| 摘要 |
The invention relates to a front device (100) for fastening a turbojet engine (1) to an aircraft fixing strut (3), which is used for absorbing trust loads of said turbojet engine and is characterised in that it comprises a top bracket (101) and a lower bracket (102), wherein a trust load absorbtion vector (V) results from a convergence point (C1) of primary vectors (v1, v'1) passing through the primary fixing points (103, 108) for connecting the top bracket to the lower bracket and from a convergence point (C2) of secondary vectors (v2, v'2) passing through the secondary fixing points (109, 110, 111) for connecting the top bracket to the turbojet engine, transfers the turbojet engine thrust loads to the fixing strut and extends along the turbojet engine axis (A). |
