| Alenia Aeronautica S.p.A. Patent applications |
| Patent application number | Title | Published |
|---|
| 20120111126 | METHOD FOR DETECTING THE THICKNESS OF THE WALLS OF HOLLOW MANUFACTURED BODIES MADE FROM NON-FERROMAGNETIC MATERIAL - A hollow manufactured body has at least one wall of non-ferromagnetic material with an outer surface and an inner surface facing a cavity of the body. Two mutually magnetically attracted sliders are positioned on the inner and outer surfaces. The outer slider is moved manually across the outer surface to a predetermined point where the wall thickness is to be detected; the inner slider on the inner surface follows the movements of the outer slider due to the effect of the magnetic attraction. A transducer on the outer slider is used to measure the force required to move a magnet away from the outer surface of the wall. The value of the thickness of the wall at the predetermined point is then derived from the measured force. | 05-10-2012 |
| 20110259508 | METHOD OF MANUFCTURING A CURVED STRUCTURAL ELEMENT MADE OF COMPOSITE MATERIAL AND HAVING A COMPLEX, OPEN CROSS-SECTION - A method of manufacturing a curved structural element made of composite material has a complex, open cross-section the structural element is formed by the assembly of components made of composite material. A plurality of flat, fresh components are prepared, each component being constituted by a flat layer of curved fibres previously infused with resin, combined with a pre-impregnated layer with straight fibres. Hot-forming of the flat, raw components is then performed. The hot-formed, fresh components are then assembled in accordance with a predetermined sequence on a polymerization tool. The tool includes a shaped, inflatable device astride which a C-shaped raw component is deposited. Finally, the fresh components assembled on the tool are subjected to a polymerization cycle in an autoclave. The inflatable device is inflated by the pressure produced in the autoclave to apply a predetermined pressure from the inside of the C-shaped fresh component. | 10-27-2011 |
| 20110253833 | BRAKE SYSTEM FOR AIRCRAFT UNDERCARRIAGE - A braking system for an aircraft provided with undercarriage, wherein an axial-flux reversible electrical machine is associated to at least one wheel of the undercarriage and is set in rotation by the rotation of the wheel. Current-dissipator means are provided, which can be connected to the windings of the axial-flux reversible electrical machine during rotation of the wheel in the landing phase for dissipating in the current-dissipator means the induced currents generated by the machine, which behaves as current generator, and producing a braking effect that slows down the movement of the wheel. An epicyclic reducer is provided set between the wheel of the undercarriage and the rotor of the reversible electrical machine; the epicyclic reducer provides a transmission ratio T in such a way that the rotor will turn at a velocity Tω with respect to the velocity of rotation ω of the wheel. | 10-20-2011 |
| 20110232829 | METHOD AND A DEVICE FOR REPAIRING PARTS OF COMPOSITE MATERIAL OF AN AIRCRAFT - In order to repair a composite-material panel forming part of the external surface of an aircraft, a portable device is applied onto that surface, the portable device including an inflatable chamber consisting of a flexible and airtight membrane and a concave body of rubber-like material sealed with the membrane. The concave body incorporates an inextensible inner reinforcement. Pressurized air is introduced into the chamber via a valve. A further valve, which passes through the membrane in a zone of the membrane external to the chamber, is used to suck air from one side of the membrane to the other. | 09-29-2011 |
| 20110226407 | METHOD OF MANUFACTURING SPARS, LONGERONS AND FUSELAGE BEAMS HAVING A VARIABLE H CROSS-SECTION - A beam of fibre-reinforced curable thermosetting composite material is preliminarily assembled in an uncured condition. The beam is placed between two forming tools, namely a lower and an upper tool, shaped in such a way as to give the lower and upper flanges a predetermined shape, at least one of the flanges having a non-rectilinear profile viewed in a longitudinal vertical plane. Two longitudinally elongate rigid inserts are placed between the flanges at the sides of the web and are covered in respective airtight tubular bags. The spaces between the upper tool and the lower tool on the two opposite longitudinal sides are sealed. The open opposite ends of the tubular bags are also sealed in such a manner that the pressure applied in an autoclave during the step of curing causes the tubular bags to swell and presses them against the two opposite faces of the web and against the flanges of the beam. On completion of curing, the upper forming tool is removed and the inserts are extracted sideways. | 09-22-2011 |
| 20110118385 | PROCESS FOR PREPARING SELF-HEALING COMPOSITE MATERIALS OF HIGH EFFICIENCY FOR STRUCTURAL APPLICATIONS - A process is for preparing a self-healing composite material including a matrix of epoxy polymer in which a catalyst of ring opening metathesis reaction and vessels containing at least one monomer able to polymerize due to a ring opening metathesis reaction are dispersed. The process includes the preliminary step of dispersing at molecular level the catalyst in a mixture containing at least one precursor of the epoxy polymer, and then the steps of dispersing, in the mixture, the vessels and a tertiary amine acting as curing agent of the precursor, and the step of curing the mixture by at least a first heating stage performed at a temperature between 70 and 90° C. for a time between 1 and 5 hours, and a second heating stage performed at a temperature between 90 and 170° C. for a time between 2 and 3 hours. | 05-19-2011 |
| 20110100538 | METHOD OF MANUFACTURING A FUSELAGE FRAME OF COMPOSITE MATERIAL - For an arcuate structural member ( | 05-05-2011 |
| 20110087442 | PROCEDURE FOR THE PROGNOSTIC OF A STRUCTURE SUBJECT TO LOADS - A method for prognostics of a structure subject to loads, particularly an aircraft structure, includes, detecting the state (strains) of the structure at multiple primary points and additional points. The loads acting on the structure associated with the state detected in the primary points are determined. Based on the determined loads, the state of the structure in the additional points is estimated. The estimated state of the structure is compared with the state detected in the additional points. A soundness state of the structure is assessed if the estimated and detected values of the state quantity are in agreement, or a defectiveness state of the structure if such values differ. | 04-14-2011 |
| 20100327117 | AIR INTAKE, IN PARTICULAR FOR AN AIRCRAFT CHAFF DISPENSER - An aircraft chaff dispenser includes an elongated hollow housing intended to be fixed to the structure of the aircraft so as to be oriented in the longitudinal direction of the aircraft. The housing has a pair of side walls and the front of each side wall is provided with a pair of lateral air intakes each having a circular through-hole with a diameter d and a fence located behind the hole in the longitudinal direction, or in the direction of travel, of the aircraft at a distance 1 from the center of the hole and having a shape in the form of a horizontally lying V with its vertex directed away from the hole. The diameter d of the hole is between 8 and 12 mm. The ratio h/1 between the height h of the fence at the vertex of the V and the distance 1 is between 0.8 and 1, while the ratio h/d between the height h and the diameter d is between 1.5 and 2. | 12-30-2010 |
| 20100252190 | METHOD FOR APPLYING A VACUUM BAG AROUND A FUSELAGE BARREL MADE OF COMPOSITE MATERIAL TO BE POLYMERIZED - A vacuum bag is applied around a fuselage barrel made of composite material to be polymerized, formed by lamination on the outer surface of a mandrel having the form of a solid of rotation about a longitudinal axis. A bag material in the form of a sheet having a transverse width corresponding to the longitudinal length of the fuselage barrel is provided alongside the mandrel. A first transverse end portion of the sheet is fastened or sealed on the outer surface of the barrel or the mandrel. Then the mandrel is rotated around the axis, so as to wrap the sheet about the barrel. While the mandrel rotates, the opposite axial end edges of the sheet are sealed on the mandrel. Finally, a second transverse end portion of the sheet is sealed on the outer surface of the barrel or the mandrel. | 10-07-2010 |
| 20100193115 | METHOD OF MANUFACTURING A CURVED ELEMENT MADE OF COMPOSITE MATERIAL - A method of manufacturing a curved element made of composite material includes: preparing at least one dry, flat reinforcing layer with curved fibres. A resin film is combined with the dry, flat reinforcing layer, and heat and pressure are applied in controlled manner to bring about the infusion of the resin into the reinforcing layer and to obtain at least one layer of pre-infused material. At least one prepreg layer is prepared with straight fibres impregnated with resin compatible with the resin of the pre-infused material. The layer of pre-infused material and the prepreg layer are superimposed on one another to obtain a layered structure. The layered structure, arranged on a shaped support tool is subjected to a polymerization cycle to obtain the curved element. | 08-05-2010 |
| 20100186519 | APPARATUS FOR TESTING FUSELAGE PANELS - Gripping claws and pairs of arched angular profiles are arranged along the perimeter of a cylindrical surface segment so as to grip the edges of a fuselage panel, closing the opening of a pressurizable chamber. | 07-29-2010 |
| 20100185345 | METHOD OF ESTIMATING AN ANGLE OF ATTACK AND AN ANGLE OF SIDESLIP OF AN AIRCRAFT - A method for estimating an angle of attack and an angle of sideslip of an aircraft has a plurality of control surfaces each adjustable with respect to an associated reference surface. The method includes measuring quantities representative of the angle formed by each control surface with respect to the associated reference surface; measuring the effective rolling speed, the effective pitching speed, and effective yawing speed of the aircraft. A linearized model of a state observer is defined according to the following equations: | 07-22-2010 |
| 20100181433 | METHOD FOR INCREASING THE LIFT OF AERODYNAMIC SURFACES AND FOR REDUCING THE DRAG - A jet of air is impelled on to the upper surface of a flap in order to increase its lift. Part of the air in this air jet is drawn, through air intakes, from the air stream flowing over an upper surface of the fixed part of the wing, located upstream of the flap. The air jet drawn in by suction by the air intakes is reinforced by a jet of compressed air blown through a passage which opens immediately downstream of the air intakes. This creates a combined jet of the air sucked in and the blown jet, which is ejected on to the upper surface of the flap through outlet apertures located on the rear edge of the fixed part of the wing. | 07-22-2010 |
| 20100181016 | CURING METHOD AND APPARATUS FOR MANUFACTURING BEAMS OF COMPOSITE MATERIAL WITH A J-SHAPED CROSS-SECTION - In order to manufacture beams of composite material with a J-shaped cross-section, a curing apparatus includes a bar supported parallel to a table by two end supports. A J-shaped beam of uncured composite material is prepared and arranged on the apparatus, positioning the bottom flange of the beam so that it faces the table and resting the web and the upper flange against two respective sides of the bar. The beam is covered with a vacuum bag and pressure and heat are applied inside an autoclave in order to cure the resin in the beam. | 07-22-2010 |
| 20100175816 | METHOD, PLANT AND APPARATUS FOR MAKING PARTS MADE OF COMPOSITE MATERIAL - The invention concerns a plant for manufacturing parts made of composite material, in particular sections for an aircraft fuselage, having at least a compaction station in which, in operation, there are provided a mandrel coated of composite material to be compacted and a transport mechanism arranged to transport at least one compaction device on said composite material. The transport mechanism is associated with at least one sling having at least one strip of porous material that, in operation, is in direct contact with the compaction device, and the sling is configured to transport the compaction device onto the composite material through application of a vacuum source at least to the strip of porous material. The invention also concerns a method of and an apparatus for manufacturing parts made of composite material. | 07-15-2010 |
| 20100170637 | PRE-IMPREGNATED MATERIAL WITH SEMI-CRYSTALLINE MATRIX AND AMORPHOUS SURFACE LAYER - A pre-impregnated material includes a resin matrix reinforced with a fiber material. The matrix has a semi-crystalline layer based on semi-crystalline thermoplastic resin having a melting point T | 07-08-2010 |
| 20100140405 | LEADING EDGE FOR AIRCRAFT WINGS AND EMPENNAGES - A leading edge structure includes two or more multilayer panels at least partially overlapping and suitably curved with at least partially congruent concavities. Each multilayer panel includes at least the following three layers: a first metal foil layer metal foil, a second intermediate layer of fibre-glass securely fixed to the first layer, and a third metal honeycomb layer securely fixed to the second layer. | 06-10-2010 |
| 20100126658 | METHOD OF MANUFACTURING A Z-SECTION COMPONENT FROM COMPOSITE MATERIAL - A method of manufacturing a Z-section component from composite material uses a mould having a convex mould portion and a concave mould portion. The method includes the preparation of a vacuum bag for a polymerization cycle, including the covering the fresh component with a layer of peel ply formed from a plurality of strips of peel ply and fixing the layer of peel ply perimetrically to the mould using an adhesive tape. A line of sealant is positioned perimetrically above the adhesive tape around the fresh component and a separator film is positioned above the layer of peel ply so as to cover the layer of peel ply and the perimetric line of sealant. A ventilation textile is placed perimetrically on the mould, the textile having an aperture which is positioned so as to leave uncovered an underlying part substantially coinciding with the fresh component. A vacuum bag is applied for the polymerization cycle. | 05-27-2010 |
| 20100117665 | PROCESS FOR MONITORING THE CURING REACTION OF A POLYMERIC MATRIX OF A COMPOSITE MATERIAL - The process for monitoring the curing reaction of a polymeric matrix, in which carbon nanotubes are dispersed whereby a composite material is formed, provides for:
| 05-13-2010 |
| 20100096504 | STRUCTURAL ELEMENT FOR COVERING AN ELONGATE GAP ON AN AERODYNAMIC SURFACE OF AN AIRCRAFT - A covering structural element is adapted to close an elongate gap provided on an aerodynamic surface of an aircraft. Such an element has a strip-shaped body made of metal material, including a fixing portion, adapted to be fixed along one of the longitudinal borders of the elongate gap; a sliding portion adapted to urge in a sliding manner on the other of the longitudinal borders of the strip-shaped gap; and a connection portion, connecting the sliding portion to the fixing portion, the thickness of which is so sized as to allow, in use, a controlled elastic bending of the structural covering element. The covering structural element has a profile so sized as to be tapered at the transition from the fixing portion to the connection portion and from the sliding portion to the connection portion, the covering structural element having a smooth surface on the side intended to face away from the elongate gap. | 04-22-2010 |
| 20100094789 | METHOD AND A SYSTEM FOR ESTIMATING THE IMPACT AREA OF A MILITARY LOAD LAUNCHED FROM AN AIRCRAFT - A system and a method are for the estimation of the impact area of a smart load that can be launched from an aircraft as a function of data or signals indicative of the aircraft flight conditions upon release of the load and of predetermined impact conditions on the target. The estimation of a polygonal impact area defined by the coordinates of a central point and of a predetermined number of vertices is by corresponding neural networks. | 04-15-2010 |
| 20100019096 | ACTUATOR DEVICE BASED ON A SHAPE MEMORY ALLOY, AND A WING FLAP ASSEMBLY FITTED WITH SUCH AN ACTUATOR DEVICE - A wing-flap assembly includes a flap made up of a plurality of flap sections, in which each flap section is connected to the preceding one in a rotatable manner, and one or more actuator devices adapted to control the rotation of the flap sections. Each actuator device includes an extended element made of shape memory alloy and an arch-shaped framework made of elastic material, to which the extended element is fixedly connected under tension. Each end of the extended element is fixed to a respective end of the arch-shaped framework. At least one of the actuator devices is connected at one end to the first of the flap sections, and on the other side it is adapted to be connected to a wing structure. | 01-28-2010 |
| 20090250165 | METHOD, SYSTEM AND EQUIPMENT FOR MAKING PARTS MADE OF COMPOSITE MATERIAL, IN PARTICULAR REINFORCED PARTS FOR AIRCRAFT FUSELAGES - The present invention relates to a system to manufacture composite material parts comprising a supporting mandrel having at least one compacting zone configured to contain at least one composite material element to be compacted by applying a certain degree of vacuum. The system comprises also at least one compacting equipment comprising a frame having a plurality of interconnected arms along a predetermined perimeter, at least one vacuum bag attached to a side of the frame along its perimeter and configured to compact the element, at least one porous material attached to the vacuum bag along the frame's perimeter and configured to adhere in a removable way to the compacting zone and to impede the air influx during the compacting of element. The invention also relates to a compacting equipment and to a method to manufacture composite material parts. | 10-08-2009 |
