Patent ID: 8827203

Claim:
An aircraft propulsion system comprising: a bypass turbojet engine surrounded by a nacelle defining a passage in which a secondary stream flows, and a connection device that connects the engine under a structural element of an aircraft, the connection device comprising a pylon situated radially outside the flow passage for the secondary stream and lying in a plane substantially parallel to a longitudinal axis of the engine, and a suspension device that suspends the engine from the pylon, the plane of the pylon being angularly offset from a vertical plane containing the longitudinal axis of the engine, wherein the suspension device that suspends the engine from the pylon comprises two parallel and substantially horizontal transverse beams that connect the pylon to hinges on top portions of casings of the engine, and wherein the pylon further comprises an additional arm supporting an engine thrust take-up device, the additional arm extending from the pylon towards the engine and being connected at its free end to a crossbar having ends connected to an intermediate casing via links.