| 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 |
| 20090320292 | METHOD AND APPARATUS FOR FORMING AND INSTALLING STRINGERS - A hands-free method and related apparatus are used to shape, place and compact a composite stringer on a composite skin of an aircraft. A composite charge is placed on a tool assembly that used to shape the charge into a preformed stringer. With the stringer held on the tool assembly, the tool assembly is used to move the preformed stringer into proximity with the skin and both place and compact the stringer against the skin. Following compaction of the stringer, the tool assembly is removed and the skin and the stringer are co-cured. | 12-31-2009 |
| 20100006739 | Composite Mandrel For Autoclave Curing Applications - A composite mandrel includes a generally elongated mandrel body comprising a resilient mandrel core and an elastomeric mandrel outer layer disposed outside the mandrel core. A method for fabricating a contoured stiffened composite panel is also disclosed. | 01-14-2010 |
| 20100009124 | Mandrel for Autoclave Curing Applications - A mandrel used to cure a composite part layup has an elastic body and at least one internal open space therein. The internal open space is configured to allow substantially uniform thermal expansion of the body during curing. | 01-14-2010 |
| 20100140834 | Extrusion of Adhesives for Composite Structures - A structural filler is installed in a gap between at least first and second composite members by extruding a flowable filler material, placing the extruded filler on one of the composite structural members, and assembling the composite members. | 06-10-2010 |
| 20100154984 | AUTOMATED ELONGATE INSERT WRAPPING SYSTEM - A method and apparatus for a tray, a folding section connected to the tray, and a tape application system. The tray has a channel for receiving an elongate insert for a composite material with a number of layers for a release system. The folding section is capable of folding a number of layers around the elongate insert to cover the elongate insert as the elongate insert is moved through the folding unit. The tape application system is capable of applying a tape to the number of layers for covering the elongate insert to form the release system. | 06-24-2010 |
| 20100155984 | MANUFACTURING ONE-PIECE COMPOSITE SECTIONS USING OUTER MOLD LINE TOOLING - A method for manufacturing composite parts. A temporary removal layer may be placed on an inner mold line tool. A composite material may be laid up on the inner mold line tool for a composite part. The inner mold line tool may be positioned with the composite part inside an outer mold line tool. The composite part and the temporary removal layer may be transferred from the inner mold line tool to the outer mold line tool. The inner mold line tool and the temporary removal layer may be removed from inside of the outer mold line tool after transferring the composite part and the temporary removal layer to the outer mold line tool. | 06-24-2010 |
| 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 |
