Abstract: Systems for securing fixtures to the floor of a transportation vehicle. The securing system has a simplified structure comprising a securing device with two C-profiles comprising a web extending between a top plate and a bottom plate, the profiles being joined by an omega-shape fishplate. Vertical lateral walls formed by the webs of the profiles are perforated.

Abstract: Systems for securing fixtures to the floor of a transportation vehicle. The securing system has a simplified structure comprising a securing device with two C-profiles comprising a web extending between a top plate and a bottom plate, the profiles being joined by an omega-shape fishplate. Vertical lateral walls formed by the webs of the profiles are perforated.

Abstract: A joining part with a wing comprises a through bore defining a fastening direction perpendicular to the wing. The wing comprises at least one non-through pocket configured to reduce the stress gradient in a peripheral zone of the through bore and/or at least one relief configured to reduce the stress gradient in a peripheral zone of the through bore, the non-through pocket forming a cavity in the thickness of the wing and comprising a curved side at a distance from the peripheral edge of the through bore. The joining part may be part of a lug, such as, for an aircraft fitting.

Abstract: A joining part with a wing comprises a through bore defining a fastening direction perpendicular to the wing. The wing comprises at least one non-through pocket configured to reduce the stress gradient in a peripheral zone of the through bore and/or at least one relief configured to reduce the stress gradient in a peripheral zone of the through bore, the non-through pocket forming a cavity in the thickness of the wing and comprising a curved side at a distance from the peripheral edge of the through bore. The joining part may be part of a lug, such as, for an aircraft fitting.

Abstract: A method for designing repair kits for a predefined area of the external/internal structure of an aircraft, the repair kits each including an external/internal structural part having predefined shape and size, suitable for being placed within the existing external/internal structure, instead of an equivalent shape including a damaged area, which can be removed or not, the method including creating a range of standardised repair kits, optimized according to an estimate of the most likely types of accidental damage in the studied area.

Abstract: The method for tracking deformation of a metal part subjected to a pressure force (F) includes the steps of measuring the displacement (d) of the metal part in the deformation zone, of measuring the intensity of the pressure force (F), of calculating, during a first period, the constant ratio (?) between the intensity of the pressure force (F) and the displacement (d) of the metal part, and of determining, during a second period, displacement values (de) and (dp) related respectively to an elastic deformation and to a plastic deformation of the metal part from the constant ratio (?) and a displacement (da) measured during the said second period.

Abstract: The method for tracking deformation of a metal part subjected to a pressure force (F) comprises the steps of measuring the displacement (d) of the metal part in the deformation zone, of measuring the intensity of the pressure force (F), of calculating, during a first period, the constant ratio (?) between the intensity of the pressure force (F) and the displacement (d) of the metal part, and of determining, during a second period, displacement values (de) and (dp) related respectively to an elastic deformation and to a plastic deformation of the metal part from the constant ratio (?) and the displacement (d) measured during the said second period. Use in particular for straightening or forming a metal part.