| Patent application number | Description | Published |
|---|
| 20080257490 | STRINGER HOLDING DEVICE - In accordance with the present invention an apparatus for securing a plurality of stringers to a mandrel during lay-up is provided, the plurality of stringers and mandrel forming a lay-up surface. The apparatus includes a vacuum source and a first vacuum attachment assembly comprising a first vacuum cup assembly and a first flexible tube assembly in communication with said vacuum source to tightly secure down against the lay-up surface. A second vacuum attachment assembly comprises a second vacuum cup assembly and a second flexible tube assembly in communication with the vacuum source to force it tightly down against the lay-up. A flexible spacer is in rigid communication with the second vacuum cup assembly and includes an extended end in communication with the first vacuum cup assembly such that the flexible spacer presses one of the stringers against the mandrel. | 10-23-2008 |
| 20090123588 | Apparatus For Forming Structural Members - A method and associated apparatus for forming a composite structural member from a charge are provided. The charge can be disposed on a first die of the apparatus and formed to a desired configuration defined by a recess of the die by inserting a second die or a tool into the recess. In some cases, the first die can include two portions that are adjustable in a transverse direction so that the recess can be opened by the insertion of the second die or tool. The second die or tool can be a substantially rigid member or an inflatable bladder. In either case, the charge can be disposed on the first die, formed, and then further processed on the first die, thereby facilitating indexing of the charge for each operation. | 05-14-2009 |
| 20090133261 | CONFORMAL VACUUM CUP APPARATUS AND METHOD - During the manufacture an aircraft, a tool-carrying rail is removably attached to a rail-side surface of the aircraft with a vacuum cup. The tool-carrying rail includes a longitudinal axis to mount a tool. The vacuum cup is stiffened along a first axis transverse to the longitudinal axis of the tool-carrying rail and the vacuum cup is stiffened along a second axis parallel to the rail-side surface of the aircraft. To removably attach the tool-carrying rail, a perimeter of the vacuum cup is removably sealed to the rail-side surface of the aircraft against vacuum loss and a point on the rail is rigidly positioned with respect to a point on the rail-side surface of the aircraft. In addition, a vacuum source is coupled to a spatial volume occupying all of a space between the vacuum cup and the rail-side surface of the aircraft and the tool is slidably positioned along the longitudinal axis of the tool-carrying rail. | 05-28-2009 |
| 20090140038 | Production System And An Associated Index Device For Use As A Reference Feature - A production system for manufacturing a workpiece comprises an index system including a plurality of index devices removably mounted on the workpiece at known longitudinally spaced locations therealong, and a longitudinally extending index member releasably engaged with at least two of the index devices such that a position and orientation of the index member are fixed relative to the workpiece by the index devices, the index member having position-indicating features distributed therealong. The production system further comprises a machine module mounted for longitudinal movement along the index member and operable to perform an operation, the machine module being operable to detect the position-indicating features on the index member and thereby determine a position of the machine module relative to the workpiece. | 06-04-2009 |
| 20090145545 | Composite Manufacturing Method - A modular composite manufacturing method. An illustrative embodiment of the method includes providing a plurality of composite modules; inspecting the composite modules; providing a curing tool; and placing the composite modules on the curing tool. | 06-11-2009 |
| 20090148647 | Method of Fabricating Structures Using Composite Modules and Structures Made Thereby - A large scale composite structure is fabricated by forming a plurality of composite laminate modules and joining the modules together along their edges using scarf joints. | 06-11-2009 |
| 20090297358 | MODIFIED BLADE STIFFENER AND FABRICATION METHOD THEREFOR - The disclosure is generally directed to a modified blade stiffener having enhanced mechanical properties. An illustrative embodiment of the modified blade stiffener includes a stiffener-forming material shaped into a pair of coupled blades having first and second ends, a filler cavity provided at the first end of the blades, a blade filler provided in the filler cavity and a pair of blade flanges provided at the second end of the blades. | 12-03-2009 |
| 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 |
| 20100011580 | METHOD AND APPARATUS FOR LAYUP PLACEMENT - Method and apparatus for layup placement on a layup structure is provided. The method includes iteratively loading a layup for the layup structure on a support frame of a saddle module; aligning the saddle module with a pre-selected registration position corresponding to a predetermined application path on the layup structure; and impressing the layup into forced contact with the layup structure along the predetermined application path using a predetermined application force. The apparatus includes a plurality of saddle modules configured to operate in unison, wherein the plurality of saddle modules is configured to receive a pre-selected composite material layup. | 01-21-2010 |
| 20100012260 | PRE-PATTERNED LAYUP KIT AND METHOD OF MANUFACTURE - A pre-patterned layup kit with layup patterned to accommodate an airframe topological feature, trimmed to fit a preselected target region of a layup structure, and conformed to the target region contour. The kit can be fabricated in advance of airframe manufacture and stored until use. The kit includes a flexible carrier upon which the layup is laid, and a release layer between the layup and the carrier. The layup has multiple laminae oriented to an carrier indexing element, and indexed to the target region thereby. A kit manufacturing method includes preparing the laminae constituent of the layup, preparing the carrier, and laying down the laminae on the carrier to make the kit. The kit can be compacted, inspected, and prepared for storage. The layup can be fabricated of a pre-patterned lamina or multiple laminae that are shaped and trimmed to accommodate an airframe topological feature. | 01-21-2010 |
| 20100068326 | Tools for Manufacturing Composite Parts and Methods for Using Such Tools - Tools for manufacturing composite parts and methods for using such tools are disclosed herein. A method in accordance with one aspect of the invention includes manufacturing a fiber-reinforced resin part from a plurality of fibers positioned on a tool having a female mold surface. The mold surface can include a first side region, a second side region, an interior region between the first and second side regions, and transition regions between the first and second side regions and the interior region. The method includes positioning a compaction tool over the mold surface. The compaction tool includes a first pressing device and a second pressing device carrying the first pressing device. The method further includes pressing a first portion of the fibers against the transition regions with the first pressing device without generally compacting the portions of the fibers outboard of the transition regions. After pressing the first portion of the fibers, the method includes pressing a second portion of the fibers against the first and second side regions and shoulder regions of the mold surface outboard of the first and second side regions. | 03-18-2010 |
| 20100084087 | Apparatus and method for composite material trim-on-the-fly - Disclosed is a method and apparatus for manufacturing multiple layer composite structures and structures containing components made of multiple layer composite structures, comprising dispensing layers of composite material, trimming each layer to its final shape as it is being dispensed, and positioning it properly with respect to prior layers in the part lay-up. | 04-08-2010 |
| 20100102482 | Method and Apparatus for Forming Highly Contoured Composite Parts - A method of forming a flat composite charge into a contoured composite part reduces wrinkles in the part as the charge is being formed. Dies are used to form a portion of charge to the steepest contour of the part, while tension is maintained on the charge as the remaining portions of the charge are formed. | 04-29-2010 |
| 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 |
| 20100283195 | PRODUCTION SYSTEM AND AN ASSOCIATED INDEX DEVICE FOR USE AS A REFERENCE FEATURE - A production system for manufacturing a workpiece comprises an index system including a plurality of index devices removably mounted on the workpiece at known longitudinally spaced locations therealong, and a longitudinally extending index member releasably engaged with at least two of the index devices such that a position and orientation of the index member are fixed relative to the workpiece by the index devices, the index member having position-indicating features distributed therealong. The production system further comprises a machine module mounted for longitudinal movement along the index member and operable to perform an operation, the machine module being operable to detect the position-indicating features on the index member and thereby determine a position of the machine module relative to the workpiece. | 11-11-2010 |
