Abstract: 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 and 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A damping device for damping flexural vibration of a shaft rotating about a first axis, the device having: a supporting body; and a member, which defines an annular opening fitted through with the shaft, and is movable, with respect to the supporting body and radially with respect to the first axis, between a first and a second position when the shaft flexes radially with respect to the first axis. The member is set to the first position, and the opening is traversed loosely by the shaft when the rotation speed of the shaft is within a first range; the member is set to the second position, and the opening cooperates with the shaft, when the rotation speed of the shaft is within a second range differing from the first range and including at least one critical speed of the shaft; and the damping device has elastic means interposed between the supporting body and the member.

Abstract: 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.

Abstract: The present system determines a significant stress value (?) 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 (?).

Abstract: 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.

Abstract: There is described a convertiplane comprising: a pair of semi-wings; at least two rotors which may rotate about relative first axes and tilt about relative second axes together with first axis with respect to semi-wings between a helicopter mode and an aeroplane mode; first axis being, in use, transversal to a longitudinal direction of convertiplane in helicopter mode, and being, in use, substantially parallel to longitudinal direction in aeroplane mode; convertiplane further comprises at least two through openings within which said rotor may tilt, when said convertiplane moves, in use, between said helicopter and said aeroplane mode.

Abstract: 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.

Abstract: 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.

Abstract: 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.