Patent application number | Description | Published |
20100028352 | COMPOSITIONS AND METHODS COMPRISING GLYCYL-tRNA SYNTHETASES HAVING NON-CANONICAL BIOLOGICAL ACTIVITIES - Isolated glycyl-tRNA synthetase polypeptides and polynucleotides having non-canonical biological activities are provided, as well as compositions and methods related thereto. | 02-04-2010 |
20100297149 | COMPOSITIONS AND METHODS COMPRISING HISTIDYL-TRNA SYNTHETASE SPLICE VARIANTS HAVING NON-CANONICAL BIOLOGICAL ACTIVITIES - Isolated histidyl-tRNA synthetase splice variant polynucleotides and polypeptides having non-canonical biological activities are provided, as well as compositions and methods related thereto. | 11-25-2010 |
20130108630 | AMINO ACYL TRNA SYNTHETASES FOR MODULATING INFLAMMATION | 05-02-2013 |
20130236455 | COMPOSITIONS AND METHODS COMPRISING GLYCYL-tRNA SYNTHETASES HAVING NON-CANONICAL BIOLOGICAL ACTIVITIES - Isolated glycyl-tRNA synthetase polypeptides and polynucleotides having non-canonical biological activities are provided, as well as compositions and methods related thereto. | 09-12-2013 |
20130243766 | COMPOSITIONS AND METHODS COMPRISING HISTIDYL-TRNA SYNTHETASE SPLICE VARIANTS HAVING NON-CANONICAL BIOLOGICAL ACTIVITIES - Isolated histidyl-tRNA synthetase splice variant polynucleotides and polypeptides having non-canonical biological activities are provided, as well as compositions and methods related thereto. | 09-19-2013 |
20130273045 | AMINO ACYL TRNA SYNTHETASES FOR MODULATING INFLAMMATION - Inflammatory and other cellular response-modulating compositions are provided comprising aminoacyl-tRNA synthetase polypeptides, including active fragments and/or variants thereof Also provided are methods of using such compositions in the treatment of conditions that benefit from the modulation of inflammation, such as inflammatory diseases or conditions. | 10-17-2013 |
20140302075 | ASPARTYL-TRNA SYNTHETASES - The present invention provides aspartyl-tRNA synthetase derived proteins (DRS polypeptides) with altered cysteine content, compositions comprising the same, and methods of using such polypeptides and compositions for treating or diagnosing a variety of conditions. The DRS polypeptides of the invention have immunomodulatory properties, and exhibit improved activity and stability. | 10-09-2014 |
20140363415 | COMPOSITIONS AND METHODS COMPRISING GLYCYL-TRNA SYNTHETASES HAVING NON-CANONICAL BIOLOGICAL ACTIVITIES - Isolated glycyl-tRNA synthetase polypeptides and polynucleotides having non-canonical biological activities are provided, as well as compositions and methods related thereto. | 12-11-2014 |
20140371294 | COMPOSITIONS AND METHODS COMPRISING HISTIDYL-TRNA SYNTHETASE SPLICE VARIANTS HAVING NON-CANONICAL BIOLOGICAL ACTIVITIES - Isolated histidyl-tRNA synthetase splice variant polynucleotides and polypeptides having non-canonical biological activities are provided, as well as compositions and methods related thereto. | 12-18-2014 |
20150140072 | AMINOACYL TRNA SYNTHETASES FOR MODULATING INFLAMMATION - Inflammatory and other cellular response-modulating compositions are provided comprising aminoacyl-tRNA synthetase polypeptides, including active fragments and/or variants thereof. Also provided are methods of using such compositions in the treatment of conditions that benefit from the modulation of inflammation, such as inflammatory diseases or conditions. | 05-21-2015 |
Patent application number | Description | Published |
20090139641 | COMPOSITE SECTIONS FOR AIRCRAFT FUSELAGES AND OTHER STRUCTURES, AND METHODS AND SYSTEMS FOR MANUFACTURING SUCH SECTIONS - Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections, are disclosed herein. A method for manufacturing a shell structure in accordance with one embodiment of the invention includes applying composite material to an interior mold surface of a tool to form a skin extending 360 degrees around an axis. The method can further include positioning a plurality of stiffeners on an inner surface of the skin. After the stiffeners have been positioned, a vacuum bag can be installed over the stiffeners and evacuated to press the stiffeners and the skin outwardly against the interior mold surface of the tool. Next, the skin/stiffener combination can be cocured to bond the stiffeners to the skin and harden the shell structure. | 06-04-2009 |
20090142130 | DOUBLE SHEAR JOINT FOR BONDING IN STRUCTURAL APPLICATIONS - Embodiments of methods and apparatus for providing a double shear joint for bonding in structural applications are disclosed. In one embodiment, a bonded composite joint includes a base having a foot configured to couple to a member, the base including a flange extending outward from the foot. The joint further includes a panel having a core configured between opposing skins, the skins having inner walls proximate the core, the skins extending outward beyond the core on at least one end of the panel to define a recess between the skins, the recess configured to receive the flange. A bonding agent is used to couple the flange to the inner walls of the panel. | 06-04-2009 |
20090184204 | DISTRIBUTION OF POINT LOADS IN HONEYCOMB PANELS - Composite panels used in aircraft are formed by a sandwich including a lightweight honeycomb core reinforced by a solid plank in medial regions of the panel. The plank is bonded to the honeycomb and forms an integral part of the core where a strut is attached to the panel. The plank distributes point loads imposed on the panel by the strut. | 07-23-2009 |
20090314894 | AIRPLANE FAIRING PANEL ADJUSTABLE FITTING ASSEMBLY, KIT AND METHOD - An airplane fairing panel adjustable fitting assembly allows for installation and removal of a fairing panel from outside the fairing. Blind retention features are provided and a pivoting link structure is facilitated to accommodate flexing of an aircraft structure in use. Kits and methods of attaching fairing panels are also disclosed. | 12-24-2009 |
20100230042 | Double Shear Joint For Bonding in Structural Applications - A bonded composite joint may include a base having a foot configured to couple to a member. The base may include a flange extending outward from the foot. The joint further may include a panel having a core positioned between opposing skins, where the skins have inner walls proximate the core and the skins extend outward beyond the core on at least one end of the panel to define a recess between the skins. The recess between the skins may receive the flange. A bonding agent may be used to couple the flange to the inner walls of the panel. | 09-16-2010 |
20110039057 | LAMINATED COMPOSITE ROD AND FABRICATION METHOD - A laminated composite rod includes a rod body having a generally circular or oval cross-section and comprising a plurality of laminated composite plies disposed at various orientations with respect to each other. | 02-17-2011 |
20130034705 | Molybdenum Composite Hybrid Laminates and Methods - In an embodiment of the disclosure, there is provided a molybdenum composite hybrid laminate. The laminate has a plurality of composite material layers. The laminate further has a plurality of surface treated molybdenum foil layers interweaved between the composite material layers. The laminate further has a plurality of adhesive layers disposed between and bonding adjacent layers of the composite material layers and the molybdenum foil layers. | 02-07-2013 |
20140293497 | Method and Apparatus for Providing a Current Return Network in an Aircraft Structure - According to an embodiment a current return network assembly, for an aircraft having a predetermined potential lightning strike zone, is mounted within the predetermined potential lightning strike zone. The current return network assembly includes an electrically conductive honeycomb central core that conducts electrical current both through the assembly and through the predetermined potential lightning strike zone. The electrical current is caused by a lightning strike on the aircraft at the predetermined potential lightning strike zone. According to an embodiment, an aircraft has a predetermined potential lightning strike zone. A current return network assembly is within the zone. An electrically conductive honeycomb central core is provided for conducting electrical current through the assembly and through the zone wherein the electrical current has been caused by a lightning strike on the aircraft at the zone. | 10-02-2014 |
20150306859 | MOLYBDENUM COMPOSITE HYBRID LAMINATES AND METHODS - A method of forming a molybdenum composite hybrid laminate is disclosed. The method includes treating a surface of each of a plurality of molybdenum foil layers. The method further includes interweaving the surface treated molybdenum foil layers with a plurality of composite material layers. The method further includes bonding with an adhesive layer each of the surface treated molybdenum foil layers to adjacent composite material layers to form a molybdenum composite hybrid laminate having improved yield strength. | 10-29-2015 |
Patent application number | Description | Published |
20120180942 | Composite Sections for Aircraft Fuselages and Other Structures and Methods and Systems for Manufacturing Such Sections - Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections, are disclosed herein. A method for manufacturing a shell structure in accordance with one embodiment of the invention includes applying composite material to an interior mold surface of a tool to form a skin extending 360 degrees around an axis. The method can further include positioning a plurality of stiffeners on an inner surface of the skin. After the stiffeners have been positioned, a vacuum bag can be installed over the stiffeners and evacuated to press the stiffeners and the skin outwardly against the interior mold surface of the tool. Next, the skin/stiffener combination can be cocured to bond the stiffeners to the skin and harden the shell structure. | 07-19-2012 |
20130037217 | COMPOSITE SECTIONS FOR AIRCRAFT FUSELAGES AND OTHER STRUCTURES, AND METHODS AND SYSTEMS FOR MANUFACTURING SUCH SECTIONS - Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections, are disclosed herein. A method for manufacturing a shell structure in accordance with one embodiment of the invention includes applying composite material to an interior mold surface of a tool to form a skin extending 360 degrees around an axis. The method can further include positioning a plurality of stiffeners on an inner surface of the skin. After the stiffeners have been positioned, a vacuum bag can be installed over the stiffeners and evacuated to press the stiffeners and the skin outwardly against the interior mold surface of the tool. Next, the skin/stiffener combination can be cocured to bond the stiffeners to the skin and harden the shell structure. | 02-14-2013 |
20130040008 | Composite Sections for Aircraft Fuselages and Other Structures, and Methods and Systems for Manufacturing Such Sections - Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections, are disclosed herein. A method for manufacturing a shell structure in accordance with one embodiment of the invention includes applying composite material to an interior mold surface of a tool to form a skin extending 360 degrees around an axis. The method can further include positioning a plurality of stiffeners on an inner surface of the skin. After the stiffeners have been positioned, a vacuum bag can be installed over the stiffeners and evacuated to press the stiffeners and the skin outwardly against the interior mold surface of the tool. Next, the skin/stiffener combination can be cocured to bond the stiffeners to the skin and harden the shell structure. | 02-14-2013 |