Aircraft jet engine pylon suspension attachment

1. A turbojet suspension pylon for an aircraft, comprising:

a rigid structure including a longitudinal central box and two lateral boxes fixed to a forward part of the central box, each of the lateral boxes including an upper skin and a lower skin; and

a first and a second engine forward suspensions to resist forces applied along a longitudinal direction of the pylon, the first and the second engine forward suspensions arranged on the two lateral boxes, respectively, and interposed between the rigid structure and a turbojet, wherein

each lateral box is closed at a forward end by a forward closing frame oriented along a plane defined by a transverse direction and a vertical direction of the pylon,

the central box is closed at a forward end in the same plane as the lateral boxes, and

the first and second engine forward suspensions are fixed to the two forward closing frames of the lateral boxes, respectively.

2. A turbojet suspension pylon for an aircraft according to claim 1 , wherein the two lower skins together delimit a part of a substantially cylindrical surface with a circular section and a longitudinal axis.

3. A turbojet suspension pylon for an aircraft according to claim 2 , wherein the two lateral boxes together form a part of a substantially cylindrical envelope with a semi-circular section.

4. A turbojet suspension pylon for an aircraft according to claim 2 , wherein a plane defined by the longitudinal axis of the surface and a transverse direction of the pylon passes through the first and second engine forward suspensions.

5. A turbojet suspension pylon for an aircraft according to claim 2 , wherein the first and second engine forward suspensions each resist forces applied along the longitudinal direction of the pylon, and along a vertical direction of the pylon.

6. A turbojet suspension pylon for an aircraft according to claim 5 , further comprising:

a plurality of engine suspensions including the first and second engine forward suspensions located symmetrically about a plane defined by the longitudinal axis of the surface and the vertical direction of the pylon;

a third engine forward suspension through which the plane passes; and

an engine aft suspension fixed to the longitudinal central box.

7. A turbojet suspension pylon for an aircraft according to claim 6 , wherein the third engine suspension only resists forces applied along the transverse direction of the pylon, and the engine aft suspension only resists forces applied along the vertical direction of the pylon.

8. A turbojet suspension pylon for an aircraft according to claim 6 , wherein the plurality of engine suspensions are mounted to the turbojet suspension pylon such that the plurality of engine suspensions form a statically determinate mounting system.

9. A turbojet suspension pylon for an aircraft according to claim 5 , further comprising:

a plurality of engine suspensions including the first and second engine forward suspensions located symmetrically about a plane defined by the longitudinal axis of the surface and the vertical direction of the pylon; and

an engine aft suspension fixed to the longitudinal central box.

10. A turbojet suspension pylon for an aircraft according to claim 9 , wherein the engine aft suspension resists forces applied along the transverse direction of the pylon and along the vertical direction of the pylon.

11. A turbojet suspension pylon for an aircraft according to claim 1 , wherein the suspension pylon is configured to be disposed in an aircraft.