Thrust reverser supporting structure including composite reinforcements and a base having an unclosed cross section
An aircraft nacelle includes: a thrust reverse device having movable cowls, and a supporting structure to support the thrust reverser device. The supporting structure includes: a base body extending along a longitudinal direction of the nacelle and made from a composite material, and a wall of the base body forming an unclosed cross section having an open portion to provide access to an inner surface of the supporting structure from outside, and a plurality of reinforcements which is made from a composite material, and attached on the inner surface along the longitudinal direction. In particular, the reinforcements are integrated in the inner surface of the supporting structure.
1. An aircraft nacelle comprising: a thrust reverser device comprising at least one movable cowl; a supporting structure configured to support the thrust reverser device, the supporting structure comprising: at least one base body extending along a longitudinal direction of the nacelle and made from a composite material, wherein open walls of the base body form an open L-shaped bending section such that the entire base body in the form of the open L-shaped bending section provides access to an inner surface of the supporting structure from outside of the supporting structure, and a plurality of reinforcements attached on the inner surface of the supporting structure and distributed along the longitudinal direction, the reinforcements comprising a plurality of cores and plies draping the cores, wherein the cores and the plies are integrated with at least one open wall of the base body and form a portion of the open L-shaped bending section.
2. The aircraft nacelle according to claim 1 , wherein the base body is made using a resin infusion molding method.
3. The aircraft nacelle according to claim 1 , further comprising at least one guide means of the rail type for slidingly mounting a movable cowl of the thrust reverser device.
4. The aircraft nacelle according to claim 1 , wherein the supporting structure is connected to part of a panel of an inner fixed fairing structure of a turbojet engine.
5. The aircraft nacelle according to claim 4 , wherein the panel of the inner fixed fairing structure is attached on the supporting structure.
6. The aircraft nacelle according to claim 5 , wherein the panel of the inner fixed fairing structure is attached so as to close the open L-shaped bending section.
7. The aircraft nacelle according to claim 4 , wherein the panel of the inner fixed fairing structure is integrated into the supporting structure.
8. The aircraft nacelle according to claim 1 , further comprising at least one yoke or fitting for fastening to a load-bearing structure of the pylon type or another supporting structure.
9. The aircraft nacelle according to claim 8 , wherein the supporting structure is a 12 o'clock beam.
10. The aircraft nacelle according to claim 8 , wherein the supporting structure is a 6 o'clock beam.
11. The aircraft nacelle according to claim 1 , wherein the supporting structure integrates at least one connecting portion for connecting to a front frame.
12. The aircraft nacelle according to claim 1 , wherein the supporting structure integrates a fairing wall and forms inner aerodynamic lines with the faring wall inside a secondary flow circulation tunnel.