| 摘要 |
The invention relates to a spigot-type fastener (1) for an aircraft, designed to be interposed between the structure of the aircraft and an attachment structure of the aircraft engine, said fastener being designed to absorb the force generated by the engine along two orthogonal axes (OX) and (OZ). According to the invention, this fastener comprises a first part (2), one end of said first part being secured to a second part (14), one end (9) of the second part being separated from the first part by a distance j and the opposite end (10) of the second part being fit into a recess (4) of a third part (3) via a protrusion (11), such that the force along both axes is transmitted by the first part (2) to the third part (3) by means of the second part (14) and the means for measuring the force are mounted on at least one of the parts. |
