| 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 |
| 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 |
| 20100129589 | REINFORCED FOAM-FILLED COMPOSITE STRINGER - A method and apparatus for manufacturing a composite stringer. A composite material and foam are laid up onto a tool in the form of a stringer. The foam has a plurality of structural members within the foam. The plurality of structural members has a number of orientations to resist a number of loads. The composite material, the foam in the form of the stringer, and the plurality of structural members are cured to form the composite stringer. | 05-27-2010 |
| 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 |
| 20110097554 | CURVED COMPOSITE FRAMES AND METHOD OF MAKING THE SAME - A curved composite aircraft frame comprises a multi-ply composite laminate having a generally Z-shaped cross section. At least certain of the laminate plies include unidirectional reinforcing fibers that are substantially tangent at substantially all points along the curvature of the frame. | 04-28-2011 |
| 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 |
