Patent application number | Description | Published |
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 |
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 |
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 |
20150030381 | METHODS OF MANUFACTURING ELONGATE WELDMENTS - Methods of manufacture include welding two or more elongate members together to define an elongate weldment, wherein the welding results in a weld region that is in tension and regions adjacent to the weld region that are in compression, and longitudinally stretching the elongate weldment. Tools and systems for manufacturing elongate weldments, as well as apparatuses, such as aircraft, that include elongate weldments, also are disclosed. | 01-29-2015 |