Abstract: An authentication system to authorize access to data to be protected, including a token having a memory that stores: an array containing alphanumeric information and random data; and a seal scheme vector containing information to enable access to each of the information items in their respective positions in the array. The authentication system is configured to: subject access to the token to the insertion of a password; decrypt the seal scheme vector; acquire the arrangement information and the size information of each random data from the seal scheme vector; check correspondence between the acquired arrangement information and the effective arrangement of the information in the array, and between the acquired size information and the effective size of the random data; authorize or deny access to the data to be protected on the basis of a result of the previous check.

Abstract: A straight threaded rod has three reference elements spaced apart from each other. A shoulder and a knob having a fourth reference element are screwed onto the rod. A spring is mounted on the rod between the knob and the shoulder. The rod is inserted through two axially aligned holes in two abutting pieces, with the shoulder bearing on a first surface of one of the two pieces. By adjusting the position of the shoulder and the knob along the rod it is possible to apply a calibrated clamping force to a pair of abutting pieces, regardless of the thickness of the pieces.

Abstract: A method for making hollow stiffening elements with co-curing technique on a structure made of composite material 1 includes the use of at least a lamination and polymerization spindle 2 upon which is positioned at least a rolled section 3. The rolled section 3 forms at least a hollow structure 11 where there is the spindle 2, including the following operational phases: coating the spindle 2 with at least a first anti-adherent layer 41; coating the spindle 2 with at least a second heat-shrinking layer 42; heating the coated spindle 2; positioning the spindle 2 on the surface of the structure 1; laminating the surface 1 through at least a rolled section 3; heating the structure 1 with at least a positioned rolled section 3; extracting the spindle 2 from the hollow structure 11.

Abstract: A constraint system of sectors of a device for producing an airplane fuselage in which a lamination mandrel is adapted to receive and support a band of impregnated synthetic material. The lamination mandrel comprises a plurality of sectors angularly spaced about the axis and mobile between: an expanded lamination position and a contracted disassembling position. A constraint system is provided between each sector and the sectors adjacent thereto which guarantees a predetermined arrangement of the first sector with respect to the second sector adjacent thereto, preventing any translation along two directions which lie in an adjustment plane perpendicular to an axis RD which extends radially from the symmetry axis to the external surface.

Abstract: Positioning system of sectors of a device for producing an airplane fuselage in which a lamination mandrel comprises a plurality of sectors borne by a supporting structure and mobile along guides between: an expanded lamination position and a contracted disassembling position. Each guide comprises a fixed part borne by the supporting structure and a mobile part sliding along/with respect to the fixed part in a rectilinear direction H. Between a portion of each mobile part facing towards the respective sector and a stiffening structure of the sector a positioning device is provided which allows adjustment of the position of the sector with respect to the guide in two directions which lie in a plane RP perpendicular to the axis H of the guide.

Abstract: A convertiplane having a fuselage with a first axis; and two rotors having respective shafts and fitted to a wing having a fixed portion connected to the fuselage, and a movable portion which supports the rotors, is connected to the fixed portion to rotate about a second axis crosswise to the first axis and to the shafts of the rotors, and is formed in one piece defined by two half-wings located on opposite sides of the fixed portion and each supporting a respective rotor, and by an elongated member extending along the whole wing and connecting the two half-wings; the rotors being powered by a motor via a transmission comprising a transmission shaft connecting the shafts of the rotors and coaxial with the second axis.

Abstract: An authentication system to authorize access to data to be protected, including a token having a memory that stores: an array containing alphanumeric information and random data; and a seal scheme vector containing information to enable access to each of the information items in their respective positions in the array. The authentication system is configured to: subject access to the token to the insertion of a password; decrypt the seal scheme vector; acquire the arrangement information and the size information of each random data from the seal scheme vector; check correspondence between the acquired arrangement information and the effective arrangement of the information in the array, and between the acquired size information and the effective size of the random data; authorize or deny access to the data to be protected on the basis of a result of the previous check.

Abstract: A method for evaluating the structural compatibility of an aircraft for use on a runway having a profile with one or more roughnesses in the form of bumps and/or dips using a computer-based system, and including the steps of: generating a first bump height curve representing elevations or depressions on the runway; comparing the bump height curve with a second bump height curve which is a first reference curve; generating a first power spectral density curve of the profile of the runway; comparing the first power spectral density curve with a second power spectral density curve which is a second reference curve; and authorizing or denying the aircraft the use of the runway on the basis of results of the comparison.

Abstract: Interface fitting for supporting a component of a structure to be assembled on an assembly jig, comprising a component-side part, adapted to be attached to the component, and a jig-side part, configured to bear in an orientable way on the assembly jig. The support block further comprises a spacer member interposed between the component-side part and the jig-side part, which can be operated to adjust the distance between the component-side part and the jig-side part.

Abstract: A nozzle removes by suction dust and chips from a drilling machine in an industrial plant. The nozzle has a first tubular portion for connection to a suction tube communicating with an opposite second tubular portion with an intake opening. An outer flange extends transversely from an intermediate position between the first and second tubular portions. The intake opening is directed in a lateral direction, parallel to the transverse direction of the flange. A magnetic element is incorporated in the flange. The nozzle can be applied to a drilling template having cylindrical through-openings in which respective bushings made of ferromagnetic material are fixed. When the second tubular portion is inserted through a cylindrical bushing, the magnetic element acts on the bushing, opposing axial and rotational movements of the nozzle.

Abstract: 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.

Abstract: Under-wing pylon for an aircraft which has on the upper side a pin (2) for attaching to the fuselage or to the wings of the aircraft itself, and a connector (3) for connecting the pylon to the aircraft. The pylon has a monolithic framework made with stratified unidirectional and/or woven carbon fibres, impregnated with epoxy resin.

Abstract: A method of predicting collisions between a mission air vehicle and an airborne object of a plurality of airborne objects present in a flight scenario of the mission air vehicle is described. The mission air vehicle and the airborne object move along corresponding routes. The method acquires data representing the state of flight and flight parameters of the plurality of airborne objects and the mission air vehicle; assigns to each of said airborne objects a mode of calculating the collision prediction; determines a subset of airborne objects to be surveilled; calculates equivalent routes for the mission air vehicle and for each airborne object of the subset; synchronizes the equivalent route of the mission air vehicle with the equivalent route of each airborne object of the subset; and calculates, for each airborne object, a collision prediction based on the synchronized routes according to an assigned calculation mode.

Abstract: A pin for the production and positioning of parts made of composite material and glued together in an aircraft, the pin including an elongated body (1), which is inserted in the holes purposely provided on parts of the aircraft or of the assembly jig. The pin also includes a head (2) that limits insertion of the pin in the holes, the body and the head being integrated in a single body made of a thermoplastic material. The process of production of the pin is a molding process.

Abstract: Blow-out testing devices which include a box-like housing defining two contiguous inner chambers communicating directly with one another through an inner aperture which is closable by applying a blow-out panel thereupon are provided. In such devices at least one of the two chambers is provided with a hermetically closable door. Both chambers are pressurized and sealed. Opening the door, an instant pressure drop is caused in one of the two chambers. The pressure within the other chamber causes the panel to break. Methods for blow-out testing are also provided.

Abstract: A reference tool for assembly jigs for aircraft structures includes a constraint pin (1), for being inserted into holes purposely provided on the assembly jig for aircraft structures and a reference support (2), associated with the pin, for generating a gap between the parts of the aircraft structure, during assemblage, of a known and standardized amount.

Abstract: Blow-out testing devices which include a box-like housing defining two contiguous inner chambers communicating directly with one another through an inner aperture which is closable by applying a blow-out panel thereupon are provided. In such devices at least one of the two chambers is provided with a hermetically closable door. Both chambers are pressurized and sealed. Opening the door, an instant pressure drop is caused in one of the two chambers. The pressure within the other chamber causes the panel to break. Methods for blow-out testing are also provided.

Abstract: A nozzle removes by suction dust and chips from a drilling machine in an industrial plant. The nozzle has a first tubular portion for connection to a suction tube communicating with an opposite second tubular portion with an intake opening. An outer flange extends transversely from an intermediate position between the first and second tubular portions. The intake opening is directed in a lateral direction, parallel to the transverse direction of the flange. A magnetic element is incorporated in the flange. The nozzle can be applied to a drilling template having cylindrical through-openings in which respective bushings made of ferromagnetic material are fixed. When the second tubular portion is inserted through a cylindrical bushing, the magnetic element acts on the bushing, opposing axial and rotational movements of the nozzle.

Abstract: Structural member composed of assembled plies of fibre material is embedded in a resin matrix, and includes at least one laminated part formed by these plies arranged in a stacking relationship, wherein the laminated part of the structural member is folded in such a way as to form a flange defining an inner angle with respect to a base portion of the laminated part. The edge of the flange forms a sloped surface on the concave side of the laminated part, at which sloped surface the plies of the flange which are closer to the concave side of the laminated part are folded towards the ply of the flange positioned on the convex side of the laminated part, in such a way as to cause their ends to be substantially level with the face of the flange on the convex side of the laminated part.

Abstract: A straight threaded rod has three reference elements spaced apart from each other. A shoulder and a knob having a fourth reference element are screwed onto the rod. A spring is mounted on the rod between the knob and the shoulder. The rod is inserted through two axially aligned holes in two abutting pieces, with the shoulder bearing on a first surface of one of the two pieces. By adjusting the position of the shoulder and the knob along the rod it is possible to apply a calibrated clamping force to a pair of abutting pieces, regardless of the thickness of the pieces.