AGUSTAWESTLAND S.P.A. Patent applications |
Patent application number | Title | Published |
20140299710 | HOVER-CAPABLE AIRCRAFT - A hover-capable aircraft having propulsion means; at least one rotor; transmission means for transmitting power from the propulsion means to the rotor and lubricated with a lubricant; a heat exchanger, which receives the heated lubricant from the transmission means and feeds the cooled lubricant back to the transmission means; and a fan for producing airflow through the heat exchanger to cool the lubricant, and which has an impeller with blades, and an exhaust pipe for expelling the hot air produced by cooling the lubricant; at least one portion of the wall of the exhaust pipe has dissipating means designed to selectively absorb pressure waves in a given frequency band related to the rotation speed of the impeller and to the number of blades of the impeller. | 10-09-2014 |
20140212293 | AIRCRAFT ROTOR BLADE AND RELATIVE FORMING METHOD - An aircraft rotor blade having a root portion having a through seat and designed for connection to the rotor; and a main portion extending from the root portion. The blade is produced by polymerizing an assembly having a main structure of composite material, and a composite material covering defining the outer surface of the blade. At the root portion, the main structure has a contoured block; and a lamina member extending about at least part of the block, and having a first part adhering to a first peripheral portion of the block, and a second part spaced apart from and facing a second peripheral portion of the block to form the seat; the lamina member having a pre-preg of continuous unidirectional fibres. | 07-31-2014 |
20140090820 | SYSTEM AND METHOD FOR COOLING A HOVER-CAPABLE AIRCRAFT TRANSMISSION - A system for cooling a transmission of a hover-capable aircraft, the system having: a stator; a heat exchanger connectable thermally to the transmission; a fan for creating a current of a first heat-carrying fluid from the heat exchanger to the fan itself, to remove heat from the heat exchanger; a rotary member, which rotates about an axis to rotate an impeller of the fan about the axis; and a bearing supporting the rotary member for rotation about the axis; the system also having cooling means for cooling the bearing, and in turn having conducting means for conducting a current of a second heat-carrying fluid along a path from an outside environment, external to the bearing, to and to cool the bearing itself. | 04-03-2014 |
20140059934 | Door Assembly, in Particular for a Helicopter, Provided with an Emergency Release Device - A door assembly, in particular for a helicopter, has a post; a door fitted to the post by a first and second hinge arranged on an outer wall of the post, so as to rotate about a hinge axis to open and close a door opening; and an emergency release device having a release handle, and a stem which extends through the post along a release axis substantially perpendicular to the hinge axis, rotates axially, in response to operation of the release handle, from a first to a second angular position to detach the door from the post, and is fixed at one axial end to the first hinge; the release handle being connected to the stem to rotate together with the stem about its release axis. | 03-06-2014 |
20140021299 | Door Assembly, in Particular for a Helicopter, Provided with an Emergency Release Device - A door assembly, in particular for a helicopter, has a post; a door fitted to the post by a first and second hinge arranged on an outer wall of the post, so as to rotate about a hinge axis to open and close a door opening; and an emergency release device having a release handle, and a stem which extends through the post along a release axis substantially perpendicular to the hinge axis, rotates axially, in response to operation of the release handle, from a first to a second angular position to detach the door from the post, and is fixed at one axial end to the first hinge; the release handle being connected to the stem to rotate together with the stem about its release axis. | 01-23-2014 |
20130307705 | AIRCRAFT AND METHOD FOR DISPLAYING A VISUAL INFORMATION ASSOCIATED TO FLIGHT PARAMETERS TO AN OPERATOR OF AN AIRCRAFT - There is described an aircraft, comprising a windscreen arranged in a front side of aircraft, characterized in that an edge of windscreen defines a visualization area visible by an operator, and by comprising displaying means configured for displaying at least one visual information of at least one flight parameter within visualization area, at least when aircraft is in a normal flight configuration. | 11-21-2013 |
20130172143 | EPICYCLIC GEAR TRAIN FOR AN AIRCRAFT CAPABLE OF HOVERING - An epicyclic gear train, for an aircraft capable of hovering, having a sun gear rotating about a first axis; a fixed ring gear positioned coaxially with the first axis and radially outwards with respect to the sun gear; a number of planet gears, which are interposed between and mesh with the sun gear and the ring gear, and rotate about respective second axes, in turn revolving about the first axis; and lubricant feed means; the feed means having a number of nozzles arranged about the first axis and the sun gear to produce an annular flow of lubricant. | 07-04-2013 |
20130145604 | LOCK RING AND THREADED STUD - A lock ring for securing a threaded stud to a first member, the ring having a first surface defining the ring on the side facing a first axis of symmetry of the ring, and in which a toothed impression is formed when it is forced onto a toothed portion of the threaded stud; and a conical second surface defining the ring on the opposite side to the first axis, and which is forced inside the first member. | 06-13-2013 |
20130116938 | SYSTEM AND METHOD FOR DETERMINING STRESS OF A COMPONENT MADE OF MAGNETIZABLE MATERIAL - The present system determines a significant stress value (σ) of a component made of magnetizable material. The system has a generating stage for generating a magnetic field of varying amplitude (H); and also includes a pickup stage for acquiring a Barkhausen noise signal (MBN) alongside variations in the amplitude (H) of the magnetic field. The system is characterized by having a processing unit for calculating the reciprocal (1/MBNmax) of the maximum value (MBNmax) of the signal (MBN), alongside variations in the amplitude (H) of the magnetic field. The processing unit has a memory stage storing a linear relation between the reciprocal (1/MBNmax) of the maximum value and the significant stress value (σ). | 05-09-2013 |
20130035197 | PLANETARY GEAR TRAIN AND CORRESPONDING PRODUCTION METHOD - Described herein is a planetary gear train, comprising: a sun gear that can turn about an axis and comprises a plurality of first teeth; a fixed crown wheel comprising a plurality of second teeth; and two planetary gears, each comprising a plurality of third teeth, the planetary gears each meshing with the crown wheel and the sun gear and able to turn about second axes, which are in turn able to turn about the first axis; at least two third teeth simultaneously mesh with second teeth and further two third teeth simultaneously mesh with first teeth; the third teeth comprise a first a second side, which have, respectively, a first and a second pressure angle different from one another; and the number of the third teeth is different from the absolute value of the semidifference between the number of the first teeth and of the second teeth. | 02-07-2013 |
20130026305 | CONVERTIPLANE - There is described a convertiplane comprising a pair of semi-wings, a first and a second rotor which may rotate about relative first axes and tilt about relative second axes together with first axes with respect to semi-wings between a helicopter mode and an aeroplane mode; first axes are, in use, transversal to a longitudinal direction of convertiplane in helicopter mode, and are, in use, substantially parallel to longitudinal direction in aeroplane mode; first and second rotors may tilt about relative second axes independently of each other. | 01-31-2013 |
20130026304 | CONVERTIPLANE - There is described a convertiplane comprising: a pair of semi-wings; a first rotor comprising a shaft which may rotate about first axis and tilt about a second axis together with first axis with respect to semi-wings between a helicopter mode and an aeroplane mode; first axis being transversal to a longitudinal direction of convertiplane in helicopter mode and being substantially parallel to longitudinal direction in aeroplane mode; convertiplane also comprises an electrical power storage device; and an electrical machine which comprises, in turn, a stator electrically connected to storage device; and a second rotor operatively connected to a shaft of first rotor; electrical machine acts as an electric motor for driving in rotation said first rotor by using the electrical power stored in storage device; or as an electrical power generator for re-charging storage device by causing the rotation second rotor under the action of a wind current. | 01-31-2013 |
20120254664 | AUTOMATIC TEST SYSTEM FOR DIGITAL DISPLAY SYSTEMS - The present invention relates to an automatic test system for a digital display system, which digital display system comprises display electronics configured to output a digital video stream, and a display screen connected to the display electronics to receive the digital video stream generated thereby and to display at least one image based on the received digital video stream. The automatic test system is designed to be connected to the digital display system to receive the digital video stream generated by the display electronics, and is configured to: reconstruct in memory an image based on the received digital video stream; compute a signature of the reconstructed-in-memory image; and test the digital display system by comparing the computed signature with a reference signature so as to thereby check whether the reconstructed-in-memory image completely matches an expected good display behaviour, wherein said reference signature is indicative of said expected good display behaviour. | 10-04-2012 |
20120143485 | AIRCRAFT TAKEOFF WEIGHT CALCULATING METHOD AND SYSTEM - A method of calculating the takeoff weight of an aircraft, characterized by including the steps of: recording a first and second value of a first quantity associated with the weight of the aircraft at least a first and second instant, in which the aircraft is in horizontal flight at constant height; and calculating the takeoff weight of the aircraft on the basis of the first and second value. | 06-07-2012 |
20120087821 | Pump Assembly, In Particular for Helicopter Lubrication - A pump assembly, in particular for lubrication in helicopters, has a casing, the lateral wall of which defines an intake port and a delivery port; and the casing houses two rotary pumps powered by a drive shaft via a motion-splitting transmission. | 04-12-2012 |
20120085865 | Door Assembly, in Particular for a Helicopter, Provided with an Emergency Release Device - A door assembly, in particular for a helicopter, has a post; a door fitted to the post by a first and second hinge arranged on an outer wall of the post, so as to rotate about a hinge axis to open and close a door opening; and an emergency release device having a release handle, and a stem which extends through the post along a release axis substantially perpendicular to the hinge axis, rotates axially, in response to operation of the release handle, from a first to a second angular position to detach the door from the post, and is fixed at one axial end to the first hinge; the release handle being connected to the stem to rotate together with the stem about its release axis. | 04-12-2012 |