| AIRBUS Operations S.L. Patent applications |
| Patent application number | Title | Published |
|---|
| 20120125517 | PEEL PLY MATERIAL FOR USE IN AN AUTOMATED TAPE LAYING MACHINE - A prepreg peel ply material ( | 05-24-2012 |
| 20120123743 | COMPUTER-ASSISTED METHOD FOR OPTIMISING SURFACES OF COMPOSITE-MATERIAL STRUCTURES - Computer-assisted method for optimising surfaces of composite-material structures as part of a design process that includes the following stages: a) Providing a multi-cell surface ( | 05-17-2012 |
| 20120111662 | ENGINE EXHAUST - It presents the novelty that the duct ( | 05-10-2012 |
| 20120110811 | PROCESS FOR REPAIRING AIRPLANE PANELS - A repair process for a composite material panel that forms part of a fuselage, wings, or stabilizers of an aircraft, with the panel having large dimensions and including irregular contours in some areas and edges prone to damages occurring from handling and assembly of the panel. The process a) locates the damage in the element of the composite material panel; b) sands the area that includes the damage in an area larger than the damage, makes a cut in the panel, having the cut of a same form as a piece that will serve to repair panel; c) places the piece in the cut, so that it is perfectly flush with the panel to be repaired; and d) attaches the piece to the composite material panel. | 05-10-2012 |
| 20120107435 | RE-USABLE RETAINERS FOR CO-BONDING UNCURED STRINGERS - A re-usable retainer designed to be used in the curing process of co-bonding uncured stringers. The re-usable retainer is made of metal so it is not necessary to manufacture one retainer for each manufactured stringer. The metallic retainer is placed in direct contact with the uncured resin so the cured stringer has a very good surface quality. | 05-03-2012 |
| 20120104168 | MANUFACTURING PROCEDURE OF A PART MADE OUT OF A COMPOSITE MATERIAL INTRODUCING A GEOMETRIC CHANGE IN ONE OF ITS FACES - A manufacturing procedure of a composite material part ( | 05-03-2012 |
| 20120104166 | INNER BENT REPAIRMENT - A method for repairing the skin of the fuselage of an airplane from the inside to be used when the skin of the fuselage has been damaged between a first stringer and a second stringer adjacent to the first one is provided. The method comprises four steps which are:
| 05-03-2012 |
| 20120091275 | Weathertight fitting for aircraft tail vertical stabiliser mounting - Weathertight fitting ( | 04-19-2012 |
| 20120085866 | INTERCHANGEABLE JOINT CONCEPT FOR AN AIRCRAFT REAR FUSELAGE CONE - Rear fuselage of an aircraft comprising a tail cone end and a rest of the real fuselage whereby the tail cone end is attached to the rest of the rear fuselage by means of an attachment system comprising a balancer fitting, three lugs and a waiting link. When there is a failure in one of the lugs, the balancer fitting acts supporting loads in the transversal direction of the aircraft. The waiting link only acts if a failure in other link occurs. This waiting link is able to support loads in the longitudinal direction of the aircraft. | 04-12-2012 |
| 20120074260 | REAR FUSELAGE OF AN AIRCRAFT - Rear fuselage of an aircraft comprising a tail cone end and a rest of the real fuselage whereby the tail cone end is attached to the rest of the rear fuselage by means of an attachment system comprising two upper lugs, two lower lugs and a detachable balancer fitting. The balancer fitting is an adjustable fitting, being locked in a Z and Y directions of a Cartesian axis and being movable along an X direction of the Cartesian axis providing guidance for the tail cone end and the rest of the rear fuselage. | 03-29-2012 |
| 20120064277 | DIRECTIONALLY STRENGTHENED UNION ARRANGEMENT OF PARTS MADE OUT OF COMPOSITE MATERIALS - A riveted union arrangement between parts of composite material in which, in the area of the union, at least one of the parts ( | 03-15-2012 |
| 20120001024 | INTERNAL STRUCTURE OF AIRCRAFT MADE OF COMPOSITE MATERIAL - Reinforcement structure ( | 01-05-2012 |
| 20110303357 | PROCEDURE FOR THE MANUFACTURE OF LARGE PARTS OF COMPOSITE MATERIAL CONTROLLING THE THICKNESS OF THE EDGES THEREOF - Procedure for the manufacture of large parts of composite material, controlling the thickness of the edges thereof. It relates to the manufacture of a part ( | 12-15-2011 |
| 20110290941 | Attachment system of aircraft components - An attachment system for attaching a component ( | 12-01-2011 |
| 20110268926 | INTERNAL STRUCTURE FOR AIRCRAFT IN COMPOSITE MATERIAL - Internal structure for aircraft comprising a skin ( | 11-03-2011 |
| 20110233335 | IMPACT RESISTANT AND DAMAGE TOLERANT AIRCRAFT FUSELAGE - The aircraft fuselage part ( | 09-29-2011 |
| 20110224952 | MULTIPLE DAMAGE METHOD FOR STRUCTURAL DESIGN OPTIMIZATION - A computer-aided method for carrying out the structural design of a part subjected to damages having significant effects on its structural integrity, such as an aircraft fuselage section subjected to a PBR event, comprising steps of: Obtaining FE models that include all the relevant information for an optimization analysis for the un-damaged part and for at least one possible damaged part; Defining at least one design variable of said part and at least one design constraint and one load case for said un-damaged part and for said damaged part; Providing at least one simulation module for analyzing one or more failure modes of said part; Iteratively modifying the design variables of said part for the purpose of optimizing said target function by analyzing simultaneously said un-damaged part and said at least one damaged part using said at least one simulation module. | 09-15-2011 |
| 20110174928 | JOINING ARRANGEMENT FOR THE LATERAL BOXES OF A HORIZONTAL TAIL STABILISER WITH A TUBULAR CENTRAL BOX AND MANUFACTURING METHOD FOR SAID BOX - Joining arrangement for the lateral boxes ( | 07-21-2011 |
| 20110174927 | AIRCRAFT COMPONENT WITH PANELS STIFFENED WITH STRINGERS - Aircraft component with panels ( | 07-21-2011 |
| 20110167614 | JOINING ARRANGEMENT FOR TWO BOXES OF COMPOSITE MATERIAL WITH AN INTERMEDIATE PART AND METHOD FOR MANUFACTURING SAID INTERMEDIATE PART - Joining arrangement for two boxes ( | 07-14-2011 |
| 20110161057 | METHODS AND SYSTEMS FOR OPTIMISING THE DESIGN OF AERODYNAMIC SURFACES - Methods and systems for optimising the design of aerodynamic surfaces. They include in the design process of the aerodynamic surface of a body ( | 06-30-2011 |
| 20110159244 | COMPOSITE MATERIAL PART WITH STRINGER ON RAMP - Composite material part ( | 06-30-2011 |
| 20110159242 | AIRCRAFT FUSELAGE FRAME IN COMPOSITE MATERIAL WITH STABILIZED WEB - Aircraft fuselage frame ( | 06-30-2011 |
| 20110147517 | PIVOTING STABILISING SURFACE FOR AIRCRAFT - An aircraft ( | 06-23-2011 |
| 20110127374 | METHODS AND SYSTEMS FOR MINIMIZING FLOW DISTURBANCES IN AIRCRAFT PROPELLER BLADES CAUSED BY UPSTREAM PYLONS - Methods for minimizing the effects of pylori induced disturbances of the airflow at the propeller blades ( | 06-02-2011 |
| 20110120621 | CONNECTION OF AERONAUTICAL STRUCTURAL ELEMENTS WITH OTHER THERMOPLASTIC ELEMENTS - Connection of elements ( | 05-26-2011 |
| 20110106503 | WIND TUNNEL AIRCRAFT MODEL WITH TRUNCATED WING - An aircraft model ( | 05-05-2011 |
| 20110095129 | ARRANGEMENT OF A CIRCUMFERENTIAL JOINT OF STRUCTURAL ELEMENTS WITH A COUPLING ELEMENT MANUFACTURED IN COMPOSITE MATERIAL - Arrangement of a circumferential joint of structural elements with a coupling element manufactured in composite material in a aeronautic structure, which comprises: two sections ( | 04-28-2011 |
| 20110073711 | JOINING OF STRUCTURAL AIRCRAFT ELEMENTS - Joining of a structural aircraft element ( | 03-31-2011 |
| 20110061450 | METHOD FOR LOCATING PRESSURE LOSSES IN VACUUM BAGS - Method for locating pressure losses in vacuum bags used in the manufacturing of composite material parts, according to which the vacuum bag with a part in its interior coated by airweave at a pressure lower than atmospheric pressure, is exposed to contact with a gas dispersion at atmospheric pressure of solid suspended tracing particles, preferably tar, which in the event of there being pressure losses in the vacuum bag, are deposited in the airweave areas close to them. The contact between the vacuum bag and the gas dispersion is performed preferably through an applier of said gas dispersion over the vacuum bag through an application device, either in open surroundings or in closed surroundings such as an autoclave. | 03-17-2011 |
| 20100294889 | DEVICE FOR JOINING TORSION BOXES OF AIRCRAFT - The invention relates to a device ( | 11-25-2010 |
| 20100264271 | FITTINGS FOR ATTACHING THE VERTICAL TAIL STABILIZER OF AN AIRCRAFT - The invention relates to fittings ( | 10-21-2010 |
| 20100230538 | CLOSED STRUCTURE OF COMPOSITE MATERIAL - The invention relates to a tubular-shaped closed structure ( | 09-16-2010 |
| 20100219287 | PROTECTION AGAINST DIRECT LIGHTNING STRIKES IN RIVETED AREAS OF CFRP PANELS - The invention relates to a metalization structure of aircraft panels and process for obtaining such structure, such that it comprise a structure of a panel ( | 09-02-2010 |
