| 摘要 |
The invention relates to a structural assembly (1) of an aircraft turbojet engine nacelle and a thermal protection mat (2) attached to the structure (1), the mat being attached to said structure (1) via at least one attachment device, the attachment device comprising an attachment base (11) rigidly connected to the structure (1), said attachment base (11) being rigidly connected to one end of a link (15), said link (15) passing through the mat (2) via a passage (2a, 2b, 2c) provided in the mat (2), and being rigidly connected at the other end of same to a retaining button (16), the assembly being characterised in that the attachment device comprises a removable spacer (14) inserted at least partially into a recess (2b) of the thermal protection mat (2), the spacer being disposed between the thermal protection mat (2) and the retaining button (16) and having a through-hole (14a) through which the link (15) can pass, the spacer being held in position by the retaining button (16). |
