Patent application number | Description | Published |
20080290214 | SHAPED COMPOSITE STRINGERS AND METHODS OF MAKING - A stiffened skin panel of an aircraft that includes an aircraft skin panel of composite material and a composite stringer consolidated with the aircraft skin panel. The stringer has a pair of stringer sides, each extending from a stringer top to a stringer leg. The stringer sides may each extend through a wide radius, smooth continuous curve to a stringer leg. The wide radius, smooth continuous curve may be proximate the base of the stringer side in a region where the stringer side transitions to the stringer leg. | 11-27-2008 |
20090127393 | FOAM STIFFENED HOLLOW COMPOSITE STRINGER - A method and apparatus for a composite stringer. A method is used for manufacturing a hollow composite stringer. Foam is formed with a mandrel installed into the foam. A composite material and the foam is laid up onto a tool in a form of a stringer. The composite material and the foam in the form of the stringer is cured to form a cured stringer. The mandrel from the foam is removed to form the hollow composite stringer. | 05-21-2009 |
20090261199 | METHOD FOR PRODUCING CONTOURED COMPOSITE STRUCTURES AND STRUCTURES PRODUCED THEREBY - A method is provided for forming a composite part contoured along its length and having at least one leg. The method includes forming a stack of fiber reinforced, pre-preg plies by laying down individual segments of unidirectional fibers in each ply. Each of the segments is placed in a preselected orientation related to the contour of the part. The leg is formed by bending a portion of the stack over a tool. | 10-22-2009 |
20090263618 | METHOD FOR PRODUCING CONTOURED COMPOSITE STRUCTURES AND STRUCTURES PRODUCED THEREBY - A contoured composite structure is fabricated by laying up a composite charge that includes at least one ply formed by uni-directional fiber pre-preg ply segments having substantially constant widths. The ply segments are placed in side-by-side, overlapping relationship with their longitudinal centerlines aligned in a polar orientation related to the contour of the structure. The charge is formed into the shape of the structure and cured. | 10-22-2009 |
20100078845 | WRINKLE REDUCTION IN UNCURED COMPOSITE LAMINATES - Wrinkles are removed from fiber reinforced resin plies of an uncured composite layup by subjecting the wrinkles to vibration and pressure. | 04-01-2010 |
20100080941 | COMPOSITE TRUSS PANEL HAVING FLUTED CORE AND METHOD FOR MAKING THE SAME - A composite truss structure employs a sandwich-in-sandwich construction in which a composite fluted core is sandwiched between two facesheets, and at least one structural foam stiffener is sandwiched within the core or between the facesheets and/or the core. | 04-01-2010 |
20100080942 | JOINING CURVED COMPOSITE SANDWICH PANELS - A curved composite structure, comprises at least two curved composite panel segments joined together. Each of the panel segments includes a fluted core sandwiched between first and second facesheets. A layer of adhesive is used to rigidly bond the panel segments together. | 04-01-2010 |
20110027526 | Multi-Functional Aircraft Structures - A method and apparatus for manufacturing a composite structure. A filler material with a barrier material for a channel in the filler material is formed. A composite material and the filler material with the barrier material are laid up onto a tool in a shape of the composite structure. The composite material and the filler material in the shape of the composite structure are cured. | 02-03-2011 |
20110088833 | SHAPED COMPOSITE STRINGERS AND METHODS OF MAKING - A stiffened skin panel of an aircraft that includes an aircraft skin panel of composite material and a composite stringer consolidated with the aircraft skin panel. The stringer has a pair of stringer sides, each extending from a stringer top to a stringer leg. The stringer sides may each extend through a wide radius, smooth continuous curve to a stringer leg. The wide radius, smooth continuous curve may be proximate the base of the stringer side in a region where the stringer side transitions to the stringer leg. | 04-21-2011 |
20110111183 | Foam Stiffened Hollow Composite Stringer - A method and apparatus for a composite stringer. A method is used for manufacturing a hollow composite stringer. Foam is formed with a mandrel installed into the foam. A composite material and the foam is laid up onto a tool in a form of a stringer. The composite material and the foam in the form of the stringer is cured to form a cured stringer. The mandrel from the foam is removed to form the hollow composite stringer. | 05-12-2011 |
20110300343 | Composite Truss Panel Having Fluted Core - A composite truss structure employs a sandwich-in-sandwich construction in which a composite fluted core is sandwiched between two facesheets, and at least one structural foam stiffener is sandwiched within the core or between the facesheets and/or the core. | 12-08-2011 |
20120090265 | METHOD FOR JOINING SANDWICH TRUSS CORE PANELS AND COMPOSITE STRUCTURES PRODUCED THEREFROM - Fluted core sandwich panels are joined together to form a composite structure. Variations in panel ends are accommodated by a core stiffener insert installed in a joint between ends of the panels. | 04-19-2012 |
20140034236 | RADIUS FILLERS FOR COMPOSITE STRUCTURES, COMPOSITE STRUCTURES THAT INCLUDE RADIUS FILLERS, AND SYSTEMS AND METHODS OF FORMING THE SAME - Radius fillers for composite structures, composite structures that include the radius fillers, and systems and methods of forming the radius fillers. The systems and methods may be configured to create a pre-form that may be utilized to form a radius filler and/or create a radius filler from the pre-form. Creating the pre-form may include extending a plurality of lengths of composite tape from a composite tape source and receiving the plurality of lengths of composite tape in a pre-form forming structure, converging and/or otherwise combining the plurality of lengths of composite tape within the pre-form forming structure to produce the pre-form, and/or withdrawing the pre-form from the pre-form forming structure. Creating the radius filler from the pre-form may include receiving the pre-form in a radius filler forming structure and producing the radius filler from the radius filler forming structure. | 02-06-2014 |
20140318705 | MULTI-FUNCTIONAL AIRCRAFT STRUCTURES - A method for manufacturing a composite structure. A filler material with a barrier material for a channel in the filler material is formed. A composite material and the filler material with the barrier material are laid up onto a tool in a shape of the composite structure. The composite material and the filler material in the shape of the composite structure are cured. | 10-30-2014 |
20140363595 | METHOD FOR JOINING SANDWICH TRUSS CORE PANELS AND COMPOSITE STRUCTURES PRODUCED THEREFROM - Fluted core sandwich panels are joined together to form a composite structure. Variations in panel ends are accommodated by a core stiffener insert installed in a joint between ends of the panels. | 12-11-2014 |
20150079314 | JOINING CURVED COMPOSITE SANDWICH PANELS - A curved composite structure, comprises at least two curved composite panel segments joined together. Each of the panel segments includes a fluted core sandwiched between first and second facesheets. A layer of adhesive is used to rigidly bond the panel segments together. | 03-19-2015 |