Abstract: A system for preventing icing on an aircraft surface includes a plasma actuator which is applied onto an aircraft surface operationally exposed to air and which is arranged for generating at least one plasma discharge (D) for inducing a flow (F) of ionized hot-air particles towards the surface.

Abstract: An element (26) for sound absorption is intended for being mounted on components of aircrafts, such as engine nacelles. The element includes a face-sheet (28), which is, at least in a region thereof, acoustically permeable, a substantially sound-reflective back-sheet (30) and a honeycomb layer (32), “sandwiched” between the face-sheet (28) and the back-sheet (30) and defining a mesh structure which has hollow cells (34, 34?) laterally neighboring one another. The cells (34, 34?) are adapted to make the sound waves that enter through the face-sheet (28) and are reflected by the back-sheet (30) resonate inside their side walls. The element (26) has a passage (36) that connects together a group of the cells (34, 34?), thereby causing the cells to acoustically cooperate with one another.

Abstract: Equipment for the reduction of the radar marking of an aircraft V, can be applied to at least one hot portion H of the aircraft, chosen from the following: a piloting cabin or cockpit, including at least one transparent portion; a first frame of the fuselage; a plurality of junction edges of components, including wings, tail veilings and engine air intakes; at least one motor face. Said equipment comprises at least one device for dissipating incident radar waves, which can be removably applied to at least one hot portion H of the aircraft without affecting the aerodynamic characteristics of the aircraft V.

Abstract: An aircraft (10) with improved aerodynamic performances is adapted to keep the directional stability and a very good aerodynamic behavior at medium-high incidence. The aircraft (10) includes a fuselage (12) to which shaped wings (18, 20) are associated, and a nose (52). The aircraft (10) also includes a vortex control device (72) of the extension of the leading edge of the wing at the root (LERX), shaped in order to symmetrize the bursting of the vortices generated by such LERX with a medium-high incidence. Said aircraft comprises removable equipment with at least one dissipation device of incident radar waves, on at least one hot portion of the aircraft.

Abstract: A system for preventing icing on an aircraft surface includes a plasma actuator which is applied onto an aircraft surface operationally exposed to air and which is arranged for generating at least one plasma discharge (D) for inducing a flow (F) of ionized hot-air particles towards the surface.

Abstract: An element (26) for sound absorption is intended for being mounted on components of aircrafts, such as engine nacelles. The element includes a face-sheet (28), which is, at least in a region thereof, acoustically permeable, a substantially sound-reflective back-sheet (30) and a honeycomb layer (32), “sandwiched” between the face-sheet (28) and the back-sheet (30) and defining a mesh structure which has hollow cells (34, 34?) laterally neighboring one another. The cells (34, 34?) are adapted to make the sound waves that enter through the face-sheet (28) and are reflected by the back-sheet (30) resonate inside their side walls. The element (26) has a passage (36) that connects together a group of the cells (34, 34?), thereby causing the cells to acoustically cooperate with one another.

Abstract: Equipment for the reduction of the radar marking of an aircraft V can be applied to at least one hot portion H of the aircraft, chosen from the following: a piloting cabin or cockpit, including at least one transparent portion; a first frame of the fuselage; a plurality of junction edges of components, including wings, tail veilings and engine air intakes; at least one motor face. The equipment includes at least one device for dissipating incident radar waves, which can be removably applied to at least one hot portion H of the aircraft without affecting the aerodynamic characteristics of the aircraft V.

Abstract: An aircraft (10) with improved aerodynamic performances is adapted to keep the directional stability and a very good aerodynamic behaviour at medium-high incidence. The aircraft (10) includes a fuselage (12) to which shaped wings (18, 20) are associated, and a nose (52). The aircraft (10) also includes a vortex control device (72) of the extension of the leading edge of the wing at the root (LERX), shaped in order to symmetrize the bursting of the vortices generated by such LERX with a medium-high incidence. Said aircraft comprises removable equipment with at least one dissipation device of incident radar waves, on at least one hot portion of the aircraft.