| 摘要 |
The invention relates to a mounting for attaching an engine to an aircraft structure, said mounting including a metal spring and being adapted for fulfilling the following conditions: the stiffness of the mounting for load values falling within a predetermined range ([CA, CB]) is less than the stiffness of the mounting for load values that fall below or above the predetermined range; considering a first load value (CS2) corresponding to a first operating mode (MF2), the load values due to dynamic variations during said first operating mode around said first value (CS2) fall within the predetermined range; the mounting comprising a means for limiting the movement of the spring with a given maximum value when applying a load with a value falling above the predetermined range ([CA, CB]). |
