Patent application number | Description | Published |
20080251636 | AIRCRAFT THAT COMPRISES A STRUCTURE THAT ENSURES THE STRUCTURAL AND ELECTRICAL FUNCTIONS - An aircraft includes a structure with structural elements ( | 10-16-2008 |
20090020645 | Method for Frabricating an Aircraft Fuselage in Composite Material - A method for manufacturing an aircraft fuselage includes an internal framework surrounded by an external skin made of composite material, in which the internal framework at least partially constitutes a mould for manufacture and/or the support for the mould for the external skin made of composite material. The disclosed embodiments also relate to an aircraft fuselage produced using this method. | 01-22-2009 |
20090101756 | MONOLITHIC SELF-STIFFENED PANELS - A composite panel having a first skin forming the outer wall of the panel, known as the lower face ( | 04-23-2009 |
20100264272 | AIRCRAFT STRUCTURE INCLUDING STIFFENER EDGE JUNCTIONS - An aircraft structure including stiffened panels assembled at the junction, without continuity of the stiffeners. Multiple panels are used to form the fuselage, tail units and wings of an aircraft. These panels include stiffeners which are interrupted at each panel junction. However, the stresses experienced by the stiffeners must be transmitted despite these interruptions. Known solutions require the use of at least one additional part per stiffener and per interruption. In order to solve this problem, the disclosed embodiments include a doubler necessitating at most one additional part per panel junction area for all of the interrupted stiffeners in this area. | 10-21-2010 |
20100282905 | SPLICING OF OMEGA-SHAPED STIFFENERS AT A CIRCUMFERENTIAL JOINT IN AN AIRCRAFT FUSELAGE - An aircraft fuselage produced by assembling, at a circumferential joint, at least two sections, each section including a coating and at least one element of at least one stiffener, the aforementioned two elements having a closed cross section and being assembled by a splicing piece. The elements of the stiffener and the splicing piece are made of composite. The aforementioned splicing piece, which has two flanges, is fixed to the coatings and to the stiffener elements by working fastenings positioned only on the flanges of the aforementioned splicing piece. | 11-11-2010 |