Abstract: The invention relates to a composite structuring panel (1) for the trailing edge of an aircraft element, having: an upper surface (3); a lower surface (5); an edge (7) connecting said upper (3) and lower (5) surfaces; the upper surface (3) and the lower surface (5) being connected by transverse stiffeners (9) and the structuring panel being made of a unitary part forming the upper surface (3), the lower surface (5), the edge (7), and the transverse stiffeners (9). The invention also relates to a method for manufacturing such a panel (1), and to an aircraft element comprising such a panel (1).

Abstract: A method for remotely detecting electromagnetic interference on a data transmission line of a communication network includes measuring at a client site a noise power spectrum on the data transmission line as a function of frequency, for a frequency range. The noise is present when the data transmission line is not carrying a data signal. The method further includes forwarding the measured noise power spectrum to a remote computer at a network operator's site, determining periodicities in the measured power spectrum by the remote computer, and determining the switching frequency of a power supply unit at the client site by the remote computer based on periodicities in the power spectrum.

Abstract: A method for remotely detecting electromagnetic interference on a data transmission line of a communication network includes measuring at a client site a noise power spectrum on the data transmission line as a function of frequency, for a frequency range. The noise is present when the data transmission line is not carrying a data signal. The method further includes forwarding the measured noise power spectrum to a remote computer at a network operator's site, determining periodicities in the measured power spectrum by the remote computer, and determining the switching frequency of a power supply unit at the client site by the remote computer based on periodicities in the power spectrum.

Abstract: The invention relates to a method for producing a structural composite trailing edge panel (1) for an aircraft element having: an upper surface (3), a lower surface (5), and a trailing edge (7) connecting said upper (3) and lower (5) surfaces, the upper surface (3) and the lower surface (5) being connected by transverse stiffeners (9), at least one longitudinal spar (10) being positioned in such a way that the directrix (?10) of each longitudinal spar (10) and the directrix (?9) of the transverse stiffeners (9) are not collinear and the structuring panel (1) being made up of a one-piece component forming the upper surface (3), the lower surface (5), the trailing edge (7), the transverse stiffeners (9) and the spar or spars (10).

Abstract: The invention relates to a composite structuring panel (1) for the trailing edge of an aircraft element, having: an upper surface (3); a lower surface (5); an edge (7) connecting said upper (3) and lower (5) surfaces; the upper surface (3) and the lower surface (5) being connected by transverse stiffeners (9) and the structuring panel being made of a unitary part forming the upper surface (3), the lower surface (5), the edge (7), and the transverse stiffeners (9). The invention also relates to a method for manufacturing such a panel (1), and to an aircraft element comprising such a panel (1).