Lug with pocket and/or relief
View Patent ↗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.
1. A joining part comprising:
a wing having a thickness and extending substantially in an X-Y plane comprising:
a single through bore defining a fastening direction perpendicular to said X-Y plane of the wing, and,
separated from the through bore:
at least one cavity configured to reduce a stress gradient in a peripheral zone of said through bore and having a thickness less than the thickness of the wing, said at least one cavity comprising a curved side at a distance from a peripheral edge of the through bore, and
at least one relief configured to reduce a stress gradient in a peripheral zone of said through bore and having a thickness greater than the thickness of the wing, wherein a shortest distance between said at least one relief and said through bore is less than a shortest distance between said through bore and a peripheral edge of the wing.
2. The joining part according to claim 1 , wherein said at least one cavity comprises a base extending in a plane substantially parallel to the X-Y plane of the wing.
3. The joining part according to claim 1 , wherein at least one of said at one least cavity or said at least one relief has a side extending parallel to a longitudinal edge of said wing.
4. The joining part according to claim 1 , wherein said at least one relief has a rib part extending substantially parallel to a longitudinal edge of said wing and an end part forming an angle of between 0 and 90° with said rib part.
5. The joining part according to claim 1 , wherein said at least one relief comprises
at least two reliefs, each relief configured to reduce a stress gradient in a peripheral zone of said through bore and having a thickness greater than the thickness of the wing, wherein a shortest distance between each relief and said through bore is less than a shortest distance between said through bore and a peripheral edge of the wing.
6. The joining part according to claim 1 wherein each relief is symmetrical relative to a longitudinal median axis of said wing.
7. A lug of an aircraft fitting comprising a joining part comprising:
a wing having a thickness extending substantially in an X-Y plane comprising:
a single through bore defining a fastening direction perpendicular to said X-Y plane of the wing, and,
separated from the through bore:
at least one cavity configured to reduce a stress gradient in a peripheral zone of said through bore and having a thickness less than the thickness of the wing, said at least one cavity comprising a curved side at a distance from a peripheral edge of the through bore, and,
at least one relief configured to reduce a stress gradient in a peripheral zone of said through bore and having a thickness greater than the thickness of the wing, wherein a shortest distance between said at least one relief and said through bore is less than a shortest distance between said through bore and a peripheral edge of the wing.
8. The lug according to claim 7 wherein said at least one relief comprises at least two reliefs.
9. The lug according to claim 8 , wherein each relief is symmetrical relative to a longitudinal median axis of said wing.