Propulsion system for an aircraft comprising a turbojet, a pylon and engine attachment

A propulsion system of an aircraft, said propulsion system comprising:

• a turbojet extending around a longitudinal axis and having a vertical median plane passing through the longitudinal axis and having a fan casing with a rear face perpendicular to the longitudinal axis,
• a pylon presenting a rigid structure with a front part and a lower spar with a rear fitting fixed to the lower spar,
• a front engine attachment which is fixed between an upper part of the fan casing and the front part of the rigid structure,
• a front arch with a body fixed to the lower spar and two arms arranged on either side of the vertical median plane, each arm having a first end formed one with the body and a second end fastened in an articulated manner to the rear face,
• two lateral rods arranged on either side of the vertical median plane, each rod having a first end fastened in an articulated manner to the rear fitting and a second end fastened in an articulated manner to the rear face,
• wherein the second end of each arm is fastened directly to the rear face,
• wherein the second end of each lateral rod is fastened to the arm on a same side of the vertical median plane, and
• wherein, for each arm, the propulsion system comprises a front rod having a first end fastened in an articulated manner to the rigid structure and a second end fastened in an articulated manner to said arm.