glass fiber filament) and resin (e.g., polymer matrix) constituents.
- preform refers to a green, uncured composite lay-up comprising the fiber material and resin composite as situated in grooves on a mandrel or other suitable mold, and that has undergone preliminary shaping but is not yet in its final consolidated or cured form.
- working surface refers to an exterior surface of a mandrel that is used to form, engage, sculpt, mold, hold, direct, guide, etc., a fiber-based composite material to be consolidated into a three dimensional article.
- Such working surface may have grooves or other technical or functional features formed therein and use of the term working surface refers to surfaces inside the grooves or other designs or features as well as those surfaces outside.
- the term “substantially” refers to the complete or nearly complete extent or degree of an action, characteristic, property, state, structure, item, or result.
- an object that is “substantially” enclosed would mean that the object is either completely enclosed or nearly completely enclosed.
- the exact allowable degree of deviation from absolute completeness may in some cases depend on the specific context. However, generally speaking the nearness of completion will be so as to have the same overall result as if absolute and total completion were obtained.
- the use of “substantially” is equally applicable when used in a negative connotation to refer to the complete or near complete lack of an action, characteristic, property, state, structure, item, or result.
- compositions that is “substantially free of” particles would either completely lack particles, or so nearly completely lack particles that the effect would be the same as if it completely lacked particles.
- a composition that is “substantially free of” an ingredient or element may still actually contain such item as long as there is no measurable effect thereof.
- the term “about” is used to provide flexibility to a numerical range endpoint by providing that a given value may be “a little above” or “a little below” the endpoint.
- the present invention provides mandrels for use in the fabrication of fiber-based composite articles. Examples of specific composite articles and methods for the fabrication thereof can be found in Applicants' copending U.S. Patent Applications filed Aug. 17, 2009 under Attorney Docket Nos. 3095-002.NP, 3095-003.NP, and 3095-006.NP, each of which is incorporated herein by reference.
- the mandrels of the present invention may be collapsible. In other embodiments they may be solid.
- FIG. 1 is shown a longitudinal cross-section view of a collapsible mandrel 10 , having a plurality of discrete segments 15 , coupled about a longitudinal axis and collectively forming an enclosure with a substantially continuous exterior working surface 20 .
- the working surface has a network of intersecting grooves 25 formed therein.
- the network of grooves cooperatively establish a substantially continuous interconnected lattice corresponding to a three dimensional geometric configuration to be imparted to a composite article formed using the mandrel.
- the core assembly includes a plurality of solid support members 35 and a central core 40 .
- the removable core assembly occupies the interior volume of the enclosure formed by the assembled segments and couples the segments together to form the enclosure. Further, the interior volume of the enclosure has a volume of sufficient size to permit entry of a segment into a hollow portion thereof in order to collapse the mandrel.
- the enclosure formed of segments 15 as shown in FIG. 1 is a substantially closed as the segments connect to or abut one another at the segment junctions 65 .
- the segments can be tightly fitted leaving no gap between them, or substantially no gap.
- the segments can be loosely fitted and a gap formed at the segment junctions 65 .
- the segments 15 used in forming the enclosure can take a variety of shapes and sizes as required in order to form an enclosure of desired dimensions and geometry and to also create a desired working surface configuration.
- the segments can be elongated and arcuate.
- the segments can be a half circle each and two of such shaped segments may be assembled opposite of one another in order to form a cylinder.
- four arcuate segments can be assembled in order to form a cylinder shape.
- the segments may be flat and have varying lengths.
- the segments could have other geometric configurations which lend themselves to assembly about a longitudinal axis using a removable core, such as triangular, rectangular, square, irregular, etc.
- the segments need not be all the same shape, but can be individually shaped and matched in order to produce a specific larger overall design, such as an airfoil, a wing, a hull, etc.
- the cooperation of segments 15 is relevant to the creation of the exterior working surface 20 of the enclosure as each segment has a working surface thereon.
- the working surface shape and dimensions will dictate at least in part, the configuration of the three dimensional composite article produced using the mandrel of the present invention.
- the exterior working surface of the enclosure can have a predetermined shape that matches a shape intended for the composite article.
- Such shapes can be custom configured in cooperation with the shape of the segments used in order to provide a working surface having a cross-section perpendicular to the longitudinal axis with a specific geometric form.
- geometric forms may include without limitation: a circle, and oval, an ellipse, a crescent, a triangle, a square, a rectangle, a pentagon, a hexagon, an octagon, a polygon, a star, and combination or variations thereof.
- the geometric form may be a circle.
- the geometric form may be a rectangle.
- the geometric form of the cross-section may be a square.
- the geometric form of the longitudinal cross-section may extend for substantially the entire length of the mandrel.
- mandrels with regular geometries of many different shapes may be formed, such as: a cylinder, a cone, a pyramid, a triangular prism, a rectangular prism, a pentagonal prism, a hexagonal prism, a heptagonal prism, an octagonal prism, etc.
- the working surface shape may be a cylinder.
- the shape may be an octagonal prism.
- the shape may be a rectangular prism.
- the geometric form of the longitudinal cross-section may extend for less than the entire length of the mandrel.
- various cross-section geometries may be assembled with appropriate transition areas there between.
- one portion of the working surface of the enclosure may be geometrically configured with a longitudinal cross-section of a square, while the longitudinal cross-section of a different portion of the working surface may be a circle with an appropriate transition portion in between.
- a single mandrel may include several sections with working surfaces each having different cross-sectional geometries and transitions as required in order to produce a composite article with a specific three dimensional configuration. This may be particularly true when forming an article with a custom geometric shape or irregular form, such as an airfoil, a wing, a propeller, a hull, a blade, etc.
- FIG. 5 is shown a longitudinal view of a mandrel 10 in accordance with one embodiment of the present invention.
- the working surface 20 has a network of intersecting grooves 25 formed therein.
- the grooves cooperatively form a substantially continuous interconnected lattice that corresponds or substantially corresponds, to a three dimensional geometric configuration to be imparted to a composite article formed using the mandrel.
- the lattice formed by the network of intersecting grooves may in some aspects employ several groove types, including longitudinally extending grooves (i.e. “longitudinals”), laterally extending grooves (i.e. “laterals”), or helically extending grooves (i.e. “helicals”).
- longitudinals are grooves running parallel to the longitudinal axis of the mandrel
- laterals are grooves running perpendicular to the longitudinal axis of the mandrel
- helicals are grooves running in any direction that is neither parallel nor perpendicular to the longitudinal axis of the mandrel.
- FIGS. 2 a - h show various possible intersection configurations for the grooves.
- 2 a shows an intersection of a longitudinal groove 45 and lateral groove 50 .
- FIG. 2 b shows an intersection of a longitudinal groove 45 with lateral grooves 55 .
- FIG. 2 c shows an intersection of a lateral groove 50 with helical grooves 55
- FIG. 2 d shows an intersection of longitudinal groove 45 with lateral groove 50 and helical grooves 55 .
- Other various specific cross section configurations are shown in FIGS. 2 e - 2 h.
- any lattice design required to produce a three dimensional product of specific configuration can be formed by the network of interconnected grooves on the working surface of the mandrel.
- the extent of the lattice along the working surface of the mandrel may also be controlled.
- the interconnected lattice of grooves can be an unbroken, or substantially unbroken, lattice extending substantially around the entire enclosure created by the segments.
- the lattice can be a broken lattice that extends around only a portion of the enclosure.
- the broken lattice can be extended around the majority of the enclosure, around at least half of the enclosure, around about two thirds of the enclosure, around at least three quarters of the enclosure.
- the lattice may be sectioned into specific groups or designs around various portions of the enclosure as desired.
- the cross-section shape of the grooves may be predetermined to correspond to a cross-section shape intended for individual supports contained in the composite article.
- the variation of such cross-section shapes can be used in order to impart various mechanical and physical characteristics or properties, such as certain compression strengths, etc. to the three dimensional composite article produced.
- the grooves 25 have a triangular cross-section shape with a sharp vertex at the bottom of the groove.
- FIGS. 3 a - h are shown various examples of possible groove cross-section shapes.
- Such examples include without limitation, a T shape with a flange at the top portion of the groove, a rectangle, a square, a triangle with a single vertex at the bottom of the groove, a half circle, a trapezoid with two obtuse angles at the bottom portion of the groove, a half pentagon with two obtuse angles at the bottom portion of the groove, a half hexagon with two obtuse angles at the bottom portion of the groove, a half octagon with three obtuse angles at the bottom portion of the groove, as well as others.
- the angles at the bottom of the grooves can have a sharp vertex or corners. In other embodiments, the angles at the bottom of the grooves can be rounded.
- the top portion of the groove will be wider than the bottom portion of the groove in order to facilitate release of the finished article out of the grooves and off the working surface upon collapse of the mandrel. This is especially true when the mandrel is made of a rigid material as more fully articulated below.
- the cross-section shape of the groove may be widest at a top portion of the groove and narrowest at a bottom portion of the groove. In some aspects, the width may be substantially the same at the top and bottom portions of the groove.
- the top of the groove may actually have a smaller width than the lower portions of the groove, such as the middle or bottom of the groove.
- the groove can be tapered from a narrow point at the top to a wider point at the bottom or middle.
- the grooves may include only obtuse angles or right angles.
- the grooves may include a plurality of obtuse angles at or near the bottom portion of the grooves.
- the cross-section shape of the grooves may include no acute angle smaller than about 20 degrees. Specific examples of acute angles that can be used at the bottom of the groove include without limitation angles from about 15 degrees to about 90 degrees. In some aspects, such angles may be about 45 degrees. In other aspects, the angles may be about 60 degrees. In yet other aspects, the angles may be about 22 degrees.
- the bottom of the groove may be rounded. In other aspects, the bottom of the groove may be one or more vertex. In yet another aspect, the bottom of the groove may be flat. In some aspects, the walls of the grooves may be vertical or substantially vertical. In some aspects, the walls of the grooves may be angled or substantially angled. In yet other aspects, the walls of the grooves may contain an angle, or may be rounded
- the dimension or size of the groove longitudinal cross-section can also be controlled along with cross-section shape, for example, the width of the groove and the depth of the groove.
- such characteristics may be manipulated to provide the article formed with specific characteristics, such as compression strength, lateral strength, etc.
- the grooves may have a depth of from about 0.1 inch to about 12 inches. In another aspect, the depth may be from about 0.1 inch to about 1 inch. In yet another aspect, the depth may be from about 0.05 inches to about 0.5 inches. Similar ranges may be used for the width of the grooves. In one aspect, the width may be from about 0.1 to about 12 inches. In another aspect, the width may be from about 0.1 inch to about 1 inch.
- the width may be from about 0.5 inches to about 0.5 inches.
- Such sizes will be selected based in part on the type of article being fabricated and the scale to which it must perform. For example, a boat hull may require grooves of a significantly different scale than those required for a bicycle handle bar.
- specific groove shape can be selected to work in combination with varied groove depth and width dimensions in order to achieve required specifications for processing and performance in the final article. For example, a deep groove may have a rounded bottom to facilitate easy removal of the article.
- the grooves forming the lattice on the working surface of the mandrel can all have substantially the same cross-section shape, or they may have different cross-sections.
- the longitudinal grooves may have a cross section that is different from the lateral grooves and the helical grooves.
- the longitudinal grooves may have T shaped sections while the lateral grooves and the helical grooves are a half circle.
- all the each groove type may have different shape and dimension, for example, the longitudinal grooves may have a rectangular shape while the lateral grooves have a triangle shape and the helical grooves have a circular shape.
- the same types of groove can have different shapes.
- some longitudinal grooves may have a T shape while others have a rectangle shape. A large variety of mixing and matching of groove cross-section shape and dimension is possible with the present invention.
- the exterior working surface of the segments of the present invention may be made from nearly any suitable material that can have a network of intersecting grooves formed therein.
- such materials may be rigid.
- such materials may be soft.
- rigid materials include without limitation, metals, ceramics, cured polymeric materials, composites, alloys, and mixtures thereof.
- metals and metalloids include without limitation, stainless steel, aluminum, tungeston, titanium, iron, magnesium, nickel, chromium, manganese, boron, silicon, and mixtures and alloys thereof.
- Ceramic or other superhard materials include without limitation, diamond, diamond-like carbon, silicon carbide, tungsten carbide, silicon nitride, aluminum oxide, boron nitride, cubic boron nitride (cBN), titanium carbide, as well as combinations thereof.
- cured polymers include without limitation acrylic and acrylate polymers, silicone polymers, epoxies, urethanes and polyurethanes, and rubber based polymers, among others, including combinations and mixtures thereof.
- composites include without limitation, fiber-resin composites, carbon fiber composites, particulate-polymer composites, etc.
- all of the segments, or exterior working surfaces of the segments may be made from the same materials (i.e. all are stainless steel, etc.). However, in other aspects, one or more segments may be made of a different material. In addition, when made of rigid materials, the segments may be reusable or multi-use segments. When made of softer materials, including softer materials or composites, the segments can be of limited time use, or of single use. Such segments are thought to be disposable and in some aspects can be sacrificed or destroyed as part of the collapsing process.
- the working surface including the grooves, or in some aspects, only the grooves can be provided with a lubricant.
- a lubricant can be temporarily applied prior to insertion of the fiber-based composite material into the grooves and/or onto the working surface (e.g. such as an oil, petroleum product, silicone lubricant, etc.), or such lubricant property can be more permanently affixed to the working surface (e.g. coating with a friction reducing polymer such as polytetrafluroethylene, etc.).
- the entire working surface may be coated. In other aspects, substantially all of the grooves of the working surface may be coated.
- FIG. 1 a cross-sectional view of the removable core assembly 30 .
- the core assembly occupies the interior volume of the enclosure formed by the segments 15 , and couples the segments together to form the enclosure.
- One example of a coupling mechanism that can be used is by screwing the segments to the core assembly. Screw holes, 60 can be seen in FIGS. 4 and 5 .
- a variety of other mechanisms, including adhesives, clips, etc. can be used to couple the segments to the core assembly.
- the core assembly 30 includes solid support members 35 and solid core 40 .
- Such support members fill substantially the entire interior volume of the enclosure.
- the core or one or more of the solid support members is pushed along the longitudinal axis and removed from the mandrel in order to create a hollow space of sufficient size to allow entry of one or more of the segments as part of the process of collapsing the mandrel.
- support members may be used which do not substantially file the entire interior volume of the enclosure and a hollow space may exist without removal of the core or any core pieces.
- the core assembly can consist of a single piece.
- the core assembly can include multiple integrated pieces. Such pieces can be coated with a lubricant or other friction reducing material in order to facilitate their removal from the mandrel. In other aspects, such pieces may be capable of manipulation within the enclosure in order to create or expand a hollow space and allow entry of one or more segments as shown in FIG. 6 .
- the core 40 has a specific configuration that keys the placement of specific supporting members which in turn may key the placement of the segments. Such keying can be useful in automating assembly of the segments into an enclosure with a specific working surface configuration.
- the core assembly can be non-keyed and can universally couple segments to allow interchangeability of segment location so that an operator can select and place segments at his discretion in the creation of a custom made working surface.
- such a method includes shaping a fiber-based composite material to be consolidated into a three dimensional structure.
- Such a method may include providing a mandrel as recited herein, filling the grooves with a composite material, or a composite material perform, consolidating the composite material into a three dimensional structure substantially corresponding to the geometric configuration cooperatively established by the grooves, collapsing the mandrel into pieces inside of the three dimensional consolidated structure, and removing the mandrel pieces from within the consolidated structure.
- FIG. 6 One example of a mandrel collapsed inside a consolidated structure is shown in FIG. 6 .
- the filling of the grooves with a composite material to be consolidated can include winding a carbon fiber or other fibrous material into the grooves of the mandrel and adding a curable resin to the fibrous material.
- the consolidation of the composite material can include covering the working surface of the mandrel with a wrap of a flexible resilient material, such as a silicone layer, and pressing and heating the assembled mandrel and materials using a suitable pressurized heating device. Examples of such devices and methods are more fully disclosed in the applicants' related applications previously mentioned and incorporated by reference.
- the present invention encompasses a shaped fiber-based composite material assembly.
- Such an assembly may include a mandrel, or collapsible mandrel as disclosed herein and a fiber-based composite material perform filling the groves of the interconnected lattice on the working surface thereof.
- a composite material perform can be applied to the mandrel by winding, filling, pasting, etc.
Abstract
Mandrels of various configuration, and action, including collapsible mandrels, to be used in forming composite articles with preselected three dimensional shapes and construction are disclosed and described. In one aspect, such a mandrel may have a plurality of discrete segments coupled about a longitudinal axis and collectively forming an enclosure with a substantially continuous exterior working surface. The working surface can have a network of intersecting grooves formed therein, and such grooves can cooperatively establish a substantially continuous interconnected lattice corresponding to the three dimensional geometric configuration to be imparted to a composite article formed. The mandrel may optionally include a removable core assembly to aid in collapse of the mandrel.
Description
- This application claims the benefit of U.S. Provisional Application Ser. No. 61/089,124, filed Aug. 15, 2008, which is incorporated herein by reference.
- The present invention relates to collapsible mandrel devices and their use in methods for fabrication of wound composite articles. Accordingly, the present invention involves the fields of chemistry, materials science, and engineering technology.
- Mandrels have been used for years in a variety of industries for performing many different tasks, such as lathing. Many other tasks are aided by the use of an elongated cylinder which turns about a longitudinal axis. On example of mandrel use is in shaping metal pipes or glass. Mandrels have also been used in making jewelry such as a rings or bracelets. In addition, mandrels have been used in the formation of fiber composite articles where the fibers are wound around the mandrel to create a tube and then further cured or processed into a finished article.
- The present invention sets forth mandrels for use in fabricating composite articles having desired three dimensional configurations or shapes. In one aspect, a collapsible mandrel in accordance with the present invention may include a plurality of discrete segments coupled about a longitudinal axis and collectively forming an enclosure with a substantially continuous exterior working surface. The working surface can have a network of intersecting grooves formed therein which cooperatively establish a substantially continuous interconnected lattice corresponding to the three dimensional geometric configuration to be imparted to a composite article formed using the mandrel. The mandrel may further include a removable core assembly occupying an interior volume of the enclosure and coupling the segments together to form the enclosure. The interior volume can have a size sufficient to permit entry of a segment into a hollow portion thereof in order to allow the mandrel to collapse and be removed from the formed composite article.
- In addition to the mandrel devices set forth herein, the present invention encompasses methods of shaping a fiber-based composite material to be consolidated into a three dimensional structure. In one aspect, such a method may include: 1) providing a mandrel as disclosed herein; 2) filling the grooves of the working surface of the mandrel with a composite material; 3) consolidating the composite material in the grooves into a three dimensional structure substantially corresponding to the geometric configuration cooperatively established by the grooves; 4) collapsing the mandrel into pieces inside of the three dimensional consolidated structure; and 5) removing the mandrel pieces from within the consolidated structure.
- Furthermore, the present invention encompasses shaped fiber-based composite material assemblies. In one aspect, such an assembly may include: 1) a collapsible mandrel as recited herein; and 2) a fiber-based composite material preform filling the grooves of the interconnected lattice of the working surface of the enclosure on the mandrel.
- There has thus been outlined, rather broadly, the more important features of the invention so that the detailed description thereof that follows may be better understood, and so that the present contribution to the art may be better appreciated. Other features of the present invention will become clearer from the following detailed description of the invention, taken with the accompanying drawings and claims, or may be learned by the practice of the invention.
-
FIG. 1 is a longitudinal cross-sectional view of a collapsible mandrel in accordance with an embodiment of the present invention. -
FIG. 2 a-h is show schematic views of various groove intersection configurations in accordance with various embodiments of the present invention. -
FIG. 3 a-h shows various geometric configurations for the cross-section shape of the grooves in accordance with various embodiments of the present invention. -
FIG. 4 is a side perspective view of discrete segments to be assembled and collectively form an enclosure with a working surface for the mandrel in accordance with an embodiment of the present invention. -
FIG. 5 is a longitudinal perspective view of a mandrel in accordance with an embodiment of the present invention. -
FIG. 6 is a perspective view of a collapsible mandrel engaged with a finished composite article with one or more segments in a collapsed position for removal of the mandrel from the composite article in accordance with an embodiment of the present invention. - Before the present invention is disclosed and described, it is to be understood that this invention is not limited to the particular structures, process steps, or materials disclosed herein, but is extended to equivalents thereof as would be recognized by those ordinarily skilled in the relevant arts. It should also be understood that terminology employed herein is used for the purpose of describing particular embodiments only and is not intended to be limiting.
- It must be noted that, as used in this specification and the appended claims, the singular forms “a,” “an,” and “the” include plural referents unless the context clearly dictates otherwise. Thus, for example, reference to “an abrasive precursor” includes one or more of such precursors, and reference to “a pressure medium” includes reference to one or more of such materials.
- Definitions
- In describing and claiming the present invention, the following terminology will be used in accordance with the definitions set forth below.
- As used herein, “fiber-based composite material” refers to a material comprised of carbon or other fiber (e.g., a carbon or glass fiber filament) and resin (e.g., polymer matrix) constituents.
- As used herein “preform” refers to a green, uncured composite lay-up comprising the fiber material and resin composite as situated in grooves on a mandrel or other suitable mold, and that has undergone preliminary shaping but is not yet in its final consolidated or cured form.
- As used herein, “working surface” refers to an exterior surface of a mandrel that is used to form, engage, sculpt, mold, hold, direct, guide, etc., a fiber-based composite material to be consolidated into a three dimensional article. Such working surface may have grooves or other technical or functional features formed therein and use of the term working surface refers to surfaces inside the grooves or other designs or features as well as those surfaces outside.
- As used herein, the term “substantially” refers to the complete or nearly complete extent or degree of an action, characteristic, property, state, structure, item, or result. For example, an object that is “substantially” enclosed would mean that the object is either completely enclosed or nearly completely enclosed. The exact allowable degree of deviation from absolute completeness may in some cases depend on the specific context. However, generally speaking the nearness of completion will be so as to have the same overall result as if absolute and total completion were obtained. The use of “substantially” is equally applicable when used in a negative connotation to refer to the complete or near complete lack of an action, characteristic, property, state, structure, item, or result. For example, a composition that is “substantially free of” particles would either completely lack particles, or so nearly completely lack particles that the effect would be the same as if it completely lacked particles. In other words, a composition that is “substantially free of” an ingredient or element may still actually contain such item as long as there is no measurable effect thereof.
- As used herein, the term “about” is used to provide flexibility to a numerical range endpoint by providing that a given value may be “a little above” or “a little below” the endpoint.
- As used herein, a plurality of items, structural elements, compositional elements, and/or materials may be presented in a common list for convenience. However, these lists should be construed as though each member of the list is individually identified as a separate and unique member. Thus, no individual member of such list should be construed as a de facto equivalent of any other member of the same list solely based on their presentation in a common group without indications to the contrary.
- Concentrations, amounts, and other numerical data may be expressed or presented herein in a range format. It is to be understood that such a range format is used merely for convenience and brevity and thus should be interpreted flexibly to include not only the numerical values explicitly recited as the limits of the range, but also to include all the individual numerical values or sub-ranges encompassed within that range as if each numerical value and sub-range is explicitly recited. As an illustration, a numerical range of “about 1 to about 5” should be interpreted to include not only the explicitly recited values of about 1 to about 5, but also include individual values and sub-ranges within the indicated range. Thus, included in this numerical range are individual values such as 2, 3, and 4 and sub-ranges such as from 1-3, from 2-4, and from 3-5, etc., as well as 1, 2, 3, 4, and 5, individually. This same principle applies to ranges reciting only one numerical value as a minimum or a maximum. Furthermore, such an interpretation should apply regardless of the breadth of the range or the characteristics being described.
- Invention
- The present invention provides mandrels for use in the fabrication of fiber-based composite articles. Examples of specific composite articles and methods for the fabrication thereof can be found in Applicants' copending U.S. Patent Applications filed Aug. 17, 2009 under Attorney Docket Nos. 3095-002.NP, 3095-003.NP, and 3095-006.NP, each of which is incorporated herein by reference.
- In some embodiments, the mandrels of the present invention may be collapsible. In other embodiments they may be solid. Referring now to
FIG. 1 is shown a longitudinal cross-section view of acollapsible mandrel 10, having a plurality ofdiscrete segments 15, coupled about a longitudinal axis and collectively forming an enclosure with a substantially continuousexterior working surface 20. The working surface has a network of intersectinggrooves 25 formed therein. The network of grooves cooperatively establish a substantially continuous interconnected lattice corresponding to a three dimensional geometric configuration to be imparted to a composite article formed using the mandrel. - Referring again to
FIG. 1 is shown aremovable core assembly 30. In this particular embodiment, the core assembly includes a plurality ofsolid support members 35 and acentral core 40. The removable core assembly occupies the interior volume of the enclosure formed by the assembled segments and couples the segments together to form the enclosure. Further, the interior volume of the enclosure has a volume of sufficient size to permit entry of a segment into a hollow portion thereof in order to collapse the mandrel. - The enclosure formed of
segments 15 as shown inFIG. 1 is a substantially closed as the segments connect to or abut one another at thesegment junctions 65. In some configurations, as with the one shown inFIG. 1 , the segments can be tightly fitted leaving no gap between them, or substantially no gap. However, in other embodiments, the segments can be loosely fitted and a gap formed at thesegment junctions 65. - The
segments 15 used in forming the enclosure can take a variety of shapes and sizes as required in order to form an enclosure of desired dimensions and geometry and to also create a desired working surface configuration. For example, as show inFIGS. 4 and 6 , the segments can be elongated and arcuate. As shown inFIG. 4 , the segments can be a half circle each and two of such shaped segments may be assembled opposite of one another in order to form a cylinder. By contrast, as shown inFIG. 1 , four arcuate segments can be assembled in order to form a cylinder shape. In yet other aspects of the present invention, the segments may be flat and have varying lengths. In yet other aspects, the segments could have other geometric configurations which lend themselves to assembly about a longitudinal axis using a removable core, such as triangular, rectangular, square, irregular, etc. Furthermore, the segments need not be all the same shape, but can be individually shaped and matched in order to produce a specific larger overall design, such as an airfoil, a wing, a hull, etc. - The cooperation of
segments 15 is relevant to the creation of theexterior working surface 20 of the enclosure as each segment has a working surface thereon. The working surface shape and dimensions will dictate at least in part, the configuration of the three dimensional composite article produced using the mandrel of the present invention. Accordingly, in one aspect of the present invention, the exterior working surface of the enclosure can have a predetermined shape that matches a shape intended for the composite article. Such shapes can be custom configured in cooperation with the shape of the segments used in order to provide a working surface having a cross-section perpendicular to the longitudinal axis with a specific geometric form. Examples of such geometric forms may include without limitation: a circle, and oval, an ellipse, a crescent, a triangle, a square, a rectangle, a pentagon, a hexagon, an octagon, a polygon, a star, and combination or variations thereof. In one aspect, the geometric form may be a circle. In another aspect, the geometric form may be a rectangle. In a further aspect, the geometric form of the cross-section may be a square. - In one aspect of the present invention, the geometric form of the longitudinal cross-section may extend for substantially the entire length of the mandrel. In such cases, mandrels with regular geometries of many different shapes may be formed, such as: a cylinder, a cone, a pyramid, a triangular prism, a rectangular prism, a pentagonal prism, a hexagonal prism, a heptagonal prism, an octagonal prism, etc. Nearly any regular and know geometric configuration can be produced. However, in one specific embodiment, the working surface shape may be a cylinder. In another embodiment, the shape may be an octagonal prism. In yet another embodiment, the shape may be a rectangular prism.
- In a different aspect of the present invention, the geometric form of the longitudinal cross-section may extend for less than the entire length of the mandrel. In this case, various cross-section geometries may be assembled with appropriate transition areas there between. For example, one portion of the working surface of the enclosure may be geometrically configured with a longitudinal cross-section of a square, while the longitudinal cross-section of a different portion of the working surface may be a circle with an appropriate transition portion in between. Additionally, a single mandrel may include several sections with working surfaces each having different cross-sectional geometries and transitions as required in order to produce a composite article with a specific three dimensional configuration. This may be particularly true when forming an article with a custom geometric shape or irregular form, such as an airfoil, a wing, a propeller, a hull, a blade, etc.
- Referring now to
FIG. 5 , is shown a longitudinal view of amandrel 10 in accordance with one embodiment of the present invention. As shown inFIG. 5 , the workingsurface 20 has a network of intersectinggrooves 25 formed therein. The grooves cooperatively form a substantially continuous interconnected lattice that corresponds or substantially corresponds, to a three dimensional geometric configuration to be imparted to a composite article formed using the mandrel. - The lattice formed by the network of intersecting grooves may in some aspects employ several groove types, including longitudinally extending grooves (i.e. “longitudinals”), laterally extending grooves (i.e. “laterals”), or helically extending grooves (i.e. “helicals”). As a general matter, longitudinals are grooves running parallel to the longitudinal axis of the mandrel, laterals are grooves running perpendicular to the longitudinal axis of the mandrel, and helicals are grooves running in any direction that is neither parallel nor perpendicular to the longitudinal axis of the mandrel.
-
FIGS. 2 a-h show various possible intersection configurations for the grooves. For example, 2 a shows an intersection of alongitudinal groove 45 andlateral groove 50.FIG. 2 b shows an intersection of alongitudinal groove 45 withlateral grooves 55.FIG. 2 c shows an intersection of alateral groove 50 withhelical grooves 55, andFIG. 2 d shows an intersection oflongitudinal groove 45 withlateral groove 50 andhelical grooves 55. Other various specific cross section configurations are shown inFIGS. 2 e-2 h. - Nearly any lattice design required to produce a three dimensional product of specific configuration can be formed by the network of interconnected grooves on the working surface of the mandrel. In addition, the extent of the lattice along the working surface of the mandrel may also be controlled. For example, in one embodiment, the interconnected lattice of grooves can be an unbroken, or substantially unbroken, lattice extending substantially around the entire enclosure created by the segments. In another aspect, the lattice can be a broken lattice that extends around only a portion of the enclosure. In yet other aspects, the broken lattice can be extended around the majority of the enclosure, around at least half of the enclosure, around about two thirds of the enclosure, around at least three quarters of the enclosure. Furthermore, the lattice may be sectioned into specific groups or designs around various portions of the enclosure as desired.
- In addition to variations in the lattice configuration and intersection of the grooves, the cross-section shape of the grooves may be predetermined to correspond to a cross-section shape intended for individual supports contained in the composite article. The variation of such cross-section shapes can be used in order to impart various mechanical and physical characteristics or properties, such as certain compression strengths, etc. to the three dimensional composite article produced.
- As shown in
FIG. 1 , thegrooves 25 have a triangular cross-section shape with a sharp vertex at the bottom of the groove. However, referring toFIGS. 3 a-h are shown various examples of possible groove cross-section shapes. Such examples include without limitation, a T shape with a flange at the top portion of the groove, a rectangle, a square, a triangle with a single vertex at the bottom of the groove, a half circle, a trapezoid with two obtuse angles at the bottom portion of the groove, a half pentagon with two obtuse angles at the bottom portion of the groove, a half hexagon with two obtuse angles at the bottom portion of the groove, a half octagon with three obtuse angles at the bottom portion of the groove, as well as others. In some specific embodiments, the angles at the bottom of the grooves can have a sharp vertex or corners. In other embodiments, the angles at the bottom of the grooves can be rounded. - In most aspects of the present invention, the top portion of the groove will be wider than the bottom portion of the groove in order to facilitate release of the finished article out of the grooves and off the working surface upon collapse of the mandrel. This is especially true when the mandrel is made of a rigid material as more fully articulated below. In some additional aspects, the cross-section shape of the groove may be widest at a top portion of the groove and narrowest at a bottom portion of the groove. In some aspects, the width may be substantially the same at the top and bottom portions of the groove. However, in the event that mandrel of a soft or less rigid material is used, or even in certain cases where a rigid material is used, the top of the groove may actually have a smaller width than the lower portions of the groove, such as the middle or bottom of the groove. In such cases, the groove can be tapered from a narrow point at the top to a wider point at the bottom or middle.
- Additional factors that can impact release of the article include the degree of vertex or draft angle at the bottom of the grooves. In some aspects, the grooves may include only obtuse angles or right angles. In another aspect, the grooves may include a plurality of obtuse angles at or near the bottom portion of the grooves. In a further aspect, the cross-section shape of the grooves may include no acute angle smaller than about 20 degrees. Specific examples of acute angles that can be used at the bottom of the groove include without limitation angles from about 15 degrees to about 90 degrees. In some aspects, such angles may be about 45 degrees. In other aspects, the angles may be about 60 degrees. In yet other aspects, the angles may be about 22 degrees.
- In some aspects, the bottom of the groove may be rounded. In other aspects, the bottom of the groove may be one or more vertex. In yet another aspect, the bottom of the groove may be flat. In some aspects, the walls of the grooves may be vertical or substantially vertical. In some aspects, the walls of the grooves may be angled or substantially angled. In yet other aspects, the walls of the grooves may contain an angle, or may be rounded
- As a general matter, the dimension or size of the groove longitudinal cross-section can also be controlled along with cross-section shape, for example, the width of the groove and the depth of the groove. In some aspects, such characteristics may be manipulated to provide the article formed with specific characteristics, such as compression strength, lateral strength, etc. In some aspects, the grooves may have a depth of from about 0.1 inch to about 12 inches. In another aspect, the depth may be from about 0.1 inch to about 1 inch. In yet another aspect, the depth may be from about 0.05 inches to about 0.5 inches. Similar ranges may be used for the width of the grooves. In one aspect, the width may be from about 0.1 to about 12 inches. In another aspect, the width may be from about 0.1 inch to about 1 inch. In a different aspect, the width may be from about 0.5 inches to about 0.5 inches. Such sizes will be selected based in part on the type of article being fabricated and the scale to which it must perform. For example, a boat hull may require grooves of a significantly different scale than those required for a bicycle handle bar. Moreover, specific groove shape can be selected to work in combination with varied groove depth and width dimensions in order to achieve required specifications for processing and performance in the final article. For example, a deep groove may have a rounded bottom to facilitate easy removal of the article.
- It is of course to be understood that the grooves forming the lattice on the working surface of the mandrel can all have substantially the same cross-section shape, or they may have different cross-sections. In one aspect, the longitudinal grooves may have a cross section that is different from the lateral grooves and the helical grooves. For example, the longitudinal grooves may have T shaped sections while the lateral grooves and the helical grooves are a half circle. In some other aspects, all the each groove type may have different shape and dimension, for example, the longitudinal grooves may have a rectangular shape while the lateral grooves have a triangle shape and the helical grooves have a circular shape. Moreover, the same types of groove can have different shapes. For example, some longitudinal grooves may have a T shape while others have a rectangle shape. A large variety of mixing and matching of groove cross-section shape and dimension is possible with the present invention.
- The exterior working surface of the segments of the present invention may be made from nearly any suitable material that can have a network of intersecting grooves formed therein. In some aspects, such materials may be rigid. In other aspects, such materials may be soft. Examples of rigid materials include without limitation, metals, ceramics, cured polymeric materials, composites, alloys, and mixtures thereof. Examples of metals and metalloids include without limitation, stainless steel, aluminum, tungeston, titanium, iron, magnesium, nickel, chromium, manganese, boron, silicon, and mixtures and alloys thereof. Examples of ceramic or other superhard materials include without limitation, diamond, diamond-like carbon, silicon carbide, tungsten carbide, silicon nitride, aluminum oxide, boron nitride, cubic boron nitride (cBN), titanium carbide, as well as combinations thereof. Examples of cured polymers include without limitation acrylic and acrylate polymers, silicone polymers, epoxies, urethanes and polyurethanes, and rubber based polymers, among others, including combinations and mixtures thereof. Examples of composites include without limitation, fiber-resin composites, carbon fiber composites, particulate-polymer composites, etc.
- In some aspects of the present invention, all of the segments, or exterior working surfaces of the segments, may be made from the same materials (i.e. all are stainless steel, etc.). However, in other aspects, one or more segments may be made of a different material. In addition, when made of rigid materials, the segments may be reusable or multi-use segments. When made of softer materials, including softer materials or composites, the segments can be of limited time use, or of single use. Such segments are thought to be disposable and in some aspects can be sacrificed or destroyed as part of the collapsing process.
- In order to facilitate release of the formed article from the mandrel grooves, the working surface, including the grooves, or in some aspects, only the grooves can be provided with a lubricant. Such a lubricant can be temporarily applied prior to insertion of the fiber-based composite material into the grooves and/or onto the working surface (e.g. such as an oil, petroleum product, silicone lubricant, etc.), or such lubricant property can be more permanently affixed to the working surface (e.g. coating with a friction reducing polymer such as polytetrafluroethylene, etc.). In some aspects, the entire working surface may be coated. In other aspects, substantially all of the grooves of the working surface may be coated.
- Referring again to
FIG. 1 is shown a cross-sectional view of theremovable core assembly 30. The core assembly occupies the interior volume of the enclosure formed by thesegments 15, and couples the segments together to form the enclosure. One example of a coupling mechanism that can be used is by screwing the segments to the core assembly. Screw holes, 60 can be seen inFIGS. 4 and 5 . A variety of other mechanisms, including adhesives, clips, etc. can be used to couple the segments to the core assembly. - As shown in
FIG. 1 , thecore assembly 30 includessolid support members 35 andsolid core 40. Such support members fill substantially the entire interior volume of the enclosure. In such an embodiment, the core or one or more of the solid support members is pushed along the longitudinal axis and removed from the mandrel in order to create a hollow space of sufficient size to allow entry of one or more of the segments as part of the process of collapsing the mandrel. However, in other embodiments, support members may be used which do not substantially file the entire interior volume of the enclosure and a hollow space may exist without removal of the core or any core pieces. - In one aspect, the core assembly can consist of a single piece. In other aspects, the core assembly can include multiple integrated pieces. Such pieces can be coated with a lubricant or other friction reducing material in order to facilitate their removal from the mandrel. In other aspects, such pieces may be capable of manipulation within the enclosure in order to create or expand a hollow space and allow entry of one or more segments as shown in
FIG. 6 . - As shown in
FIG. 1 , thecore 40 has a specific configuration that keys the placement of specific supporting members which in turn may key the placement of the segments. Such keying can be useful in automating assembly of the segments into an enclosure with a specific working surface configuration. In alternative embodiments, the core assembly can be non-keyed and can universally couple segments to allow interchangeability of segment location so that an operator can select and place segments at his discretion in the creation of a custom made working surface. - In addition to the mandrel devices and structures disclosed herein, the present invention additionally encompasses methods of using such mandrels. In one aspect, such a method includes shaping a fiber-based composite material to be consolidated into a three dimensional structure. Such a method may include providing a mandrel as recited herein, filling the grooves with a composite material, or a composite material perform, consolidating the composite material into a three dimensional structure substantially corresponding to the geometric configuration cooperatively established by the grooves, collapsing the mandrel into pieces inside of the three dimensional consolidated structure, and removing the mandrel pieces from within the consolidated structure. One example of a mandrel collapsed inside a consolidated structure is shown in
FIG. 6 . - In some aspect, the filling of the grooves with a composite material to be consolidated can include winding a carbon fiber or other fibrous material into the grooves of the mandrel and adding a curable resin to the fibrous material. Furthermore, the consolidation of the composite material can include covering the working surface of the mandrel with a wrap of a flexible resilient material, such as a silicone layer, and pressing and heating the assembled mandrel and materials using a suitable pressurized heating device. Examples of such devices and methods are more fully disclosed in the applicants' related applications previously mentioned and incorporated by reference.
- Furthermore, the present invention encompasses a shaped fiber-based composite material assembly. Such an assembly may include a mandrel, or collapsible mandrel as disclosed herein and a fiber-based composite material perform filling the groves of the interconnected lattice on the working surface thereof. As previously mentioned, such a composite material perform can be applied to the mandrel by winding, filling, pasting, etc.
- Of course, it is to be understood that the above-described arrangements are only illustrative of the application of the principles of the present invention. Numerous modifications and alternative arrangements may be devised by those skilled in the art without departing from the spirit and scope of the present invention and the appended claims are intended to cover such modifications and arrangements. Thus, while the present invention has been described above with particularity and detail in connection with what is presently deemed to be the most practical and preferred embodiments of the invention, it will be apparent to those of ordinary skill in the art that numerous modifications, including, but not limited to, variations in size, materials, shape, form, function and manner of operation, assembly and use may be made without departing from the principles and concepts set forth herein.
Claims (40)
1. A collapsible mandrel comprising:
a plurality of discrete segments coupled about a longitudinal axis and collectively forming an enclosure with a substantially continuous exterior working surface, said working surface having a network of intersecting grooves formed therein, said grooves cooperatively establishing a substantially continuous interconnected lattice corresponding to a three dimensional geometric configuration to be imparted to a composite article formed using the mandrel; and
a removable core assembly occupying an interior volume of the enclosure and coupling the segments together to form the enclosure, said interior volume having a size sufficient to permit entry of a segment into a hollow portion thereof in order to collapse the mandrel.
2. The collapsible mandrel of claim 1 , wherein the exterior working surface of the enclosure has a predetermined shape that matches a shape intended for the composite article.
3. The collapsible mandrel of claim 2 , wherein the shape includes a cross-section perpendicular to the longitudinal axis with a geometric form selected from the group consisting of: a circle, an oval, an ellipse, a crescent, a triangle, a square, a rectangle, a pentagon, a hexagon, a heptagon, an octagon, a polygon, a star, and combinations thereof.
4. The collapsible mandrel of claim 3 , wherein the geometric form of the perpendicular cross-section extends for the entire length of the mandrel.
5. The collapsible mandrel of claim 3 , wherein the geometric form of the perpendicular cross-section extends for less than the entire length of the mandrel.
6. The collapsible mandrel of claim 2 , wherein the shape is a member selected from the group consisting of: a cylinder, a cone, a pyramid, a triangular prism, a rectangular prism, a pentagonal prism, a hexagonal prism, a heptagonal prism, and an octagonal prism.
7. The collapsible mandrel of claim 1 , wherein the shape is a cylinder.
8. The collapsible mandrel of claim 1 , wherein the network of intersecting grooves includes intersection of longitudinal grooves with lateral grooves.
9. The collapsible mandrel of claim 1 , wherein the network of intersecting grooves includes intersection of longitudinal grooves with helical grooves.
10. The collapsible mandrel of claim 1 , wherein the network of intersecting grooves includes intersection of lateral grooves with helical grooves.
11. The collapsible mandrel of claim 1 , wherein the network of intersecting grooves includes intersection of longitudinal, lateral, and helical grooves at a single intersection.
12. The collapsible mandrel of claim 1 , wherein the grooves each have a predetermined cross-section shape corresponding to a cross-section shape intended for individual supports contained in the composite article.
13. The collapsible mandrel of claim 12 , wherein the cross-section shape is substantially identical for each groove.
14. The collapsible mandrel of claim 12 , wherein the cross-section shape is substantially different for longitudinal, lateral, and helical grooves.
15. The collapsible mandrel of claim 12 , wherein the cross-section shape is widest at a top portion of the groove and a narrowest at a bottom portion of the groove.
16. The collapsible mandrel of claim 15 , wherein the cross-section shape has no acute angle smaller than about 20 degrees.
17. The collapsible mandrel of claim 15 , wherein the cross-section shape has a plurality of obtuse angles at the bottom portion of the groove.
18. The collapsible mandrel of claim 15 , wherein the bottom portion of the groove is rounded.
19. The collapsible mandrel of claim 15 , wherein the groove shape is a member selected from the group consisting of: a T shape with a flange at the top portion of the groove, a rectangle, a square, a triangle with a single vertex at the bottom portion of the groove, a half circle, a trapezoid with two obtuse angles at the bottom portion of the groove, a half pentagon with two obtuse angles at the bottom portion of the groove, a half hexagon with two obtuse angles at the bottom portion of the groove, and a half octagon with three obtuse angles at the bottom portion of the groove.
20. The collapsible mandrel of claim 19 , wherein the angles of the shapes at the bottom of the grooves are rounded rather than having a sharp vertex.
21. The collapsible mandrel of claim 1 , wherein the interconnected lattice of grooves is an unbroken lattice extending substantially around the entire enclosure.
22. The collapsible mandrel of claim 1 , wherein the interconnected lattice of grooves is a broken lattice extending around only a portion of the enclosure.
23. The collapsible mandrel of claim 22 , wherein the portion of the enclosure is a majority of the enclosure.
24. The collapsible mandrel of claim 22 , wherein the portion of the enclosure is at least half of the enclosure.
25. The collapsible mandrel of claim 22 , wherein the portion of the enclosure is at least two thirds of the enclosure.
26. The collapsible mandrel of claim 22 , wherein the portion of the enclosure is at least three quarters of the enclosure.
27. The collapsible mandrel of claim 1 , wherein the exterior working surface of the segments is a rigid material selected from the group consisting of: metals, ceramics, cured polymeric materials, composites, alloys, and mixtures thereof.
28. The collapsible mandrel of claim 27 , wherein the material is a metal.
29. The collapsible mandrel of claim 1 , wherein the exterior working surfaces of the segments are all made of the same material.
30. The collapsible mandrel of claim 1 , wherein the exterior working surfaces of the segments are made of different materials.
31. The collapsible mandrel of claim 1 , further comprising a lubricant coating coated over at least a portion of the working surface.
32. The collapsible mandrel of claim 1 , wherein the lubricant coating is coated in substantially all the grooves of the working surface.
33. The collapsible mandrel of claim 1 , wherein the removable core assembly is a single piece.
34. The collapsible mandrel of claim 1 , wherein the removable core assembly comprises a multiple integrated pieces.
35. The collapsible mandrel of claim 1 , wherein the removable core assembly occupies less than the entire interior volume of the enclosure.
36. The collapsible mandrel of claim 1 , wherein the removable core assembly occupies substantially the entire interior volume of the enclosure and the hollow portion of the interior volume is created by removal of at least a portion of the core assembly.
37. The collapsible mandrel of claim 1 , wherein the removable core assembly has a configuration which keys the placement of specific segments at specific locations in the enclosure.
38. The collapsible mandrel of claim 1 , wherein the removable core assembly has a configuration which universally couples segments to allow segment location in the enclosure to be interchangeable.
39. A method of shaping a fiber-based composite material to be consolidated into a three dimensional structure, comprising:
providing a mandrel as recited in claim 1 ;
filling the grooves with a composite perform material;
consolidating the composite perform material into a three dimensional structure substantially corresponding to the geometric configuration cooperatively established by the grooves;
collapsing the mandrel into pieces inside of the three dimensional consolidated structure; and
removing the mandrel pieces from within the consolidated structure.
40. A shaped fiber-based composite material assembly comprising:
a collapsible mandrel as recited in claim 1 ; and
a fiber-based composite material preform filling the grooves of the interconnected lattice.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/542,613 US20100075074A1 (en) | 2008-08-15 | 2009-08-17 | Collapsible Mandrel Tools and Associated Methods for Fabrication of Wound Composite Articles |
US13/657,698 US20130196087A1 (en) | 2008-08-15 | 2012-10-22 | Collapsible Mandrel Tools and Associated Methods for Fabrication of Wound Composite Articles |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US8912408P | 2008-08-15 | 2008-08-15 | |
US12/542,613 US20100075074A1 (en) | 2008-08-15 | 2009-08-17 | Collapsible Mandrel Tools and Associated Methods for Fabrication of Wound Composite Articles |
Publications (1)
Publication Number | Publication Date |
---|---|
US20100075074A1 true US20100075074A1 (en) | 2010-03-25 |
Family
ID=41669736
Family Applications (7)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/542,613 Abandoned US20100075074A1 (en) | 2008-08-15 | 2009-08-17 | Collapsible Mandrel Tools and Associated Methods for Fabrication of Wound Composite Articles |
US12/542,442 Abandoned US20100064612A1 (en) | 2008-08-15 | 2009-08-17 | Lattice Support Structures |
US12/542,555 Expired - Fee Related US8444900B2 (en) | 2008-08-15 | 2009-08-17 | Method and system for forming composite geometric support structures |
US13/657,698 Abandoned US20130196087A1 (en) | 2008-08-15 | 2012-10-22 | Collapsible Mandrel Tools and Associated Methods for Fabrication of Wound Composite Articles |
US13/692,879 Abandoned US20130167462A1 (en) | 2008-08-15 | 2012-12-03 | Lattice support structures |
US13/866,846 Abandoned US20130233492A1 (en) | 2008-08-15 | 2013-04-19 | Composite geometric support structures and associated methods and systems |
US14/035,703 Abandoned US20140150363A1 (en) | 2008-08-15 | 2013-09-24 | Lattice Support Structures |
Family Applications After (6)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/542,442 Abandoned US20100064612A1 (en) | 2008-08-15 | 2009-08-17 | Lattice Support Structures |
US12/542,555 Expired - Fee Related US8444900B2 (en) | 2008-08-15 | 2009-08-17 | Method and system for forming composite geometric support structures |
US13/657,698 Abandoned US20130196087A1 (en) | 2008-08-15 | 2012-10-22 | Collapsible Mandrel Tools and Associated Methods for Fabrication of Wound Composite Articles |
US13/692,879 Abandoned US20130167462A1 (en) | 2008-08-15 | 2012-12-03 | Lattice support structures |
US13/866,846 Abandoned US20130233492A1 (en) | 2008-08-15 | 2013-04-19 | Composite geometric support structures and associated methods and systems |
US14/035,703 Abandoned US20140150363A1 (en) | 2008-08-15 | 2013-09-24 | Lattice Support Structures |
Country Status (4)
Country | Link |
---|---|
US (7) | US20100075074A1 (en) |
BR (1) | BRPI0917867A2 (en) |
CA (1) | CA2770481A1 (en) |
WO (3) | WO2010019964A2 (en) |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100064612A1 (en) * | 2008-08-15 | 2010-03-18 | Wilson Erich A | Lattice Support Structures |
US20100065192A1 (en) * | 2008-08-15 | 2010-03-18 | Wilson Erich A | Method and System For Forming Composite Geometric Support Structures |
US20120299215A1 (en) * | 2011-05-24 | 2012-11-29 | Lockheed Martin Corporation | Mechanically collapsible shell for long cylinder production |
US20130036785A1 (en) * | 2011-08-12 | 2013-02-14 | Gfm-Gmbh | Apparatus for forging a hollow body |
US20130075025A1 (en) * | 2011-03-25 | 2013-03-28 | Maurice Guitton | Method of Manufacturing Hollow Composite Parts with In Situ Formed Internal Structures |
US20130181374A1 (en) * | 2012-01-16 | 2013-07-18 | Airbus Operations Gmbh | Molding tool and method for manufacturing a fiber reinforced plastic aerodynamic aircraft component |
CN106002097A (en) * | 2016-06-13 | 2016-10-12 | 中国科学院力学研究所 | Preparation method of lattice material reinforced square-to-circle special-shaped section thin-wall structure |
US20180281325A1 (en) * | 2015-12-11 | 2018-10-04 | Contitech Luftfedersysteme Gmbh | Apparatus for making conical bellows |
US20200378646A1 (en) * | 2018-06-20 | 2020-12-03 | Johns Manville | Methods, materials, and equipment to form improved fit duct liner insulation for round and oval hvac duct systems |
Families Citing this family (40)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB0611061D0 (en) * | 2006-06-06 | 2006-07-12 | Qinetiq Ltd | Self opening hinges |
DE102010018541A1 (en) * | 2010-04-28 | 2011-11-03 | Acandis Gmbh & Co. Kg | Method of manufacturing a medical device |
JP5220811B2 (en) * | 2010-07-30 | 2013-06-26 | 三菱重工業株式会社 | Pressure vessel and method for manufacturing the same |
US9126374B2 (en) | 2010-09-28 | 2015-09-08 | Russell B. Hanson | Iso-grid composite component |
DE102011121639B4 (en) * | 2011-12-20 | 2013-08-01 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Rotationally symmetric structural element in grid construction and method for its production |
US20130243989A1 (en) * | 2011-12-30 | 2013-09-19 | Sigma-Tek, Llc | Lattice Support Structure |
US9404249B2 (en) * | 2012-01-18 | 2016-08-02 | Adc Acquisition Company | Ultra light fiber placed truss |
US9597821B2 (en) | 2012-09-27 | 2017-03-21 | General Electric Company | Frame assembly, mold, and method for forming rotor blade |
JP6184808B2 (en) * | 2013-09-05 | 2017-08-23 | 三菱重工業株式会社 | Manufacturing method of core type and hollow structure |
US9234351B1 (en) | 2014-12-17 | 2016-01-12 | United Launch Alliance, L.L.C. | Polar-oriented lattice isogrid for circular structures |
US10336006B1 (en) * | 2015-05-19 | 2019-07-02 | Southern Methodist University | Methods and apparatus for additive manufacturing |
US9957031B2 (en) * | 2015-08-31 | 2018-05-01 | The Boeing Company | Systems and methods for manufacturing a tubular structure |
US9965582B2 (en) | 2015-08-31 | 2018-05-08 | The Boeing Company | Systems and methods for determining sizes and shapes of geodesic modules |
US9789548B2 (en) * | 2015-08-31 | 2017-10-17 | The Boeing Company | Geodesic structure forming systems and methods |
CN106544776A (en) * | 2015-09-22 | 2017-03-29 | 中国科学院长春应用化学研究所 | A kind of three dimensional fabric |
RU2620430C1 (en) * | 2015-12-10 | 2017-05-25 | Российская Федерация от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) | Power grid from polymer composite material |
US10953575B2 (en) * | 2016-02-12 | 2021-03-23 | The Boeing Company | Enhanced systems that facilitate vacuum bag curing of composite parts |
US10974467B2 (en) | 2016-02-12 | 2021-04-13 | The Boeing Company | Enhanced systems that facilitate vacuum bag curing of composite parts |
EP3241671A1 (en) * | 2016-05-04 | 2017-11-08 | Alfa Laval Corporate AB | Assembly for a dewatering apparatus and dewatering apparatus comprising such an assembly |
ES2820708T3 (en) * | 2016-08-30 | 2021-04-22 | Mondi Ag | Process for the manufacture of a product composed of plastic fabric sheets, made of plastic fabric sheets, as well as a packaging bag from a plastic fabric sheet compound |
US10119266B1 (en) * | 2016-12-22 | 2018-11-06 | The Government Of The United States Of America As Represented By The Secretary Of The Air Force | Extensible sparse-isogrid column |
DE102017203404A1 (en) * | 2017-03-02 | 2018-09-06 | Bayerische Motoren Werke Aktiengesellschaft | Fiber component with fiber rods connected to a framework |
US10230182B2 (en) | 2017-03-03 | 2019-03-12 | Glxt Holdings, Llc | Electrical grounding systems |
US10180000B2 (en) | 2017-03-06 | 2019-01-15 | Isotruss Industries Llc | Composite lattice beam |
US10584491B2 (en) * | 2017-03-06 | 2020-03-10 | Isotruss Industries Llc | Truss structure |
USD896401S1 (en) | 2018-03-06 | 2020-09-15 | Isotruss Industries Llc | Beam |
USD895157S1 (en) | 2018-03-06 | 2020-09-01 | IsoTruss Indsutries LLC | Longitudinal beam |
RU2684699C1 (en) * | 2018-07-02 | 2019-04-11 | Акционерное общество "Центр перспективных разработок АО ЦНИИСМ" | Grid shell from composition materials |
US11298600B1 (en) * | 2019-03-21 | 2022-04-12 | Cobra Golf Incorporated | Additive manufacturing for golf club shaft |
US11273610B2 (en) * | 2019-03-21 | 2022-03-15 | Goodrich Corporation | Manufacturing methods for composite driveshafts |
CN110861790B (en) * | 2019-10-31 | 2024-02-06 | 上海宇航系统工程研究所 | Pure lattice force-bearing cylinder |
RU196827U1 (en) * | 2019-11-27 | 2020-03-17 | Акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнёва" | POWER STRUCTURE OF SPACE VEHICLE HOUSING |
RU197021U1 (en) * | 2019-12-19 | 2020-03-25 | Акционерное общество «Информационные спутниковые системы» имени академика М.Ф. Решетнёва" | POWER STRUCTURE OF SPACE VEHICLE HOUSING |
RU196913U1 (en) * | 2020-01-09 | 2020-03-19 | Акционерное общество «Информационные спутниковые системы» имени академика М.Ф. Решетнёва" | POWER STRUCTURE OF SPACE VEHICLE HOUSING |
US11260605B2 (en) | 2020-01-21 | 2022-03-01 | Goodrich Corporation | Flexible thermoplastic composite coupling and method of manufacture |
EP3878635B1 (en) * | 2020-03-09 | 2023-08-02 | Airbus Operations, S.L.U. | Method for manufacturing a part |
RU2753557C1 (en) * | 2020-08-24 | 2021-08-17 | Александр Владимирович Лямин | Lyamin's woven spatial structure (variants) |
RU203508U1 (en) * | 2020-09-03 | 2021-04-08 | Акционерное общество «Информационные спутниковые системы» имени академика М.Ф. Решетнёва» | POWER STRUCTURE OF THE CASE OF THE PAYLOAD OF THE SPACE VEHICLE |
RU203407U1 (en) * | 2020-11-27 | 2021-04-02 | Акционерное общество «Информационные спутниковые системы» имени академика М.Ф. Решетнёва" | POWER STRUCTURE OF THE SPACE VEHICLE CASE |
US11760038B2 (en) | 2021-01-08 | 2023-09-19 | Trelleborg Sealing Solutions Germany Gmbh | Optimized rib-stiffened composite structure |
Citations (60)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US31777A (en) * | 1861-03-26 | wto-uto wto-utoogb | ||
US1766961A (en) * | 1929-09-25 | 1930-06-24 | Arthur B Steuart | Fuselage frame |
US1818423A (en) * | 1929-05-20 | 1931-08-11 | Harvey C Mummert | Metal framed structure for aeroplanes |
US1975726A (en) * | 1931-09-15 | 1934-10-02 | Martinage Leon | Endless track vehicle |
US2060387A (en) * | 1935-02-27 | 1936-11-10 | Vickers Aviat Ltd | Aircraft body structure |
US2114274A (en) * | 1937-11-27 | 1938-04-12 | Delamere Co Inc | Tubular braid |
US2157042A (en) * | 1937-04-21 | 1939-05-02 | Vickers Armstrongs Ltd | Wing, fuselage, or other aircraft body |
US2456513A (en) * | 1945-04-20 | 1948-12-14 | Theodore L Johnson | Molding of hollow articles |
US2639876A (en) * | 1947-09-03 | 1953-05-26 | Misfeldt Charles Clayton | Molded structure |
US2928360A (en) * | 1956-10-16 | 1960-03-15 | Jr Edmund C Heine | Flexural tension framing system and structural unit thereof |
US3007497A (en) * | 1956-01-23 | 1961-11-07 | Samuel M Shobert | Reinforced plastic rods and method of fabricating the same |
US3300354A (en) * | 1962-04-18 | 1967-01-24 | Whittaker Corp | Method of making a filament wound sandwich core |
US3644866A (en) * | 1971-01-11 | 1972-02-22 | Owens Corning Fiberglass Corp | Tightly bound bundle of filaments and method of producing same |
US3645833A (en) * | 1970-05-20 | 1972-02-29 | Us Army | Article and method of quasi-isotropic core filaments |
US3857415A (en) * | 1970-09-15 | 1974-12-31 | Everflex Prod Inc | Reinforced convoluted tubing of polytetrafluoroethylene |
US3887739A (en) * | 1969-11-10 | 1975-06-03 | Aerojet General Co | Honeycomb structures |
US3940891A (en) * | 1974-08-05 | 1976-03-02 | General Dynamics Corporation | Conical structure |
US3962393A (en) * | 1974-05-07 | 1976-06-08 | Lockheed Aircraft Corporation | Method for making a hollow laminated article |
US4025675A (en) * | 1973-12-19 | 1977-05-24 | Messerschmitt-Bolkow-Blohm Gmbh | Reinforced laminates |
US4086378A (en) * | 1975-02-20 | 1978-04-25 | Mcdonnell Douglas Corporation | Stiffened composite structural member and method of fabrication |
US4118262A (en) * | 1976-05-21 | 1978-10-03 | Brunswick Corporation | Longitudinal load carrying method for fiber reinforced filament wound structures |
US4137354A (en) * | 1977-03-07 | 1979-01-30 | Mcdonnell Douglas Corporation | Ribbed composite structure and process and apparatus for producing the same |
GB2004835A (en) * | 1977-09-22 | 1979-04-11 | Math F C | Lattice structures |
GB2049613A (en) * | 1979-05-04 | 1980-12-31 | British Petroleum Co | Structures |
US4254599A (en) * | 1978-03-29 | 1981-03-10 | Societe Europeenne De Propulsion | Annular three-dimensional structure usable in particular as reinforcement |
US4260143A (en) * | 1979-01-15 | 1981-04-07 | Celanese Corporation | Carbon fiber reinforced composite coil spring |
US4278490A (en) * | 1979-12-21 | 1981-07-14 | Owens-Corning Fiberglas Corporation | Sleeve for changing diameter of collapsible mandrel |
US4278485A (en) * | 1978-08-02 | 1981-07-14 | The Boeing Company | Method of forming composite wound structure |
US4284679A (en) * | 1978-11-06 | 1981-08-18 | Lockheed Corporation | Filled resin coated tape |
US4321854A (en) * | 1979-06-01 | 1982-03-30 | Berkley & Company, Inc. | Composite line of core and jacket |
US4347287A (en) * | 1980-08-14 | 1982-08-31 | Lord Corporation | Segmented pultrusions comprising continuous lengths of fiber having selected areas along the lengths containing resin matrix impregnations |
US4366658A (en) * | 1980-01-17 | 1983-01-04 | Societe Europeenne De Propulsion | Annular three-dimensional structure |
US4381820A (en) * | 1981-12-24 | 1983-05-03 | Uop Inc. | Filament reinforced plastic screen and apparatus for making same |
US4473217A (en) * | 1982-01-07 | 1984-09-25 | Kato Hatsujo Kaisha, Limited | Fiber-reinforced resin coil spring and method of manufacturing the same |
US4475323A (en) * | 1982-04-30 | 1984-10-09 | Martin Marietta Corporation | Box truss hoop |
US4695342A (en) * | 1985-03-28 | 1987-09-22 | General Motors Corporation | Method of forming truck cab frames |
US4706430A (en) * | 1985-12-26 | 1987-11-17 | Shimizu Construction Co., Ltd. | Concrete reinforcing unit |
US4786341A (en) * | 1986-04-15 | 1988-11-22 | Mitsubishi Chemical Industries Limited | Method for manufacturing concrete structure |
US4940617A (en) * | 1987-03-10 | 1990-07-10 | Akzo Nv | Multilayer hollow fiber wound body |
US5048441A (en) * | 1989-06-15 | 1991-09-17 | Fiberspar, Inc. | Composite sail mast with high bending strength |
US5051226A (en) * | 1989-09-18 | 1991-09-24 | The Boeing Company | Method of curing composite parts |
US5200251A (en) * | 1991-06-20 | 1993-04-06 | General Dynamics Corporation, Space Systems Division | Filament wound composite structure, its tooling and method of manufacture |
US5266137A (en) * | 1992-11-10 | 1993-11-30 | Hollingsworth Ritch D | Rigid segmented mandrel with inflatable support |
US5463970A (en) * | 1995-03-13 | 1995-11-07 | Harken, Inc. | Furling foil for sailing vessel |
US5505035A (en) * | 1992-06-24 | 1996-04-09 | Lalvani; Haresh | Building systems with non-regular polyhedral nodes |
US5556677A (en) * | 1994-01-07 | 1996-09-17 | Composite Development Corporation | Composite shaft structure and manufacture |
US5814386A (en) * | 1995-12-01 | 1998-09-29 | Mcdonnell Douglas Corporation | Composite shell formed as a body of rotation, and method and mandrel for making same |
US5871117A (en) * | 1994-04-28 | 1999-02-16 | Mcdonnell Douglas Corporation | Tubular load-bearing composite structure |
US5921048A (en) * | 1996-04-18 | 1999-07-13 | Brigham Young University | Three-dimensional iso-tross structure |
US5962150A (en) * | 1993-03-18 | 1999-10-05 | Jonathan Aerospace Materials Corporation | Lattice block material |
US6013341A (en) * | 1996-08-19 | 2000-01-11 | Mcdonnell Douglas Corporation | Carrying (bearing) pipe-casing made of composite materials, the method and the setting (straightening device) for its manufacturing |
US6050315A (en) * | 1998-04-30 | 2000-04-18 | Alliant Techsystems Inc. | Method and apparatus for producing fiber reinforced structures |
US6053696A (en) * | 1998-05-29 | 2000-04-25 | Pratt & Whitney Canada Inc. | Impact resistant composite shell for gas turbine engine fan case |
US6076324A (en) * | 1996-11-08 | 2000-06-20 | Nu-Cast Inc. | Truss structure design |
US6264684B1 (en) * | 1995-03-10 | 2001-07-24 | Impra, Inc., A Subsidiary Of C.R. Bard, Inc. | Helically supported graft |
US7132027B2 (en) * | 2001-08-17 | 2006-11-07 | Brigham Young University | Complex composite structures and method and apparatus for fabricating same from continuous fibers |
US20070175031A1 (en) * | 2006-01-31 | 2007-08-02 | Pham Doan D | One-piece inner shell for full barrel composite fuselage |
US20100064612A1 (en) * | 2008-08-15 | 2010-03-18 | Wilson Erich A | Lattice Support Structures |
US20100065192A1 (en) * | 2008-08-15 | 2010-03-18 | Wilson Erich A | Method and System For Forming Composite Geometric Support Structures |
US7976925B2 (en) * | 2002-03-04 | 2011-07-12 | Ole-Bendt Rasmussen | Cross-laminate of oriented films, method of manufacturing same, and coextrusion die suitable in the process |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1174920A (en) | 1966-12-20 | 1969-12-17 | Space Age Materials Corp | Method of Making High Purity and Non-Melting Filaments |
KR890008010Y1 (en) * | 1986-09-15 | 1989-11-18 | 현광식 | Rice box |
JP2571327B2 (en) * | 1992-07-14 | 1997-01-16 | 新日本製鐵株式会社 | Hot strip winding mandrel |
JP2644455B2 (en) * | 1994-09-08 | 1997-08-25 | 株式会社協和製作所 | Uncoiler machine |
JP2603455B2 (en) * | 1995-03-27 | 1997-04-23 | 岐阜県 | Bobbin and prebulky processing method and cheese dyeing method |
JPH11244940A (en) * | 1998-03-05 | 1999-09-14 | Ishikawajima Harima Heavy Ind Co Ltd | Winding and unwinding drum |
US7032027B1 (en) * | 2000-10-13 | 2006-04-18 | Lucent Technologies Inc. | Method of processing nested message layers |
-
2009
- 2009-08-17 BR BRPI0917867A patent/BRPI0917867A2/en not_active IP Right Cessation
- 2009-08-17 US US12/542,613 patent/US20100075074A1/en not_active Abandoned
- 2009-08-17 CA CA 2770481 patent/CA2770481A1/en not_active Abandoned
- 2009-08-17 WO PCT/US2009/054083 patent/WO2010019964A2/en active Application Filing
- 2009-08-17 WO PCT/US2009/054044 patent/WO2010019948A2/en active Application Filing
- 2009-08-17 US US12/542,442 patent/US20100064612A1/en not_active Abandoned
- 2009-08-17 WO PCT/US2009/054091 patent/WO2010019966A2/en active Application Filing
- 2009-08-17 US US12/542,555 patent/US8444900B2/en not_active Expired - Fee Related
-
2012
- 2012-10-22 US US13/657,698 patent/US20130196087A1/en not_active Abandoned
- 2012-12-03 US US13/692,879 patent/US20130167462A1/en not_active Abandoned
-
2013
- 2013-04-19 US US13/866,846 patent/US20130233492A1/en not_active Abandoned
- 2013-09-24 US US14/035,703 patent/US20140150363A1/en not_active Abandoned
Patent Citations (63)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US31777A (en) * | 1861-03-26 | wto-uto wto-utoogb | ||
US1818423A (en) * | 1929-05-20 | 1931-08-11 | Harvey C Mummert | Metal framed structure for aeroplanes |
US1766961A (en) * | 1929-09-25 | 1930-06-24 | Arthur B Steuart | Fuselage frame |
US1975726A (en) * | 1931-09-15 | 1934-10-02 | Martinage Leon | Endless track vehicle |
US2060387A (en) * | 1935-02-27 | 1936-11-10 | Vickers Aviat Ltd | Aircraft body structure |
US2157042A (en) * | 1937-04-21 | 1939-05-02 | Vickers Armstrongs Ltd | Wing, fuselage, or other aircraft body |
US2114274A (en) * | 1937-11-27 | 1938-04-12 | Delamere Co Inc | Tubular braid |
US2456513A (en) * | 1945-04-20 | 1948-12-14 | Theodore L Johnson | Molding of hollow articles |
US2639876A (en) * | 1947-09-03 | 1953-05-26 | Misfeldt Charles Clayton | Molded structure |
US3007497A (en) * | 1956-01-23 | 1961-11-07 | Samuel M Shobert | Reinforced plastic rods and method of fabricating the same |
US2928360A (en) * | 1956-10-16 | 1960-03-15 | Jr Edmund C Heine | Flexural tension framing system and structural unit thereof |
US3300354A (en) * | 1962-04-18 | 1967-01-24 | Whittaker Corp | Method of making a filament wound sandwich core |
US3887739A (en) * | 1969-11-10 | 1975-06-03 | Aerojet General Co | Honeycomb structures |
US3645833A (en) * | 1970-05-20 | 1972-02-29 | Us Army | Article and method of quasi-isotropic core filaments |
US3857415A (en) * | 1970-09-15 | 1974-12-31 | Everflex Prod Inc | Reinforced convoluted tubing of polytetrafluoroethylene |
US3644866A (en) * | 1971-01-11 | 1972-02-22 | Owens Corning Fiberglass Corp | Tightly bound bundle of filaments and method of producing same |
US4025675A (en) * | 1973-12-19 | 1977-05-24 | Messerschmitt-Bolkow-Blohm Gmbh | Reinforced laminates |
US3962393A (en) * | 1974-05-07 | 1976-06-08 | Lockheed Aircraft Corporation | Method for making a hollow laminated article |
US3940891A (en) * | 1974-08-05 | 1976-03-02 | General Dynamics Corporation | Conical structure |
US4086378A (en) * | 1975-02-20 | 1978-04-25 | Mcdonnell Douglas Corporation | Stiffened composite structural member and method of fabrication |
US4118262A (en) * | 1976-05-21 | 1978-10-03 | Brunswick Corporation | Longitudinal load carrying method for fiber reinforced filament wound structures |
US4137354A (en) * | 1977-03-07 | 1979-01-30 | Mcdonnell Douglas Corporation | Ribbed composite structure and process and apparatus for producing the same |
GB2004835A (en) * | 1977-09-22 | 1979-04-11 | Math F C | Lattice structures |
US4254599A (en) * | 1978-03-29 | 1981-03-10 | Societe Europeenne De Propulsion | Annular three-dimensional structure usable in particular as reinforcement |
US4278485A (en) * | 1978-08-02 | 1981-07-14 | The Boeing Company | Method of forming composite wound structure |
US4284679A (en) * | 1978-11-06 | 1981-08-18 | Lockheed Corporation | Filled resin coated tape |
US4260143A (en) * | 1979-01-15 | 1981-04-07 | Celanese Corporation | Carbon fiber reinforced composite coil spring |
GB2049613A (en) * | 1979-05-04 | 1980-12-31 | British Petroleum Co | Structures |
US4321854A (en) * | 1979-06-01 | 1982-03-30 | Berkley & Company, Inc. | Composite line of core and jacket |
US4278490A (en) * | 1979-12-21 | 1981-07-14 | Owens-Corning Fiberglas Corporation | Sleeve for changing diameter of collapsible mandrel |
US4366658A (en) * | 1980-01-17 | 1983-01-04 | Societe Europeenne De Propulsion | Annular three-dimensional structure |
US4347287A (en) * | 1980-08-14 | 1982-08-31 | Lord Corporation | Segmented pultrusions comprising continuous lengths of fiber having selected areas along the lengths containing resin matrix impregnations |
US4381820A (en) * | 1981-12-24 | 1983-05-03 | Uop Inc. | Filament reinforced plastic screen and apparatus for making same |
US4473217A (en) * | 1982-01-07 | 1984-09-25 | Kato Hatsujo Kaisha, Limited | Fiber-reinforced resin coil spring and method of manufacturing the same |
US4475323A (en) * | 1982-04-30 | 1984-10-09 | Martin Marietta Corporation | Box truss hoop |
US4695342A (en) * | 1985-03-28 | 1987-09-22 | General Motors Corporation | Method of forming truck cab frames |
US4706430A (en) * | 1985-12-26 | 1987-11-17 | Shimizu Construction Co., Ltd. | Concrete reinforcing unit |
US4819395A (en) * | 1985-12-26 | 1989-04-11 | Shimizu Construction Co., Ltd. | Textile reinforced structural components |
US4786341A (en) * | 1986-04-15 | 1988-11-22 | Mitsubishi Chemical Industries Limited | Method for manufacturing concrete structure |
US4940617A (en) * | 1987-03-10 | 1990-07-10 | Akzo Nv | Multilayer hollow fiber wound body |
US5048441A (en) * | 1989-06-15 | 1991-09-17 | Fiberspar, Inc. | Composite sail mast with high bending strength |
US5051226A (en) * | 1989-09-18 | 1991-09-24 | The Boeing Company | Method of curing composite parts |
US5200251A (en) * | 1991-06-20 | 1993-04-06 | General Dynamics Corporation, Space Systems Division | Filament wound composite structure, its tooling and method of manufacture |
US5505035A (en) * | 1992-06-24 | 1996-04-09 | Lalvani; Haresh | Building systems with non-regular polyhedral nodes |
US5266137A (en) * | 1992-11-10 | 1993-11-30 | Hollingsworth Ritch D | Rigid segmented mandrel with inflatable support |
US5962150A (en) * | 1993-03-18 | 1999-10-05 | Jonathan Aerospace Materials Corporation | Lattice block material |
US5556677A (en) * | 1994-01-07 | 1996-09-17 | Composite Development Corporation | Composite shaft structure and manufacture |
US5871117A (en) * | 1994-04-28 | 1999-02-16 | Mcdonnell Douglas Corporation | Tubular load-bearing composite structure |
US6264684B1 (en) * | 1995-03-10 | 2001-07-24 | Impra, Inc., A Subsidiary Of C.R. Bard, Inc. | Helically supported graft |
US5463970A (en) * | 1995-03-13 | 1995-11-07 | Harken, Inc. | Furling foil for sailing vessel |
US5814386A (en) * | 1995-12-01 | 1998-09-29 | Mcdonnell Douglas Corporation | Composite shell formed as a body of rotation, and method and mandrel for making same |
US5921048A (en) * | 1996-04-18 | 1999-07-13 | Brigham Young University | Three-dimensional iso-tross structure |
US6013341A (en) * | 1996-08-19 | 2000-01-11 | Mcdonnell Douglas Corporation | Carrying (bearing) pipe-casing made of composite materials, the method and the setting (straightening device) for its manufacturing |
US6076324A (en) * | 1996-11-08 | 2000-06-20 | Nu-Cast Inc. | Truss structure design |
US6050315A (en) * | 1998-04-30 | 2000-04-18 | Alliant Techsystems Inc. | Method and apparatus for producing fiber reinforced structures |
US6290799B1 (en) * | 1998-04-30 | 2001-09-18 | Alliant Techsystems Inc. | Method for producing fiber reinforced structures |
US6053696A (en) * | 1998-05-29 | 2000-04-25 | Pratt & Whitney Canada Inc. | Impact resistant composite shell for gas turbine engine fan case |
US7132027B2 (en) * | 2001-08-17 | 2006-11-07 | Brigham Young University | Complex composite structures and method and apparatus for fabricating same from continuous fibers |
US7976925B2 (en) * | 2002-03-04 | 2011-07-12 | Ole-Bendt Rasmussen | Cross-laminate of oriented films, method of manufacturing same, and coextrusion die suitable in the process |
US20070175031A1 (en) * | 2006-01-31 | 2007-08-02 | Pham Doan D | One-piece inner shell for full barrel composite fuselage |
US20100064612A1 (en) * | 2008-08-15 | 2010-03-18 | Wilson Erich A | Lattice Support Structures |
US20100065717A1 (en) * | 2008-08-15 | 2010-03-18 | Wilson Erich A | Method and System For Forming Composite Geometric Support Structures |
US20100065192A1 (en) * | 2008-08-15 | 2010-03-18 | Wilson Erich A | Method and System For Forming Composite Geometric Support Structures |
Cited By (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100065192A1 (en) * | 2008-08-15 | 2010-03-18 | Wilson Erich A | Method and System For Forming Composite Geometric Support Structures |
US8313600B2 (en) | 2008-08-15 | 2012-11-20 | Sigma-Tek, Llc | Method and system for forming composite geometric support structures |
US20100064612A1 (en) * | 2008-08-15 | 2010-03-18 | Wilson Erich A | Lattice Support Structures |
US20130075025A1 (en) * | 2011-03-25 | 2013-03-28 | Maurice Guitton | Method of Manufacturing Hollow Composite Parts with In Situ Formed Internal Structures |
US8668800B2 (en) * | 2011-03-25 | 2014-03-11 | Maurice Guitton | Method of manufacturing hollow composite parts with in situ formed internal structures |
US20120299215A1 (en) * | 2011-05-24 | 2012-11-29 | Lockheed Martin Corporation | Mechanically collapsible shell for long cylinder production |
US8834147B2 (en) * | 2011-05-24 | 2014-09-16 | Lockheed Martin Corporation | Mechanically collapsible shell for long cylinder production |
US9409226B2 (en) * | 2011-08-12 | 2016-08-09 | Gfm-Gmbh | Apparatus for forging a hollow body |
US20130036785A1 (en) * | 2011-08-12 | 2013-02-14 | Gfm-Gmbh | Apparatus for forging a hollow body |
US20130181374A1 (en) * | 2012-01-16 | 2013-07-18 | Airbus Operations Gmbh | Molding tool and method for manufacturing a fiber reinforced plastic aerodynamic aircraft component |
US9144949B2 (en) * | 2012-01-16 | 2015-09-29 | Airbus Operations Gmbh | Molding tool and method for manufacturing a fiber reinforced plastic aerodynamic aircraft component |
US20180281325A1 (en) * | 2015-12-11 | 2018-10-04 | Contitech Luftfedersysteme Gmbh | Apparatus for making conical bellows |
CN106002097A (en) * | 2016-06-13 | 2016-10-12 | 中国科学院力学研究所 | Preparation method of lattice material reinforced square-to-circle special-shaped section thin-wall structure |
US20200378646A1 (en) * | 2018-06-20 | 2020-12-03 | Johns Manville | Methods, materials, and equipment to form improved fit duct liner insulation for round and oval hvac duct systems |
Also Published As
Publication number | Publication date |
---|---|
WO2010019948A2 (en) | 2010-02-18 |
WO2010019966A3 (en) | 2010-06-24 |
BRPI0917867A2 (en) | 2017-02-07 |
CA2770481A1 (en) | 2010-02-18 |
US20130196087A1 (en) | 2013-08-01 |
WO2010019964A3 (en) | 2010-04-01 |
US8444900B2 (en) | 2013-05-21 |
US20100065717A1 (en) | 2010-03-18 |
US20100064612A1 (en) | 2010-03-18 |
WO2010019948A3 (en) | 2010-07-22 |
WO2010019964A2 (en) | 2010-02-18 |
US20130233492A1 (en) | 2013-09-12 |
US20130167462A1 (en) | 2013-07-04 |
US20140150363A1 (en) | 2014-06-05 |
WO2010019966A2 (en) | 2010-02-18 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US20130196087A1 (en) | Collapsible Mandrel Tools and Associated Methods for Fabrication of Wound Composite Articles | |
US7815160B2 (en) | Composite mandrel | |
US20130243989A1 (en) | Lattice Support Structure | |
DE60130660T2 (en) | TUBULAR STRUCTURES OF HIGH PERFORMANCE COMPOUNDS | |
US20170052007A1 (en) | Arrow or Crossbow Bolt Shafts Having a Profiled Inner Diameter | |
EP1928633B1 (en) | Base for a rotating grinding or cutting tool, and grinding or cutting tool produced therefrom | |
JP5460821B2 (en) | Applicable blade | |
US20160114884A1 (en) | Method of fabricating a force transfer part having a lug made of composite material, and a part obtained by such a method | |
CN108129158A (en) | A kind of charcoal-charcoal thin-walled porous member and preparation method thereof | |
CA3039385C (en) | Filament-reinforced composite material with load-aligned filament windings | |
US10478996B1 (en) | Method of making ceramic composite bearings | |
US10988340B2 (en) | Fracking tools and methods of forming the same | |
KR20060000826A (en) | A composite rebar for concrete and the apparatus using the same | |
US20050056503A1 (en) | Filament wound strut and method of making same | |
KR102013968B1 (en) | Mandrel with sliding exterior projection | |
WO2016196817A1 (en) | Fishing rod with graphene and method of manufacturing | |
US11655636B2 (en) | Reinforcing body and method for its manufacturing | |
JP2001225273A (en) | Polishing/grinding material | |
US6231709B1 (en) | Method of making a spring out of thermostructural composite material | |
CN101733980A (en) | Fiber reinforced resin tapered rod and manufacturing method thereof | |
EP3597410A1 (en) | Composite component and manufacture thereof | |
DE102008057779A1 (en) | Molding core for making hollow, fibrous moldings with aerospace applications, is pulled out, causing it to unwind continuously as strip or series of segments | |
EP1010513A2 (en) | Foam mandrel for a filament wound composite casing | |
JP3174132B2 (en) | Core material for bending plastic pipes | |
US10569482B2 (en) | Method of manufacturing a strut and a strut formed thereby |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: SIGMA-TEK, LLC,UTAH Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:WILSON, ERICH A.;KIPP, MICHAEL D.;RIDGES, MICHAEL D.;SIGNING DATES FROM 20091201 TO 20091222;REEL/FRAME:023713/0712 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |