초록 ▼

A rear attachment suspension or device of a turbo engine to an aircraft pylon includes an upper brace fitted with a pylon fastening device and hinged by second ball joint connections, first and second rocker bars transversal to the longitudinal axis of the engine on both sides of the axis of the eng

A rear attachment suspension or device of a turbo engine to an aircraft pylon includes an upper brace fitted with a pylon fastening device and hinged by second ball joint connections, first and second rocker bars transversal to the longitudinal axis of the engine on both sides of the axis of the engine and a third rocker bar disposed there between. The rocker bars are linked to the engine by first ball joint connections. The first and second rocker bars each include a third stand-by link and the upper brace is formed of a beam fixed rigidly to the pylon. The rocker bars are designed to ensure their interchangeability, thereby reducing the risks of error during assembly.

대표청구항 ▼

What is claimed is: 1. A device to attach an aircraft gas turbine engine to an aircraft pylon, comprising: an upper brace configured to be connected to the aircraft pylon; first and second connecting rods each having a stand-by link and being connected to the engine and to the upper brace by ball-

What is claimed is: 1. A device to attach an aircraft gas turbine engine to an aircraft pylon, comprising: an upper brace configured to be connected to the aircraft pylon; first and second connecting rods each having a stand-by link and being connected to the engine and to the upper brace by ball-joint connections; and a third connecting rod being connected to the engine and to the upper brace by ball-joint connections and being disposed between the first and second connecting rods, wherein said first and second connecting rods are disposed on opposite sides of a longitudinal axis of the engine and said connecting rods are disposed substantially transverse to the longitudinal axis of the engine, wherein said connecting rods are rectilinear. 2. A device to attach an aircraft gas turbine engine to an aircraft pylon, comprising: an upper brace configured to be connected to the aircraft pylon; first and second connecting rods each having a stand-by link having a backlash and being connected to the engine and to the upper brace by ball-joint connections; and a third connecting rod being connected to the engine and to the upper brace by ball-joint connections and being disposed between the first and second connecting rods, wherein said first and second connecting rods are disposed on opposite sides of a longitudinal axis of the engine and said connecting rods are disposed substantially transverse to the longitudinal axis of the engine, wherein backlashes in the stand-by links in the first and second connecting rods are identical to each other. 3. A device to attach an aircraft gas turbine engine to an aircraft pylon, comprising: an upper brace configured to be connected to the aircraft pylon; first and second connecting rods each having a stand-by link and being connected to the engine and to the upper brace by ball-joint connections; and a third connecting rod being connected to the engine and to the upper brace by ball-joint connections and being disposed between the first and second connecting rods, wherein said first and second connecting rods are disposed on opposite sides of a longitudinal axis of the engine and said connecting rods are disposed substantially transverse to the longitudinal axis of the engine, wherein the first connecting rod is interchangeable with the second connecting rod. 4. A device to attach an aircraft gas turbine engine to an aircraft pylon, comprising: an upper brace configured to be connected to the aircraft pylon; first and second connecting rods each having a stand-by link and being connected to the engine and to the upper brace by ball-joint connections; and a third connecting rod being connected to the engine and to the upper brace by ball-joint connections and being disposed between the first and second connecting rods, wherein said first and second connecting rods are disposed on opposite sides of a longitudinal axis of the engine and said connecting rods are disposed substantially transverse to the longitudinal axis of the engine, wherein the third connecting rod is tilted with respect to a horizontal direction and configured to transmit to a carrying structure a torque exerted by an engine casing due to a rotation of the engine. 5. A device configured to attach a turbo engine to an aircraft pylon including an upper brace fitted with pylon fastening means, whereon three connecting rods are each hinged by first ball joint connections, the three connecting rods being transverse to a longitudinal axis of the engine, a first connecting rod of said connecting rods being disposed on one side of the longitudinal axis of the engine, a second connecting rod of said connecting rods being disposed on the second side of the engine's longitudinal axis, and a third of said connecting rods being disposed between said first and second connecting rods, the connecting rods being themselves linked with the engine by second ball joint connections, wherein the first and second connecting rods each include a stand-by link having a backlash and wherein the upper brace is formed of a beam fixed rigidly to the pylon, wherein backlashes in the stand-by links in the first and second connecting rods are identical to each other. 6. A device configured to attach a turbo engine to an aircraft pylon including an upper brace fitted with pylon fastening means, whereon three connecting rods are each hinged by first ball joint connections, the three connecting rods being transverse to a longitudinal axis of the engine, a first connecting rod of said connecting rods being disposed on one side of the longitudinal axis of the engine, a second connecting rod of said connecting rods being disposed on the second side of the engine's longitudinal axis, and a third of said connecting rods being disposed between said first and second connecting rods, the connecting rods being themselves linked with the engine by second ball joint connections, wherein the first and second connecting rods each include a stand-by link and wherein the upper brace is formed of a beam fixed rigidly to the pylon, wherein the first connecting rod is interchangeable with the second connecting rod. 7. A device configured to attach a turbo engine to an aircraft pylon including an upper brace fitted with pylon fastening means, whereon three connecting rods are each hinged by first ball joint connections, the three connecting rods being transverse to a longitudinal axis of the engine, a first connecting rod of said connecting rods being disposed on one side of the longitudinal axis of the engine, a second connecting rod of said connecting rods being disposed on the second side of the engine's longitudinal axis, and a third of said connecting rods being disposed between said first and second connecting rods, the connecting rods being themselves linked with the engine by second ball joint connections, wherein the first and second connecting rods each include a stand-by link and wherein the upper brace is formed of a beam fixed rigidly to the pylon, wherein the third connecting rod is tilted with respect to a horizontal direction and configured to transmit to a carrying structure a torque exerted by an engine casing due to a rotation of the engine.