Abstract: A convertiplane is described that comprises a fuselage, having a first longitudinal axis, with a nose and a tail portion; a pair of wings arranged on respective opposite sides of said fuselage, carrying respective rotors; a pair of engines operatively connected to respective said rotors; at least one first lifting surface arranged on said tail portion; and a pair of canards arranged on said nose of said fuselage and defining respective second lifting surfaces adapted to generate a third lift/negative lift value; each rotor comprising a mast rotatable about a second axis and about an relative third axis transversal to said second axis and with respect to the fuselage, so as to set said convertiplane between a helicopter configuration and an aeroplane configuration; each second axis, in use, being transversal to the first axis of said convertiplane in said helicopter configuration and being parallel to said first axis in said aeroplane configuration.

Abstract: A helicopter is described comprising a fuselage elongated along a first axis and extending between a nose and a tail boom; a tailplane with a pair of first aerodynamic surfaces elongated along a second axis; the first and second axis define a first plane; the helicopter comprises a pair of elements transversal to the first aerodynamic surfaces; and a pair of second aerodynamic surfaces generating respective second aerodynamic forces, connected to first elements, and facing and spaced from respective first aerodynamic surfaces; each second aerodynamic surface comprises one first root end connected to the respective said element, a second free end spaced from said tail boom, a first leading edge, a first trailing edge opposite to said first leading edge, a first chord at said first root end and a second chord at said second free end parallel to said first axis; the first and the second chord define a second plane tilted with respect to said first plane.

Abstract: A convertiplane is described that comprises a fuselage, having a first longitudinal axis, with a nose and a tail portion; a pair of wings arranged on respective opposite sides of said fuselage, carrying respective rotors; a pair of engines operatively connected to respective said rotors; at least one first lifting surface arranged on said tail portion; and a pair of canards arranged on said nose of said fuselage and defining respective second lifting surfaces adapted to generate a third lift/negative lift value; each rotor comprising a mast rotatable about a second axis and about an relative third axis transversal to said second axis and with respect to the fuselage, so as to set said convertiplane between a helicopter configuration and an aeroplane configuration; each second axis, in use, being transversal to the first axis of said convertiplane in said helicopter configuration and being parallel to said first axis in said aeroplane configuration.

Abstract: An aircraft having a fuselage and a detecting device for detecting the presence of ice caused by solidification of supercooled liquid droplets having a characteristic dimension above a threshold value. The detecting device has a preferential first portion for accumulating the droplets, and the preferential first portion is located so as to be visible from inside the fuselage.

Abstract: An aircraft, capable of hovering, having drive means; and at least one exhaust duct connected to an outlet of the drive means to expel the exhaust gas, produced by fuel combustion, from the aircraft. At least part of the exhaust duct has a thermoelectric conversion circuit for Seebeck-effect converting to electric energy the thermal gradient produced between the inside and outside of the exhaust duct by flow of the exhaust gas.

Abstract: An aircraft, capable of hovering, having drive means; and at least one exhaust duct connected to an outlet of the drive means to expel the exhaust gas, produced by fuel combustion, from the aircraft. At least part of the exhaust duct has a thermoelectric conversion circuit for Seebeck-effect converting to electric energy the thermal gradient produced between the inside and outside of the exhaust duct by flow of the exhaust gas.

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 helicopter comprising a drive having an air intake conduit, a main rotor connected functionally to the drive and a transmission interposed functionally between the main rotor and the drive and housed in a housing. The helicopter further comprises at least one air intake having a first inlet fluidly connected to the intake conduit, at least one second inlet fluidly connected to the housing and deflecting means interacting, in use, with an airflow to divide the airflow into a first and a second airflow. The air intake also has guide means for guiding the first airflow along a first path extending from the deflecting means to the first inlet, and for guiding the second airflow along a second path separate from the first path and extending from the deflecting means to the second inlet.

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 a fuselage and a detecting device for detecting the presence of ice caused by solidification of supercooled liquid droplets having a characteristic dimension above a threshold value. The detecting device has a preferential first portion for accumulating the droplets, and the preferential first portion is located so as to be visible from inside the fuselage.

Abstract: A helicopter having a drive in turn having an air intake conduit; a main rotor connected functionally to the drive; and a transmission interposed functionally between the main rotor and the drive and housed in a housing. The helicopter has at least one air intake in turn having: a first inlet connected fluidically to the intake conduit; at least one second inlet connected fluidically to the housing; and deflecting means interacting, in use, with an airflow to divide the airflow into a first and a second airflow. The air intake also has guide means for guiding the first airflow along a first path extending from the deflecting means to the first inlet, and for guiding the second airflow along a second path separate from the first path and extending from the deflecting means to the second inlet.

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 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.