Abstract: A linking member between a first and a second structural member of a fuselage of an aircraft allowing improved dissipation of stresses. The linking member has a first part made of a solid structure and at least one second part made of a lattice structure. The first part made of the solid structure is configured to dissipate static stresses and to withstand fatigue up to a predetermined maximum stress and fatigue threshold. This configuration allows improved dissipation of the stresses exerted on the linking member.

Abstract: To increase a compactness of damping systems intended to operate in the event of a dynamic landing of an aircraft, a damping system comprises a primary damper device and a secondary damper device. The primary damper device comprises at least one beam, each beam extending along a direction of a longitudinal axis. The damping system is configured so that at rest, the primary damper device has a stiffness greater than a stiffness of the secondary damper device in the direction of the longitudinal axis. When a force is applied to the damping system along the direction of the longitudinal axis, with a value less than a limit value, each beam remains in a compression state. When the force applied has a value greater than or equal to the limit value, each beam undergoes buckling and the secondary damper device undergoes elastic deformation.

Abstract: To increase a compactness of damping systems intended to operate in the event of a dynamic landing of an aircraft, a damping system comprises a primary damper device and a secondary damper device. The primary damper device comprises at least one beam, each beam extending along a direction of a longitudinal axis. The damping system is configured so that at rest, the primary damper device has a stiffness greater than a stiffness of the secondary damper device in the direction of the longitudinal axis. When a force is applied to the damping system along the direction of the longitudinal axis, with a value less than a limit value, each beam remains in a compression state. When the force applied has a value greater than or equal to the limit value, each beam undergoes buckling and the secondary damper device undergoes elastic deformation.

Abstract: The subject of the invention is a control unit (A), which comprises actuation units (F) such as a rudder and brakes for a pilot in an aircraft, which comprises a rotating shaft (2) mobile in rotation around an axis (40); said shaft is driven in rotation when the pilot performs an action on the actuation units (F), in particular the brake pedals, by mechanical transmission between said shaft and said actuation units, and which comprises a device for generating resistive torque (1) designed to be fastened along the rotating axis of the control unit; the device for generating resistive torque comprises a friction disk (3, 4, 5) mounted axially and fastened to the rotating axle (2), a first annular track (6, 7, 8) fastened to a frame element (9) of the control unit; and means of support (10, 11, 12).

Abstract: The subject of the invention is a control unit (A), which comprises actuation units (F) such as a rudder and brakes for a pilot in an aircraft, which comprises a rotating shaft (2) mobile in rotation around an axis (40); said shaft is driven in rotation when the pilot performs an action on the actuation units (F), in particular the brake pedals, by mechanical transmission between said shaft and said actuation units, and which comprises a device for generating resistive torque (1) designed to be fastened along the rotating axis of the control unit; the device for generating resistive torque comprises a friction disk (3, 4, 5) mounted axially and fastened to the rotating axle (2), a first annular track (6, 7, 8) fastened to a frame element (9) of the control unit; and means of support (10, 11, 12).

Abstract: A detection device for shocks on a part comprises a base intended to be fixed by a lower face onto a surface of the part where the occurrence of a shock is to be detected and comprises one or more detectors fixed at the base and protruding with respect to the base, a detector being deformed in a persistent way with a magnitude equal to or greater than a threshold magnitude when it is subjected to a shock with an energy equal to or greater than a threshold energy. Under the effect of such a shock with energy or greater, a detector is simply deformed or broken such that the visual inspection allows the occurrence of the shock to be detected.

Abstract: A stiffened panel includes a panel at least one of whose surfaces is equipped with stiffeners each of which includes a base that is pressed against the surface of panel, as well as a core that is oriented orthogonally relative to the base and whose first longitudinal edge is integral to the latter. At least one of the stiffeners includes a multitude of notches that cross over a second longitudinal edge of the core opposite the first edge, so that they extend towards the outside of the stiffener.

Abstract: A detection device (10) for shocks on a part (20) comprises a base (11) intended to be fixed by a lower face (111) onto a surface of the part (20) where the occurrence of a shock is to be detected and comprises one or more detectors (12) fixed at the base (11) and protruding with respect to the base, a detector (12) being deformed in a persistent way with a magnitude equal to or greater than a threshold magnitude As when it is subjected to a shock with an energy equal to or greater than a threshold energy Es. Under the effect of such a shock with energy Es or greater, a detector (12) is simply deformed or broken such that the visual inspection allows the occurrence of the shock to be detected.

Abstract: An assembly of at least two concentric axisymmetric parts intended to work at least in tension, wherein at least one axisymmetric part is equipped with at least one dust removal groove, the groove being cut from a plain surface of the first axisymmetric part in contact with a plain surface of a concentric second axisymmetric part so as to open toward the plain surface of the second axisymmetric part, the groove being capable of collecting the dust that lies in the area of contact between the two axisymmetric parts.

Abstract: An assembly of at least two concentric axisymmetric parts intended to work at least in tension, wherein at least one axisymmetric part is equipped with at least one dust removal groove, the groove being cut from a plain surface of the first axisymmetric part in contact with a plain surface of a concentric second axisymmetric part so as to open toward the plain surface of the second axisymmetric part, the groove being capable of collecting the dust that lies in the area of contact between the two axisymmetric parts.