AIRBUS Operations S.L. Patent applications |
Patent application number | Title | Published |
20150053332 | METHOD AND DEVICE FOR MANUFACTURING COMPOSITE MATERIAL PARTS - The manufacturing method object of the invention comprises the following stages: A) stacking strips of prepreg material on a laminating tool ( | 02-26-2015 |
20140352877 | HYBRID TOOL FOR CURING PIECES OF COMPOSITE MATERIAL - A hybrid tool for curing composite structures for aircrafts, such as stringers, torsion boxes, skin panels, wing surfaces, horizontal tail or vertical stabilizers, etc. The hybrid tool comprises a metallic portion and an elastic portion arranged on a surface of the metallic portion. The elastic portion and the metallic portion are permanently joined to each other so that the metallic portion and the elastic portion together define a surface having a shape which copies at least part of a surface of a piece of composite material to be cured. The tool is capable of satisfactorily curing pieces of composite material which have a minimum thickness and/or a very aggressive change of thickness. | 12-04-2014 |
20140339370 | TRAILING EDGE OF AN AIRCRAFT AERODYNAMIC SURFACE - The invention discloses a trailing edge ( | 11-20-2014 |
20140216635 | METHOD FOR ASSEMBLING ELEMENTS OF COMPOSITE MATERIAL FOR AIRCRAFTS, WITH STRESS RELAXATION IN THE ELEMENTS - The invention relates to a method of assembling composite material parts ( | 08-07-2014 |
20140183301 | AIRCRAFT VENTRAL FAIRING WITH AN IMPROVED STORAGE CAPACITY - The invention provides an aircraft with a ventral fairing able to store equipment and systems in lateral zones. The ventral fairing ( | 07-03-2014 |
20140151506 | HIGHLY INTEGRATED STRUCTURE INCLUDING LEADING AND TRAILING EDGE RIBS FOR AN AIRCRAFT LIFTING SURFACE - The invention provides an aircraft lifting surface with a monolithic main supporting structure ( | 06-05-2014 |
20140138486 | OPTIMIZED TORSION BOX FOR AN AIRCRAFT - The invention provides an aircraft lifting surface with a torsion box ( | 05-22-2014 |
20140133987 | HIGHLY INTEGRATED LEADING EDGE OF AN AIRCRAFT LIFTING SURFACE - A method for manufacturing a leading edge profile section of an aircraft lifting surface is provided. The method comprises the following steps: a) providing a set of laminated preforms of a composite material configured with a suitable shape for constituting the leading edge profile section; b) arranging said laminated preforms in a curing tooling and subjecting the assembly to an autoclave cycle to co-cure said laminated preforms; c) demoulding the curing tooling in a spanwise direction towards the aircraft symmetry plane. The invention also comprises a leading edge profile section manufactured by said method comprising in addition to the skin of the leading edge profile section, one or more of the following structural elements: an auxiliary spar, a longitudinal stiffener reinforcing an auxiliary spar, a longitudinal stringer reinforcing the skin of the leading edge profile. | 05-15-2014 |
20140048652 | HIGHLY INTEGRATED INNER STRUCTURE OF A TORSION BOX OF AN AIRCRAFT LIFTING SURFACE - The invention provides a method for manufacturing a monolithic torsion box inner structure ( | 02-20-2014 |
20140021294 | MEASUREMENT OF THE INERTIAL PROPERTIES OF AN AIRCRAFT MOVABLE CONTROL SURFACE - A method for obtaining the inertial properties of a movable rotating around a hinge line in an aircraft control surface. The method includes the steps of removing the mechanical connections of the actuators from the movable, leaving the movable free to rotate around its hinge line, further balancing the movable and calculating in a first approach its coarse static momentum. The method includes refining the coarse static momentum and obtaining simultaneously a frictional momentum of the movable; incorporating an elastic element on the control surface and configuring a second order mechanical system; inducing forced oscillations on the movable at a certain frequency, this frequency being increased until it is sensibly close to the resonance frequency of the movable to produce a wave response; calculating, from the wave response, the momentum of inertia of the movable. | 01-23-2014 |
20130338973 | METHOD FOR OPTIMISING THE DESIGN OF MANHOLE OPENINGS ON AN AIRCRAFT - Method for optimising the design of sealing rings of internal manhole covers which close the manhole openings over the inner surface of the skin of an aircraft structure, the surface that is in contact with the inner surface of the skin being the optimized surface of said sealing rings, the method including dividing the outer contour and the inner contour of the optimised surface into n points; grouping into families F | 12-19-2013 |
20130320144 | AIRCRAFT LANDING GEAR - An aircraft ( | 12-05-2013 |
20130306796 | OUTER FUEL TANK ACCESS COVER, WING AND AIRCRAFT DESCRIPTION - The present invention describes an outer fuel access tank cover (FTAC) of an aircraft, a wing comprising such outer FTAC of an aircraft and an aircraft. The invention belongs to the field of “designing auxiliary pieces in the wing of aircrafts to control the risk of gases from an explosion occurred in the FTAC entering the fuel tank”. | 11-21-2013 |
20130287954 | METHOD FOR PREVENTION OF POROSITY IN COMPOSITE MATERIAL PARTS - The invention discloses a method for prevention of porosity in composite material parts ( | 10-31-2013 |
20130280008 | Bolted joint of the cover of an access opening in an aircraft lifting surface - A bolted joint for connecting a cover of an opening in a primary structure of a lifting surface of an aircraft to the primary structure. The bolted joint includes two first bolted joints on either side of a symmetry axis of the cover arranged without any lateral clearance, two second bolted joints on either side of the symmetry axis on the side of the cover opposite to that of the two first bolted joints, arranged without any lateral clearance in the holes of the primary structure and with a linear lateral clearance in the holes of the cover; a plurality of third bolted joints along the border of the cover arranged without any lateral clearance in the holes of the primary structure and with a radial clearance in the holes of the cover. | 10-24-2013 |
20130264422 | Aircraft frame and method for obtaining the same - An aircraft frame and a method for obtaining an aircraft frame, which frame is made of composite material, and which frame comprises several partitions ( | 10-10-2013 |
20130214090 | AIRCRAFT WITH FUSELAGE-MOUNTED ENGINES AND AN INTERNAL SHIELD - Internal shield in the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it; the rear fuselage having at least a vertical symmetry plane; the rear fuselage being made of a composite material; the internal shield being located in said vertical symmetry plane and extended in an area that covers the possible trajectories of a set of pre-defined fragments detached from one of said engines in a failure event that would impact on critical elements of the opposite engine; the internal shield having a flat shape and an energy absorption capability that allows stopping said fragments. The invention also refers to a method for determining the area of an internal shield and to an aircraft having said internal shield. | 08-22-2013 |
20130212883 | Riveting device for aircraft fuselages - A head of a riveting device—for Hi-Lite type rivets—of at least two components of a structure for installing automatically collars on pins previously inserted in the structure. The head comprises: a collar installation tool; a collar supply to supply collars to the collar installation tool; a tool actuating device; a linear displacement device to linearly move the tool during the threading operation; a withdrawal device arranged to withdraw the second part of the collars; a control arrangement configured to automatically perform the installation of collars on pins and after this the withdrawal of the second part of the collars, using tools and collars appropriate for the pins. Also a robot having as end-effector the head and to a method of riveting two components of an aircraft fuselage are provided. | 08-22-2013 |
20130198426 | HETEROGENEOUS PARALLEL SYSTEMS FOR ACCELERATING SIMULATIONS BASED ON DISCRETE GRID NUMERICAL METHODS - A system for executing a given scientific code using a suitable finite-volume or finite-element solver for a large dataset represented as a grid, comprising a plurality of equal computing nodes interconnected by node communication means and a parallel computing software package for distributing and controlling the execution in sub-grids among said computing nodes; each computing node comprising at least a CPU-based first processing means and a FPGA-based second processing means interconnected by a bus; said package being configured for the simultaneous execution of at least one first solver process (which is fully executed in a first processing means) and one second solver process (which is fully executed in a second processing means) in each computing node for one sub-grid of said grid and for managing the exchange of boundary data with the solver processes that solve neighbour sub-grids. | 08-01-2013 |
20130193271 | DRAINAGE MAST OF THE COMPARTMENT OF THE AUXILIARY POWER UNIT OF AN AIRCRAFT - A drainage mast ( | 08-01-2013 |
20130187015 | COMPOSITE ROD, MANUFACTURING METHOD AND TOOL - The present invention describes composite rods keeping two elements apart a determined distance carrying the loads between them, such as railways, industrial premises, etc. Besides, the manufacturing method thereof and the tool involved in this process are also described. | 07-25-2013 |
20130187002 | PROTECTIVE SHIELD AGAINST ICE IMPACTS ON AIRCRAFT - Protective shield against ice impacts on aircraft, wherein the shield comprises plies of composite material ( | 07-25-2013 |
20130181088 | AIRCRAFT VERSATILE POWER SYSTEM - An aircraft versatile power system ( | 07-18-2013 |
20130169956 | MARKING AND DEFECT RECOGNITION PROCEDURE IN PREPREG MATERIAL - A defect recognition procedure in prepreg materials ( | 07-04-2013 |
20130168009 | METHOD FOR MANUFACTURING PIECES OF COMPOSITE MATERIAL HAVING VARIED THICKNESSES - A method for manufacturing pieces of composite material having varied thicknesses is disclosed. The method includes a first stacking stage and a second forming and drying stage. In the second stage, a forming tool, which is adapted to the configuration of the piece, except in the zone affected by the change in thickness, is used. In the first stage, one or more pre-forms of the piece are stacked successively with some cloths having the dimensions needed for producing the change of thickness, some laminates of a peelable material, and some supplementary cloths in such a way that the resulting layers have the thickness needed to be adapted to the forming tool. At the end of the second stage, laminates resulting from the supplementary cloths and laminates of a peelable material are removed. | 07-04-2013 |
20130160295 | METHOD, APPARATUS AND COMPUTER PROGRAM PRODUCT FOR DETERMINING THE STRAIN INDUCED AT A SELECTED POINT IN A STIFFENED PANEL STRUCTURE IN RESPONSE TO A LOAD, TAKING INTO ACCOUNT ONE OR MORE OUT OF PLANE (OOP) EFFECTS - A method, apparatus and computer program product is disclosed for determining the strain induced at a selected point in a stiffened panel structure in response to a load, taking into account one or more out of plane (OOP) effects. | 06-27-2013 |
20130153140 | COMPACTION PROCESS OF A PIECE OF COMPOSITE MATERIALS - It comprises applying a mould release agent on a compaction tool ( | 06-20-2013 |
20130140401 | HIGHLY LOADED FRAME OF AN AIRCRAFT FUSELAGE WITH A LATTICE STRUCTURED WEB - Frame of a fuselage section of an aircraft that receives external loads, such as the rear section that receives the loads of the tail planes, comprising a first sector ( | 06-06-2013 |
20130133171 | MANUFACTURING METHOD FOR "T" SHAPED STRINGERS WITH AN ANGLE DIFFERENT FROM 90 BETWEEN THE WEB AND THE FOOT - Method of manufacturing “T” shaped stringers ( | 05-30-2013 |
20130119201 | PROTECTION DEVICE FOR SENSITIVE AREAS AGAINST IMPACT OF FOREIGN OBJECTS - A protection device includes a flexible laminar body resistant to impacts, arranged separately from the body to be protected and put in the way of the beam of possible trajectories with which a foreign object could impact on the object to be protected, and it includes a plurality of energy absorption elements, provided with device clamping elements over a support structure positioned outside of the beam of possible trajectories, in order for the flexible laminar body to intercept an impact trajectory by the foreign object, resulting in its deformation and the subsequent progressive extension of the energy absorption elements reducing the loads to be supported by the support structure. The protection device is applied to prevent birds or other objects from impacting on sensitive areas of aircraft. The protection device is of a textile nature of reduced weight. | 05-16-2013 |
20130101801 | OPTIMIZED STRINGER RUN-OUT ZONES IN AIRCRAFT COMPONENTS - Aircraft component, such as an aircraft wing, that comprises at least one panel ( | 04-25-2013 |
20130099057 | IMPACT RESISTANT AND DAMAGE TOLERANT AIRCRAFT FUSELAGE - Aircraft fuselage section ( | 04-25-2013 |
20130098491 | PRESSURE COMPENSATION DEVICE IN AIRCRAFT - Pressure compensation device ( | 04-25-2013 |
20130081706 | AIR INTAKE WITH DOUBLE INLET DOOR - An APU air intake (AI) is disclosed having a foldable intake door ( | 04-04-2013 |
20130060538 | METHOD FOR PREDICTING THE IMPACT ON AN AIRCRAFT OF DEBRIS SHED OFF FROM IT - Computer-aided method to predict the location of an impact on an aircraft of debris shed off from the own aircraft comprising the following steps: a) providing the nominal position on the aircraft of said debris before its detachment; b) represent the debris by a body of a size and density appropriate to its characteristics; c) calculating a predetermined number of trajectories in three dimensions of said body in a predetermined fluid field when it is detached from the aircraft using an analytical model for calculating said trajectories and randomly varying one or more of the following initial conditions: the initial position of the body; the dimensions of the body; the damping coefficients of the angular velocity; the initial angles of roll, pitch and yaw; d) calculating the points of impact of said trajectories in the aircraft. | 03-07-2013 |
20130056585 | AIRCRAFT TAIL SURFACE WITH A LEADING EDGE SECTION OF UNDULATED SHAPE - An aircraft tail surface ( | 03-07-2013 |
20130056150 | PROCESS FOR APPLYING RESIN ON THE SURFACE OF A MOULDING BASE TOOL, TREATED WITH MOULD-RELEASE SUBSTANCES, IN ORDER TO OBTAIN BODIES OF COMPOSITE MATERIAL - The invention comprises, a first preliminary step of cleaning the treatment surface of the moulding base tool and a second step in which the necessary layers of mould-release agent are applied to the treatment surface of the moulding base tool. Based on said preliminary steps, the process is characterized in that, in a later step, the treatment surface ( | 03-07-2013 |
20130026294 | MANUFACTURING PROCEDURE OF A COMPOSITE PART OF A CLOSED COMPARTMENT WITH AN INTEGRATED ACCESS ASSEMBLY - Procedure for the manufacture of a composite part ( | 01-31-2013 |
20130001356 | REINFORCED AIRCRAFT FUSELAGE - Aircraft having attached to the rear fuselage ( | 01-03-2013 |
20120303337 | SYSTEMS AND METHODS FOR IMPROVING THE EXECUTION OF COMPUTATIONAL ALGORITHMS - The invention refers to systems and methods to optimize the memory and communications that suits the memory organization of many scientific codes, such as Computer Fluid Dynamics codes, that operate on meshes, such the mesh of an object that moves through a fluid medium. The methods adjust the order in which the data are used inside the algorithm, by means of traversing and ordering the mesh. This ordered mesh is streamed into the lower memory levels and allows for minimal data transfer requirements. The method also reduces the memory needs dramatically and improves the execution time of the scientific code. The systems and methods are particularly useful in the aeronautic industry for designing new aircrafts. | 11-29-2012 |
20120301681 | LAYING-UP METHOD FOR NON-PLANAR COMPOSITE COMPONENTS - A method for laying-up the tapes of a prepeg composite material in the 0° direction of a non-planar composite component on a suitable mould using an ATL machine comprising steps of: a) determining the trajectories of said tapes as modified trajectories of geodesic trajectories complying with the following conditions in their projections in an horizontal plane: that the curvature radius R | 11-29-2012 |
20120282430 | COMPOSITE MATERIAL PART WITH LARGE VARIATION IN THICKNESS - A composite material part and method for manufacturing the part. The part has a large variation in thickness between a first zone having a thickness E | 11-08-2012 |
20120248247 | AIRCRAFT FUSELAGE WITH HIGH STRENGTH FRAMES - Fuselage section of an aircraft whose structure comprises a skin ( | 10-04-2012 |
20120234978 | LOAD TRANSFER DEVICES AT A STRINGER RUN-OUT - Device for transferring in an stiffened skin of an aircraft component made of a composite material the load of an stringer ( | 09-20-2012 |
20120187247 | Manhole assembly in the lower skin of an aircraft wing made of a composite material - A manhole assembly in the lower skin ( | 07-26-2012 |
20120186062 | METHOD FOR ASSEMBLING FUSELAGE SECTIONS OF AN AIRCRAFT - The method comprises the manufacture of a front section ( | 07-26-2012 |
20120171424 | COMPOSITE MATERIAL PART WITH REINFORCED AREAS AND MANUFACTURING PROCEDURE - Procedure for the manufacture of a composite material part ( | 07-05-2012 |
20120170971 | BALL-JOINT SUPPORT IN THIN PARTS - The ball joints are embedded via the coaxial orifice thereof, centered on a longitudinal shaft. The invention is characterized in that it comprises a bush ( | 07-05-2012 |
20120168563 | ADJUSTABLE IRON FITTING FOR THE INSTALLATION AND FITTING OF AIRCRAFT FAIRING - It is intended for installing and fitting, in conjunction with other iron fittings, a fairing on an aircraft in correspondence with a housing located at the junction of a stabiliser and a fuselage of an aircraft structure. Wherein each iron fitting comprises:
| 07-05-2012 |
20120167675 | WIND TUNNEL WITH A CLOSED SECTION FOR AEROACOUSTIC MEASUREMENTS WITH AN ANECHOIC COATING - A wind tunnel with a closed section for aeroacoustic measurements with an anechoic coating including: a) a first cavity having a thickness D | 07-05-2012 |
20120166037 | AIRCRAFT BLACK BOX - Commercial aircraft ( | 06-28-2012 |
20120160411 | METHOD FOR INTEGRATING METALLIC ELEMENTS INTO COMPOSITE MATERIALS - A method for integrating metallic components into composite materials comprising curing layers of dry composite fibres ( | 06-28-2012 |
20120153083 | OPTIMIZATION OF STRUCTURES SUBJECTED TO HOT GAS STREAMS - Optimisation of structures subjected to hot gas streams. The invention refers to a fairing ( | 06-21-2012 |
20120145825 | LIGHTNING AND CORROSION PROTECTION ARRANGEMENT IN AN AIRCRAFT STRUCTURAL COMPONENT - A lightning and corrosion protection arrangement for a joint between an outer metallic part ( | 06-14-2012 |
20120138779 | LIQUID FUEL TANK FOR MEASURING FUEL VOLUME - Its object is to allow measurement of the volume of fuel ( | 06-07-2012 |
20120138738 | SYSTEM FOR INCREASING CONTROLLABILITY FOR AN AIRCRAFT - The system includes deflection transmission means ( | 06-07-2012 |
20120132754 | INTERFACE ARRANGEMENT BETWEEN TWO-COMPONENTS OF AN AIRCRAFT STRUCTURE - Interface arrangement between a first component ( | 05-31-2012 |
20120132749 | TAIL-CONE OF AN AIRCRAFT WITH MOVABLE FAIRING - A tail-cone of an aircraft includes a skin provided with a movable fairing which, by a swing articulated mechanism, is supported on the skin in order to allow the opening/closing of the movable fairing and gain access to the inside of the tail-cone. The tail-cone includes actuators for operating the swing articulated mechanism in order to permit the automatic opening and closing of the movable fairing to be carried out. | 05-31-2012 |
20120132743 | AIRCRAFT LIFTING SURFACE SKIN - A mult-rib box-shaped aeronautical structure comprising upper and lower skins ( | 05-31-2012 |
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 |