TURBOJET ENGINE FRONT SUSPENSION TO AIRCRAFT PYLON Russian patent published in 2010 - IPC B64D27/26 

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, namely to design of turbojet engine front suspension to aircraft pylon. Proposed device comprises upper load bearing elements 101 and lower load bearing elements 102, primary attachment points 103, 108 that secure said upper load bearing elements to lower load bearing elements and secondary attachment points 109, 110, 111 to secure lower load bearing elements with turbojet engine. Thrust up taking vector (V) combining, on one side, convergence point (C1) of primary vectors (v1, v'1) passing through primary attachment points (103, 108) that secures upper with load bearing elements with lower load bearing elements, and, on the other side, convergence point (C2) of secondary vectors (v2, v'2) passing through secondary attachment points (109, 110, 111) passes along axis (A) of turbojet engine.

EFFECT: attachment that transfers thrust forces to pylon without applying bending strains to engine.

9 cl, 5 dwg