Abstract: A rotor for a helicopter, the rotor having a drive shaft rotating about a first axis; a hub connected functionally to the drive shaft in angularly fixed manner with respect to the first axis and in rotary manner with respect to a second axis crosswise to the first axis; and two blades connected to the hub in angularly fixed manner with respect to the first and second axis and in rotary manner with respect to respective third axes; the rotor also having supporting means for supporting the blades with respect to the hub in rotary manner about the respective third axes; the supporting means having at least one supporting member made at least partly of elastomeric material and interposed between a first surface and a second surface integral with a respective blade and the hub respectively; and the supporting member deforming, in use, to permit rotation of the blade, with respect to the hub, about the respective third axis.

Abstract: A blade for an antitorque tail rotor of a helicopter, having a leading edge and a trailing edge opposite each other and elongated along a longitudinal axis of the blade; the trailing edge, in use, interacts with the air current after the leading edge; the blade also has two opposite surfaces extending between the leading edge and the trailing edge, and a root portion extending from a radially inner first end, with respect to a rotation axis of the blade, towards a second end opposite the first end; and the root portion, when sectioned in a plane perpendicular to the leading edge and trailing edge, has a profile asymmetrical with respect to a chord joining the leading edge and trailing edge.

Abstract: An aircraft having at least one in-flight attitude control system, in turn having at least one actuator; and a hydraulic circuit connected to the actuator and having at least one pump designed to deliver a first flow when the pressure of the hydraulic circuit is above a presettable threshold value. The pump is designed to deliver a second flow greater than the first flow, and the aircraft has a sensor for detecting a quantity associated with the pressure of the hydraulic circuit; and a programmable central control unit, which controls the pump to deliver the second flow when the quantity detected by the sensor corresponds to a pressure of the hydraulic circuit below the threshold value.

Abstract: A support assembly for helicopter control sticks has a supporting structure; an instrument panel fixed to the supporting structure; and a connecting device for connecting the sticks to the supporting structure. The connecting device has a longitudinally elongated arm fitted on one end with the sticks; and the arm slides to move the sticks to/from the supporting structure, and rotates about a horizontal axis to adjust the height of the sticks.

Abstract: A retractable helicopter landing gear has a suspension structure supporting one wheel, and is movable between a withdrawn position, to reduce drag on the helicopter, and a lowered position for landing and takeoff of the helicopter. The landing gear also has a skid, which is located between the axis of rotation of the wheel and the periphery of the wheel, is diametrically opposite the suspension structure, and is connected to the suspension structure by a connecting device having a torsion bar.

Abstract: A transmission joint for angularly connecting a first and a second member, and having a coupling member interposed functionally between the first and second member and extending about an axis; the coupling member has: a first portion connectable angularly to the first member, a second portion connectable angularly to the second member and located radially outwards of the first portion, and an intermediate portion interposed radially between the first and second portion and elongated in a direction crosswise to the axis; the intermediate portion of the coupling member has, from the first portion to the second portion, a first portion decreasing in thickness crosswise to the direction, and a second portion of constant thickness.

Abstract: A drive for a helicopter, has at least one rotary member, a casing housing the rotary member and defining a compartment containing a lubricating fluid and air, and separating device for separating the lubricating fluid from the air and retaining the lubricating fluid inside the casing in the presence of airflow outwards of the casing and produced by pressure gradients between the compartment and the outside. The separating device is angularly integral with the rotary member to centrifugally separate the lubricating fluid from the air radially with respect to the axis.

Abstract: There is described a transmission for a helicopter, the transmission having a movable transmission member; a casing housing the movable member; lubricated supporting means for supporting the movable member inside the casing and for rotation about an axis; and feed means for feeding a lubricating fluid to the supporting means; the transmission also has storage means permitting gradual release of the lubricating fluid, and which are connected fluidically to the feed means and to the supporting means to permit lubrication of the supporting means in the event of breakdown of the feed means; and the storage means are angularly integral with the movable member and located radially inwards of the supporting means to feed the lubricating fluid centrifugally to the supporting means.

Abstract: There is described a rotor for a helicopter, having a hub rotating about a first axis; a number of blades projecting from the hub in respective longitudinal directions lying in a plane crosswise to the first axis, and each connected to the hub so as to be movable at least about a second axis crosswise to the first axis and to the relative longitudinal direction; and a number of damping devices for damping vibration of the helicopter, each interposed between a respective blade and the hub; each damping device has a plate member fixed, on one side, to the hub, elastically connected, on the opposite side, to the relative blade, and flexible, during movement of the blade, about a third axis coaxial with the second axis.

Abstract: A helicopter collapsible deck having at least one longitudinal member and at least one cross member, which extend respectively in a first and second direction intersecting at a point; the cross member is interrupted at the point of intersection; the deck also has an anchoring device for connecting the longitudinal member and the cross member at the point of intersection; and the anchoring device has at least one local permanent deformation section lying in a plane crosswise to the deck and for dissipating the energy transmitted to the deck in the event of impact.

Abstract: An aircraft capable of hovering, and having a fuselage defining an access opening; driving means for operating a rescue cradle; and a first wall movable between a closed position engaging a first portion of the opening, and a first open position allowing access to the first portion of the opening. The aircraft has a member connected functionally to the first wall and in turn having at least one flat surface; and the member is movable with respect to the wall into a first position, in which the flat surface defines a supporting surface for the cradle when the first wall is in the first open position.

Abstract: A blade for an antitorque tail rotor of a helicopter, having a leading edge and a trailing edge opposite each other and elongated along a longitudinal axis of the blade; the trailing edge, in use, interacts with the air current after the leading edge; the blade also has an end portion extending between a reference section and a radially outer end of the blade with respect to a rotation axis of the blade; the rotation axis is outside the blade and crosswise with respect to the longitudinal axis; the length of the chord at the end portion decreases from the reference section to the radially outer end; and the leading and trailing edges are joined at the radially outer end.

Abstract: A blade for an antitorque tail rotor of a helicopter, having a leading edge and a trailing edge opposite each other and elongated along a longitudinal axis of the blade; the trailing edge, in use, interacts with the air current after the leading edge; the blade also has two opposite surfaces extending between the leading edge and the trailing edge, and a root portion extending from a radially inner first end, with respect to a rotation axis of the blade, towards a second end opposite the first end; and the root portion, when sectioned in a plane perpendicular to the leading edge and trailing edge, has a profile asymmetrical with respect to a chord joining the leading edge and trailing edge.

Abstract: A wing for an aircraft having at least one weapon, and a feed duct for feeding the weapon with ammunition supplied in the form of a belt; the wing has a compartment for housing a portion of the belt and connectable to a loading opening of the feed duct.

Abstract: A rotor for a helicopter, the rotor having a drive shaft rotating about a first axis; a hub connected functionally to the drive shaft in angularly fixed manner with respect to the first axis and in rotary manner with respect to a second axis crosswise to the first axis; and two blades connected to the hub in angularly fixed manner with respect to the first and second axis and in rotary manner with respect to respective third axes; the rotor also having supporting means for supporting the blades with respect to the hub in rotary manner about the respective third axes; the supporting means having at least one supporting member made at least partly of elastomeric material and interposed between a first surface and a second surface integral with a respective blade and the hub respectively; and the supporting member deforming, in use, to permit rotation of the blade, with respect to the hub, about the respective third axis. (FIG.

Abstract: A helicopter having a rotor, a fuselage connected to the rotor by connecting means, and a control device for controlling vibration of the fuselage; the control device including generating means for generating signals associated with vibration of the fuselage, and actuating means for producing a force on the fuselage associated with the signals to reduce vibration; and the actuating means being carried by the connecting means.

Abstract: There is described a helicopter having a transmission for transmitting motion from a driving member to a driven member; the transmission has at least a first gear driven by the driving member, and a second gear meshing with the first gear and in turn driving the driven member; the first and second gear have teeth shaped so that the gears mesh with one another at at least two pairs of respective simultaneously meshing teeth; the teeth of at least one of the gears have a profile having an end portion relieved with respect to a starting theoretical involute; and the pattern of the distance between the points of the end portion and the starting involute along an axis of the tooth has at least a first and a second segment sloping with respect to each other.

Abstract: A device for indicating a residual power margin of aircraft turbine engines includes a measuring stage associated with at least one turbine engine of an aircraft to measure a number of first parameters related to a power output of the engine; a calculating unit associated with the measuring unit to calculate at least one second parameter indicating the power output of the engine on the basis of the first parameters; and a display. The display includes a power scale having at least one reference indicator indicating an operating limit of the engine; and at least one cursor cooperating with the power scale and the reference indicator to simultaneously display a current value of the second parameter and an available power margin of the engine.

Abstract: A helicopter having a fuselage; and two rear wings located on opposite sides of the fuselage and having winglets, each projecting transversely from a free end of the relative wing.

Abstract: There is described a hub for a helicopter rotor, having a main body, and a number of connecting members projecting from the main body and for the connection of respective blades; the main body and the connecting members being defined by separate components connectable to one another by releasable fastening means.