Abstract: A damping structure includes a member defining an internal cavity; an aggregate which includes at least solid bodies in contact and which completely fills the internal cavity; a rigid plate for closing off the internal cavity; and an elastic element which exerts elastic pressure on the rigid plate so as to constrain the aggregate. The member defining the cavity may be elongate with the internal cavity being formed longitudinally inside the member. At least some of said solid bodies may be hollow or solid, compact, made of different materials, of different shapes, and/or of different sizes.

Abstract: Structural assembly of part of an aircraft and aircraft, particularly a rotary-wing aircraft, comprising such a structural assembly. The structural assembly comprises an outer structure (3) equipped with a floor (4), a cladding assembly (5) comprising cladding panels (6) forming a self-supporting envelope (7) which is arranged inside (9) the outer structure (3) and mounted on the floor (4), and a connecting system (10) for connecting the self-supporting envelope (7) to the outer structure (3). The connecting system (10) comprises a number of connecting means (11) which, by rigid and permanent connections, fix the self-supporting envelope (7) to the outer structure (3) and perform this rigid and permanent fixing only between the floor (4) of the outer structure (3) and ends (12) of cladding panels (6) of the self-supporting envelope (7).

Abstract: Structural assembly of part of an aircraft and aircraft, particularly a rotary-wing aircraft, comprising such a structural assembly.

Abstract: Process and device for reducing the spectral line noise inside an aircraft, especially a rotating-wing aircraft, in particular a helicopter. Said device (1) comprises sensors (Ca, Cb) for measuring the values of vibratory and/or acoustic parameters, controllable mechanical elements (A) forming secondary sources of noise, and a main computer (CAL) determining, on the basis of the values measured by the sensors (Ca, Cb), control commands for the mechanical elements (A), as well as at least one reference sensor (CO) for measuring a reference parameter which is correlated with the noise, and possibly an auxiliary computer (4) for calculating, on the basis of the values measured by the reference sensor (CO), a reference signal, and said main computer (CAL) determines the control commands by carrying out filtering with respect to the reference signal.

Abstract: Process and device for reducing the spectral line noise inside an aircraft, especially a rotating-wing aircraft, in particular a helicopter.

Abstract: The present invention relates to a device for reducing the noise inside a rotary-wing aircraft, especially a helicopter. According to the invention, said device (1) comprises at least one sensor (Ca, Cb) for measuring the values of at least one vibrational and/or acoustic parameter representing a vibrational and/or acoustic effect of at least one source of noise, at least one mechanical means (A) that can be controlled and is capable of creating a force capable of reducing said vibrational and/or acoustic effect, and a control unit (UC) for controlling the mechanical means (A), on the basis of the values measured by the sensor (Ca, Cb).