Abstract: A method for producing parts including at least one internal cavity. In the method at least two metal sheets are diffusion bonded; then the bonded metal sheets are bent; and then each of internal cavities is inflated by superplastic forming. The method is carried out by a mold allowing at least one first part to be diffusion bonded and then bent while inflating at least one second part by superplastic forming during a single operation, whereby the mold is heated. The method can be applied, e.g., to the field of aeronautics.

Abstract: The invention relates to a method of producing and checking a double-resonator honeycomb acoustic panel. The aforementioned panel is characterised in that, following the assembly of the two honeycombs and the partition and prior to the assembly of at least one of the two liners, the perforation rate of said partition is checked by scanning same with digital camera. The successive images thus obtained are transmitted to a computer which determines the perforation rate T of the partition by applying formula T=N1/N, wherein N1 is the number of pixels that correspond to the holes and N is the number of pixels in the image.

Abstract: The invention provides a locking system on a cascade thrust reverser for a bypass turbojet, the reverser (20) comprising guide means (60) for the movable parts (50), and the guide means (60) comprising rails (64) attached to the movable parts (50) and tracks (62) attached to the longitudinal members (36). According to the invention, the locking system (80) comprises locks (82) located at the end (62a) of each track (62) in the opening direction (52), each lock comprising a bolt (110) capable of preventing the rail (64) moving in the opening direction (52).

Abstract: The invention relates to a device comprising gratings, which are used to form a reverse flow from a jet engine thrust flow. The inventive device comprises a plurality of flow diverter gratings which are disposed side-by-side at the outer edge of an annular thrust flow circulation channel. Each of the gratings comprises a plurality of intersecting inner transverse blades and inner longitudinal blades, two adjacent gratings being separated by a side clearance which generates a leakage flow. The device also comprises means of re-directing the aforementioned leakage flow in a direction such as to increase the effectiveness of the reverse flow, said re-direction means comprising aerodynamic appendages which are mounted to at least one outer longitudinal edge of each grating.

Abstract: The invention relates to a method of producing and checking a double-resonator honeycomb acoustic panel. The aforementioned panel is characterised in that, following the assembly of the two honeycombs (30, 50) and the partition (40) and prior to the assembly of at least one of the two liners (20, 60), the perforation rate of said partition (42) is checked by scanning same with digital camera (84). The successive images (92) thus obtained are transmitted to a computer (94) which determines the perforation rate T of the partition (40) by applying formula T=N1/N, wherein N1 is the number of pixels (100) that correspond to the holes (42b) and N is the number of pixels in the image (92).

Abstract: The invention concerns a method for making a soundproofing panel with at least one double resonator used for example on pods enclosing aircraft turbojets. Said method is characterized in that the septum is formed by assembling a plurality of parts against one of the honeycomb cores, said parts being cut out in foil, said parts being defined to enable the shape of the septum to be more or less adapted to extensible surfaces, said parts enabling significant reduction of the cost for perforating the septum.

Abstract: The invention relates to a dual flow turbojet comprising an engine of axis X housed completely inside a tubular pod whose inside wall co-operates with the case of said engine to define an annular passage for a secondary flow delivered by a fan, said pod having an air inlet upstream of the engine, thrust-reverser means in its middle section, and a common nozzle for ejecting both the primary flow and the secondary flow, the outlet of the nozzle being situated downstream from the engine, said thrust-reverser means being suitable for taking up an active position in which the secondary flow is diverted outwards and forwards from said pod, said nozzle having an enclosure defined by the inside and outside walls of said nozzle.