Hinge device of a nacelle cowling of an aircraft engine on a supporting structure
View Patent ↗A hinge device of a nacelle cowling of an aircraft engine on a supporting structure is disclosed. The hinge device includes two fittings and a link rod connected thereto and mounted on the fitting by an end connection. The link rod is further mounted on the fitting by an intermediate connection including a pivot pin slidably housed in a hole, and the end connection includes a guide pin slidably housed in a guide ramp. The connections are designed so as to create, upon rotation of the link rod about the pin, a relative movement of the axis in the ramp, simultaneously causing a relative movement of the pin in the hole.
1. A hinge device of a nacelle cowling of an aircraft engine on a supporting structure, comprising:
a first fitting which is securely mounted on one of the nacelle cowling or the supporting structure;
a second fitting which is securely mounted to the other of the nacelle cowling or the supporting structure; and
a link rod connected to said first and second fittings and extending in a longitudinal link rod direction,
wherein said link rod includes a first end mounted on the first fitting by a first end connection including an assembly pin which is centered on a hinge axis of the nacelle cowling a second end mounted on said second fitting by a second end connection,
wherein said link rod is further mounted on said second fitting by an intermediate connection including a pivot pin slidably housed in a hole formed on one of the second fitting or the link rod, and the pivot pin is supported by the other of the second fitting or the link rod, wherein said second end connection includes a guide pin slidably housed in a guide ramp,
wherein said second end connection and intermediate connection are designed so as to cause, upon rotation of the link rod about the pivot pin, a relative movement of said guide pin in said guide ramp which causes a relative movement of the pivot pin in the hole of said intermediate connection, and
wherein the pivot pin is slidably housed in the hole formed on one of the second fitting or the link rod in a plane orthogonal to an axis of rotation of the pivot pin.
2. The hinge device according to claim 1 , wherein said second end connection and intermediate connection are designed so as to cause the movement of said first link rod end, upon rotation of the link rod about said pivot pin along an axis of movement.
3. The hinge device according to claim 1 , wherein said hole is formed in said link rod, and wherein said pivot pin is supported by the second fitting.
4. The hinge device according to claim 3 , wherein said hole extends parallel to said longitudinal link rod direction, and wherein said pivot pin is orthogonal to said longitudinal link rod direction and to said hinge axis of the nacelle cowling.
5. The hinge device according to claim 1 , wherein said guide ramp is formed in said second fitting, and wherein the guide pin is supported by the link rod.
6. The hinge device according to claim 5 , wherein said guide pin is supported by the link rod and a swivel.
7. The hinge device according to claim 5 , wherein said guide pin is orthogonal to said longitudinal link rod direction and to said hinge axis of the nacelle cowling.
8. The hinge device according to claim 1 , wherein said guide ramp is a double ramp which cooperates with the two ends of the guide pin.
9. The hinge device according to claim 1 , wherein said assembly pin is supported by said first end of the link rod and a swivel.
10. A hinge system of a nacelle cowling of an aircraft engine on a supporting structure, comprising at least one hinge device according to claim 1 .
11. An engine assembly for an aircraft, including an engine and a nacelle comprising a plurality of nacelle cowlings, wherein at least one of said nacelle cowlings is equipped with a hinge device according to claim 1 .
12. The engine assembly according to claim 11 , further comprising an engine mounting structure forming said supporting structure for the hinge device.
13. An aircraft comprising at least one engine assembly according to claim 11 , assembled on a wing or on a rear portion of the fuselage of said aircraft.
14. The hinge device according to claim 1 , wherein the guide ramp is arcuate in shape.
15. The hinge device according to claim 1 , wherein an axis of the guide pin and an axis of the pivot pin are both orthogonal to the hinge axis and both extend in a vertical direction.