Abstract: A structure for an aircraft comprises a first wall and a second wall. The first wall comprises two jackets of composite material disposed on either side of an intermediate arrangement and further includes at least one soleplate enabling it to be secured to the second wall. The structure further includes at least one elongate member extending facing the jacket and spaced apart therefrom, the elongate member being secured to the soleplate or to the second wall and being arranged to act as a bearing surface for a portion of the first wall that becomes separated from the soleplate after rupture.

Abstract: A structure (2) for an aircraft (1) comprises transverse walls (3-8) connected to longitudinal walls (9-12); each wall (3-12, 18, 18B) comprises two jackets (19) of composite material disposed on either side of an intermediate arrangement (20); a wall includes a corrugated core (70) presenting corrugations extending along an axis (Z) substantially parallel to the jacket, such that the capacity of the wall to absorb energy in the event of an impact along said axis is increased; a wall includes a zone of weakness (45) encouraging controlled degradation of the wall in the event of such a shock.

Abstract: An undercarriage (2) for an aircraft (1) includes anti-crash elements that are specific to a second stage of a crash after the end of a first stage. The undercarriage includes: a device for blocking a retraction actuator (6); a device for retaining the actuator (6) functionally separated from a landing gear leg (9); and a device for applying controlled braking to the pivoting of the leg (9) by irreversible lengthening of a deformable member (25).

Abstract: A structure (2) for an aircraft (1) comprises transverse walls (3-8) connected to longitudinal walls (9-12); each wall (3-12, 18, 18B) comprises two jackets (19) of composite material disposed on either side of an intermediate arrangement (20); a wall includes a corrugated core (70) presenting corrugations extending along an axis (Z) substantially parallel to the jacket, such that the capacity of the wall to absorb energy in the event of an impact along said axis is increased; a wall includes a zone of weakness (45) encouraging controlled degradation of the wall in the event of such a shock.

Abstract: A structure (2) for an aircraft (1) comprises a first wall (18V) and a second wall (18H). The first wall comprises two jackets (19) of composite material disposed on either side of an intermediate arrangement (20) and further includes at least one soleplate (54) enabling it to be secured to the second wall. The structure further includes at least one elongate member (51) extending facing the jacket (19) and spaced apart therefrom, the elongate member being secured to the soleplate or to the second wall and being arranged to act as a bearing surface for a portion (18V1) of the first wall that becomes separated from the soleplate after rupture.

Abstract: An undercarriage (2) for an aircraft (1) includes anti-crash elements that are specific to a second stage of a crash after the end of a first stage. The undercarriage includes: a device for blocking a retraction actuator (6); a device for retaining the actuator (6) functionally separated from a landing gear leg (9); and a device for applying controlled braking to the pivoting of the leg (9) by irreversible lengthening of a deformable member (25).

Abstract: A process is proposed for the fabrication of parts with large dimensions formed of a skin (10) and stiffeners (12, 16) such as aircraft fuselage segments made of a composite material with a thermoplastic matrix. After stiffeners have been made separately by lay-up, consolidation and shaping, these stiffeners are placed on a tooling (23) and the skin (10) is simultaneously fabricated and assembled to the stiffeners (12, 16) by diffusion welding. More precisely, the skin (10) is laid up and continuously consolidated by the lay-up head (36) such that the required part is obtained directly.